Note: Descriptions are shown in the official language in which they were submitted.
MONITORING SYSTEM
TECHNICAL FIELD
[0001] The present invention pertains to a monitoring system
for flight crew
members or passengers of airplanes or aircraft. Airplanes or aircraft are
defined as
airplanes or helicopters of the civil or military aviation, e.g., passenger
planes in
scheduled or charter service as well as ultrafast airplanes close to the range
or above the
range of supersonic speed. In particular, flights with jet planes (jets) with
supersonic
speeds and/or at flight altitudes above 15,000 m above sea level represent
high
requirements on the flight crew members, especially on the pilots of jet
planes,
concerning the fitness to fly comprising physical and mental fitness,
attention, ability to
concentrate and alertness.
BACKGROUND
[0002] In order for the physical and mental fitness and the
alertness necessary for
piloting the aircraft to be guaranteed at any time at high altitudes, during
terrifically fast
flight maneuvers or in flight positions, for example, curve flight, during
nosedives,
inverted flying at high speeds (> Mach 1) and with accelerations above or even
several
times the gravitational acceleration as well as also in-flight refueling,
secured supply of
the aviator with satisfactory breathing air that is harmless for health is
also very essential
in addition to a reliable equipment of the airplane. For example, systems
which use -
usually processed or air-conditioned and filtered - outside air from the
environment as the
1
CA 03173467 2022- 9- 26
source of the breathing gas, are used to supply aviators, pilots, copilots or
passengers with
breathing air or breathing gas, but systems in which additional oxygen is
added to the
breathing air or to the breathing gas are used as well. The oxygen may be
carried along
in the airplane here, for example, under high pressure (<200 bar) in
compressed oxygen
cylinders and its pressure can be reduced to a pressure suitable for breathing
by means of
suitable pressure-reducing devices or it may be generated for the consumption
during the
mission by a chemical oxygen generator, for example, from sodium chlorate,
which is
carried along, in a chemical process. It is often made possible for the
aviator, pilot or
copilot to activate the dispensing or supply of oxygen independently and/or to
set or
preset the quantity and/or a concentration of oxygen and/or a composition of
the
breathing gas independently. The breathing air/breathing gas supply may be
ensured in
this case directly from the air of the cabin or cockpit, but it is also
possible to use a tube
system with mouth/nose mask for the direct feed and/or removal of breathing
air/breathing gas to the aviator, pilot or copilot. It is necessary in each
case for the on-
board equipment of the airplane or aircraft to supply the aviator, pilot or
copilot during
the mission with satisfactory breathing gas that is harmless for the health.
This includes,
on the one hand, that the qualitative and quantitative composition of the
breathing gas,
especially the percentages of oxygen and/or carbon dioxide, in the breathing
gas be in a
range that is harmless for health. In addition to such components as nitrogen
and noble
gases, oxygen (02) is present in the natural atmosphere at a percentage of 21
vol.%. The
percentage of carbon dioxide (CO2) is currently below 0.05 vol.% as a
worldwide average
in the natural atmosphere. According to recommendations of the U.S. Federal
Aviation
Administration (FAA), a carbon dioxide concentration of 30,000 ppm,
corresponding to 3
2
CA 03173467 2022- 9- 26
vol.% CO2, represents the highest allowable value for passengers in airplanes.
The
American Society of Heating, Refrigerating and Air-Conditioning Engineers
(ASHRAE)
recommends as the upper limit a carbon dioxide concentration of 1,000 ppm,
corresponding to 0.1 vol.% of CO2. Thus, a concentration above 21 vol.% is
also
desirable for the supply of breathing gas for aviators, pilots or copilots or
passengers for
the percentage of oxygen and an upper limit of 0.1 vol.% of CO2 is desirable
for the
concentration of carbon dioxide during the mission at least according to the
recommendations of the U.S. Federal Aviation Administration (FAA) and
according to
the recommendations of the American Society of Heating, Refrigerating and Air-
Conditioning Engineers (ASHRAE). It is considered to be scientifically
ascertained that
concentrations of carbon dioxide above 1 vol.% to 3 vol.% may cause a carbon
dioxide
poisoning, which is characterized, for example, by nausea, headache and
dizziness.
Carbon dioxide concentrations above 12% are immediately lethal. Supply with an
insufficient quantity of oxygen may also be harmful for health especially for
aviators,
pilots or copilots, because the oxygen partial pressure in the blood may be
reduced in
case of a supply with insufficient quantities of oxygen, and a so-called
hypoxic state
(hypoxia) develops. Such a reduction of the arterial oxygen partial pressure
in the blood -
also called hypoxemic hypoxia (hypoxemia) - frequently develops in persons who
are at a
high altitude. Symptoms of hypoxia are, for example, anxiety and restlessness,
dyspnea,
cyanosis, tachycardia, an increase in blood pressure, confusion, dizziness,
bradycardia
and even cardiac arrest.
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CA 03173467 2022- 9- 26
TECHNICAL BACKGROUND
[0003] A device and a process for monitoring inhaled gas is
known from EP
3287173 Al. A pressure level of the entire inhaled breathing air and an oxygen
partial
pressure in the inhaled breathing air are determined during the admission of
the breathing
air into a face mask of a person and a partial pressure of the oxygen in the
lungs of the
person is estimated from this. A breathing mask with display device, which is
configured
to provide data and/or information for aviators, pilots or copilots in a
visual form, is
known from US 2007181129 A. The display device is configured as a so-called
head-up
display. The data and/or information are projected here on the inside onto the
visor into
the field of view of the aviator, pilot or copilot. Another head-up display is
known from
US 7391574 B2. A face mask with a detection device for ambient temperature and
the
display and visualization thereof are known from US 2016253561 A. A display
device
for a face mask in a configuration as a so-called in-mask display is known
from US
2019118008 A. A device for oxygen supply for an airplane, for example,
according to
the principle of the pressure swing adsorption, is known from US 8210175 B.
Oxygen is
provided, in addition, from an oxygen reserve. The air is processed with
molecular sieve
beds, which are scavenged with oxygen from the oxygen reserve at the beginning
of the
operation. Other devices for oxygen supply in airplanes are known from US
7407528 B,
US 2004245390 A and US 7264647 B. A compressed air monitoring system for
monitoring compressed air with a measuring air line for the continuous
sampling of
compressed air from a compressed air supply line and with at least one sensor
for the
continuous detection of at least one parameter of the compressed air is known
from DE
102010014222 B4. A sensor for detecting a concentration of carbon dioxide, a
sensor for
4
CA 03173467 2022- 9- 26
detecting a concentration of nitrogen dioxide, a sensor for detecting a
concentration of
sulfur dioxide, a sensor for detecting a concentration of oxygen as well as a
sensor for
detecting a relative humidity of the air in the measured air line are
mentioned as sensors
for the continuous detection of at least one parameter of the compressed air.
EP 2148616
B1 shows a measuring system with a plurality of sensor mechanisms, such as
flow sensor
mechanism, temperature sensor mechanism, pressure sensor mechanism, humidity
sensor
mechanism, gas sensor mechanism for the measurement of oxygen, carbon dioxide,
carbon monoxide, nitrogen, nitrogen oxides, anesthetic gases, gaseous
components in the
exhalation as well as other gases. DE 102006030242 Al shows a configurable
measuring
system with a plurality of gas sensors. Electrochemical, infrared optical and
catalytic gas
sensors may be configured as gas sensors in the measuring system. A pump for
delivering quantities of air is known from US 20130167843 Al. The pump has a
piezoelectric manner of functioning. Such a pump is suitable for delivering
quantities of
gas from a measuring point to a location of the sensor mechanism and/or for
measurement-based detection by means of the measured gas line (sample line)
and is
suitable, for example, for use for a side stream measurement (side stream) for
an analysis
of gas components, especially also carbon dioxide and oxygen, close to the
mouth/nose
area of a person or patient for the analysis of inhaled/exhaled air. Many
different
embodiments and configurations of and with gas delivery devices, pumps or
devices for
transporting gas for supplying persons with breathing gases, also in
embodiments and
with suitability for ventilating persons, are known from the patent documents
WO
2018033224 Al, US 20180163712 Al, WO 2018033225 Al, US 20180133420 Al, US
20180110957 Al, WO 2019072606 Al, DE 102017009605 Al, DE 102017009606 Al,
CA 03173467 2022- 9- 26
DE 102018004341 Al and also DE 202012013442 Ul. Other embodiments of gas
delivery devices, pumps or devices for transporting gas for supplying persons
are known
from the German patent applications 102019003643.3, 102019003607.7,
102019004450.9 and 102019004451.7, which have not yet been laid open to public
inspection. Many different embodiments and configurations of gas delivery
devices,
pumps or devices for transporting gas for feeding gases to be measured to a
gas
measuring device are known from the patent documents DE 102016013756 Al, US
20180143171 Al, US 20180143170 Al and US 201803354 Al. A connection element, a
so-called Y-piece, for connecting ventilation tubes at the mouth/nose area of
a person or
of a patient with sensor mechanism components, components for measured value
acquisition, signal processing, signal analysis and display is known from US
2008264418
A. The sensor mechanism components comprise a breath flow sensor mechanism
with
pressure sensor mechanism, a sensor mechanism for measuring the oxygen partial
pressure, temperature sensor mechanism, flow rate sensor mechanism, configured
as a
hot wire anemometer or ultrasonic flow sensor, as well as connection elements
for EKG
and blood pressure measurement. Oxygen sensors according to the principle of
measurement of the so-called luminescence quenching, which may be arranged in
the
side stream in or at the breathing gas path of a patient, are known from US
7897109 B,
US 7335164 B, US 6616896 B, US 5789660 B and US 6312389 B. An oxygen sensor
with a bioreactor array is known from DE 102010037923 B4. A system for
detecting a
reduced oxygen supply in pilots and for reducing the reduction of the oxygen
supply in
pilots is known from US 9867563 B. A galvanic cell for measuring oxygen is
known
from US 2003194351 A. Electrochemical oxygen sensors are known from DE
6
CA 03173467 2022- 9- 26
102004062052 B4 and DE 19726453 C2. An electrochemical sensor for measuring
gaseous components in a gas mixture is known from DE 2155935. Many different
embodiments of electrochemical gas sensors, which are suitable for a
measurement-based
detection of oxygen or other gases, are known from US 5958200 B, DE
102009010773
B4, DE 102005026491 B4, DE 102005026306 B4 and US 8496795 B. DE
102005007539 Al shows an electrochemical gas sensor for a quantitative
determination
of redox-active substances in very low concentration ranges. The
electrochemical
principle of measurement is suitable, depending on the configuration of the
electrodes
and of the electrolyte, for the detection of different gases, for example,
oxygen, ammonia,
sulfur dioxide, hydrogen peroxide, hydrogen sulfide, nitrogen dioxide,
nitrogen
monoxide, arsine, silanes, formaldehyde, acetylene, carbon monoxide, phosgene,
and
phosphine. An electrochemical carbon monoxide sensor is known from DE 19912100
Al. An electrochemical carbon dioxide sensor is known from US 4851088 B. US
5473304 B and DE 4020385 C2 show heat tone sensors manufactured according to
ceramic film technology. US 7875244 B, GB 2210980 Al and DE 19610912 Al show
heat tone sensors of the pellistor configuration. US 2010221148 A and US
5902556 B
show catalytic gas sensors with semiconductor chips as measuring elements.
Catalytic
gas sensors are known from US 2816863 B, US 2019178827 A, US 8425846 B, US
9625406 B, US 6756016 B, US 2016178412 A, and US 6344174 B. The catalytic
principle of measurement, also called heat tone principle, is especially
suitable for
detecting combustible and/or explosive gases, especially hydrocarbon
compounds, as
well as for the determination of residual components of combustion processes.
For
example, toluene, ammonia, benzene, propane, methane, methanol, octane,
butane,
7
CA 03173467 2022- 9- 26
ethylene can be detected by measurement based on the heat tone principle.
Catalytic
sensors are frequently used to monitor limit values, e.g., the LEL (Lower
Explosion
Limit). US 4175422 B shows a gas sensor with a semiconductor element as the
measuring element. A gas sensor device with semiconductor sensor mechanism
configured according to chip technology for monitoring combustion processes in
internal
combustion engines of a motor vehicle is known from US 9958305 B. Miniaturized
semiconductor gas sensors are known from DE 102004048979 B4 and US 4902138 B.
A
semiconductor type carbon monoxide sensor is known from DE 102012022136 B4.
Miniaturized semiconductor oxygen sensors, configured according to the
microstructured
technology, so-called M EMS (micro-electromechanical system) technology, are
known
from US 9818937 B and US 9234876 B. Furthermore, gas sensors with solid
electrolytes, e.g., on the basis of zirconium dioxide, are known. Thus, DE
102008056279
B4 shows a device with a heated solid electrolyte oxygen sensor and with an
ultrasonic
sensor for the indirect detection of the concentration of carbon dioxide. US
5026992 B
shows a gas sensor for the measurement-based optical detection of methane. US
8399839 B shows a gas sensor for the measurement-based optical detection of
carbon
dioxide. A device with a lambda probe for detecting a quantity of residual
oxygen in the
exhaust gas of an internal combustion engine is known from EP 0149619 Al. A
Hall
effect oxygen sensor is known from US 4667157 B. US 8596109 B, US 9360441 B2,
US
4808921 B, US 6430987 B, US 6952947 B, US 6895802 B, US 6405578 B, US 4683426
B, US 4173975 B, US 3646803 B, US 3584499 B, US 2944418 B and WO 16162287 Al
show devices for measuring concentrations of paramagnetic gases. Especially a
qualitative and also quantitative measurement-based detection of oxygen is
possible with
8
CA 03173467 2022- 9- 26
such devices, because oxygen possesses paramagnetic properties. A measuring
element
for a paramagnetic gas sensor, especially for an oxygen sensor, is known from
US
9360441 B. The paramagnetic gas sensor or oxygen sensor may preferably be
arranged
in the side stream in or at the breathing gas path of a patient. Gas-measuring
devices are
described in DE 102010047159 B4 and in US 2004238746 A. An infrared optical
gas-
measuring device is described in US 5739535 B. An infrared optical carbon
dioxide
sensor, a so-called IR carbon dioxide sensor, is known from US 8399839 B.
