Note : Les descriptions sont présentées dans la langue officielle dans laquelle elles ont été soumises.
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In an ILS (instrument landing system), two trans-
mitters are located near an airport to transmit an electrical
signal corresponding to glide slope and localizer information.
The airborne ILS equipment will include two receivers with
corresponding display(s), that being a glide slope display
and a localizer display, both of which conventionally use
plus or minus 150 microamp meter movements. Meter movements
currently representing the state of the art are of the d'Arson-
val type which operate from an open loop in an effort to
process the raw data.
The information presented by the various indicators
may also be routed to an auto pilot and/or flight director
when available. The raw data is processed in the auto pilot
and/or flight director and is utilized to automatically oper-
ate the flight controlling surfaces of the aircraft. In -
any event, when an auto pilot effectively flies the airplane,
the pilot will nonetheless visually monitor appropriate meter
movements to ascertain that the auto pilot is operating cor- ~-
rectly.
The subject invention has primary utility with avi-
onics equipment indicating the above described glide slope
and localizer data. However, other indicators heretofore re-
quiring d'Arsonval meter movements may benefit substantially
~y the unique circuit combination and rotary solenoid actua-
tor. For illustrative purposes, the glide slope data is re-
ceived and summed together with the output from an optical
position transducer. Additionally, a flag signal input is
delivered to the summer circuit. In this fashion, a closed
loop is formed for operating the rotary solenoid and thusly
moving the indicator pointer to the proper location. -
The rotary solenoid is provided with a pair of re-
tract poles which automatically moves the indicator pointer,
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via a rotary magnet, out of view if a flag signal (or loss
of power) occurs and is accomplished without the use of springs
or other tension biasing methods. Further, two pointers are
in fact operated by the single magnet. A scale is provided
for each pointer and a switch means permits either one of the
two scales to have pertinent data thereon.
An object of the invention is to provide a uniquely
constructed circuit and indicator for visually displaying glide
slope and localizer dataO
A further object of the invention is to provide a
eircuit of the character described which utilizes a closed
loop and which has obviated the necessity of conventional d'
'Arsonval meter movement indicator devices.
A still further object o~ the invention is to pro-
vide a uniquely constructed rotary solenoid indicating device
that has particular utility when utilized in an avionics dis-
play device.
Another object of the invention is to provide a de-
vice capable of accepting selectable inputs and displaying
data corresponding to the inputs on at least two scales. This
- feature is accomplished at least in part by the actuator hav-
ing two pointers thereon and a switch means capable of causing
the desired scale to be read at the proper time.
Another object of the invention is to provide a clos-
ed loop circuit of the character described above which incorp-
orates the utilization of an optical transducer in conjunction
with a uniquely constructed rotary solenoid for optimizing
the display of glide slope and localizer data to the pilot
utilizing subject deviceO
Another objeet of the invention is to provide a u-
niquely eonstrueted display deviee for avionics equipment w
which is extremely rugged, substantially impervious to the
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ambient conditions surrounding the indicator, and which provides
reliable flag or failure information when the appropriate signals
are not being received. It is a feature of this object that
the circuitry utilized therewith is a closed loop circuit
and that a rotary solenoid replaces more conventional d'Arsonval
meter movements within the circuit. The rotary solenoid, with
feedback and retract poles, optimizes the flag condition
positioning of the indicator pointer used therewith in a manner
not known in any prior art devices.
A further object of the invention is to provide a
unique circuit and actuating device for use in avionics equipment
of any type which presents a visual indication of electrically
received raw data. It is a feature of the invention that it is
particularly applicable to glide slope and localizer information
but it should be understood that the subject invention is
adaptable to and advantageously used with many other types
of avionics equipment.
Another object of the invention is to provide uniquely
constructed visual display for avionics equipment that is
inexpensive, reliable and substantially insensitive to vibrations
and dusty atmosphere.
A further object is to provide an improved avionics
display device which insures that accurate updated information
is being displayed thereon. It is a feature of the invention
that the closed loop circuit and optical transducer cooperate
in updating the displayed data for optimizing pilot monitoring
and corrective actions.
The invention is directed to an avionics indicator
device having an indicator pointer operable to visually indicate
aircraft deviation from a preselected condition. The device
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comprises a deviation signal input, means for producing an
electrical signal corresponding to the position of said pointer,
means for summing said pointer position signal with said
deviation signal input, said summing means having an output
signal corresponding to the difference in said deviation signal
input and said pointer position signal, means for positioning
said pointer in accordance with the output signal emanating
from said summing means, said pointer positioning means including
a rotary solenoid, said solenoid having a rotary magnet that
is positionable in accordance with said summing means output
signal, said indicator pointer being mechanically linked to said
rotary magnet and operable to indicate said aircraft deviation,
and wherein said rotary solenoid includes at least one retract
pole located adjacent said rotary magnet, said retract pole
operable to automatically remove said pointer from view during
a flag condition.
