Language selection

Search

Patent 2876630 Summary

Third-party information liability

Some of the information on this Web page has been provided by external sources. The Government of Canada is not responsible for the accuracy, reliability or currency of the information supplied by external sources. Users wishing to rely upon this information should consult directly with the source of the information. Content provided by external sources is not subject to official languages, privacy and accessibility requirements.

Claims and Abstract availability

Any discrepancies in the text and image of the Claims and Abstract are due to differing posting times. Text of the Claims and Abstract are posted:

  • At the time the application is open to public inspection;
  • At the time of issue of the patent (grant).
(12) Patent Application: (11) CA 2876630
(54) English Title: UNMANNED ROTARY WING AIRCRAFT WITH COMPACT FOLDING ROTOR ARMS
(54) French Title: AERONEF A VOILURE ROTATIVE NON HABITE DOTE DE BRAS DE ROTOR PLIANTS COMPACTS
Status: Dead
Bibliographic Data
(51) International Patent Classification (IPC):
  • B64C 1/30 (2006.01)
  • B64C 27/50 (2006.01)
  • B64C 27/08 (2006.01)
  • B64C 39/02 (2006.01)
(72) Inventors :
  • WOOD, GREG (Canada)
(73) Owners :
  • DRAGANFLY INNOVATIONS INC. (Canada)
(71) Applicants :
  • DRAGANFLY INNOVATIONS INC. (Canada)
(74) Agent: DLA PIPER (CANADA) LLP
(74) Associate agent:
(45) Issued:
(22) Filed Date: 2015-01-02
(41) Open to Public Inspection: 2016-07-02
Examination requested: 2019-12-20
Availability of licence: N/A
(25) Language of filing: English

Patent Cooperation Treaty (PCT): No

(30) Application Priority Data: None

Abstracts

Sorry, the abstracts for patent document number 2876630 were not found.

Claims

Note: Claims are shown in the official language in which they were submitted.


CLAIMS:
1. A multi-rotor UAV comprising:
a. a body;
b. a plurality of arms extending radially from the body;
c. a rotor assembly connected to an outside end of each arm; and,
d. a folding mechanism connected to the body and each of the arms for
pivoting the
arms from an unfolded position, where the arms extend radially outward from
the
body such that the rotor assemblies are spaced in a predetermined
configuration,
to a folded position, where compared to the unfolded position an extension of
the
arms from the body is substantially reduced, and wherein the arms are pivoted
such that an outer portion of each arm is enabled to cross the pivot and an
inner
arm portion of one adjacent arm.
Page 19

Description

Note: Descriptions are shown in the official language in which they were submitted.


CA 02876630 2015-01-02
UNMANNED' ROTARY :WING itIRCRAFT WITH COMPACT FOLDING
RorroR ARMS :
Wood
A multi-rotor UAV comprises a body and a plurality of arms extending radially
from the
body. A rotor assembly is connected to an outside end of each arm. A folding
mechanism
is connected to the body and each of the arms for pivoting the arms from an
unfolded
position, where the arms extend radially outward from the body such that the
rotor
assemblies are spaced in a predetermined configuration, to a folded position,
where
compared to the unfolded position an extension of the arms from the body is
substantially
reduced, and wherein the arms are pivoted such that an outer portion of each
arm is
enabled to cross the pivot and an inner arm portion of one adjacent arm.
Page 1

CA 02876630 2015-01-02
UNMANNED ROTARY WING AIRCRAFT WITH COMPACT FOLDING
ROTOR ARMS
FIELD OF THE INVENTION
The present invention relates to rotary wing aircrafts, and more particularly,
to unmanned
rotary wing aircrafts with compact folding rotor arms.
BACKGROUND OF THE INVENTION
Due to the present-day advances in computer and telecommunication
technologies, there
has been a resurgence of interest in the use of Unmanned Anal Vehicles (UAVs),
and in
particular, of rotary wing type UAVs for performing a variety of aerial
missions where
the use of manned flight vehicles is not deemed possible or appropriate. Such
aerial
missions include, for example, surveillance with associated data acquisition
and one-way
delivery of small payloads.
Typically, rotary wing type UAVs are preferred over fixed wing aircraft due
to: the
ability to vertically takeoff and land from a static position; the ability to
hover; the ability
to move sideways; and, the ability to quickly transition between the different
types of
Page 2