Devices for
the measurement of the concentration of carbon dioxide in breathing gas by
measuring
the thermal conductivity are known from DE 102010047159 B4 and US 6895802 B.
The
configuration according to DE 102010047159 B4 shows a carbon dioxide sensor
with a
semiconductor chip as a measuring element for detecting changes in thermal
conductivity. Infrared optical carbon dioxide sensors are known from US
5696379 B, US
2004203169 A and US 4050823 B. Infrared optical carbon dioxide sensors, which
may
be arranged in the main stream in the breathing gas path of a patient, are
known from US
8448642 B, US 5095900 B, US 5067492 B, WO 20109115 Al, US 2019105457 A, US
6095986 B, USD 727492 51 and US 5942755 B. Gas-measuring devices or sensors
for
the measurement-based detection of carbon dioxide, especially also suitable
for the
measurement-based detection of carbon dioxide in breathing gases, are known
from US
2002036266 A, US 2004238746 A, US 20180120224 Al and US 20180116555 Al.
Other gas-measuring devices or sensors for the measurement-based detection of
carbon
dioxide are known from the German patent applications 102020114972.7 and
102020114968.9, which have not yet been laid open to public inspection. A
combined
sensor comprising an infrared optical carbon dioxide sensor with a flow
sensor, which
9
CA 03173467 2022- 9- 26
may be arranged in the main stream in the breathing gas path of a patient, is
known from
US 6571622 B. Infrared optical carbon dioxide sensors, which may be arranged
in the
side stream in or at the breathing gas path of a patient, are known from US
2004238746
A and US 2002036266 A. US 6954702 B, US 7606668 B, US 8080798 B, US 7501630
B, US 7684931 B, US 432508 B, and US 7183552 B show gas-measuring systems for
detecting gas concentrations in the side stream and in the main stream.
Interferometers
configured as gas measuring devices are described in US 9939374 B and US
7705991 B.
Laser-based devices for detecting gas components are known from US 6274879 B
and EP
2788739 B1. A gas sensor configured as a photoionization detector is known
from US
9459235 B. Other aspects concerning a qualitative and quantitative composition
of the
breathing gas pertain to the requirement that the breathing gas should be
largely free from
impurities, for example, it should be largely free from foreign bodies or
particles, e.g.,
soot, dust, pollen or vapors of materials, through which the breathing gas
flows on its
way to aviators, pilots, copilots and passengers. Furthermore, no or no
substantial
quantities of gases or gas mixtures that are harmful to health, such as carbon
monoxide
(CO), ozone, traces of other gases or traces of aviation fuel or kerosene,
quantities of
exhaust gases or residues of the combustion or other air-borne pollutants
shall be present
in the breathing gas. These include, for example, many different compositions
of
hydrocarbons, benzenes, nitrogen oxides (NO2, NOR), sulfur oxides (SO2, SON),
dioxins,
furanes, particles, e.g., soot, fine dust, and ultrafine particles. In
particular, carbon
monoxide poisoning shall also be pointed out, in particular, in this
connection in addition
to the above-mentioned carbon dioxide poisoning. Even concentrations above 200
ppm
(0.02%) cause headache and a loss of judgement, and concentrations above 800
ppm
CA 03173467 2022- 9- 26
(0.08%) cause dizziness, restlessness, nausea, anxiety and spasms within 45
minutes and
loss of consciousness within 2 hours, possibly leading to death. The oxygen
transportation capacity of the blood decreases in case of carbon monoxide
poisoning due
to a reduction of the hemoglobin level (anemia) or due to impairment of the
oxygen-
binding capacity in the blood, and anemic hypoxia develops.
SUMMARY
[0004] Therefore, the need arises to ensure the situation for
aviators, pilots,
copilots, and passengers that satisfactory and high-quality breathing gas is
provided by
the on-board equipment of an airplane or aircraft during the flying operation
and it can be
administered to aviators, pilots, copilots and passengers of airplanes or
aircraft. From
this arises as an object of the present invention the need to provide a
monitoring system
for aviators, pilots, copilots and passengers of airplanes or aircraft or to
provide a process,
which makes it possible to monitor breathing gases and breathing air on the
basis of
measurements in airplanes or aircraft. From this arises as another object of
the present
invention the need to provide a process for the measurement-based monitoring
of
breathing gases and breathing air in airplanes or aircraft.
[0005] The object is accomplished, in particular, by a
monitoring system for
monitoring a gas composition of breathing gases in airplanes or aircraft with
the features
according to the invention.
11
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[0006] The object is also accomplished by a process for
operating a monitoring
system for monitoring a gas composition of breathing gases in airplanes or
aircraft with
the features of according to the invention. Further features and details of
the present
invention and advantageous embodiments appear from the description and from
the
drawings. References used here refer to the further configuration of the
subject of the
principal claim by the features of the respective subclaim and they shall not
be considered
to represent abandonment of the wish to achieve an independent concrete
protection for
the combinations of features of the referred-back subclaims. Furthermore, it
shall be
assumed in respect to an interpretation of the claims as well as of the
description in case
of a more specific concretization of a feature in a dependent claim that such
a limitation
is not present in the respective preceding claims as well as in a more general
embodiment
of the concrete system or process. Any reference in the description to aspects
of
dependent claims shall accordingly also expressly imply a description of
optional features
even without a special reference. Finally, it shall be noted that the
monitoring system
being proposed here may also be varied corresponding to the process claims and
vice
versa, for example, by the monitoring system comprising devices that are
intended and/or
set up for carrying out one or more process steps or by the process comprising
steps that
can be carried out by means of the monitoring system or are suitable for
operating the
monitoring system. Features and details that are described in connection with
the
monitoring system being proposed for flight crew members or passengers of
airplanes or
aircraft and of possible embodiments are thus, of course, also valid in
connection with
and in respect to a process carried out during the operation of the monitoring
system and
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vice versa, so that reference is and can always mutually be made to the
individual aspects
of the present invention concerning the disclosure.
[0007]
Embodiments create possibilities for a measurement-based monitoring of
the gas composition of air, breathing air or breathing gases in airplanes or
aircraft. At
least some exemplary embodiments of the present invention pertain to a
monitoring
system for monitoring the gas composition of air, breathing air or breathing
gases in
airplanes or aircraft. At least some exemplary embodiments of the present
invention
pertain to a monitoring system for monitoring the gas composition of air,
breathing air or
breathing gases in airplanes or aircraft. At least some exemplary embodiments
of the
present invention pertain to a process for operating a monitoring system for
monitoring
the gas composition of air, breathing air or breathing gases in airplanes or
aircraft. A
measurement-based detection of properties of at least one gas may be made
possible by
means of a sensor mechanism of a monitoring system in at least some exemplary
embodiments. Properties of a gas may include, for example, physical and other
properties: Pressure, density, viscosity, thermal conductivity, electrical and
magnetic
properties, temperature, gas composition, moisture content, toxicity,
calorific value,
combustibility, binding capacities with other gases or liquids, for example,
water or
blood. A qualitative measurement-based detection of at least one gas may be
made
possible in at least some exemplary embodiments. A quantitative measurement-
based
detection of at least one gas and/or of a concentration of a gas may be made
possible in at
least some exemplary embodiments. A qualitative and a quantitative measurement-
based
detection of at least one gas may be made possible in at least some exemplary
13
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embodiments. A qualitative and a quantitative measurement-based detection of
oxygen
may be made possible in at least some exemplary embodiments. A qualitative and
a
quantitative measurement-based detection of carbon dioxide may be made
possible in at
least some exemplary embodiments. A qualitative and a quantitative measurement-
based
detection of another gas, especially carbon monoxide, may be made possible in
at least
some exemplary embodiments.
[0008] A control unit is arranged in the monitoring system or
is associated with
the monitoring system in at least some exemplary embodiments. The control unit
is
configured and intended to organize, to control or to regulate a course of a
measurement-
based monitoring of the gas composition of air, breathing air or breathing
gases in
airplanes or aircraft. The control unit is preferably configured from
components (RC, [LP,
PC) with corresponding operating system (OS), memory (RAM, ROM, [[PROM) as
well as SW code, software for process control, control, and regulation. In at
least some
exemplary embodiments, additional electronic components, for example,
components for
signal detection (AID C), signal amplification, for analog and/or digital
signal processing
(ASIC), components for analog and/or digital signal filtering (DSP, FPGA, GAL,
[IC,
pP), and signal conversion (A/D converter) are assigned to the control unit or
are
connected to the control unit in at least some exemplary embodiments.
[0009] In at least some exemplary embodiments, a qualitative
and a quantitative
measurement-based detection of a concentration of oxygen may be made possible
in at
least some exemplary embodiments. The concentration of oxygen may be
determined in
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CA 03173467 2022- 9- 26
this case by measurement, for example, in the form of a partial pressure in a
gas mixture
of, for example, the breathing air or of the breathing gas or in the form of a
volume
concentration or in the form of a mass per unit volume. In at least some
exemplary
embodiments, a qualitative and a quantitative measurement-based detection of a
concentration of carbon dioxide may be made possible by means of the sensor
mechanism in at least some exemplary embodiments. The concentration of carbon
dioxide may be determined in this case by measurement, for example, in the
form of a
partial pressure in a gas mixture, for example, of the breathing air or of the
breathing gas
or in the form of a volume concentration or in the form of a mass per unit
volume. In at
least some exemplary embodiments, a qualitative and a quantitative measurement-
based
detection of a concentration of carbon monoxide may be made possible by means
of the
sensor mechanism. The concentration of carbon monoxide may be determined in
this
case by measurement, for example, in the form of a partial pressure in a gas
mixture, for
example, of the breathing air or of the breathing gas or in the form of a
volume
concentration or in the form of a mass per unit volume. The sensor mechanism
may have
at least one sensor in at least some exemplary embodiments. The at least one
sensor is
preferably configured in this case as an oxygen sensor, as a carbon dioxide
sensor or at
least one additional gas sensor, especially carbon monoxide sensor. In at
least some
exemplary embodiments, a paramagnetic oxygen sensor or a measuring module with
a
paramagnetic oxygen sensor may be used for the qualitative and quantitative
measurement-based detection of the concentration of oxygen. An electrochemical
oxygen sensor may be used in this case in another advantageous manner. An
oxygen
sensor or a measuring module with an oxygen sensor, which operates according
to the
CA 03173467 2022- 9- 26
principle of luminescence quenching or fluorescence quenching, may be used in
this case
in another advantageous manner. A semiconductor oxygen sensor, preferably in
the form
of a so-called M EMS oxygen sensor or a measuring module with a semiconductor
oxygen sensor or with a M EMS oxygen sensor, may be used in this case in
another
advantageous manner. An electrochemical oxygen sensor and/or paramagnetic
oxygen
sensor or a measuring module with an electrochemical oxygen sensor and/or with
a
paramagnetic oxygen sensor may be used in this case in another advantageous
manner.
An electrochemical oxygen sensor and/or a semiconductor oxygen sensor or a
measuring
module with an electrochemical oxygen sensor and/or with a semiconductor
oxygen
sensor may be used in this case in another advantageous manner. A paramagnetic
oxygen
sensor and/or a semiconductor oxygen sensor and/or with an electrochemical
oxygen
sensor or a measuring module with a paramagnetic oxygen sensor and/or with a
semiconductor oxygen sensor and/or with an electrochemical oxygen sensor may
be used
in this case in another advantageous manner. A paramagnetic oxygen sensor
and/or a
semiconductor oxygen sensor or a measuring module with a paramagnetic oxygen
sensor
and/or with a semiconductor oxygen sensor may be used in this case in another
advantageous manner. An optical carbon dioxide sensor, preferably in the form
of an
infrared optical, a so-called IR carbon dioxide sensor, or a measuring module
with an
optical, preferably infrared optical carbon dioxide sensor, with a so-called
IR sensor, may
be used in at least some exemplary embodiments for the qualitative and
quantitative
measurement-based detection of the concentration of carbon dioxide. A
semiconductor
carbon dioxide sensor, preferably in the form of a so-called M EMS carbon
dioxide sensor
or a measuring module with a semiconductor carbon dioxide sensor or with a M
EMS
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carbon dioxide sensor may be used in this case in another advantageous manner.
A
semiconductor carbon dioxide sensor, preferably in the form of a so-called M
EMS carbon
dioxide sensor and/or an optical carbon dioxide sensor, preferably in the form
of an
infrared optical, so-called IR carbon dioxide sensor or a measuring module
with a
semiconductor carbon dioxide sensor or a M EMS carbon dioxide sensor and/or
with an
optical carbon dioxide sensor or IR carbon dioxide sensor may be used in this
case in
another advantageous manner.
