CN114248912A - Undercarriage folding and unfolding and cabin door linkage mechanism for small-sized fixed wing unmanned aerial vehicle - Google Patents
Undercarriage folding and unfolding and cabin door linkage mechanism for small-sized fixed wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN114248912A CN114248912A CN202010998907.7A CN202010998907A CN114248912A CN 114248912 A CN114248912 A CN 114248912A CN 202010998907 A CN202010998907 A CN 202010998907A CN 114248912 A CN114248912 A CN 114248912A
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- Prior art keywords
- landing gear
- door
- undercarriage
- electric push
- push rod
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- 230000007246 mechanism Effects 0.000 title abstract description 41
- 230000009471 action Effects 0.000 claims description 7
- 230000005484 gravity Effects 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 2
- 238000009434 installation Methods 0.000 description 8
- 230000000670 limiting effect Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
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- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05F—DEVICES FOR MOVING WINGS INTO OPEN OR CLOSED POSITION; CHECKS FOR WINGS; WING FITTINGS NOT OTHERWISE PROVIDED FOR, CONCERNED WITH THE FUNCTIONING OF THE WING
- E05F15/00—Power-operated mechanisms for wings
- E05F15/60—Power-operated mechanisms for wings using electrical actuators
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- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05Y—INDEXING SCHEME RELATING TO HINGES OR OTHER SUSPENSION DEVICES FOR DOORS, WINDOWS OR WINGS AND DEVICES FOR MOVING WINGS INTO OPEN OR CLOSED POSITION, CHECKS FOR WINGS AND WING FITTINGS NOT OTHERWISE PROVIDED FOR, CONCERNED WITH THE FUNCTIONING OF THE WING
- E05Y2900/00—Application of doors, windows, wings or fittings thereof
- E05Y2900/50—Application of doors, windows, wings or fittings thereof for vehicles
- E05Y2900/502—Application of doors, windows, wings or fittings thereof for vehicles for aircraft
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- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05Y—INDEXING SCHEME RELATING TO HINGES OR OTHER SUSPENSION DEVICES FOR DOORS, WINDOWS OR WINGS AND DEVICES FOR MOVING WINGS INTO OPEN OR CLOSED POSITION, CHECKS FOR WINGS AND WING FITTINGS NOT OTHERWISE PROVIDED FOR, CONCERNED WITH THE FUNCTIONING OF THE WING
- E05Y2900/00—Application of doors, windows, wings or fittings thereof
- E05Y2900/50—Application of doors, windows, wings or fittings thereof for vehicles
- E05Y2900/53—Application of doors, windows, wings or fittings thereof for vehicles characterised by the type of wing
- E05Y2900/531—Doors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention provides a landing gear retraction and release and cabin door linkage mechanism for a small-sized fixed wing unmanned aerial vehicle, which comprises: a landing gear bay; one side of the landing gear cabin door is rotatably connected with the landing gear cabin body; the undercarriage is rotatably connected with the undercarriage cabin body; the deflector rod is connected with the undercarriage; the electric push rod is respectively connected with the undercarriage cabin body and the undercarriage and is used for realizing retraction and extension of the undercarriage relative to the undercarriage cabin body; the stop block is positioned at the joint of the undercarriage cabin body and the undercarriage cabin door and is fixedly connected with the undercarriage cabin door, and the stop block is used for being matched with the shift lever to realize the closing and opening of the undercarriage cabin door along with the retraction and the extension of the undercarriage. By applying the technical scheme provided by the invention, the technical problems that the undercarriage folding and unfolding and cabin door linkage mechanism in the prior art is high in weight, the actuating mechanism is complex and difficult to miniaturize, and the undercarriage folding and unfolding and cabin door linkage mechanism cannot be suitable for a small-sized fixed wing unmanned aerial vehicle can be solved.
Description
Technical Field
The invention relates to the technical field of small-sized fixed wing unmanned aerial vehicles, in particular to a landing gear retraction and release and cabin door linkage mechanism for a small-sized fixed wing unmanned aerial vehicle.
Background
For small-size fixed wing unmanned aerial vehicle, use retractable undercarriage and the hatch door that can close can effectively reduce flight resistance, save fuel consumption, play crucial effect to the flying speed and the time of endurance that promote unmanned aerial vehicle. And the undercarriage that traditional has man-machine or large-scale unmanned aerial vehicle to adopt receive and releases and there is the structure weight height with hatch door switch scheme, actuates the mechanism complicacy to and be difficult to miniaturized not enough, be not applicable to small-size fixed wing unmanned aerial vehicle.