CA 02876630 2015-01-02
=
movement.
More recently, multi-rotor designs using a plurality of pairs of identical
fixed pitched
propellers -with one propeller rotating clockwise and one propeller rotating
counter-
clockwise - are employed in numerous designs of UAVs. Control of the UAV is
achieved
by altering the rotation rate of one or more of the propellers to change
torque and lift
using an electronic control system and electronic sensors.
There are several advantages of the multi-rotor design compared to a single-
rotor design.
First, the multi-rotor design does not require mechanical linkages to vary the
rotor blade
pitch angle while rotating, thus substantially simplifying the construction
and
maintenance of the aircraft. Second, the use of a plurality of rotors allows
each rotor to
have a smaller diameter, thus reducing the kinetic energy of each rotor during
flight
resulting in a simpler and safer construction of the aircraft.
Typically, multi-rotor UAVs comprise a body having a plurality of arms
extending
radially therefrom and a rotor assembly connected to an outside end of each
arm, as
disclosed, for example, in US Patent Applications 2010/108801 and 2012/138732.
The
arms are connected to the body such that the arms can be pivoted from a flying
position,
where the arms extend radially outward from the body such that the rotor
assemblies are
spaced in a desired configuration, to a folded position where the arms are
positioned
substantially parallel and adjacent to each other for transport and storage
making the
Page 3

CA 02876630 2015-01-02
aircraft less susceptible to damage.
However, the folding mechanism disclosed in the US Patent Applications
2010/108801
and 2012/138732 still leaves the folded arms extending outward from the body
on one
side thereof, making handling of the folded aircraft during transport and
storage awkward
and making the arms and rotors susceptible to damage.
Furthermore, recent designs of multi-rotor UAVs comprise more than 4 arms ¨
such as,
for example, 6 or 8 - for further reducing the size of the rotors and
providing further
improved control of the aircraft, in particular in case of loss of a rotor.
Unfortunately, use
of more than 4 arms substantially complicates the folding of the arms.
It is desirable to provide a multi-rotor UAV having a folding mechanism that
enables the
arms to be folded into a substantially compact form.
It is also desirable to provide a multi-rotor UAV having a folding mechanism
that enables
the arms to be folded such that an extension of the arms from the body of the
UAV is
substantially reduced.
It is also desirable to provide a multi-rotor UAV having a folding mechanism
that enables
more than 4 arms to be folded into a substantially compact form.
Page 4

CA 02876630 2015-01-02
SUMMARY OF THE INVENTION
Accordingly, one object of the present invention is to provide a multi-rotor
UAV having
a folding mechanism that enables the arms to be folded into a substantially
compact form.
Another object of the present invention is to provide a multi-rotor UAV having
a folding
mechanism that enables the arms to be folded such that an extension of the
arms from the
body of the UAV is substantially reduced.
Another object of the present invention is to provide a multi-rotor UAV having
a folding
mechanism that enables more than 4 arms to be folded into a substantially
compact form.
According to one aspect of the present invention, there is provided a multi-
rotor UAV.
The multi-rotor UAV comprises a body and a plurality of arms extending
radially from
the body. A rotor assembly is connected to an outside end of each arm. A
folding
mechanism is connected to the body and each of the arms for pivoting the arms
from an
unfolded position, where the arms extend radially outward from the body such
that the
rotor assemblies are spaced in a predetermined configuration, to a folded
position, where
compared to the unfolded position an extension of the arms from the body is
substantially
reduced, and wherein the arms are pivoted such that an outer portion of each
arm is
enabled to cross the pivot and an inner arm portion of one adjacent arm.
Page 5

CA 02876630 2015-01-02
The advantage of the present invention is that it provides a multi-rotor UAV
having a
folding mechanism that enables the arms to be folded into a substantially
compact form.
A further advantage of the present invention is that it provides a multi-rotor
UAV having
a folding mechanism that enables the arms to be folded such that an extension
of the arms
from the body of the UAV is substantially reduced.
A further advantage of the present invention is that it provides a multi-rotor
UAV having
a folding mechanism that enables more than 4 arms to be folded into a
substantially
compact form.
BRIEF DESCRIPTION OF THE DRAWINGS
A preferred embodiment of the present invention is described below with
reference to the
accompanying drawings, in which:
Figures la and lb are simplified block diagrams illustrating a top view and a
side
view, respectively of a multi-rotor UAV according to a preferred embodiment of
the invention with the arms in an unfolded position;
Figures lc and id are simplified block diagrams illustrating a top view and a
side
Page 6