[0010] The measuring modules with at least one oxygen sensor
are also called
oxygen measuring modules in the context of the present invention. The
measuring
modules with at least one carbon dioxide sensor are also called carbon dioxide
measuring
modules in the context of the present invention.
[0011] The oxygen measuring modules and/or carbon dioxide
measuring modules
may also have additional sensors in some embodiments or additional sensors may
also be
associated with the oxygen measuring modules and/or carbon dioxide measuring
modules
in some embodiments and/or such additional sensors may be arranged at the
modules.
The oxygen measuring module and/or the carbon dioxide measuring module may
optionally be configured in some embodiments such that they are combined with
additional gas sensors and optionally with additional sensors for the
measurement-based
detection of measured variables or substance parameters, for example,
pressure, ambient
pressure, airway pressure, mask pressure, density, temperature, thermal
conductivity,
thermal capacity, volume flow, mass flow, flow rate, volumes, or they are
configured as
17
CA 03173467 2022- 9- 26
an environmental or ambient analysis module. Thus, a pressure sensor in the
monitoring
system may be arranged, for example, as a component of the oxygen measuring
module
or of the carbon dioxide measuring module, which is configured to detect a
pressure level
in the measured gas line. In addition, a flow sensor or flow rate sensor in
the monitoring
system may be arranged, for example, as a component of the oxygen measuring
module
or of the carbon dioxide measuring module, which is configured for the
detection of a
flow rate or of a flow in the measured gas line. Measured values of the flow
sensor, flow
rate sensor as well as of the pressure sensor may be made available to the
control unit.
[0012] In some embodiments, the monitoring system or such
modules as gas
measuring modules, measuring modules, environmental or ambient analysis
modules,
may have at least one gas transport module. The gas transport module has to
this end a
gas delivery device, preferably a pump, with a gas port, which gas delivery
device is
configured to deliver a defined quantity of gas from a measuring point located
at a
distance from the sensor mechanism or from the oxygen measuring module, carbon
dioxide measuring module or gas measuring module to the oxygen measuring
module, to
the carbon dioxide measuring module or to the gas measuring module or to the
oxygen
sensor or to the carbon dioxide sensor in order for the measurement-based
detection of
the oxygen concentration and/or carbon dioxide concentration to be made
possible. The
pump or the gas transport module is configured such as to suck in quantities
or partial
quantities of breathing gas or breathing air from a measuring point,
especially from the
breathing mask and/or from the cabin or from the cockpit and to deliver it to
the
monitoring system or to the oxygen measuring module and/or to the carbon
dioxide
18
CA 03173467 2022- 9- 26
measuring module or to the sensor mechanism, especially to the oxygen sensor
and/or to
the carbon dioxide sensor. The breathing mask may be configured, for example,
as a
partial mask, half mask or full mask or as a combination of a safety helmet
with a mask.
Valves may additionally be arranged in the incoming flow in front of the pump
or in the
outgoing flow behind the pump in order to largely or completely prevent back
flows or to
avoid unintended flows or flowthrough. The gas transport module is preferably
connected pneumatically and/or fluidically to the measuring point in a gas-
carrying
manner preferably by means of a measured gas line (sample line). A gas-
carrying
component is preferably used as a measuring point in the area of the face,
i.e., close to the
mouth/nose area of the aviator, pilot or copilot to monitor the breathing gas
supply of the
aviator, pilot or copilot. One end of the measured gas line is preferably
arranged at the
mouth/nose area, for example, at the breathing mask, in order to make possible
a flow of
quantities of gas from the mouth/nose area to the gas transport module of the
monitoring
system. The other end of the measured gas line is preferably connected
pneumatically or
fluidically to a gas port for an incoming flow into the gas transport module
such that a
delivery of quantities of gas or of partial quantities of breathing gas is
made possible, for
example, at a flow rate in the range of 25 mL/min to 250 mL/min by means of
the gas
transport module to the oxygen measuring module and/or to the carbon dioxide
measuring module. The gas transport module is connected to this end
pneumatically
and/or fluidically to an additional gas port for the outgoing flow or delivery
to the oxygen
measuring module and/or to the carbon dioxide measuring module. The control
unit can
control the gas transport module by means of the flow sensor or flowthrough
sensor and it
can control, regulate or set the quantities of gas to be delivered or to be
sucked in in the
19
CA 03173467 2022- 9- 26
measured gas line. The control unit can monitor the pressure level in the
measured gas
line by means of the pressure sensor and it can also control, regulate or set
it by means of
the gas transport module. If the flowthrough sensor is configured as a
pressure difference
sensor ( P sensor) of a difference measurement of two pressure measurement
points over
a flow diaphragm, a pressure measurement of the pressure level in the measured
gas line
can also be made possible with this sensor with the detection of one of the
two pressure
measurement points with reference to the environment.
[0013] In a preferred embodiment, the gas transport module in
the form of a
pump may be arranged at a gas inlet of the monitoring system. In such an
exemplary
constellation, the gas transport module sucks in quantities of gas through the
measured
gas line from the breathing mask of the aviator into the monitoring system and
it then
delivers these quantities of gas to and through the sensor mechanism for the
determination of the gas concentration. After flowing through the sensor
mechanism, the
quantities of gas enter into the environment through a gas outlet.
[0014] In another preferred embodiment, the gas transport
module in the form of
a pump may be arranged at a gas outlet of the monitoring system. In such an
exemplary
constellation, the gas transport module sucks quantities of gas through the
measured gas
line from the breathing mask of the aviator into the monitoring system through
the sensor
mechanism for the determination of the gas concentration. After flowing
through the
pump, the quantities of gas enter the environment through a gas outlet. With
the pump
being arranged at the gas outlet, possible contaminants cannot reach the
sensor
CA 03173467 2022- 9- 26
mechanism through the pump. Quantities or partial quantities of breathing gas
can be
transported via the gas transport module, especially the pump, via the
pneumatic and/or
fluidic connection to the oxygen measuring module and/or to the carbon dioxide
measuring module or to the oxygen sensor and/or to the carbon dioxide sensor,
so that a
measurement-based detection of concentrations of oxygen and/or carbon dioxide
is made
possible. The monitoring system is configured in such a construction that it
can be
arranged in or at the clothing of the aviator, pilot or copilot. The measured
gas line has a
corresponding length, so that such an arrangement is made possible.
Accommodation or
arrangement of the monitoring system in a breast pocket, leg pocket or thigh
pocket of a
flight suit (aviator overall) is especially advantageous. The gas delivery
module is
configured and constructed such that quantities of gas can be delivered from
the
measuring point to the preferred location of arrangement in a breast pocket,
leg pocket or
thigh pocket of the flight suit. The gas transport module may be configured,
for example,
as a centrifugal pump, axial pump, radial pump, reciprocating pump or a
diaphragm
pump. A pump with low energy consumption is especially advantageous for use in
the
monitoring system for mobile and energy-self-sufficient use. A
piezoelectrically
operated pump, also often called piezo pump, makes possible, for example, an
energy-
saving use for gas concentration measurement in the monitoring system. Such a
pump is
available commercially, for example, from Murata Manufacturing Corp. of Kyoto,
Japan,
as a so-called "piezoelectric blower" or "microblower" with the names
MZB1001T02 as
well as MZB 1001. These pumps do not block the flow even without electrical
actuation
or activation, and it is therefore advantageous in case of use for the
monitoring system to
provide a valve, which ensures the flow in the measured gas line in a reliable
and
21
CA 03173467 2022- 9- 26
reproducible manner and unambiguously with two states, namely, "release" and
"blockage." A shut-off valve, a so-called "flow-lock valve," which may
preferably be
arranged at the gas outlet, is advantageous for the embodiment with the pump
at the gas
outlet as well as for the embodiment with the pump at the gas inlet. The
arrangement of
the shut-off valve at the gas outlet of the monitoring system makes possible
the use of the
pressure sensor arranged in the interior of the monitoring system for
determining the
pressure in the breathing mask of the aviator by means of a measurement
maneuver to
determine the pressure in the breathing mask, because the pressure level in
the interior of
the monitoring system corresponds to the pressure level in the measured gas
line as well
as to the pressure level in the breathing mask with the shut-off valve closed
in the no-
flow state. A reversing valve, a so-called "3/2-way valve," which may
preferably be
arranged at the gas inlet, is advantageous, as an alternative, for the
embodiment with the
pump at the gas inlet. This reversing valve makes it possible, on the one
hand, to feed
quantities of gas from the measured gas line into the monitoring system, and,
on the other
hand, it can thus also be made possible to feed quantities of gas from the
environment,
i.e., from the cabin of the aircraft. The control unit can simultaneously
determine the
pressure level in the breathing mask by means of a measurement maneuver for
determining the pressure in the breathing mask during the feed of quantities
of gas from
the cabin.
[0015]
An additional gas port with a reversing valve is arranged in the
monitoring
system in a preferred embodiment. An additional gas port with a reversing
valve is
arranged in or at the gas transport module in another preferred embodiment.
This
22
CA 03173467 2022- 9- 26
reversing valve makes possible a switching between a feed of quantities of gas
from the
measured gas line and a feed of quantities of gas by means of the additional
gas port from
the environment, for example, from the cabin of the aircraft. In another
preferred
embodiment, an additional pump is arranged in or at the additional gas port.
This
additional pump makes it possible to feed quantities of gas by means of the
additional gas
port from the environment, for example, from the cabin of the aircraft. In
addition to the
shut-off valve at the gas outlet, an optional reversing valve may be arranged
at the gas
inlet for switching between a monitoring of quantities of gas from the
measured gas line
from the breathing mask and of quantities of gas from the cabin for the
embodiment with
the pump at the gas outlet. Thus, the control unit is then enabled to carry
out at any time
a switching between the feed of quantities of breathing gas from the breathing
mask of
the aviator and a feed of gas from the cabin independently from times at which
the
pressure in the mask is determined.
[0016] The control unit may be configured in some embodiments
to determine
breathing phase information, i.e., a duration in time of an inhalation, a
duration in time of
an exhalation, a ratio (I:E ratio) of the duration of inhalation to the
duration of exhalation,
as well a respiratory frequency of the aviator, pilot or copilot, from the
measured values
of the carbon dioxide sensor.
[0017] The sensor mechanism and the control unit may be
configured in at least
some exemplary embodiments to detect at least one environmental parameter
and/or at
least one operating parameter. Operating parameters may be, for example,
parameters
23
CA 03173467 2022- 9- 26
from the flying operation, parameters from the supply of the aviator, pilot or
copilot with
breathing gases, parameters from the control and regulation of the aircraft or
of
components of the aircraft. In at least some exemplary embodiments, the sensor
mechanism and the control unit may be configured to also take into account at
least one
environmental parameter and/or to also include it in the process during the
control of the
measurement-based monitoring process.
[0018] The control unit is configured in a preferred
embodiment in conjunction
and together with a pressure sensor to determine a current pressure level in
the breathing
mask. The aviators (pilots, copilots) are supplied by means of a breathing
mask arranged
at the mouth/nose area during the flying operation of a jet airplane (jet).
The monitoring
of the current pressure level in the breathing mask of the aviator, pilot or
copilot is
therefore of particular interest. It can thus be ensured that a sufficient
pressure level of
breathing gas is made available by means of the breathing mask for the
aviator, pilot or
copilot.
[0019] Embodiments show possibilities of configuring a
detection of pressure
levels in the breathing mask by means of the sensor mechanism and of the
control unit
and of thus monitoring, providing, outputting and/or documenting the pressure
level in
the breathing mask. The control unit detects a pressure level in the measured
gas line by
means of a pressure sensor, which is arranged in the monitoring system
connected
pneumatically and fluidically in a pneumatic system to the components
breathing mask,
measured gas line, connection elements and an HM E filter element optionally
arranged in
24
CA 03173467 2022- 9- 26
a series connection in the measured gas line to detect a pressure measured
value, which
indicates a pressure level in the pneumatic system. In another preferred
embodiment for
detecting the current pressure level, a pressure measurement is initiated by
the control
unit in a measurement situation during the operation of the monitoring system,
in which
no quantities of gas are fed from the breathing mask to the sensor mechanism
with the
gas transport module deactivated and with the pump deactivated, i.e., the gas
concentration measurement by the sensor mechanism is interrupted or paused at
times.
The measured value, which indicates the pressure level in the pneumatic
system,
corresponds in such a measurement situation to the current pressure level in
the breathing
mask. In addition to the deactivation of the pump, the shut-off valve can be
brought into
a closed state in order to prevent any exchange of gas of the pneumatic system
with the
environment. A measurement and checking of the pressure level in the breathing
mask
can be carried out intermittently with such an embodiment if the feed of
quantities of gas
by the pump is deactivated at defined time intervals.