The invention is also directed to an avionics
indicator device having an indicator pointer operable to visually
indicate aircraft deviation from a preselected condition. The
device comprises a deviation signal input, means for producing
an electrical signal corresponding to the position of said
pointer, means for summing said pointer position signal with
said deviation signal input, said summing means having an
output signal corresponding to the difference in said deviation
signal input and said pointer position signal, means for
positioning said pointer in accordance with the output signal
emanating from said summing means, andwherein said device has
- a flag condition signal input thereto, said flag signal being
applied to said summing means, means operable in accordance with
a preselected flag signal condition to automatically remove said
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pointer from view thereby informing a pilot that said device
is not operating to indicate said aircraft deviation.
The pointer positioning means can include a rotary
solenoid, said solenoid having a rotary magnet that is positionable
in accordance with said summing means output signal, said
indicator pointer being mechanically linked to said rotary magnet
and operable to indicate said aircraft deviation.
The invention is also directed to an avionics indicator
device having an indicator from a preselected condition. The
device comprises a deviation signal input, means for producing
an electrical signal corresponding to the position of said
pointer, means for summing said pointer position signal with said
deviation signal input, said summing means having an output
signal corresponding to the difference in said deviation signal
input and said pointer position signal, means for positioning
said pointer in accordance with the output signal emanating from
said summing means, and wherein said signal producing means
includes an optical means for detecting the position of said
pointer.
The pointer positioning means can include a means for
positioning at least two pointers simultaneously, each one
of said pointers having a scale for different aircraft deviation
display information. The device can also include a switch means
for causing one or the other of said scales to indicate
deviation information even though both of said pointers are
visible.
The pointer positioning means can also include a rotary
solenoid, said solenoid having a rotary magnet that is positionable
in accordance with said summing means output signal, said indicator
pointer being mechanically linked to said rotary magnet and
operable to indicate said aircraft deviation.
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The rotary solenoid can also include at least one
retract pole located adjacent said rotary magnet, said retract
pole operable to automatically remove said pointer from view
during a flag condition.
In the combination, the device can have a flag
condition signal input thereto, said flag signal being applied
to said summing means, and means operable in accordance with a
preselected flag signal condition to automatically remove said
pointer from view thereby informing a pilot that said device
is not operating to indicate said aircraft condition. The
pointer positioning means can include a rotary solenoid, said
solenoid.having a rotary magnet that is positionable in
accordance with said summing means output signal, said indicator
pointer being mechanically linked to said rotary magnet and
operable to indicate said aircraft deviation.
These and other objects of the invention, together
with the features of novelty appurtenant thereto, will appear
in the course of the following description.
In the accompanying drawings, which form a part of
the specification and are to be read in conjunction therewith
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and in which like reference numerals are employed to indicate
like parts in the various views;
FIG. 1 is the front elevational view of an avionics
indicator device showing the location of the glide slope point-
er and the localizer deviation bar indicator in conjunction
with other indicating devices;
FIG. 2 is a block diagram of the closed loop circuit
employed with the subject invention;
FIG. 3 is a more detailed circuit diagram of the
circuitry shown in FIG. 2;
FIG. 4 is a top plan view of a portion of the rotary
solenoid actuator;
FIG. 5 is a partial sectional view showing the rota-
ry solenoid actuator from the side indicating the position
of the retract pole pieces in conjunction with the deflection
poles and rotary magnet; and
FIG, 6 is a perspective view of the rotary solenoid
and associated pivotal pointer carrying mechanism.
Turning now more particularly to the block diagram
shown in FIG. 2, the glide slope deviation signal from the
ILS transmitter is initially delivered to a first order lag
filter 10. This filtered signal is then fed to a summer 11
via the line lOa. As will be seen, a feedback signal will
be present on line 12 and also directed to summer 11. The
third input thereto includes the flag signal input (on line
18) which is sent through level detector l9 and finally fed
to the summer via line 20. Accordingly, summer 11 sums the
glide slope deviation signal with some gain applied thereto
on line lOa with the feedback signal on line 12 and further
with the flag signal after passing through level detector
via line 20.