CA 02876630 2015-01-02
view, respectively of the multi-rotor UAV according to a preferred embodiment
of the invention with the arms in a folded position;
Figures 2a to 2c are simplified block diagrams illustrating a top view, a side
view,
and a top perspective view, respectively, of a folding mechanism of the multi-
rotor UAV according to a preferred embodiment of the invention with the arms
in
the unfolded position;
Figures 2d to 2f are simplified block diagrams illustrating a top view, a side
view,
o and a top perspective view, respectively, of a folding mechanism of
the multi-
rotor UAV according to a preferred embodiment of the invention with the arms
in
an intermediate position;
Figures 2g to 2i are simplified block diagrams illustrating a top view, a side
view,
and a top perspective view, respectively, of a folding mechanism of the multi-
rotor UAV according to a preferred embodiment of the invention with the arms
in
the folded position;
Figures 2j to 21 are simplified block diagrams illustrating a top perspective
view, a
top view, and a cross sectional view, respectively, of pivots of the folding
mechanism of the multi-rotor UAV according to a preferred embodiment of the
invention;
Page 7

CA 02876630 2015-01-02
Figure 2m is a simplified block diagram illustrating a top view of an arm of
the
folding mechanism of the multi-rotor UAV according to a preferred embodiment
of the invention;
Figures 2n and 2o are simplified block diagrams illustrating a top view and a
cross sectional view, respectively, of a securing mechanism of the folding
mechanism of the multi-rotor UAV according to a preferred embodiment of the
invention;
Figures 3a to 3c are simplified block diagrams illustrating a top view of
another
folding mechanism of the multi-rotor UAV according to a preferred embodiment
of the invention with the arms in an unfolded position, an intermediate
position,
and a folded position, respectively;
Figure 3d is a simplified block diagram illustrating a side view of the other
folding mechanism of the multi-rotor UAV according to a preferred embodiment
of the invention with the arms in an intermediate position;
Figures 4a to 4c are simplified block diagrams illustrating a top view of yet
another folding mechanism of the multi-rotor UAV according to a preferred
embodiment of the invention with the arms in an unfolded position, an
Page 8

CA 02876630 2015-01-02
intermediate position, and a folded position, respectively; and,
Figure 4d is a simplified block diagram illustrating a side view of the yet
another
folding mechanism of the multi-rotor UAV according to a preferred embodiment
of the invention with the arms in an intermediate position.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Unless defined otherwise, all technical and scientific terms used herein have
the same
meaning as commonly understood by one of ordinary skill in the art to which
the
invention belongs. Although any methods and materials similar or equivalent to
those
described herein can be used in the practice or testing of the present
invention, the
preferred methods and materials are now described.
While the description of the preferred embodiments hereinbelow is with
reference to a
multi-rotor UAV having 6 arms, it will become evident to those skilled in the
art that the
embodiments of the invention are not limited thereto, but are also adaptable
for use with
multi-rotor UAVs having various other numbers of arms such as 4, 8, 10, etc.
Furthermore, while the description of the preferred embodiments hereinbelow is
with
reference to a mechanism for independently moving the arms for the sake of
clarity, it
Page 9