[0020] A pressure measurement is initiated by the control
unit in another
preferred embodiment for detecting the current pressure level during the
ongoing
operation of the monitoring system, in which quantities of gas are
continuously fed from
the breathing mask to the sensor mechanism. A measurement and checking of the
pressure level in the breathing mask can be carried out with such an
embodiment
continuously if an adaptation or calibration to pressure drops of the
pneumatic system,
which change during the operation, is carried out with the components
breathing mask,
measured gas line, connection elements and the H ME filter element
intermittently at
CA 03173467 2022- 9- 26
different time intervals. An adaptation or calibration, which can be carried
out
intermittently or at defined time intervals, may be configured in such a
preferred
embodiment by a measurement maneuver, which is coordinated and carried out by
the
control unit in interaction with the gas transport module or the pump, the
shut-off valve
and a memory. Such a measurement maneuver may be carried out from time to time
during the flying operation in order to continuously determine changes in or
at the
pneumatic system at defined times in the time course of the operation of the
monitoring
system during the mission at the aviator. The measurement maneuver comprises a
measurement-based detection of pressure levels for zeroing or for offset
determination at
two working points. The measurement maneuver is divided into a pressure
measurement
of a static pressure level at a working point without a gas flow in the
pneumatic system
and into a measurement-based detection of a dynamic pressure level in the form
of a
measurement at another predefined working point with a defined flow in the
pneumatic
system. A pressure measured value is detected during the measurement-based
detection
of the static pressure level without gas flow within the pneumatic system with
the
components breathing mask, measured gas line, connection elements and an HME
filter
element optionally arranged in the measured gas line in a series connection.
Without a
gas flow, i.e., with the pump shut off and with a resulting flow rate of 0.00
mLimin, no
pressure drops caused by components will occur in the pneumatic system between
the
breathing mask and the pressure sensor or the pump in the monitoring system.
The HME
filter element is used to prevent moisture from the breathing gas supply with
breathing
tube and breathing mask, which moisture is introduced into the measured gas
line by the
exhalation of the aviator during the operation, from entering into the
monitoring system
26
CA 03173467 2022- 9- 26
for monitoring a gas composition of breathing gases. Such an HME filter
element (HME
= Heat Moisture Exchange) is configured to retain quantities of moisture. The
HME
filter element is arranged in a preferred embodiment in the measured gas line,
at the gas
inlet or at the gas transport module. Due to the exhalation of moist breathing
gases by the
aviator, quantities of moisture or liquid will continuously accumulate during
the
operation in the HME filter element. This leads to changes in the flow
resistance over the
duration of the use during the flying operation with the monitoring system
operating. In
addition to the switching off of the pump, the shut-off valve will
advantageously be
brought into a closed state in order to prevent any gas exchange of the
pneumatic system
with the environment. The detected pressure measured value without gas flow in
the
measured gas line corresponds to a snapshot of the current pressure in the
breathing mask
with the shut-off valve closed and it is stored as a static pressure of the
pneumatic system
in a memory. A pressure measured value with a defined quantity of a gas flow
with
pressure drops corresponding to this gas flow at the components of the
pneumatic system
with measured gas line, with connection elements and with the optional HME
filter
element is detected at the time of the measurement-based detection of the
dynamic
pressure level. The detected pressure measured value with a defined quantity
of a gas
flow is stored as a dynamic pressure of the pneumatic system in the memory. A
range of
mL/min to 400 mL/min can be activated, controlled or regulated by the control
unit as
a suitable and defined quantity of the gas flow in the measured gas line. The
pressure
measured value with flow corresponds to the dynamic current total pressure
drop of the
pneumatic system. This pressure measured value then corresponds to the sum of
the
pressure drops in the pneumatic system, i.e., with pressure drops over the
components
27
CA 03173467 2022- 9- 26
such as breathing mask, HME filter element, measured gas line and connection
elements.
The control unit can determine from the difference of the previously
determined static
pressure level and the sum of the dynamic pressure drops the pressure drop
attributed to
the components as an offset pressure level in the pneumatic system. Changes in
the
differences determined between the dynamic and static pressure measured values
between two or more times at which the measurement maneuver is carried out
make it
possible for the control unit to draw conclusions concerning changes in the
pressure drops
and changes in the offset pressure level in the pneumatic system during the
operation.
These offset pressure levels in the pneumatic system and their differences as
well as their
changes are detected or determined continuously during the flying operation by
the
control unit and are stored in the memory, for example, in the form of a data
set or of a
table or as a log file. The control unit is advantageously configured by means
of the
measurement maneuver in this preferred embodiment to determine, subsequently
to
provide, to output and/or to store, in the form of data sets or tables, offset
pressure levels
determined by a measurement-based detection of static and dynamic pressure
drops over
the pneumatic system as calibration values for a determination of the current
mask
pressure. Thus, the measurement maneuver provides trends and changes of the
offset
pressure level during the operation of the monitoring system at the aviator,
pilot or
copilot during the mission. It is possible in this manner to determine and to
monitor the
particular, currently occurring mask pressure of the aviator even among
components of
the pneumatic system which change during the flying operation. In particular,
an
increase in the pressure drop over the HME filter element, which is due to
moisture
saturation, can be detected as a change in the offset pressure level by
continual repetitions
28
CA 03173467 2022- 9- 26
of the measurement maneuver and it can be compensated in the calculation of
current
pressure levels in the breathing mask. Such repetitions of the checking may
take place,
for example, once every 15 minutes to 60 minutes, and a more frequent
performance is
not advantageous because the monitoring concerning the gas concentrations is
interrupted
or paused for a short time for the performance of the maneuver. The
determination of the
current pressure in the breathing mask can also be carried out by the control
unit during
the operation with the pump activated and with measurement-based detection of
the gas
concentrations of oxygen and/or carbon dioxide as well as possibly other gases
or the
cabin air on the basis of a use of the offset pressure level of the components
of the
pneumatic system, which offset pressure level was determined last with the
measurement
maneuver. The current pressure level present in the breathing mask is obtained
by
subtracting the last determined offset pressure level, which is stored in the
memory and is
the last determined offset pressure level provided there, from the current
pressure
measured value obtained during the flow through the measured gas line. The
measurement maneuver, which was already described before for determining the
pressure
in the breathing mask, will also be explained in respect to the integration of
this
measurement maneuver into the measuring operation of the monitoring system for
the
measurement-based detection of the gas concentration, preferably of carbon
dioxide and
oxygen, with the functions of the components involved in that process. The
measurement
maneuver can be activated or started at predefined times from the ongoing
measuring
operation of the monitoring system. The following steps are activated,
initiated and
carried out by the control unit in a sequence of steps from a start to an end:
- a deactivation of the pump is carried out in a first
step,
29
CA 03173467 2022- 9- 26
- the shut-off valve is closed in a second step,
- a first measuring operation is carried out in a third
step by the pressure
sensor with a pressure measurement to determine the static pressure level,
- the shut-off valve is opened in a fourth step,
- the pump is activated in a fifth step to deliver
quantities of gas at a defined
flow rate in the range of 50 mL/min to 100 mL/min from the breathing mask
through the measured gas line into the monitoring system to the sensor
mechanism; the flow rate is controlled and monitored in the process by a flow
measurement by means of the flowthrough sensor,
- another measuring operation is carried out in a sixth
step by the pressure
sensor, i.e., a pressure measurement is carried out to determine the dynamic
pressure level, and
- a determination of a difference value is carried out
in a seventh step with
the pressure measured values of the first pressure measurement and of the
additional pressure measurement.
[0021] The difference value thus determined represents the
offset pressure level
and can be provided and used as a calibration value for the determination of a
mask
pressure during the further operation of the monitoring system during the
mission of the
aircraft. In optional embodiments of the sequence of steps of the measurement
maneuver,
the measurement-based detections of the static and dynamic pressure level
and/or of the
flow rates can be carried out by the control unit in the third, fifth and
sixth steps
synchronized with the breathing of the aviator, pilot or copilot. The pressure
CA 03173467 2022- 9- 26
measurements and/or the flow measurements can thus preferably be carried out
during
inspiratory or expiratory pauses.
[0022]
In a preferred embodiment, the control unit may be configured to also
take
information concerning breathing phases of the aviator into account during the
measurement-based detection and/or determination of the static pressure
measured value
and/or of the dynamic pressure measured value during the carrying out of the
measurement maneuver to determine the pressure in the breathing mask. The
detection
of the pressure measured values with a synchronization with the breathing with
performance of the measured value acquisition during pauses between inhalation
and
exhalation is advantageous because no pressure effects due to the breathing,
which are
superimposed to the static and/or dynamic pressure levels, can make unfamiliar
or
influence the pressure measured value. The synchronization with the breathing
can be
carried out by the control unit by means of breathing phase information based
on changes
in the concentrations of carbon dioxide and/or oxygen, which changes are
detected by
measurement in the monitoring system. The physiological concentration
differences in
the oxygen content in the breathing gas between inhalation (21%) and
exhalation (16%)
as well as concentration differences in the carbon dioxide content between
exhalation
(-5%) and inhalation (<1%) can be used by the control unit to determine
breathing
phases. Without such synchronization of the pressure measurement, a suitable
signal
filtering, for example, by means of low-pass filtering or - preferably sliding
- mean value
formation of the measured values of the pressure sensor, is useful in order to
remove the
components of the breathing or of the respiratory rate from the pressure
measured values.
31
CA 03173467 2022- 9- 26
[0023] Provisions can therefore be made in an especially
preferred embodiment
for the control unit to be configured, together with the signal processing
with the use of
suitable signal filtering, to determine the static and/or dynamic pressure
measured values
with removal of signal components induced by the breathing of the aviator by
means of
signal filtering. A gas analysis of the cabin air can advantageously be
carried out with the
use of the reversing valve during the time during which the mask pressure is
determined.
Predefined values (set points), reference values as threshold values of the
breathing mask
pressure can be provided by an external system, for example, via a data
interface. The
monitoring system can then determine an alarm generation situation on the
basis of such
values in case of values above or below the threshold values and provide
corresponding
alarm signals and/or data. Such a provision may be carried out, for example,
in a wired
manner, in a wireless manner by means of radio transmission, in a wireless
manner by
means of infrared transmission to external systems. Further possibilities for
generating
an alarm for the aviator are offered by visual, optical or acoustic signal
generation
systems, such as lamps, light-emitting diodes, display units, speakers,
buzzers, horns or
comparable elements. Another possibility for alarm generation for the aviator
may be
tactile alarm generation, for example, in the form of a vibration alarm.
[0024] Additional embodiments can show how additional
environmental
parameters may be able to be determined by the control unit in addition to the
mask
pressure. Environmental parameters include during the operation of airplanes
or aircraft,
for example,
32
CA 03173467 2022- 9- 26
- ambient pressure outside the cockpit or cabin of the
airplane or aircraft,
- ambient temperature within the cockpit or cabin of the
airplane or aircraft,
- gas composition within the cockpit or cabin of the
airplane or aircraft,
- absolute and/or relative humidity within the cockpit
or cabin of the
airplane or aircraft,
- density and/or ambient pressure within the cockpit or
cabin of the airplane
or aircraft,
- ambient temperature within the cockpit or cabin of the
airplane or aircraft,
- gas composition within the cockpit or cabin of the
airplane or aircraft,
- ambient pressure outside the cockpit or cabin of the
airplane or aircraft,
- ambient temperature outside the cockpit or cabin of
the airplane or
aircraft,
- gas composition outside the cockpit or cabin of the
airplane or aircraft,
- absolute and/or relative humidity outside the cockpit
or cabin of the
airplane or aircraft,
- density and/or ambient pressure outside the cockpit or
cabin of the
airplane or aircraft,
- ambient temperature outside the cockpit or cabin of
the airplane or
aircraft,
- gas composition outside the cockpit or cabin of the
airplane or aircraft,
- pressure level, pressure changes, pressure changes
over time, pressure
differences, pressure fluctuations in the breathing gas, breathing gas mixture
or in
the breathing air in the feed line to the aviator, pilot or copilot, and
33
CA 03173467 2022- 9- 26
- pressure level, pressure changes, pressure
differences, pressure
fluctuations in the on-board equipment provided (e.g., gas tanks, pressurized
oxygen cylinders, air intake, gas treatment, filtering) for breathing gas,
breathing
gas mixture or breathing air.
[0025] The control unit may be configured in at least some
exemplary
embodiments also to take into account at least one situational parameter
during the
control of the course of the measurement-based monitoring and/or to include it
in the
procedure. Situational or current situational parameters are defined as
situations and/or
states arising from situations during the operation of airplanes or aircraft.
These include, for example:
- a flight direction,
- a flight altitude,
- a flight axis position,
- a flight position,
for example, inverted flying, curve flight, nosedive, descent, ascent,
- a flight velocity,
- a horizontal acceleration,
- a vertical acceleration,
- a yaw angle or a roll angle,
- a residual oxygen or air reserve, and
- a residual reserve of pressurized oxygen or compressed
air.
34
CA 03173467 2022- 9- 26
[0026] The monitoring system may have a data interface in
some embodiments.
The data interface may be configured as a unidirectional or bidirectional data
interface
and may be configured, for example, for data supply, data reception, data
exchange or
communication with components of the airplane or aircraft.
[0027] The situational parameters and/or the ambient
parameters may be received
and/or provided in at least some exemplary embodiments by the monitoring
system
and/or by the control unit by means of the data interface. In at least some
exemplary
embodiments, the situational parameters and/or the ambient parameters may be
detected
by measurement by means of additional sensors of the sensor mechanism, which
are
arranged in or at the monitoring system, and be made available to the control
unit.