Disclosure of Invention
The invention provides a landing gear retraction and cabin door linkage mechanism for a small fixed wing unmanned aerial vehicle, which can solve the technical problems that the landing gear retraction and cabin door linkage mechanism in the prior art is high in weight, complex in actuating mechanism and difficult to miniaturize, so that the landing gear retraction and cabin door linkage mechanism cannot be suitable for the small fixed wing unmanned aerial vehicle.
The invention provides a landing gear retraction and release and cabin door linkage mechanism for a small-sized fixed wing unmanned aerial vehicle, which comprises: a landing gear bay; one side of the landing gear cabin door is rotatably connected with the landing gear cabin body; the undercarriage is rotatably connected with the undercarriage cabin body; the deflector rod is connected with the undercarriage; the electric push rod is respectively connected with the undercarriage cabin body and the undercarriage and is used for realizing retraction and extension of the undercarriage relative to the undercarriage cabin body; the stop block is positioned at the joint of the undercarriage cabin body and the undercarriage cabin door and is fixedly connected with the undercarriage cabin door, and the stop block is used for being matched with the shift lever to realize the closing and opening of the undercarriage cabin door along with the retraction and the extension of the undercarriage; when the electric push rod contracts, the electric push rod drives the undercarriage to retract, the deflector rod moves towards the undercarriage cabin body along with the undercarriage, and the deflector rod drives the stop block to drive the undercarriage cabin door to close; when the electric push rod extends, the electric push rod drives the undercarriage to transfer, the driving rod is away from the undercarriage cabin body along with the undercarriage to move, the limiting effect of the driving rod on the stop block disappears, and the undercarriage cabin door is opened under the action of gravity.
Further, the undercarriage retraction and extension and door linkage mechanism further comprises a hinge assembly, and the undercarriage door is rotatably connected with the undercarriage cabin body through the hinge assembly.
Further, the landing gear retraction and door linkage mechanism further comprises an elastic assembly, the elastic assembly is located on a rotating shaft of the hinge assembly and is used for promoting the opening of the landing gear door and keeping the landing gear door in an open state.
Further, the hinge assembly comprises a plurality of hinges, the elastic assembly comprises a plurality of elastic pieces, and the plurality of hinges and the plurality of elastic pieces are arranged in a one-to-one correspondence mode.
Further, the elastic member includes a torsion spring.
Furthermore, the undercarriage folding and unfolding and cabin door linkage mechanism further comprises an electric push rod installation shaft, and the electric push rod is fixed on the undercarriage cabin body through the electric push rod installation shaft.
The landing gear retraction and extension and cabin door linkage mechanism for the small-sized fixed wing unmanned aerial vehicle is characterized in that the landing gear retraction and extension and the cabin door linkage mechanism realize the retraction and extension of the landing gear through the electric push rod, and can realize the closing and opening of the cabin door of the landing gear along with the retraction and extension of the landing gear through the mutual matching of the deflector rod and the stop block. Compared with the prior art, the technical scheme of the invention can solve the technical problems that the undercarriage folding and unfolding and cabin door linkage mechanism in the prior art is high in weight, the actuating mechanism is complex and difficult to miniaturize, and the undercarriage folding and unfolding and cabin door linkage mechanism cannot be suitable for a small-sized fixed wing unmanned aerial vehicle.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Figure 1 shows a schematic structural view of a landing gear retraction and door linkage for a small fixed wing drone provided in accordance with a particular embodiment of the present invention;
FIG. 2 illustrates a schematic view of a door installation provided in accordance with a specific embodiment of the present invention;
FIG. 3 illustrates a schematic representation of a landing gear retraction process provided in accordance with a specific embodiment of the present invention;
figure 4 shows a schematic structural view of a landing gear provided in accordance with a specific embodiment of the present invention in a stowed state.