CA 02876630 2015-01-02
will become evident to those skilled in the art that the embodiments of the
invention are
not limited thereto, but are also adaptable for simulateously moving the arms
by coupling
the same.
Referring to Figures la to id, a multi-rotor UAV 100 according to a preferred
embodiment of the invention is provided. The multi-rotor UAV 100 has: a body
102; six
arms 106.1 ¨ 106.6 extending radially from the body 102; and six rotor
assemblies 104.1
-104.6 connected to an outside end of the respective arm 106.1 ¨ 106.6. The
rotor
assemblies 104.1 -104.6 each comprise, for example, a single rotor or coaxial
rotor pairs
driven by an electric motor. Using the six rotor assemblies 104.1 -104.6 for
creating lift,
the multi-rotor UAV 100 is capable of performing the maneuvers a typical
single rotor
helicopter is capable of, yet does not require the mechanical complexity of
the single
rotor helicopter. Preferably, the aims 106.1 ¨ 106.6 are positioned extending
at regular
intervals around a central axis 103, with each arm 106.1 ¨ 106.6 positioning
the
respective rotor assembly 104.1 -104.6 the same distance from the central axis
103. In
operation the multi-rotor UAV 100 is controlled by altering the rotation rate
of one or
more of the rotors to change torque and lift using an electronic control
system disposed in
the main body 102 and electronic sensors connected thereto, with the control
system and
electronic sensors being implemented in a conventional manner known to one of
ordinary
skill in the art. Preferably, the arms 106.1 ¨ 106.6 are hollow for
accommodating wiring -
connecting the rotor assemblies 104.1 -104.6 to the electronic control system
disposed in
the main body 102 ¨therein. Typically, payload 114 such as, for example, a
surveillance
Page 10

CA 02876630 2015-01-02
camera is mounted to the body 102 via support column 110 which also has
mounted
thereto landing gear 112.
The multi-rotor UAV 100 further comprises folding mechanism 120 having each of
the
arms 106.1 ¨ 106.6 pivotally movable mounted thereto for pivoting the arms
106.1 ¨
106.6 from an unfolded position, where the arms extend radially outward from
the body
such that the rotor assemblies 104.1 -104.6 are spaced in a predetermined
configuration,
as illustrated in Figures la and lb, to a folded position, where compared to
the unfolded
position an extension of the arms 106.1 ¨ 106.6 from the body 102 is
substantially
0 reduced, as illustrated in Figures lc and id. Folding of the arms 106.1 ¨
106.6 into a
substantially compact form as, for example, illustrated in Figures lc and Id,
is possible
by pivoting the arms 106.1¨ 106.6 such that an outer portion of each arm 106.1
¨ 106.6
is enabled to cross the pivot and an inner arm portion of one adjacent arm
106.1 ¨ 106.6
as will be disclosed in more detail hereinbelow. The folding mechanism 120 is
connected
to the body 102 via, for example, connecting columns 108 having a
predetermined length
for providing sufficient space between the same and the bottom of the body 102
for
folding/unfolding the arms 106.1 ¨ 106.6.
Referring to Figures 2a to 2o, a folding mechanism 120 of the UAV 100
according to a
preferred embodiment of the invention is provided. Figures 2a to 2i illustrate
each of
three stages ¨ unfolded, intermediate, and folded - of the folding process of
the arms
106.1 ¨ 106.6 in a top view, a side view, and a perspective top view,
respectively. As will
Page 11

CA 02876630 2015-01-02
become evident to one skilled in the art, the arms 106.1 ¨ 106.6 are unfolded
by simply
reversing the order of the stages of the folding process. Each of the arms
106.1 ¨ 106.6 is
pivotally mounted via respective pivot 120D.1 ¨ 120D.6 to folding support
structure
120A ¨ 120C, as will be described in more detail hereinbelow. In the unfolded
position,
the arms 106.1 ¨ 106.6 extend radially outward from the folding support
structure 120A ¨
120C, as illustrated in Figures 2a to 2c. Initially, the outside ends of the
arms 106.1 ¨
106.6 are moved towards each other in pairs - 106.1 & 106.2; 106.3 & 106.4;
and 106.5
& 106.6 ¨with the odd numbered arms 106.1, 106.3, and 106.5 being moved
downwardly and the even numbered arms 106.2, 106.4, and 106.6 being moved
upwardly, as indicated by the block arrows in Figures 2a to 2c. The upward and
downward movement allows the arms of each of the pairs of arms to cross each
other
while moving the outside end of the arms inwardly towards the central axis
103, as
illustrated in Figures 2d to 2E In continuation, this movement allows the arms
of each of
the pairs to cross each other's pivot and an outside portion of the folding
support
structure 120A ¨ 120C until the folded position is reached, as illustrated in
Figures 2g to
2i.
Preferably, the folding support structure 120A ¨ 120C comprises two concentric
flat rings
- inner ring 120A and outer ring 120B disposed in a plane perpendicular to the
central
axis 103, as illustrated in Figure 2a. Flat spokes 120C.1 -120C.6 connect the
two rings
and extend beyond the outside perimeter of the outer ring 120B a predetermined
distance
for securing the arms 106.1 ¨ 106.6 in the unfolded position, as will be
described
Page 12