Additional gas sensors, for example, for the measurement-based detection of
carbon
monoxide as well as additional gas sensors, e.g., in the form of
electrochemical gas
sensors, catalytic gas sensors, optical, infrared optical gas sensors,
photoionization gas
sensors, solid electrolyte gas sensors or semiconductor gas sensors may be
used for this
purpose in the sensor mechanism in addition to the sensor mechanism for the
measurement-based detection of oxygen and/or carbon dioxide, in order to make
it
possible to monitor the breathing gas in addition to the measurement-based
detection of
concentrations of oxygen and carbon dioxide with respect to other substances
as well,
such as hydrocarbons, residues or products of combustion processes. All
additional
sensors in the sensor mechanism may also be provided by pressure sensors,
which may be
configured to detect an ambient pressure from the environment, especially a
pressure or a
density within and/or outside the cockpit or cabin of the airplane or aircraft
by
CA 03173467 2022- 9- 26
measurement and to make it available to the control unit. The additional
sensors in the
sensor mechanism may be configured as temperature sensors, which may be
configured
and intended for detecting an ambient temperature of the environment,
especially a
temperature inside and/or outside a cockpit or cabin of the airplane or
aircraft, by
measurement, and to make it available to the control unit. These additional
sensors in the
sensor mechanism may be configured as humidity sensors for detecting an
absolute or
relative humidity of the environment, which may be configured or intended to
detect a
humidity in the environment, especially inside and/or outside a cockpit or
cabin of the
airplane or aircraft and to make it available to the control unit.
[0028] In some embodiments, additional sensors at/in the
sensor mechanism in
the monitoring system may be provided for detecting data to determine the
situational
parameters or they may be associated with the sensor mechanism, which make it
possible
for the control unit to determine a current flight situation with flight
altitude, flight
direction, flight velocity, flight acceleration, flight position with
orientation in space and
flight situation or flight maneuver (e.g., ascent, descent, curve flight,
approach for
landing, start). For example, pressure sensors, acceleration sensors, altitude
sensors,
compass sensors, gyro sensors, humidity sensors, and temperature sensors are
arranged
for this purpose at or in the sensor mechanism or are associated with the
sensor
mechanism.
[0029] The sensor mechanism may be arranged in some
embodiments very close
to the mouth/nose area in or at the breathing mask. Depending on the fluidic
conditions
36
CA 03173467 2022- 9- 26
at the mouth/nose area, an active transport of breathing gases to the sensor
mechanism
may be eliminated in such cases. The breathing gases reach the sensor
mechanism
passively, i.e., by diffusion from the mouth/nose area in the mask.
Integration of the
sensor mechanism into the breathing mask in or at parts of the breathing mask
may be
made possible in special configurations. Due to the progress being made in
technological
development in the area of chip and/or M E MS technology, miniaturization of
elements of
the electrochemical, catalytic or semiconductor sensor mechanisms can be
expected in
the near future, and this will then be able to make possible an integration of
the sensor
mechanism, preferably oxygen sensor mechanism, carbon dioxide sensor mechanism
and
other gas sensors as well as of additional and optional pressure sensor
mechanisms and/or
temperature sensor mechanisms directly at the measuring point.
[0030] An additional gas port may be provided at the gas
transport module in
some embodiments. The additional gas port makes it possible to connect and to
feed
quantities or partial quantities of gas or ambient air from the cabin or the
cockpit to the
monitoring system. Gas, quantities or partial quantities from the ambient air
or from the
mouth/nose area of the aviator, pilot or copilot, for example, from the
breathing mask can
be fed as desired to the pump or to the gas transport module via a reversing
valve (e.g., a
3/2-way valve) or a system of valves.
[0031] An additional pump may be provided in some embodiments
and it may be
arranged such that a pump for transporting gas, quantities or partial
quantities from the
ambient air to the oxygen measuring module and/or to the carbon dioxide
measuring
37
CA 03173467 2022- 9- 26
module or to the oxygen sensor and/or to the carbon dioxide sensor is provided
and
arranged and this additional pump is intended and arranged for transporting
gas,
quantities or partial quantities from the mouth/nose area of the aviator,
pilot or copilot,
for example, from the breathing mask, to the oxygen measuring module and/or to
the
carbon dioxide measuring module or to the oxygen sensor and/or to the carbon
dioxide
sensor. A reversing valve (e.g., a 3/2-way valve) or a system of valves for
switching
between quantities or partial quantities of breathing gas can thus be
eliminated in such an
embodiment.
[0032] The control unit may be configured in some embodiments
to control the
gas transport module. A control of the gas transport module may comprise in
this case an
activation, a deactivation, a setting, a control or a regulation of the gas
transport module.
The setting may comprise especially a setting of speed of rotation, flow rate
and/or
pressure level, for example, by means of optical or electrical control signals
(CAN bus,
PWM) or electrical control voltages. A determination concerning a leak present
in the
measured gas line can also be carried out in one variant of such embodiments
on the basis
of the detection of gas concentration values and/or pressure measured values,
for
example, also on the basis of pressure differences between the mask and the
cockpit.
[0033] The control unit may further be configured in some
embodiments also to
take into account and/or to include in the control at least one ambient
parameter or at
least one situational parameter in the control of the gas transport module.
Such a taking
into account may comprise especially an adaptation of activation,
deactivation, speed of
38
CA 03173467 2022- 9- 26
rotation, flow rate and/or pressure level of the gas delivery module. It can
thus be made
possible to deactivate the gas transport module during certain flight
maneuvers, for
example, during an ascent, descent or curve flight and/or optionally to
activate it with an
increased flow rate after the end of the maneuver.
[0034] In at least some exemplary embodiments, the monitoring
system and/or
the control unit may be configured for a determination and/or detection of an
alarm
situation and for organizing an alarm generation or for sending an alarm
and/or for
providing an alarm signal. The control unit can determine and/or detect an
alarm
situation and trigger an alarm generation and/or provide an alarm signal, for
example, at
the data interface or at another data interface on the basis of measured
values of the
sensor mechanism and/or by means of information provided for the data
interface. The
alarm generation may take place as a visual and/or acoustic and/or tactile
alarm
generation. A visual alarm generation may take place, for example, in the form
of a
white and/or colored lighting device (LED, stroboscope) or of a text output
(LCD, LED,
display). Such an alarm generation may also be carried out visually by means
of a
suitable visualization device at or in a face mask or breathing mask, for
example, as a
display on an in-mask display or head-up display. An acoustic alarm generation
may be
carried out, for example, in the form of a speech output or by means of an
acoustic alarm
generator (horn, siren). A tactile alarm generation may be carried out, for
example, in the
form of a vibration alarm to equipment of the aircraft, such as seat surfaces,
control
elements (pedals, handles) as well as pieces of equipment (breathing mask,
breathing
tube) or clothing (suit, vest, parachute, shoes) of the aviator, pilot or
copilot.
39
CA 03173467 2022- 9- 26
[0035] In some embodiments, the control unit can also take
into consideration an
ambient parameter and/or a situational parameter and/or include it in the
organization of
the alarm generation during the organization of the alarm generation or alarm
and/or
during the provision of the alarm signal. It can thus be made possible in an
advantageous
manner that relevant alarm information, which is prioritized according to
relevance, can
be provided for the aviator, pilot or copilot in a consolidated or compact
manner
concerning the situation of the measurement-based detection in the breathing
gas with
reference to the situation in the environment (temperature, gas composition in
the
breathing air) and in reference to the mission situation or to maneuver
situation of the
airplane (start phase, landing approach, in-flight refueling, descent, curve
flight, ascent).
In a special embodiment, the control unit can also take into consideration an
ambient
parameter and/or a situational parameter and also include it in an adaptation
of the signal
processing during the performance of the signal processing and/or signal
filtering of the
measured values of the sensor mechanism.
[0036] In some exemplary embodiments, the control unit can
use during the
organization of the alarm generation predefined threshold values, which may be
stored
for certain values of gas concentrations, especially concentrations of oxygen
or carbon
dioxide or carbon monoxide, in the memory of the monitoring system.
[0037] On the basis of current concentration measured values,
which were
obtained in the past and are in the form of a trend monitoring of oxygen and
carbon
CA 03173467 2022- 9- 26
dioxide, and by means of a suitable decision matrix or algorithms specially
adapted to the
problem, teachable or self-learning algorithms (SVM, Random Forest, Al, Deep
Learning, PCA), the control unit can apply in some embodiments a kind of early
warning
system for detecting hypoxia, possibly with an alarm management adapted to
this for the
onset of a developing hypoxia. In a special situation, the control unit can
also take into
consideration an ambient parameter and/or a situational parameter. In a
special
embodiment, the control unit may also take into consideration in the early
warning
system for the detection of hypoxia additional physiological data of aviators,
pilots and
copilots, for example, EKG, heart rate, heart rate variability, oxygen
saturation in the
blood, body temperature, which data were assigned, for example, by means of
the data
interface or by the monitoring system.
[0038] In some embodiments, such modules as gas measuring
modules,
measuring modules, environmental or ambient analysis modules, may have at
least one
energy storage device, e.g., a primary cell or a rechargeable battery. For
example, types
of lithium ion batteries, nickel-metal hydride batteries or nickel-cadmium
batteries are
known as types of rechargeable batteries. For example, types of alkali-
manganese
batteries, silver oxide-zinc batteries, lithium batteries and aluminum-air
batteries are
known as types of primary cells.
[0039] Battery charging systems and/or battery management
systems for
monitoring battery charge and/or battery state as well as interfaces for
supplying the
battery charging systems and/or battery management systems with charging
electrical
41
CA 03173467 2022- 9- 26
energy may usually also be integrated additionally in the monitoring system in
embodiments with rechargeable batteries. Battery management systems usually
have
interfaces for communication to the outside, in order, for example, to be able
to provide
data or information on the state of the battery, and such interfaces may have
a wired (e.g.,
CAN bus), contactless (e.g., RFID, NFC), wireless (e.g., Bluetooth) or
infrared optical
(e.g., I rDA) configuration. In addition, such modules as gas measuring
modules,
measuring modules, environmental or ambient analysis modules may have
additional
components, for example, components for signal detection (AD C), signal
amplification,
for analog and/or digital signal processing (ASIC); components for analog
and/or digital
signal filtering (DSP, FPGA, GAL, C, [113), signal conversion (A/D
converters),
components ( C, P) for controlling, regulating, components ( C, P) for
process control
of the operation and for user interaction; input and output interfaces, user
interface with at
least one operating element and/or with at least one display element. The at
least one
operating element as well as the at least one display element may be arranged
in or at the
monitoring system or may be associated with the monitoring system.
[0040] For example, an operation with beginning (start,
activation) or end (stop,
deactivation) of the monitoring system, a selection between different modes of
operation
of the monitoring system, performance of maintenance, adjustment or
calibration
processes can be made possible for the user in some embodiments by means of
the at
least one operating element.
42
CA 03173467 2022- 9- 26
[0041] The user can be enabled in some embodiments by means
of the at least
one display element to be informed of events, situations, current measured
values and/or
measured values obtained in the past, which were detected and provided by
measurement
by means of the sensors or measuring modules, especially of the oxygen sensors
and/or of
the carbon dioxide sensors or of the oxygen measuring modules and/or carbon
dioxide
measuring modules. In addition, measured variables derived from the measured
values,
for example, maximum or minimal values, mean values, trends, statistics,
events, alarm
situations, may be provided for the user by means of the display elements. In
addition,
general information on the current operating state of the monitoring system,
such as the
state of the battery, residual battery life, maintenance information,
information on the
monitoring system itself, such as type, name, variant, version, serial number,
initial start-
up, expected maintenance intervals, status data, operating state (ready, in-
OP, Stand-by),
information on malfunctions, error memory, as well as operating instructions,
may be
provided for the user by means of the display elements.
[0042] The display elements may be configured as graphic user
interface
(graphical user interface, GUI) in some embodiments.
[0043] In addition to the display elements, input elements
may be provided in
some embodiments. The input elements may be configured as mechanical or touch-
sensitive buttons or switches, rotary controls or slide controls as well as in
the form of a
graphic user interface (graphical user interface, GUI). Display elements may
be
configured in some embodiments such that they are combined with input
elements. In an
43
CA 03173467 2022- 9- 26
embodiment with a touch-sensitive display (touch screen), there are, for
example,
possibilities for designing changeable display possibilities and operating
possibilities,
e.g., a use of gestures (wiping, pulling) in order thus to vary the type of
the display, for
example, in order to enlarge or to reduce display elements (zoom function).
The
combination of display elements with input elements may preferably be
configured as a
graphic user interface (graphical user interface, GUI, touch pad).
[0044] It is possible in some embodiments to provide an input
element, which
makes it possible for the user or operator of the monitoring system to
initiate, annotate,
trigger, start or end defined actions or states at the monitoring system. Such
an input
element may be configured, for example, as an annotation button and/or as a
panic
button, which can preferably be operated by actuation by hand. As an
alternative,
operation with speech command may also be possible, in which case the
annotation
button and/or the panic button is equipped correspondingly with devices for
speech
detection, speech processing and speech recognition with command detection.