Wherein the figures include the following reference numerals:
10. a landing gear bay; 20. a landing gear bay door; 30. a landing gear; 40. a deflector rod; 50. an electric push rod; 60. a stopper, 70, a hinge assembly; 71. a hinge; 80. an elastic component; 81. an elastic member; 90. the installation axle of electric push rod.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
As shown in fig. 1 to 4, according to an embodiment of the present invention, there is provided a landing gear retraction and door linkage mechanism for a small fixed wing drone, the landing gear retraction and door linkage mechanism including: landing gear bay 10, landing gear bay door 20, landing gear 30, shift lever 40, electric push rod 50 and stop block 60. One side of the landing gear bay door 20 is rotatably connected to the landing gear bay body 10. The landing gear 30 is rotatably connected to the landing gear body 10. The shifter lever 40 is connected to the landing gear 30. The electric push rod 50 is respectively connected with the landing gear body 10 and the landing gear 30, and the electric push rod 50 is used for realizing the retraction of the landing gear 30 relative to the landing gear body 10. The stop block 60 is located at the junction of the landing gear body 10 and the landing gear door 20 and is fixedly connected with the landing gear door 20, and the stop block 60 is used for cooperating with the shift lever 40 to close and open the landing gear door 20 along with the retraction and extension of the landing gear 30. When the electric push rod 50 contracts, the electric push rod 50 drives the landing gear 30 to retract, the shift lever 40 moves towards the landing gear cabin 10 along with the landing gear 30, and the shift lever 40 shifts the stop block 60 to drive the landing gear cabin door 20 to close; when the electric push rod 50 extends, the electric push rod 50 drives the landing gear 30 to descend, the shift lever 40 moves away from the landing gear cabin body 10 along with the landing gear 30, the limiting effect of the shift lever 40 on the stop block 60 disappears, and the landing gear door 20 is opened under the action of gravity.
By applying the configuration mode, the undercarriage retracting and cabin door linkage mechanism for the small-sized fixed wing unmanned aerial vehicle is provided, the undercarriage retracting and cabin door linkage mechanism achieves retracting and releasing of the undercarriage 30 through the electric push rod 50, and can achieve closing and opening of the undercarriage cabin door 20 along with retracting and releasing of the undercarriage 30 through mutual matching of the shift lever 40 and the stop dog 60, the linkage mechanism can achieve controllable retracting and releasing of the undercarriage 30 on the premise of not sacrificing too much structural weight, and meanwhile, the cabin door can achieve automatic closing and opening along with retracting and releasing of the undercarriage 30. Compared with the prior art, the technical scheme of the invention can solve the technical problems that the undercarriage folding and unfolding and cabin door linkage mechanism in the prior art is high in weight, the actuating mechanism is complex and difficult to miniaturize, and the undercarriage folding and unfolding and cabin door linkage mechanism cannot be suitable for a small-sized fixed wing unmanned aerial vehicle.
Further, in the present invention, in order to achieve the rotatable connection of the landing gear door 20 with the landing gear body 10, the configurable landing gear retraction and door linkage further comprises a hinge assembly 70, and the landing gear door 20 is rotatably connected with the landing gear body 10 by the hinge assembly 70. The landing gear body 10 is part of the airframe structure and is the physical space that houses the landing gear 30, and the landing gear 30 serves to carry the airframe weight. As one embodiment of the present invention, the hinge assembly 70 may include a plurality of hinges 71. The plurality of hinges 71 may be evenly distributed between the landing gear doors 20 and the landing gear body 10. The number of hinges 71 may be adjusted depending on the size of the landing gear door 20 and the actual requirements, for example, as shown in figure 2, the hinge assembly 70 may comprise three hinges 71 and the stop 60 may be provided at the middle hinge 71.
In addition, in the present invention, in order to prevent the landing gear door 20 from being opened normally only under the action of gravity and prevent the landing gear door 20 from shaking during the flight of the unmanned aerial vehicle, the landing gear retraction and door linkage mechanism may further include an elastic component 80, the elastic component 80 is located on the rotating shaft of the hinge component 70, and the elastic component 80 is used for urging the landing gear door 20 to be opened and maintaining the landing gear door 20 in the opened state. As an embodiment of the present invention, the elastic assembly 80 may include a plurality of elastic members 81, and the plurality of hinges 71 are disposed in one-to-one correspondence with the plurality of elastic members 81. The number of the elastic members 81 can also be adjusted according to actual requirements, for example, as shown in fig. 2, the elastic assembly 80 comprises three elastic members 81.
Further, in the present invention, as shown in fig. 2, in order to achieve the control of the opening state of the landing gear door 20 by the elastic member 81, the elastic member 81 may be selected to be a torsion spring, by which the landing gear door 20 is urged to be opened and the landing gear door 20 is maintained in the opened state. In the present invention, other elastic members 81 capable of urging the landing gear door 20 open and maintaining the landing gear door 20 in the open state may be selected besides the torsion spring, and the electric push rod 50 is a power source for retracting and extending the landing gear 30.