CA 02876630 2015-01-02
hereinbelow. This structure provides sufficient strength while substantially
minimizing
weight. Of course, other shapes such as, for example, a single wide ring
having spokes
protruding the perimeter may be employed. Preferably, the folding support
structure
120A ¨ 120C is made of a carbon fiber material using standard manufacturing
techniques. Alternatively other sufficiently strong light-weight materials
such as, for
example, plastic, wood, or aluminum may be employed.
The pivots 120D of the odd numbered arms 106 are placed a predetermined
distance D3
to the left of the intersection of the respective spoke 120C on the outer ring
120B, while
the pivots 120D of the even numbered arms 106 are placed a predetermined
distance D4
to the right of the intersection of the respective spoke 120C on the outer
ring 120B, as
illustrated in Figures 2j and 2k. The axes of the pivots 120D are angled a
predetermined
angle ¨ a for even numbered arms 106 and 13 for odd numbered arms 106 ¨ with
respect
to a plane 120E through the central axis 103 and oriented radially outwardly
in order to
enable the upward/downward movement of the arms 106. Alternatively, the axes
of the
pivots 120D may be angled with respect to a plane oriented perpendicular to
the plane
120E or with respect to both planes. Furthermore, the axes of the pivots 120D
are offset a
predetermined distance ¨ D1 for odd numbered arms 106 and D2 for even numbered

arms 106 ¨ from the central axis of the respective arm 106, as illustrated in
Figure 2k.
The distances D1-D4 are determined in dependence upon the size and geometry of
the
folding support structure 120A ¨ 120C and the arms 106 as well as the space
available for
folding the arms 106. Preferably, the angles a and 13 are in the range between
50 and 25c).
Page 13

CA 02876630 2015-01-02
It is noted that the angles a and may be the same.
The pivots 120D are provided in a standard, for example, hinge type fashion,
as
illustrated in Figure 21. For example, the folding support structure 120A ¨
120C
comprises pin type protrusions 120F which are accommodated in a bore of the
barrel
section 106A of the respective arm 106. The arm 106 is then secured to the
folding
support structure 120A ¨ 120C via screw 122 and washer 124. The folding
support
structure 120A ¨ 120C comprising the pin type protrusions 120F is, for
example, made as
a single unit from carbon fiber material using standard manufacturing
techniques.
Alternatively, the pins are mounted to the folding support structure 120A ¨
120C in a
standard fashion. The arms 106 comprising the barrel section 106A are, for
example,
made as a single unit from carbon fiber material or suitable plastic material
using
standard manufacturing techniques. Alternatively, the barrel section 106A is
mounted to
the arm 106 in a conventional manner. Further alternatively, the arms 106 are
made of
another light weight material such as, for example, wood or aluminum.
Preferably, the arms 106 are curved in order to reduce the space needed for
the folding
process as well as for reducing the space used in the folded position, as
illustrated in
Figure 2m. Camber C is determined in dependence upon the size and geometry of
the
folding support structure 120A ¨ 120C and the length L of the arms 106 as well
as the
space available for folding the arms 106. Alternatively, straight arms 106 are
employed at
the cost of a greater space needed for the folding process and a greater
extension of the
Page 14

CA 02876630 2015-01-02
arms 106 from the body 102 in the folded position.
Preferably, the arms 106 are secured in the unfolded position using clips 120G
fastened
to the respective spoke 120C in a conventional manner using, for example, an
adhesive,
as illustrated in Figures 2n and 2o. The clips 120G are made of a resilient
material such
as, for example, a plastic material or a strip of metal sheet material and
comprise upper
and lower clip legs. When the arm 106 contacts the clip120G the lower clip leg
is forced
downward such that the arm 106 can move into the upper and lower grooves
disposed in
the respective upper and lower clip legs. After insertion the clip legs move
together and
maintain the arm 106 in the grooves. The clips 120G are oriented such that
when the
arms 106 are engaged the rotor assemblies 104 are placed at their
predetemiined position.
The folding mechanism 120 enables the arms 106 to be folded such that an
extension of
the arms from the body 102 is substantially reduced, for example, from a
distance of 5
is feet from the central axis 103 to a distance of 1.5 feet to 2 feet.
Furthermore, the folding
mechanism enables more than 4 arms 106 to be folded into a substantially
compact form.
Referring to Figures 3a to 3d, another embodiment 220 of a folding mechanism
for use
with the multi-rotor UAV 100 is provided, with Figures 3a to 3c illustrating
three stages ¨
unfolded, intermediate, and folded - of the folding process of the arms 206.1
¨ 206.6 in a
top view and Figure 3d illustrating the intermediate stage in a side view. As
will become
evident to one skilled in the art, the arms 206.1 ¨206.6 are unfolded by
simply reversing
Page 15