[0045] The input element may also be complemented in other
alternative
embodiments by an acceleration sensor or may be configured by such an
acceleration
sensor. For example, data or measured values of an acceleration sensor, which
is
provided as a component of an additional sensor mechanism at/in the sensor
mechanism
in the monitoring system for detecting data for determining situational
parameters, may
also be used for this purpose by the control unit in order to detect by
measurement a
current flight situation with flight altitude, flight direction, flight
velocity, flight
44
CA 03173467 2022- 9- 26
acceleration, flight position with orientation in space and flight situation
or flight
maneuvers (e.g., ascent, descent, curve flight, landing approach, start) in
the monitoring
system. As an alternative, an additional 2-axis or 3-axis acceleration sensor,
which
represents a functionality of an input element in conjunction with the control
unit, may be
arranged in or at the monitoring system. Movements or excursions of the
monitoring
system, movements or excursions of a housing of the monitoring system, as well
as
mechanical, tactile stimuli or tactile stimulations can be detected by means
of sensors by
means of the acceleration sensor and they can be made available as measured
values or
data to the control unit. Mechanical or tactile stimuli or stimulations are
sent from the
aviator, pilot or copilot to the acceleration sensor as a force action, energy
feed or force
feed in the direction of at least one of the directions or axes detectable in
a sensor-based
manner by the acceleration sensor in the form of actuation acting on the
monitoring
system by means of movements of the hand, in the form of application of
pressure, in the
form of the action of an impact (push, hit, tapping). This is made
advantageously
possible for the aviator, pilot or copilot especially if the monitoring system
is arranged as
a mobile module in a closed pocket in or on the clothing, for example, on or
in a vest,
jacket or a suit. The force feed may thus take place as an actuating activity
through the
clothing to the acceleration sensor in the monitoring system. The use of the
acceleration
sensor as an input device or input element makes possible an actuation or
operation of the
monitoring system by the aviator, pilot or copilot during the mission when he
cannot
reach other input elements at the monitoring system configured as a mobile
module. This
happens, for example, when the monitoring system is arranged as a mobile
module in a
pocket in or on the clothing. The acceleration sensor thus offers an
alternative to an
CA 03173467 2022- 9- 26
operation of the monitoring system by means of a manual button or of a manual
switching element. A control unit may be used for the analysis of the measured
values or
data of the acceleration, but it is also possible to provide an additional
unit, which is
equipped in the monitoring system to detect and analyze data of the
acceleration sensor.
Such an analysis of the data of the acceleration sensor is based essentially
on time
measurements. An analysis can be carried out by means of time measurements in
conjunction with threshold values for the measured values or data of the
acceleration
sensor concerning the duration of the tactile stimulation as well as
concerning durations
between two or more tactile stimulations of the acceleration sensor. The
control unit may
be configured in an exemplary embodiment to detect a first-time force action
or force
feed to the acceleration sensor by means of a comparison with a threshold
value on the
basis of the measured values or data of the acceleration sensor. If a measured
value of
the acceleration sensor is exceeded in respect to a predefined threshold value
for a first
predefined duration, the control unit interprets this situation as a first
force action in the
direction of at least one of the directions or axes detectable in a sensor-
based manner by
the acceleration sensor. An indicator is thus obtained for a start of an input
activity of the
aviator by means of a movement of the hand as an input operation. If the
measured
values of the acceleration sensor are subsequently exceeded once again for a
second
predefined time period for a second predefined threshold value, the control
unit interprets
this situation as the end of the first force action. If a measured value of
the acceleration
sensor is then exceeded within a third predefined duration in respect to the
first
predefined threshold value for the first predefined duration, the control unit
interprets this
situation as a further force action in the direction of at least one of the
directions or axes
46
CA 03173467 2022- 9- 26
detectable in a sensor-based manner by the acceleration sensor. An indicator
is thus
obtained for a continuation of the input activity of the aviator. If values
below the second
predefined threshold value are then obtained for a second predefined time
period from
measured values or data of the acceleration sensor, the control unit
interprets this
situation as the end of the further force action. If no further force actions
on the
acceleration sensor are detected and recognized within a fourth predefined
duration, an
indicator is obtained for the end of the input activity of the aviator. With
this type of
analysis the control unit is configured and able to detect and recognize an
input activity of
a "double tap" by a movement of the hand of the aviator by means of an
analysis of the
measured values of the acceleration sensor concerning the first and second
threshold
values and of the first, second, third and fourth durations during the
operation of the
monitoring system and it can then trigger further actions based on this in or
at the
monitoring system. Such actions may correspond in terms of their manner of
functioning, for example, to functions of an annotation button and/or of a
panic button.
[0046] In addition to the "double tap," the configuration of
the control unit may
be expanded in respect to the analysis in some embodiments such as to make
possible
inputs by a "triple tap" or "quadruple tap" as well. A simple coding is
obtained in this
manner for inputs effected by means of the acceleration sensor, so that the
control unit
can make a distinction between different input situations by means of a case
differentiation between "double tap," "triple tap" or "quadruple tap." It is
also possible, in
principle, to configure a "single tap," and the duration of the stimulation,
which the
47
CA 03173467 2022- 9- 26
"single tap" indicates, would be set now in such a manner that possibilities
of confusion
with other stimulations by the aviator, the aircraft or the equipment are
ruled out.
[0047] In addition to the analysis of durations of the
tactile stimulations, the
configuration of the control unit may additionally also include in the
analysis in some
embodiments differences of durations between the tactile stimulations of the
acceleration
sensor. These differences can then be used by the control unit, in addition to
analyses of
forms of "multiple tapping," to increase the number of events that can be
distinguished
from one another, for example, by a distinction between a "short pause" and a
"long
pause" as durations between the tactile stimulations of the acceleration
sensor. A type of
Morse code is thus obtained due to this variation of pause lengths during the
analysis of
the tactile stimulations, which offers a further possibility for coding events
with the
acceleration sensor as the input element.
[0048] Possibilities and advantages are consequently obtained
due to the fact that
when different input situations are distinguished with assignment to acts or
actions
triggered with the input, the aviator, pilot or copilot can start, for
example, a
measurement maneuver by hand with the acceleration sensor as the input element
during
the flying operation, he can make an entry (annotation) or set a time mark in
a log book
or can mark a special health situation, e.g., a sensation of dizziness during
the data
recording or data storage, without having to operate a button or switch at the
monitoring
system with visual contact with the monitoring system. A measurement maneuver
may
be, for example, a measurement maneuver to determine static and dynamic
pressure
48
CA 03173467 2022- 9- 26
levels in the pneumatic system or a measurement maneuver to activate the
reversing
valve to detect gas concentrations in the cabin.
[0049]
In some embodiments, a memory for storing measured values of measured
variables derived from measured values, for example, maxima or minima, mean
values,
trends, statistics, events and alarm situations may be arranged in or at the
monitoring
system or may be associated with the monitoring system. Such a memory may be
configured as a volatile or non-volatile memory (RAM, ROM, EEPROM) and may be
configured either as a fixed component of the monitoring system or also as a
removable
and/or portable memory module (USB stick, SD card). The memory may be used for
data recording or data storage of inputs made by means of the input element
and provide
to this end functions of a log book or flight recorder. In an embodiment with
tables, lists
and data sets, the log book may advantageously receive an analysis of gas
concentration
measured values, flow measured values, pressure measured values, temperature
measured
values over time with assignment to a time and marking (annotation), further
events or
manual inputs by means of the input element and keep them available and
provide them
for a simultaneous or subsequent analysis. When the events are entered,
measured values
or measured signals of the acceleration sensor may be added in order to put
the respective
marks/notation made in the log book by the pilot into a context with flight
situations or
with flight maneuvers for a real-time or later analysis. When entering the
events,
measured values or measured signals of an altitude sensor may be added in
order to put
the respective marks/notation made by the pilot in the log book into a context
with flight
situations (flight altitude) for a real-time or later analysis. When entering
the events,
49
CA 03173467 2022- 9- 26
measured values or data of the gas sensor mechanism may be added in order to
put the
mark/notation made by the pilot in the log book into a context with the gas
supply (CO2,
02) for a real-time or later analysis.
[0050] In a special configuration of some embodiments, the
control unit may be
configured to also take into consideration an environmental parameter and/or a
situational
parameter when the signal processing and/or signal filtering is carried out
and/or to
include it in the adaptation of the signal processing.
[0051] The control unit may be configured in some embodiments
to use
predefined threshold values, which may be stored for defined values of gas
concentrations, especially concentrations of oxygen or carbon dioxide and
carbon
monoxide, in the memory of the monitoring system during the organization of
the alarm
generation.
[0052] The control unit may be configured in some embodiments
to employ an
early warning system for the detection of hypoxia on the basis of current and
past
measured values of the sensor mechanism, for example, in the form of a trend
monitoring
of concentrations of oxygen and/or carbon dioxide,
- by means of a decision matrix,
- or by means of specially adapted algorithms, and
- or by means of teachable or self-learning algorithms
(e.g., SVM, Random
Forest, Al, Deep Learning, ICA, PCA).
CA 03173467 2022- 9- 26
[0053] The control unit may also take into account in this
case an environmental
parameter and/or a situational parameter in special configurations of some
embodiments.
[0054] In other special configurations of some embodiments,
the control unit may
use an alarm management adapted to the early warning system. In a special
configuration
of some embodiments, the control unit may be configured to take into
consideration
further physiological data of aviators, pilots and copilots, which were
provided, for
example, by means of the data interface or by the monitoring system, for
example, EKG,
heart rate, heart rate variability, oxygen saturation in the blood and body
temperature, in
the early warning system for the detection of hypoxia.
[0055] Further exemplary embodiments create processes for the
operation of a
monitoring system.
[0056] In some embodiments of the process for operating a
monitoring system,
the control unit performs in a first step an activation of the sensor
mechanism of the
monitoring system, and preparations are made for data storage along with
initialization of
a memory in a second step. Measurement-based detection of measured values of
the
sensor mechanism of the monitoring system is carried out with a time control
in a third
step. Data storage of the measured values is carried out in the memory with
corresponding time information in a fourth step. The third and fourth steps
are continued
51
CA 03173467 2022- 9- 26
continuously by the control unit until the process for operating a monitoring
system is
ended.
[0057] In some embodiments of the process for operating a
monitoring system, an
additional storage of situational parameters and/or environmental parameters
can be made
possible during the data storage of the measured values of the sensor
mechanism with the
corresponding time information in the memory.
[0058] In some embodiments of the process for operating a
monitoring system, an
additional detection of measured values of the sensor mechanism, which
detection
depends on the time control, can be made possible when an input element is
activated by
a user.
[0059] Further actions improving the present invention appear
from the following
description of some exemplary embodiments of the present invention, which are
shown in
the figures. All the features and/or advantages, including design details and
arrangements
in space, which appear from the claims, from the description or from the
drawings, may
be essential for the present invention both in themselves and in the different
combinations. The various features of novelty which characterize the invention
are
pointed out with particularity in the claims annexed to and forming a part of
this
disclosure. For a better understanding of the invention, its operating
advantages and
specific objects attained by its uses, reference is made to the accompanying
drawings and
descriptive matter in which preferred embodiments of the invention are
illustrated.
52
CA 03173467 2022- 9- 26
BRIEF DESCRIPTION OF THE DRAWINGS
[0060] In the drawings:
[0061] Figure la is a schematic view showing a monitoring
system with a sensor
mechanism;
[0062] Figure lb is a schematic view showing the monitoring
system with a
sensor mechanism;
[0063] Figure 2a is a schematic view showing a monitoring
system according to
Figure la, lb with a measurement functionality for oxygen and carbon dioxide;
[0064] Figure 2b is a schematic view showing a monitoring
system according to
Figure la, lb with the measurement functionality for oxygen and carbon
dioxide;
[0065] Figure 3 is a schematic view showing an expansion of
the variants
according to the monitoring systems according to Figures la, lb, 2a, 2h;
[0066] Figure 4 is a schematic view showing one of two
variants of the
monitoring systems according to Figures la, lb, 2a, 2b, 3 with additional
sensor
mechanisms;
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CA 03173467 2022- 9- 26
[0067] Figure 5 is a schematic view showing another of two
variants of the
monitoring systems according to Figures la, lb, 2a, 2b, 3 with additional
sensor
mechanisms;
[0068] Figure 6 is a schematic view showing a variant of the
monitoring system
according to Figure 3;
[0069] Figure 7 is a schematic view showing another variant
of the monitoring
system according to Figure 3;
[0070] Figure 8 is a schematic view showing an alternative
variant of the
monitoring system according to Figure 6; and
[0071] Figure 9 is a schematic view showing a flow chart for
determining a
pressure in a breathing mask.
DESCRIPTION OF PREFERRED EMBODIMENTS
[0072] Referring to the drawings, Figures la, lb show a
monitoring system 100,
which is connected with a measured gas line 10 to a breathing mask 20 of a
person 99.
Identical elements in Figures la, lb are designated by the same reference
numbers in
Figures la, lb. The person 99 in this Figure 1 is an aviator (pilot, copilot)
or passenger of
an airplane, especially of a jet plane (jet). The breathing mask 20 has a gas
port 21, a
connection element 23 as well as hose lines 24, 25. The hose lines 24, 25 are
used to
54
CA 03173467 2022- 9- 26
remove and feed breathing gases to the person 99. The hose lines are shown in
this
Figure la as two separate hose lines 24, 25. As is shown in Figure lb,
embodiments with
a connection element 23', in which embodiments only one hose line 25 is
present for
supplying breathing gas for inhalation, and the exhalation takes place via an
exhalation
valve 29 in the breathing mask 20 to an environment, are also possible.
Another
possibility is offered by an embodiment of a coaxial hose system, which has
two hose
lines 24, 25 as a common element. The removal and feed of breathing gases into
the
airplane or aircraft and the devices or elements necessary therefor for making
the
breathing gas available are not shown in this Figure la and in the other
figures for the
sake of clarity. The monitoring system 100 has operating elements 40, display
elements
44, at least one gas delivery module 50, and a sensor mechanism 60 with at
least one
sensor 66. The gas delivery module 50 is preferably configured as a pump PM,
more
preferably as a piezoelectric pump PM. In addition, the monitoring system 100
has a
control unit 70.