In addition, in the present invention, in order to realize the fixed installation of the electric push rod 50, the landing gear retraction and door linkage mechanism may be further configured to include an electric push rod installation shaft 90, the electric push rod 50 is fixed on the landing gear body 10 through the electric push rod installation shaft 90, and the electric push rod installation shaft 90 is a supporting member of the electric push rod 50.
As an embodiment of the present invention, the connections between the components, for example, between the landing gear 30 and the landing gear body 10, between the shift lever 40 and the landing gear 30, between the electric push rod 50 and the electric push rod mounting shaft 90 and the landing gear 30, between the stop block 60 and the landing gear door 20, etc., may be connected by bolts, pins, or hinges, etc. to achieve the functions of the whole system.
With the above configuration, under the control of an electrical instruction, when the electric push rod 50 contracts, the electric push rod 50 drives the landing gear 30 to retract, the shift lever 40 moves along with the landing gear 30 toward the landing gear body 10, when the shift lever 40 moves to the position of the stop block 60 at the landing gear door hinge 71, the shift lever 40 shifts the stop block 60 to move toward the landing gear body 10, and because the stop block 60 is fixedly connected with the landing gear door 20, the stop block 60 drives the landing gear door 20 to close toward the landing gear body 10. When the electric push rod 50 extends, the electric push rod 50 drives the landing gear 30 to descend, the shift lever 40 moves away from the landing gear cabin body 10 along with the landing gear 30, the limiting effect of the shift lever 40 on the stop block 60 disappears, and the landing gear door 20 is opened under the action of gravity and a torsion spring and is kept in an open state under the action of the torsion spring. In the present invention, the close of the landing gear doors 20 can be achieved at the same time as the landing gear 30 is stowed in place by a refinement in the cross-sectional shape of the stop 60 and the position of the toggle lever 40.
The undercarriage retraction and extension and cabin door linkage mechanism for the small-sized fixed wing unmanned aerial vehicle can realize controllable retraction and extension of the undercarriage 30 on the premise of not sacrificing too much structural weight, and simultaneously, the cabin door can realize automatic closing and opening along with retraction and extension of the undercarriage 30, has the characteristics of simple structure, light weight and easiness in maintenance, can effectively reduce the structural weight ratio of the undercarriage system, and improves the use and maintenance performance.
For further understanding of the present invention, the landing gear retraction and door linkage mechanism for a small fixed wing drone according to the present invention is described in detail below with reference to fig. 1 to 4.
As shown in fig. 1 to 4, according to an embodiment of the present invention, there is provided a landing gear retraction and door linkage mechanism for a small fixed wing drone, the landing gear retraction and door linkage mechanism including: landing gear bay 10, landing gear bay door 20, landing gear 30, shift lever 40, electric push rod 50, stop 60, plurality of hinges 71, plurality of torsion springs, and electric push rod mounting shaft 90.
One side of the landing gear door 20 is rotatably connected to the landing gear bay body 10 by a plurality of hinges 71. The landing gear 30 is rotatably connected to the landing gear body 10. The shifter lever 40 is connected to the landing gear 30. The electric push rod 50 is connected with the landing gear body 10 through an electric push rod mounting shaft 90, meanwhile, the electric push rod 50 is connected with the landing gear 30, and the electric push rod 50 is used for achieving retraction and extension of the landing gear 30 relative to the landing gear body 10. The stop block 60 is located at the junction of the landing gear body 10 and the landing gear door 20 and is fixedly connected with the landing gear door 20, and the stop block 60 is used for cooperating with the shift lever 40 to close and open the landing gear door 20 along with the retraction and extension of the landing gear 30. A plurality of torsion springs are located on the axis of rotation of the hinge assembly 70, and the plurality of hinges 71 are arranged in one-to-one correspondence with the plurality of torsion springs for urging the landing gear door 20 open and maintaining the landing gear door 20 in an open state.
When the electric push rod 50 contracts, the electric push rod 50 drives the landing gear 30 to retract, the shift lever 40 moves towards the landing gear cabin 10 along with the landing gear 30, and the shift lever 40 shifts the stop block 60 to drive the landing gear cabin door 20 to close; when the electric push rod 50 extends, the electric push rod 50 drives the landing gear 30 to descend, the shift lever 40 moves away from the landing gear cabin body 10 along with the landing gear 30, the limiting effect of the shift lever 40 on the stop block 60 disappears, and the landing gear door 20 is opened under the action of gravity.