CA 02876630 2015-01-02
the order of the stages of the folding process.
Each of the arms 206.1 ¨ 206.6 is pivotally mounted via respective pivot
220D.1 ¨220D.6 to the folding support structure similar to the one described
hereinabove. In the
unfolded position the arms 206.1 ¨ 206.6 extend radially outward from the
folding
support structure, as illustrated in Figure 3a. Here all arms 206.1 ¨ 206.6
are rotated
about their respective pivots 220D.1 ¨ 220D.6 in a same, for example,
clockwise,
direction, as indicated by the block arrows in Figures 3a and 3b. While being
rotated all
arms 206.1 ¨ 206.6 are moved downwardly, as indicated by the block arrows in
Figure
3d. The downward movement allows an outer portion of each of the arms 206.1 ¨
206.6
to cross the pivot and an inner arm portion of one adjacent arm, i.e. the
following arm in
clockwise direction, to reach the folded position illustrated in Figure 3c.
The pivots 220D
of the arms 206 are placed and oriented similar to the pivots 120D of the odd
numbered
arms 106 described hereinabove for enabling the downward movement while being
rotated. The folding support structure, the pivots 220D and the arms 206 are
implemented
in a similar fashion as disclosed hereinabove. Since all the arms 206.1 ¨
206.6 are moved
downward the folding support structure of the folding mechanism 220 can be
directly
mounted to the body 102, obviating the connecting columns 108 at the cost of a
greater
extension of the arms 206 from the body 102 in the folded position.
Furthermore, since
all arms 206 are mounted and moved in a same fashion, the folding mechanism
220 is
implementable for even as well as odd numbers of arms 206.
Page 16

CA 02876630 2015-01-02
Referring to Figures 4a to 4d, yet another embodiment 320 of a folding
mechanism for
use with the multi-rotor UAV 100 is provided, with Figures 4a to 4c
illustrating three
stages - unfolded, intermediate, and folded - of the folding process of the
arms 306.1 -
306.6 in a top view and Figure 4d illustrating the intermediate stage in a
side view. As
will become evident to one skilled in the art, the arms 306.1 - 306.6 are
unfolded by
simply reversing the order of the stages of the folding process.
Each of the arms 306.1 -306.6 is pivotally mounted via respective pivot 320D.1
-
320D.6 to three parallel folding support structures 320.1 - 320.3, each being
similar to
110 the one described hereinabove, with odd numbered aims 306 being mounted
between the
two top folding support structures 320.1 and 320.2 and the even numbered arms
306
being mounted between the two bottom folding support structures 320.2 and
320.3, as
illustrated in Figure 4d. Here the pivots 320D.1 - 320D.6 are oriented
parallel to the
central axis 103. In the unfolded position the arms 306.1 - 306.6 extend
radially outward
from the folding support structure, as illustrated in Figure 4a. All anns
306.1 - 306.6 are
rotated about their respective pivots 320D.1 - 320D.6 in a same, for example,
clockwise,
direction, as indicated by the block arrows in Figures 4a and 4b. Alternating
placement of
the pivots 320D.1 - 320D.6 between the three parallel folding support
structures 320.1 -
320.3 allows an outer portion of each of the aims 306.1 -306.6 to cross the
pivot and an
inner arm portion of one adjacent arm, i.e. the following arm in clockwise
direction, to
reach the folded position illustrated in Figure 4c.
Page 17