In any event, the glide slope deviation signal,
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combined with the other two signals, is directed to a second
order lag filter indicated by 13 via line 13a. From here (fil-
ter 13) the signal is directed to the actuator 14 with the
output of same being mechanically linked via 15 to the optical
position transducer 16. The optical position transducer has
an output directed to the shaping network 17 and from thence
via the above described line 12 back to summer 11. It should
be noted that the optical position transducer is similar in
design and operability to that detailed in the co-pending ap-
plication of Clarence Van Englehoven, bearing serial
number 216,358, and which is owned by the same assignee as
the subject invention. - -
As will be seen, the above described block diagram
is a closed loop device with both the glide slope deviation
and flag signal being delivered to the summer 11. Further,
the actuator which will be described in more detail later, -
operates to move the indicator pointer(s) to the appropriate
position and further will automatically remove the pointer
from sight when a "flag condition" is to be displayed. This
particular circuit provides a substantial increase in band - -
width thereby accurately presenting information to the pilot
with little or no lag. Accordingly, data is presented for
aircraft operation that can be acted upon almost instantan- -
eously and will not present late or needless information which -
could heretofore arrive after aircraft navigation correction
maneuvers were needed.
A more complete circuit diagram, disclosed in FIG.
3, operates in a similar fashion to that discussed with respect
to the block diagram in FIG. 2. The circuitry (in FIG. 3) will
likewise he discussed in terms of glide slope deviation with
the glide slope deviation signal input means shown in the up-
per left hand corner thereof. As will be seen VNAV informa-
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tion and the two pointer concept are further improvements.
The operational amplifier circuit generally indicated by the
number 25 operates to provide a proper impedance matching ele-
ment for the input signal and gain scaling and also rejects
the common mode voltage accompanying the received signal.
The operational amplifier circuit 25 (as shown including the
associated resistors) accepts standard glide slope ARINC in-
puts for further utilization thereof. The output from the
operational amplifier circuit 25 is directed to a first order
lag filter generally represented by the numeral 26. This oper-
ational amplifier circuit including the associated resistors
and capacitors gets rid of noise and is generally a gain one
element with a half a second first order lag designation.
The output from the operational amplifier circuit
26 is delivered via line 26a to a summer circuit 27. This
circuit (including its associated operational amplifier) is -,
a gain five stage which increases the amplitude of the devia-
tion signal to a proper level for further operation thereof.
The output of the summer 27 is delivered to the second order
lag filter circuit identified by the numeral 28 includes the
indicated operational amplifier with the various capacitors
and resistors. Accordingly, the circuit has taken a low level
signal at the glide slope input of approximately 150 micro
amps and has amplified same and rejected all unwanted compon-
ents so that a proper output from the second order lag filter
circuit 28 is delivered to the transistor Q9. The output from
Q9 on the emitter thereof is delivered to the actuator and
glide slope indicator which is a rotary solenoid that will
be discussed in more detail with respect to FIGS. 4 and 5.
Transistor Q9 will have positive ~oltage from the indicated
power supply coming in on the collector thereof so that the
output from the second order lag filter 28 is controlled in
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a linear fashion as it is being fed to the glide slope pointer
and indicator (conveniently referred to in both FIGS. 2 and
3 by the numerals 14). The optical position transducer is
indicated by the numeral 29 in FIG. 3 and operates in a manner
similar to that disclosed in the above mentioned patent appli-
cation of Clarence Van Englehoven. As discussed in the Van
Englehoven application, a light emitting diode (CRl) will il-
luminate a portion of two photo resistors Rl and R2 which
are located in the associated bridge circuit. Since the glide
slope pointer has a movable shutter (not shown) associated
therewith that controls the amount of light impinging on the
photo resistors, the bridge circuit configuration will produce
a differential voltage directly proportional to the position
pointer. This optical circuit produces a position signal di-
rectly proportional to the glide slope pointer position with
the output of same going to another operational amplifier cir~ ~ -
cuit 30 that develops a differential signal and impedance match-
es the input thereto. Actually, the operational amplifier
circuit 30 may be thought of as a shaping circuit since, with
any servo mechanism and in particular with the rotary solenoid
discussed later, the device will be in operation at a fast
rate even though the feedback is somewhat slower. Accordingly,
a lead network compensating for the difference in rates is - -
utilized herein. This circuit actually will derive the first
derivative of the pointer position signal proportional to the
change occurring so that the feedback loop may react accord- --
ingly.
The output from the circuit 30 is directed to the
above mentioned summer circuit 27 thereby closing the loop
and obtaining a stabilized output from the actuator (the rotary
solenoid). With a positive input being delivered to the sum- -
mer, the output signal resulting from the pointer movement
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generates in effect a negative signal which cancels the posi-
tive input. Accordingly, the error signal emanating from sum-
mer 27 operates to keep the glide slope pointer properly posi-
tioned. As a result, a gradual shift in pointer indication
is obtained and the accuracy of same along with ability to
track the input are su~stantially increased over what has here-
tofore been known in the avionics art.