In conclusion, the invention provides the undercarriage retraction and extension and cabin door linkage mechanism for the small-sized fixed wing unmanned aerial vehicle, the undercarriage retraction and extension of the cabin door linkage mechanism are realized through the electric push rod, the closing and opening of the cabin door of the undercarriage along with the retraction and extension of the undercarriage can be realized through the mutual matching of the shift lever and the stop block, the linkage mechanism can realize the controllable retraction and extension of the undercarriage on the premise of not sacrificing too much structural weight, and simultaneously, the cabin door can realize the automatic closing and opening along with the retraction and extension of the undercarriage. Compared with the prior art, the technical scheme of the invention can solve the technical problems that the undercarriage folding and unfolding and cabin door linkage mechanism in the prior art is high in weight, the actuating mechanism is complex and difficult to miniaturize, and the undercarriage folding and unfolding and cabin door linkage mechanism cannot be suitable for a small-sized fixed wing unmanned aerial vehicle.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. The utility model provides a undercarriage receive and release and hatch door link gear for small-size fixed wing unmanned aerial vehicle which characterized in that, undercarriage receive and release and hatch door link gear includes:
a landing gear bay (10);
a landing gear door (20), one side of the landing gear door (20) being rotatably connected with the landing gear cabin (10);
a landing gear (30), the landing gear (30) being rotatably connected to the landing gear body (10);
a deflector rod (40), the deflector rod (40) being connected to the landing gear (30);
the electric push rod (50), the electric push rod (50) is respectively connected with the landing gear cabin body (10) and the landing gear (30), and the electric push rod (50) is used for realizing the retraction and the extension of the landing gear (30) relative to the landing gear cabin body (10);
the stop block (60) is positioned at the joint of the landing gear cabin body (10) and the landing gear door (20) and is fixedly connected with the landing gear door (20), and the stop block (60) is used for being matched with the shift lever (40) to realize the closing and opening of the landing gear door (20) along with the retraction and the extension of the landing gear (30);
when the electric push rod (50) is contracted, the electric push rod (50) drives the landing gear (30) to retract, the shift lever (40) moves towards the landing gear cabin body (10) along with the landing gear (30), and the shift lever (40) shifts the stop block (60) to drive the landing gear cabin door (20) to close; when the electric push rod (50) extends, the electric push rod (50) drives the landing gear (30) to be lowered, the shift rod (40) moves along with the landing gear (30) away from the landing gear cabin body (10), the limit effect of the shift rod (40) on the stop block (60) disappears, and the landing gear cabin door (20) is opened under the action of gravity.
2. The landing gear stowing and door linkage for a small fixed wing drone according to claim 1, characterized in that it further comprises a hinge assembly (70), the landing gear door (20) being rotatably connected to the landing gear bay (10) by means of the hinge assembly (70).
3. The landing gear stowing and door linkage for a small fixed wing drone according to claim 2, characterized in that it further comprises a resilient assembly (80), the resilient assembly (80) being located on the axis of rotation of the hinge assembly (70), the resilient assembly (80) being used to urge the landing gear door (20) open and to hold the landing gear door (20) in the open condition.
4. The landing gear stowing and door linkage for a small fixed wing drone according to claim 3, wherein the hinge assembly (70) includes a plurality of hinges (71), the resilient assembly (80) includes a plurality of resilient members (81), the plurality of hinges (71) being arranged in one-to-one correspondence with the plurality of resilient members (81).
5. The landing gear stowing and door linkage for small fixed wing drones according to claim 3 or 4, characterized in that the elastic member (81) comprises a torsion spring.