CA 02876630 2015-01-02
Since all the arms 306.1 ¨ 306.6 are moved in two planes perpendicular to the
central
axis, the folding support structure of the folding mechanism 320 can be
directly mounted
to the body 102, obviating the connecting columns 108 at the cost of a greater
extension
of the arms 206 from the body 102 in the folded position. Furthermore, folding
mechanism 320 allows the payload and the landing gear to be directly mounted
to the
bottom thereof
The present invention has been described herein with regard to preferred
embodiments.
However, it will be obvious to persons skilled in the art that a number of
variations and
modifications can be made without departing from the scope of the invention as
described herein.
Page 18

Representative Drawing
A single figure which represents the drawing illustrating the invention.
Administrative Status

For a clearer understanding of the status of the application/patent presented on this page, the site Disclaimer , as well as the definitions for Patent , Administrative Status , Maintenance Fee  and Payment History  should be consulted.

Administrative Status

Title Date
Forecasted Issue Date Unavailable
(22) Filed 2015-01-02
(41) Open to Public Inspection 2016-07-02
Examination Requested 2019-12-20
Dead Application 2022-07-19

Abandonment History

Abandonment Date Reason Reinstatement Date
2016-07-26 FAILURE TO COMPLETE 2017-01-18
2019-01-02 FAILURE TO PAY APPLICATION MAINTENANCE FEE 2019-12-20
2021-07-19 R86(2) - Failure to Respond
2022-07-04 FAILURE TO PAY APPLICATION MAINTENANCE FEE

Payment History

Fee Type Anniversary Year Due Date Amount Paid Paid Date
Application Fee $200.00 2015-01-02
Registration of a document - section 124 $100.00 2015-07-17
Maintenance Fee - Application - New Act 2 2017-01-03 $50.00 2016-12-20
Expired 2019 - Reinstatement - failure to complete $200.00 2017-01-18
Expired 2019 - The completion of the application $200.00 2017-01-18
Maintenance Fee - Application - New Act 3 2018-01-02 $50.00 2017-12-20
Registration of a document - section 124 2019-11-04 $100.00 2019-11-04
Maintenance Fee - Application - New Act 4 2019-01-02 $50.00 2019-12-20
Request for Examination 2020-01-02 $400.00 2019-12-20
Reinstatement: Failure to Pay Application Maintenance Fees 2020-01-02 $200.00 2019-12-20
Maintenance Fee - Application - New Act 5 2020-01-02 $100.00 2019-12-20
Maintenance Fee - Application - New Act 6 2021-01-04 $100.00 2020-12-30
Owners on Record

Note: Records showing the ownership history in alphabetical order.

Current Owners on Record
DRAGANFLY INNOVATIONS INC.
Past Owners on Record
DRAGAN, ZENON
DRAGANFLY INNOVATIONS INC.
Past Owners that do not appear in the "Owners on Record" listing will appear in other documentation within the application.
Documents

To view selected files, please enter reCAPTCHA code :



To view images, click a link in the Document Description column. To download the documents, select one or more checkboxes in the first column and then click the "Download Selected in PDF format (Zip Archive)" or the "Download Selected as Single PDF" button.

List of published and non-published patent-specific documents on the CPD .

If you have any difficulty accessing content, you can call the Client Service Centre at 1-866-997-1936 or send them an e-mail at CIPO Client Service Centre.


Document
Description 
Date
(yyyy-mm-dd) 
Number of pages   Size of Image (KB) 
Office Letter 2019-12-23 1 70
Reinstatement / Maintenance Fee Payment 2019-12-20 2 62
Request for Examination 2019-12-20 2 62
Description 2016-12-20 19 764
Claims 2016-12-20 4 129
Abstract 2016-12-20 1 13
Drawings 2016-12-20 27 664
Office Letter 2020-02-18 1 195
Examiner Requisition 2021-03-18 3 161
Drawings 2015-01-02 21 1,079
Description 2015-01-02 18 626
Claims 2015-01-02 1 16
Representative Drawing 2016-06-06 1 12
Cover Page 2016-08-02 1 31
Correspondence 2016-12-20 4 98
Prosecution-Amendment 2016-12-20 55 1,729
Assignment 2015-01-02 6 156
Correspondence 2015-01-12 2 33
Correspondence 2015-01-12 2 35
Correspondence 2016-04-26 2 37
Correspondence 2017-01-09 1 23
Filing Certificate Correction 2017-01-18 3 144