Also indicated on the left hand portion of FIG. 3
is an input designated as GS flag or glide slope flag. This
input, via the appropriate switch contacts, is delivered to
an impedance matching stage which includes the operational
amplifier generally indicated by the numeral 31. This stage
also has a substantial gain with the output of same being di-
rected to a hysteresis switch level detector 32. This oper-
ational amplifier (32) operates to monitor the input voltage
so that when same reaches a certain level it changes or immedi-
ately increases to the large positive voltage. When the glide
slope flag level reaches a certain stage, (the flag level
normally is about a 260 micro amp magnitude), it is required
that a flag condition be shown. In this event, the output
from the hysteresis switch level detector 32 is delivered di-
rectly to the operational amplifier circuit 28 along with the
summer output from the circuit 27. The signal outputs through
resistors R3 and R4 are delivered to the circuit 28 and oper-
ate to turn off transistor Q9 which effectively cuts off the
power to the glide slope pointer actuator circuit. As will
be shown, glide slope pointer is then magnetically pulled out
of view so that if there was any type of a loss of power,
the magnet action itself will automatically remove the pointer
from view. Actually, the operation of the flag signal is to
bias transistor Q9 in such a fashion that it is turned off
so thaS the associated magnetic circuits in the rotary
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solenoid are not energized.
Turning now more particularly to the construction
of the rotary solenoid and with specific reference to FIGS. -
4, 5 and 6, reference numeral 40 represents a rotary magnet
with the indicator supporting pointer yoke 41 movable there-
with. The magnet 40 is surrounded by the deflection poles
42, each of said deflection poles being semi-circular in shape
and circumscribing slbstantially all of the circular edge of -
rotary magnet 40. A pair of retract poles 43 are located sub-
stantially 180 apart and will cause rotary magnet 40 to align
therewith when no power is being applied to the electromagnet
44.
As indicated above, the indicator supporting pointer
yo~e 41 with its two pointers 41a and 41b (see FIG. 1). The
pointer 41a will be deflected between a total of two dots (41c)
on the vertical scale to visually indicate the glide slope
-condition to the pilot. Tnis physical positioning of pointer
41a is the result of the above described circuitry shown in ~-
FIGS. 2 and 3. The closed loop circuit, as indicated therein,
will operate to effectively rotate the rotary magnet 40 and
to properly orient yoke 41 and pointer 4la in accordance with
the received gIide slope signal. However, if a flag indica-
tion is received, the circuitry will operate to cut off the
power to the electromagnets so that the rotary magnet 40 will
immediately align with the retract poles 43. This operates
to remove the pointers 41a and 41b from sight and will auto-
matically indicate to the pilot that a flag condition (the
inoperativeness of the indicator) is being received and that
this particular instrument should be disregarded.
With the combined circuit and rotary solenoid des- -~
cribed above, the meter movement utilizes considerably more
torgue than conventional d'Arsonval meter movements and is
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a complete closed loop system. If for any reason the power
input thereto should fail, the meter movement will automatical-
ly and immediately be moved to one end or the other of the
particular instrument and out of sight from the pilot. The
chances of the movement being unable to be moved off center
are highly remote so that failure in the circuitry is readily
detected by the pilot since the pointer is pulled out of view.
The above explanation has been with reference to
the glide slope signal. Figure 3 shows the required switch
10` contacts so that vertical navigation can also be selected.
When it is selected, the device functions as previously des-
cribed for glide slope but the pilot reads the VNAV pointer
41b and scale. In FIG. 4 the VNAV pointer is indicated by
the numeral 41b with the data selection switch depicted at
56O
It should be understood that the localizer deflec-
tion bar identified by the numeral 50 in FIG. 1 is very suit-
able to a similar type of closed loop rotary solenoid indica-
tor movement and that the same circuit concepts and benefits
are also inherent when applied thereto. Other types of avi-
onics equipment likewise utilized the above described concepts
without departins from the scope of the invention.
From the foregoing it will be seen that this inven-
tion is one well adapted to attain all the ends and objects
herein set forth, together with other advantages which are -
obvious and which are inherent to the structure.
It will be understood that certain features and sub-
combinations are of utility and may be employed without refer-
ence to other features and subcombinations. This is contem-
plated by and is within the scope of the claims.
As many possible embodiments may be made of the in-
vention withoùt departing from the scope thereof, it is to
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be understood that all matter herein set forth or shown in
the accompanying drawings is to be interpreted as illustrative
and not in a limiting sense.
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