6. The landing gear stowing and door linkage for a small fixed wing drone according to any one of claims 1 to 5, characterized in that it further comprises an electric push rod mounting shaft (90), by means of which the electric push rod (50) is fixed on the landing gear body (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010998907.7A CN114248912A (en) | 2020-09-22 | 2020-09-22 | Undercarriage folding and unfolding and cabin door linkage mechanism for small-sized fixed wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010998907.7A CN114248912A (en) | 2020-09-22 | 2020-09-22 | Undercarriage folding and unfolding and cabin door linkage mechanism for small-sized fixed wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN114248912A true CN114248912A (en) | 2022-03-29 |
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| CN202010998907.7A Pending CN114248912A (en) | 2020-09-22 | 2020-09-22 | Undercarriage folding and unfolding and cabin door linkage mechanism for small-sized fixed wing unmanned aerial vehicle |
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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100140395A1 (en) * | 2008-12-05 | 2010-06-10 | Messier-Dowty Inc. | Double hook door mechanism |
| US20120168562A1 (en) * | 2009-07-03 | 2012-07-05 | Messier-Bugatti-Dowty | Device for controlling trapdoors closing the hold of aircraft landing gear |
| WO2014009616A1 (en) * | 2012-07-12 | 2014-01-16 | Aerolia | Device for opening and closing a hatch of an aircraft gear casing |
| GB201412403D0 (en) * | 2014-07-11 | 2014-08-27 | Airbus Uk Ltd | Door abutment |
| CN104176244A (en) * | 2014-09-17 | 2014-12-03 | 江西洪都航空工业集团有限责任公司 | Linked landing gear cabin door folding and unfolding device |
| CN104527972A (en) * | 2014-12-05 | 2015-04-22 | 中国航天空气动力技术研究院 | Unmanned plane undercarriage cabin door retraction-extension servo mechanism |
| CN107745810A (en) * | 2015-12-23 | 2018-03-02 | 钟水龙 | A kind of unmanned plane |
| CN108791917A (en) * | 2018-04-10 | 2018-11-13 | 清远市巨劲科技有限公司 | A kind of unmanned plane of taking photo by plane of multi-faceted shooting |
| CN210044858U (en) * | 2019-05-20 | 2020-02-11 | 东莞市飞翼电子科技有限公司 | Spring type undercarriage cabin door switch structure |
| CN110803279A (en) * | 2019-12-06 | 2020-02-18 | 沈阳航空航天大学 | Aircraft landing gear for enhancing closing tightness of furled cabin door |
| CN111470034A (en) * | 2020-04-29 | 2020-07-31 | 江苏工程职业技术学院 | Linkage mechanism of follow-up switch of landing gear cabin door of airplane |
| CN111619783A (en) * | 2020-05-13 | 2020-09-04 | 河北三丰航空科技股份有限公司 | Unmanned aerial vehicle with collapsible unmanned aerial vehicle support piece |
-
2020
- 2020-09-22 CN CN202010998907.7A patent/CN114248912A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100140395A1 (en) * | 2008-12-05 | 2010-06-10 | Messier-Dowty Inc. | Double hook door mechanism |
| US20120168562A1 (en) * | 2009-07-03 | 2012-07-05 | Messier-Bugatti-Dowty | Device for controlling trapdoors closing the hold of aircraft landing gear |
| WO2014009616A1 (en) * | 2012-07-12 | 2014-01-16 | Aerolia | Device for opening and closing a hatch of an aircraft gear casing |
| GB201412403D0 (en) * | 2014-07-11 | 2014-08-27 | Airbus Uk Ltd | Door abutment |
| CN104176244A (en) * | 2014-09-17 | 2014-12-03 | 江西洪都航空工业集团有限责任公司 | Linked landing gear cabin door folding and unfolding device |
| CN104527972A (en) * | 2014-12-05 | 2015-04-22 | 中国航天空气动力技术研究院 | Unmanned plane undercarriage cabin door retraction-extension servo mechanism |
| CN107745810A (en) * | 2015-12-23 | 2018-03-02 | 钟水龙 | A kind of unmanned plane |
| CN108791917A (en) * | 2018-04-10 | 2018-11-13 | 清远市巨劲科技有限公司 | A kind of unmanned plane of taking photo by plane of multi-faceted shooting |
| CN210044858U (en) * | 2019-05-20 | 2020-02-11 | 东莞市飞翼电子科技有限公司 | Spring type undercarriage cabin door switch structure |
| CN110803279A (en) * | 2019-12-06 | 2020-02-18 | 沈阳航空航天大学 | Aircraft landing gear for enhancing closing tightness of furled cabin door |
| CN111470034A (en) * | 2020-04-29 | 2020-07-31 | 江苏工程职业技术学院 | Linkage mechanism of follow-up switch of landing gear cabin door of airplane |
| CN111619783A (en) * | 2020-05-13 | 2020-09-04 | 河北三丰航空科技股份有限公司 | Unmanned aerial vehicle with collapsible unmanned aerial vehicle support piece |
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