[0073]
The operating elements 40, the display elements 44, the sensor mechanism
60, and the gas delivery module 50 are connected to the control unit 70 via
signal and
data lines or control lines. These control lines or signal and data lines may
be configured,
for example, as a bus system (CAN) or network. These control lines or signal
and data
lines are not shown in Figure la as well as in the other figures for the sake
of clarity. The
control unit 70 is configured and intended to control and/or to actuate the
gas delivery
module 50 such that a delivery of breathing gases from the breathing mask 20
through the
measured gas line 10 and through a gas inlet 51 to the sensor mechanism will
take place.
CA 03173467 2022- 9- 26
A quantity or partial quantity of breathing gas is thus then available to the
at least one
sensor 66 in the gas sensor mechanism 60 in order to detect it by measurement
and/or to
analyze it and to make it available to the control unit 70 as measured values.
The control
unit 70 makes it possible to analyze and process the measured values and to
display them
at least on partial elements of the display elements 44.
[0074]
Figures 2a, 2b show monitoring systems 100, 110 according to Figures la,
lb with the peculiar feature that the sensor 66 in the sensor mechanism 60 is
configured
as an oxygen sensor 68 and, in addition, an additional sensor acting as a
carbon dioxide
sensor 64 is likewise arranged in the sensor mechanism 60. Identical elements
in Figures
la, lb, 2a, 2b are designated by the same reference numbers in Figures la, lb,
2a, 2b.
Figure 2a shows a variant 110 of a monitoring system according to Figure 2a
with an
oxygen sensor 68 and with a carbon dioxide sensor 64, wherein the monitoring
system
110 is arranged without a measured gas line 10 directly at the breathing mask
20 or is
configured as a part of the breathing mask 20. A pump PM, as in the variants
according
to Figures la, lb, 2a for delivering quantities of breathing gas from the
breathing mask 20
to the sensor mechanism 60 may optionally be eliminated. In case quantities of
gas are
optionally also to be delivered from the cabin or from the cockpit to the
sensor
mechanism, an optional pump 56 is also arranged in or at the sensor mechanism
in the
arrangement according to Figure 2b. The arrangement of such an optional pump
56 in
the monitoring system 110 is not shown for the sake of clarity. An energy
storage device
85 is also shown as an example in Figure 2b, and it is also an optional
component of the
embodiments according to Figures la, 2a, 3, 4, 5 in a similar configuration.
Such an
56
CA 03173467 2022- 9- 26
energy storage device 85, configured as a primary cell or chargeable or
rechargeable
battery (rechargeable battery, storage battery), has a suitable configuration
for supplying
the various components (60, 70, 40, 44, 75) of the monitoring systems 110, 108
(Figure
4), 109 (Figure 5), 100 (Figure la, Figure lb, Figure 2a, Figure 3) with
electrical energy.
An optional embodiment with an additional display element 45 arranged at or in
the mask
20 is shown in Figure lb, and there also is a similar configuration as an
optional
component of the configurations according to Figures la, 2a, 3, 4, 5. This
additional
display element 45 is connected to the control unit 70 by means of signal or
data lines,
not shown for the sake of clarity. This additional display element may be
configured, for
example, in the form of an in-mask display or head-up display. Figure 2a
additionally
shows a data interface 90, which may be configured, on the one hand, to
receive data
from the outside and then to provide these data for the control unit 70. The
data lines
belonging to the data interface are not shown in Figure 2a as well as in the
other figures
for the sake of clarity. On the other hand, for example, measured values of
the
monitoring system 100 or of the sensor mechanism 60 can be sent to the outside
by
means of the data interface 90. Current environmental parameters or
situational
parameters on the situation of the airplane or aircraft can thus be received
via this data
interface 90, for example, from components of the airplane or aircraft, and
made
available to the control unit 70 for being taken into consideration in the
processing of
measured values and/or in the control of the pump PM 50. Furthermore, measured
values
and/or measured variables derived from the measured values or parameter as
well as
information or state data may be made available by the control unit 70 by
means of the
data interface to components of the airplane or aircraft. It is possible in
this manner, for
57
CA 03173467 2022- 9- 26
example, to display measured values and/or measured values derived from the
measured
values or parameters as well as information or state data on external display
elements of
the airplane or aircraft. The data interface may have a unidirectional or
bidirectional
configuration, for example, a wired (CAN bus, LAN, Ethernet, RS485, NMEA183)
or
wireless (WLAN, Bluetooth, NFC) configuration. The following parameters shall
be
mentioned, for example, as current environmental parameters for an
environmental
situation of the airplane or aircraft:
- ambient pressure outside the cockpit or cabin of the
airplane or aircraft,
- ambient temperature within the cockpit or cabin of the
airplane or aircraft,
- gas composition within the cockpit or cabin of the
airplane or aircraft,
- absolute and/or relative humidity within the cockpit
or cabin of the
airplane or aircraft,
- density and/or ambient pressure within the cockpit or
cabin or the airplane
or aircraft,
- ambient temperature within the cockpit or cabin of the
airplane or aircraft,
- gas composition within the cockpit or cabin of the
airplane or aircraft,
- ambient pressure outside the cockpit or cabin of the
airplane or aircraft,
- ambient temperature outside the cockpit or cabin of
the airplane or
aircraft,
- gas composition outside the cockpit or cabin of the
airplane or aircraft,
- absolute and/or relative humidity outside the cockpit
or cabin of the
airplane or aircraft,
58
CA 03173467 2022- 9- 26
- density and/or ambient pressure outside the cockpit or
cabin of the
airplane or aircraft,
- ambient temperature outside the cockpit or cabin of
the airplane or
aircraft,
- gas composition outside the cockpit or cabin of the
airplane or aircraft,
- pressure level, pressure changes, pressure-time curve,
pressure differences, pressure fluctuations in the breathing gas, breathing
gas
mixture or in the breathing air in the feed line to the aviator, pilot or
copilot,
- pressure level, pressure changes, pressure
differences, pressure
fluctuations in the on-board equipment provided (e.g., gas tanks, pressurized
oxygen cylinders, air intake, gas processing, filtering, gas delivery) for
breathing
gas, breathing gas mixture or breathing air.
[0075] For example, the following parameters shall be
mentioned as situational or
current situational parameters of the situation of the airplane or aircraft:
- a flight direction,
- a flight altitude,
- a flight axis position,
- a flight position,
for example, inverted flying, curve flight, nosedive, descent, ascent,
- a flight velocity,
- a horizontal acceleration,
- a vertical acceleration,
59
CA 03173467 2022- 9- 26
- a yaw angle or a roll angle,
- a residual oxygen or air reserve, and
- a residual pressurized oxygen gas or compressed air
reserve.
[0076] Figure 3 shows a monitoring system 100 according to
Figure la, lb, 2a
with the peculiar feature that an input element 80 with a signal or data
connection to the
control unit 70 is arranged at the monitoring system. Identical elements in
Figures la, lb,
lc, 2, 3 are designated by the same reference numbers in Figures la, lb, lc,
2, 3. It is
made possible to the aviator, pilot or copilot via the input element 80 to
mark certain
events or situations of the flying operation, as well as certain personal
events, for
example, events, situations or symptoms related to health, such as fever,
racing heart or a
feeling of dizziness, during the course of the mission. This marking can be
used by the
control unit 70 to combine the events or situations with time information and
then to store
the combination of time information, event or situation in a memory 75. The
memory 75
may be configured as a volatile or non-volatile memory (RAM, ROM, EEPROM) and
be
arranged either as a fixed component or as a removable memory module (USB
stick, SD
card) in or at the monitoring system 100, 110 (Figure 2b). A provision and/or
an
exchange of the data may also be made possible with an external analysis unit,
not shown
in the figures, for example, by means of a data interface 90 in a
configuration similar to
that shown and described in Figure 2b. This input element 80 can thus be used
to
complement the detected measured values of the sensor mechanism 60 and the
events and
situations of the flying operation by additional information, which is made
available by
means of the input element of the aviator, pilot or copilot, and to provide it
with time
CA 03173467 2022- 9- 26
information, for example, in the form of a time stamp. It is also possible,
however, to
configure the input element as a panic button, which makes it directly
possible to the
aviator, pilot or copilot to make themself noticeable in a situation that is a
special
situation based on his own perception, for example, in a situation with a
special,
objectively or subjectively perceived danger situation or in a risk situation.
The marked
measured values and/or events, situation and also the special situations can
be made
directly available to the direct external outside environment for example, by
means of the
data interface 90, and they can possibly be transmitted, likewise directly (on-
line), via a
communication system of the airplane or aircraft, to a ground station or to
other airplanes
or aircraft. Furthermore, an analysis of the marked measured values and/or
events,
situations and special situations later after the mission (off-line) can be
made possible by
means of the memory 75 and/or the data interface 90.
[0077] Figures 4 and 5 show variants of the monitoring system
100, 110
according to Figures la, lb, 2a, 2b, 3 with additional components of the
sensor
mechanism 60. The corresponding control lines or signal and data lines for the
additional
sensors of the sensor mechanism 60 are not shown in Figures 4 and 5 for the
sake of
clarity. Identical elements in Figures la, lb, lc, 2, 3, 4, 5 are designated
by the same
reference numbers in Figures la, lb, lc, 2, 3, 4, 5. These additional sensors
in the sensor
mechanism 60 may be used for determining current environmental parameters
within
and/or outside the cockpit or cabin of the airplane or aircraft and/or for
determining
current situational parameters and situations as well as for determining
physical
properties for an additional determination of the composition of the breathing
gas. The
61
CA 03173467 2022- 9- 26
following additional sensors, which shall also be considered to represent
optional
possibilities of configuration for Figures la, lb, 2a, 2b, 3, 5, shall be
shown as examples
as additional components of the sensor mechanism 60 in the monitoring system
108 in
Figure 4:
- at least one acceleration sensor 61
in the form of a 2-axis or 3-axis acceleration sensor (accelerometer),
- at least one compass sensor 62,
for example, an electronic compass,
gyro compass or fluxgate compass,
- at least one altitude sensor 58, and
- at least one gyro sensor 63.
[0078] The following additional sensors, which should also be
considered to be
optional possibilities of the configuration for Figures la, lb, 2a, 2b, 3, 4,
are shown as
examples in Figure 5 as additional components of the sensor mechanism 60:
- at least one temperature sensor 69, 69',
- at least one pressure sensor 67, 67',
- at least one humidity sensor 59, 59'.
[0079] The additional sensors in the sensor mechanism 60 may
be configured as
pressure sensors, which may be configured and intended to detect by
measurement an
ambient pressure from the environment, especially a pressure or a density
within and/or
outside the cockpit or cabin of the airplane or aircraft and to make it
available to the
control unit 70. The additional sensors in the sensor mechanism 60 may be
configured as
62
CA 03173467 2022- 9- 26
temperature sensors, which may be configured and intended to detect by
measurement an
ambient temperature in the environment, especially a temperature within and/or
outside
the cockpit or cabin of the airplane or aircraft and to make it available to
the control unit
70. These additional sensors in the sensor mechanism 60 may be configured as
humidity
sensors for detecting an absolute or relative humidity of the environment,
which may be
configured and intended to detect by measurement a humidity in the
environment,
especially within and/or outside the cockpit or cabin of the airplane or
aircraft and to
make it available to the control unit 70. The additional sensors in the sensor
mechanism
60 may be configured as at least one additional gas sensor 65 for detecting a
gas
composition in the environment, which may be configured and intended for
detecting by
measurement a gas composition in the environment, especially within and/or
outside the
cockpit or cabin of the airplane or aircraft and to make it available to the
control unit 70.
Electrochemical gas sensors, catalytic gas sensors, optical, infrared optical
gas sensors,
photoionization gas sensors, solid electrolyte gas sensors or semiconductor
gas sensors
may be used as other gas sensors in order to make it possible to also monitor
the
breathing gas concerning additional substances, such as carbon monoxide,
hydrocarbons,
residues or products of combustion processes, in addition to the measurement-
based
detection of concentrations of oxygen and carbon dioxide. A reversing valve 55
shown in
Figure 4, configured, for example, as a valve module or as a part of a valve
module,
makes possible the switching of quantities or partial quantities of gas
samples between
the gas inlet 51 and another gas port 52. It is thus made possible to deliver
breathing gas
from the breathing mask 20 to the sensor mechanism 60 by means of the pump PM
50, on
the one hand, but it is also possible, in addition, to deliver quantities of
gas or gas mixture
63
CA 03173467 2022- 9- 26
from an environment 5 to the sensor mechanism 60 by means of the pump PM and
to
detect it by measurement by means of the sensor mechanism 60. The reversing
valve 55
is controlled by the control unit 70. Outside air can thus be fed from the
outside of the
airplane or aircraft or inside air can be fed from the cabin or cockpit of the
airplane or
aircraft via the additional gas port 52 and monitoring of gas concentrations
in the
breathing mask 20, cockpit, cabin or outside air can alternatingly be made
possible, with
control by the control unit 70.
[0080]
The additional sensors 59', 64', 68', 69', which are shown in Figure 5 in
the
monitoring system 109 in addition to the other gas sensors 65 and to the
sensors 59, 67,
69, are connected pneumatically or fluidically to another pump PA 56.
Identical elements
in Figures la, lb, lc, 2, 3, 4, 5 are designated by the same reference numbers
in Figures
la, lb, lc, 2, 3, 4, 5. This additional pump PA 56 makes possible the feed of
gas from an
environment 5 via an additional gas port 53, for example, of outside air from
the outside
of the airplane or aircraft or of inside air from the cabin or cockpit of the
airplane or
aircraft. The additional pump PA 56 is controlled by the control unit 70.
Outside air
from the outside of the airplane or aircraft or inside air from the cabin or
cockpit of the
airplane or aircraft can thus be fed via the additional gas port 53. A
simultaneous
monitoring of gas concentrations in the breathing mask 20 and of gas
concentrations in
the cockpit, cabin or outside air is thus made possible. Additional sensors in
the sensor
mechanism 60 may be configured to detect the current situation of the airplane
or aircraft
by measurement. A current flight situation with flight altitude, flight
direction, flight
velocity, flight acceleration, flight position with orientation in space (XYZ
orientation)
64
CA 03173467 2022- 9- 26
and flight situation or flight maneuver (e.g., ascent, descent, curve flight,
landing
approach, start) can be determined by the control unit (70) by means of the
data of an
acceleration sensor 61, preferably configured as a 3-axis acceleration sensor
(3-axis
accelerometer) in combination with an altitude sensor 58 (altimeter), gyro
sensor 63 and
by the optional addition of information of a compass sensor 62.
[0081]
Figure 6 shows a variant as a variant of Figure 3, wherein the pump PM 50
or the gas transport module is arranged at a gas outlet 49 of the monitoring
system 100'.
Compared to the variant shown in Figure 3 with the pump at the gas inlet of
the
monitoring system, this has the advantage that no traces or impurities can
reach the
monitoring system 100', especially the sensor mechanism 60 with a carbon
dixoide sensor
64 and with an oxygen sensor 68, from the pump PM 50. Identical elements in
Figures
la, lb, lc, 2, 3, 4, 5, 6 are designated by the same reference numbers in
Figures la, lb,
lc, 2, 3, 4, 5, 6. Components that may be needed for controlling the pump PM
50 and for
the feed of quantities of gases are preferably arranged in the immediate
vicinity of the
pump PM 50. A pressure sensor 47, a flow sensor 48 and a shut-off valve 57 are
arranged for this purpose close to the pump PM 50. The flow sensor 48 is used
for a
measurement-based control of the flow rate delivered by the pump (PM) 50.
After
flowing through the pump PM 50 and the flow sensor 48, the quantity of gas
being
delivered flows to the outside of the monitoring system 100' into the
environment 5. The
pressure sensor 47 is arranged upstream in the gas stream in relation to the
shut-off valve
57 such that the pressure measurement can detect the mask pressure in the
breathing
mask 20, which pressure is identical now to the pressure level at the gas
inlet 51 and to
CA 03173467 2022- 9- 26
the pressure level in the measured gas line 10 in the closed state of the shut-
off valve 57
in the now no-flow state. As an alternative, the pressure sensor may also be
arranged at
the gas stream in the vicinity of the gas inlet, at the measured gas line 10
or close to the
gas sensors 60, 64, 68. A reversing valve 55, which, described in a comparable
manner
as it was described in connection with the reversing valve 55 in Figure 4,
makes possible
a switching of quantities or partial quantities of gas samples between the gas
inlet 51 and
an additional gas port 52, is provided at the gas inlet 51. The reversing
valve is
preferably configured as a 3/2-way valve. This arrangement makes it possible
to deliver,
on the one hand, breathing gas from the breathing mask 20 to the sensor
mechanism 60 at
the gas inlet 51 by means of the pump PM 50, but it is, moreover, also
possible to deliver
quantities of gas or gas mixture through the additional gas inlet 52 by means
of the pump
PM 50 from an environment 5 to the sensor mechanism 60 and to detect it by
measurement by means of the sensor mechanism 60. The reversing valve 55 is
controlled
by the control unit 70. Outside air can thus be fed from the outside of the
airplane or
aircraft or inside air can be fed from the cabin or cockpit of the aircraft
via the additional
gas port 52 and - with control by the control unit 70 - a monitoring of gas
concentrations
in the breathing mask 20, cockpit, cabin or outside air can alternatingly be
made possible.
To protect the sensor mechanism 60 from moisture or condensation, which is fed
from
the breathing mask 20 through the measured gas line 10 by means of the pump PM
50 to
the sensor mechanism 60, a filter element (HME filter) 54 may be arranged in a
series
connection in the measured gas line or at the outlet of the reversing valve
55.
66
CA 03173467 2022- 9- 26
[0082] Instead of the input element 80 configured in the form
of a switching
element, as in the device 100 according to Figure 3, an acceleration sensor
61, which is
configured and intended as an alternative actuating or input element for
detecting
actuations performed by the aviator by hand, is provided as an input element
in this
embodiment 100' according to Figure 6. By means of this alternative actuating
or input
element or the acceleration sensor 61, the aviator, pilot or copilot is
enabled to mark
defined events or situations of the flying operation and also to mark defined
personal
events, situations or symptoms, for example, those related to health, such as
fever, racing
heart or a feeling of dizziness in the time course of the mission. This
marking may be
used by the control unit 70 to combine the events or situations with time
information and
then to store the combination of time information and event or situation in a
memory 75.
The memory 75 may be configured as a volatile or non-volatile memory (RAM,
ROM,
EEPROM) and be arranged either as a fixed component or as a removable memory
module (USB stick, SD card) in or at the monitoring system 100'. Provision
and/or
exchange of the data with an external analysis unit, not shown in the figures,
may also be
made possible, for example, by means of a data interface 90 in a configuration
similar to
that shown and described in Figure 2b. This alternative actuating or input
element or the
acceleration sensor 61 may thus be used to complement the detected measured
values of
the sensor mechanism 60 and the events and situations of the flying operation
by
additional information, which is provided by means of the alternative
actuating or input
element or of the acceleration sensor 61 by the aviator, pilot or copilot, and
to provide it
with time information, for example, in the form of a time stamp. It is,
however, also
possible to configure the alternative actuating or input element or the
acceleration sensor
67
CA 03173467 2022- 9- 26
51 as a panic button, which makes it directly possible for the aviator, pilot
or copilot to
make themself noticeable in a situation that is a special situation according
to his
perception, for example, a situation with a special, objectively or
subjectively perceived
danger situation or a risk situation. The marked measured values and/or
events, situations
as well as the special situations may be made available to the direct external
environment,
for example, by means of the data interface 90 and may optionally be
transmitted,
likewise directly (on-line) via a communication system of the airplane or
aircraft, to a
ground station or to other airplanes or aircraft. Furthermore, an analysis of
the marked
measured values and/or events, situations and special situations later after
the mission
(off-line) is made possible by means of the memory 75 or of the data interface
90.
[0083]
Figure 7 shows, in a detail view as a detail drawing of the area around
the
gas inlet 51 and unlike the view in Figure 6, a monitoring system 111 with an
arrangement of filter element (HME filter) 54, pump PM 50, sensor mechanism
60,
pressure sensor 47, flow sensor 48, shut-off valve 57 in an arrangement at the
gas inlet 51
without reversing valve for switching between a monitoring of breathing gases
of the
pilot and a monitoring of the cabin air. Identical elements in Figures la, lb,
lc, 2, 3,4, 5,
6, 7 are designated by the same reference numbers in Figures la, lb, lc, 2, 3,
4, 5, 6, 7.
The pressure sensor 47 is arranged upstream, in the gas stream in relation to
the shut-off
valve 57 such that the flow measurement can detect in the now no-flow state
the mask
pressure in the breathing mask 20, which is now identical to the pressure
level at the gas
inlet 51 and in the measured gas line 10. As an alternative, the pressure
sensor 47 may
68
CA 03173467 2022- 9- 26
also be arranged at the gas stream in the vicinity of the gas inlet 51, at the
measured gas
line 10 or close to the sensor mechanism 60 with the gas sensors.
[0084]
Figure 8 shows, as a detail view as a detail drawing of the area around
the
gas inlet 51 and unlike the view in Figures 6 and 7, a monitoring system 111,
112 with an
arrangement of filter element (HME filter) 54, pump PM 50, sensor mechanism
60,
pressure sensor 47 at the gas inlet 51 and with a reversing valve 55
configured as a 3/2-
way valve. Identical elements in Figures la, lb, lc, 2, 3, 4, 5, 6, 7, 8 are
designated by
the same reference numbers in Figures la, lb, lc, 2, 3, 4, 5, 6, 7, 8. The
reversing valve
55 can release the path for quantities of gas from an environment 5, e.g., the
cabin, to the
sensor mechanism 60 and thus make a cabin air monitoring possible. The
reversing valve
closes at the same time the path for quantities of gas from the breathing mask
20. The
reversing valve 55 also has in this configuration according to Figure 8 a
manner of
functioning as a shut-off valve for the performance of a measurement maneuver
for
determining the pressure in the breathing mask in addition to the switching
between the
measurement of breathing gases and cabin air. The pressure sensor 47 is
arranged at the
gas inlet 51 in relation to the reversing valve 55 and the measured gas line
10 such that in
the state of the reversing valve 55 with cabin air monitoring, the pressure
measurement
can detect the mask pressure in the breathing mask 20, which is now identical
to the
pressure level at the gas inlet 51 and in the measured gas line 10. The
reversing valve 55
makes it possible to switch between monitoring of breathing gases of the pilot
and
monitoring of the cabin air.
69
CA 03173467 2022- 9- 26
[0085] Figure 9 schematically shows a procedure 200 of a
measurement
maneuver for determining a pressure level in the breathing mask 20 (Figure 6)
with a
monitoring system 100' according to Figure 6. Identical elements in Figures
la, lb, lc, 2,
3, 4, 5, 6, 7, 8, 9 are designated by the same reference numbers in Figures
la, lb, lc, 2, 3,
4, 5, 6, 7, 8, 9. Beginning with a start 201, the measurement maneuver is
carried out in
an embodiment with a shut-off valve (flow-lock valve) 57 (Figure 6) by the
control unit
70 (Figure 6). A deactivation 202 of the pump PM 50 (Figure 6) is carried out
after the
START 201, and the shut-off valve 57 (Figure 6) is closed at that time or with
a slight
time delay. The flow is thus stopped in the measured gas line 10 (Figure 6)
and the sensor
mechanism 60 (Figure 6) comes into a resting state. A first measurement
operation of a
pressure measurement 204 is carried out to determine the static pressure
level. The shut-
off valve 57 (Figure 6) is then opened 205 and the pump PM 50 (Figure 6) is
activated
206. The pump PM 50 (Figure 6) begins to suck quantities of gas from the
breathing
mask 20 (Figure 6) through the measured gas line 10 (Figure 6) and the sensor
mechanism 60 (Figure 6) at a defined flow rate in the range of 50 mL/min to
100
mL/min. A flow measurement 207 is carried out now with the flow sensor 48
(Figure 6)
to control and monitor the flow rate. An additional measurement operation of a
pressure
measurement 208 is subsequently carried out to determine the dynamic pressure
level. A
difference value, which indicates the current pressure drop over the pneumatic
system, is
determined 209 from the pressure measured values of the first pressure
measurement 204
and the additional pressure measurement 208. The measurement maneuver
procedure
thus comes to an end 210. The difference value thus determined can then be
made
CA 03173467 2022- 9- 26
available and used to determine the mask pressure during the further operation
of the
monitoring system during the mission of the aircraft.
[0086] While specific embodiments of the invention have been shown and
described in
detail to illustrate the application of the principles of the invention, it
will be understood
that the invention may be embodied otherwise without departing from such
principles.
71
CA 03173467 2022- 9- 26
LIST OF REFERENCE NUMBERS
Environment, atmosphere, outside air, cockpit or cabin
Measured gas line
Breathing mask
21 Gas port at the breathing mask
24, 25 Hose lines
23, 23' Connection element
29 Exhalation valve
40 Operating elements
44, 45 Display elements
46 Wireless interface, radio interface
47 Pressure sensor
48 Flow sensor (flow sensor, delta P sensor)
49 Gas outlet
50 Gas delivery module, pump PM
51 Gas inlet
52, 53 Additional gas port
54 Filter element (HME filter)
55 Reversing valve (3/2-way valve), valve
module
56 Additional pump PA
57 Shut-off valve (flow lock valve)
58 Altitude sensor (altimeter)
72
CA 03173467 2022- 9- 26
59, 59' Humidity sensor
60 Sensor mechanism
61 Acceleration sensor
62 Compass sensor
63 Gyro sensor
64, 64' Carbon dioxide sensor
65 Additional gas sensor
66 Sensor
67, 67' Pressure sensor
68, 68' Oxygen sensor
69, 69 Temperature sensor
70 Control unit
80 Input element
90 Data interface
99 Person, pilot, aviator
100, 100' Monitoring system
108, 109, 110, 111, 112 Monitoring system
200 Measurement maneuver procedure
201 Beginning, START
202 Pump: Deactivation
203 Shut-off valve: Close valve
204 First pressure measurement: Static
pressure level
205 Shut-off valve: Open valve
73
CA 03173467 2022- 9- 26
206 Pump: Activation
207 Flow measurement
208 Additional pressure measurement: Dynamic
pressure level
209 Determination of the value of the current
pressure drop
210 End, STOP
74
CA 03173467 2022- 9- 26
