CN114248912B - Landing gear retracting and cabin door linkage mechanism for small fixed wing unmanned aerial vehicle - Google Patents
Landing gear retracting and cabin door linkage mechanism for small fixed wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN114248912B CN114248912B CN202010998907.7A CN202010998907A CN114248912B CN 114248912 B CN114248912 B CN 114248912B CN 202010998907 A CN202010998907 A CN 202010998907A CN 114248912 B CN114248912 B CN 114248912B
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- Prior art keywords
- landing gear
- door
- cabin
- electric push
- push rod
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- 230000007246 mechanism Effects 0.000 title abstract description 33
- 230000009471 action Effects 0.000 claims description 10
- 230000005484 gravity Effects 0.000 claims description 6
- 230000000670 limiting effect Effects 0.000 claims description 4
- 230000001737 promoting effect Effects 0.000 claims 1
- 238000000034 method Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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 ASSOCIATED WITH SUBCLASSES E05D AND E05F, RELATING TO CONSTRUCTION ELEMENTS, ELECTRIC CONTROL, POWER SUPPLY, POWER SIGNAL OR TRANSMISSION, USER INTERFACES, MOUNTING OR COUPLING, DETAILS, ACCESSORIES, AUXILIARY OPERATIONS NOT OTHERWISE PROVIDED FOR, APPLICATION THEREOF
- 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 or spacecraft
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- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05Y—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES E05D AND E05F, RELATING TO CONSTRUCTION ELEMENTS, ELECTRIC CONTROL, POWER SUPPLY, POWER SIGNAL OR TRANSMISSION, USER INTERFACES, MOUNTING OR COUPLING, DETAILS, ACCESSORIES, AUXILIARY OPERATIONS NOT OTHERWISE PROVIDED FOR, APPLICATION THEREOF
- E05Y2900/00—Application of doors, windows, wings or fittings thereof
- E05Y2900/50—Application of doors, windows, wings or fittings thereof for vehicles
- E05Y2900/53—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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power-Operated Mechanisms For Wings (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention provides a landing gear retracting and cabin door linkage mechanism for a small fixed wing unmanned aerial vehicle, which comprises the following components: a landing gear bay; the landing gear cabin door is rotatably connected with the landing gear cabin body at one side; the landing gear is rotatably connected with the landing gear cabin body; the deflector rod is connected with the landing gear; the electric push rod is respectively connected with the landing gear cabin body and the landing gear, and is used for realizing retraction and extension of the landing gear relative to the landing gear cabin body; the stop block is positioned at the joint of the landing gear cabin body and the landing gear cabin door and fixedly connected with the landing gear cabin door, and the stop block is used for being matched with the deflector rod to realize that the landing gear cabin door is closed and opened along with the retraction of the landing gear. By applying the technical scheme of the invention, the technical problems that the landing gear 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 landing gear folding and unfolding and cabin door linkage mechanism cannot be suitable for a small fixed wing unmanned aerial vehicle can be solved.
Description
Technical Field
The invention relates to the technical field of small fixed wing unmanned aerial vehicles, in particular to a landing gear retracting and cabin door linkage mechanism for a small fixed wing unmanned aerial vehicle.
Background
For a small fixed-wing unmanned aerial vehicle, the retractable landing gear and the closable cabin door can effectively reduce flight resistance, save fuel consumption and play a vital role in improving the flight speed and the endurance time of the unmanned aerial vehicle. The landing gear retraction and cabin door opening and closing scheme adopted by the traditional unmanned aerial vehicle or the large unmanned aerial vehicle has the defects of high structural weight, complex actuating mechanism and difficult miniaturization, and is not suitable for the small fixed wing unmanned aerial vehicle.
Disclosure of Invention
The invention provides a landing gear retracting and cabin door linkage mechanism for a small fixed wing unmanned aerial vehicle, which can solve the technical problems that the landing gear retracting 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 retracting and cabin door linkage mechanism cannot be suitable for the small fixed wing unmanned aerial vehicle.
The invention provides a landing gear retracting and cabin door linkage mechanism for a small fixed wing unmanned aerial vehicle, which comprises the following components: a landing gear bay; the landing gear cabin door is rotatably connected with the landing gear cabin body at one side; the landing gear is rotatably connected with the landing gear cabin body; the deflector rod is connected with the landing gear; the electric push rod is respectively connected with the landing gear cabin body and the landing gear, and is used for realizing retraction and extension of the landing gear relative to the landing gear cabin body; the stop block is positioned at the joint of the landing gear cabin body and the landing gear cabin door, is fixedly connected with the landing gear cabin door and is used for being matched with the deflector rod to realize that the landing gear cabin door is closed and opened along with the retraction of the landing gear; when the electric push rod contracts, the electric push rod drives the landing gear to retract, the deflector rod moves towards the landing gear cabin body along with the landing gear, and the deflector rod drives the stop block to drive the landing gear cabin door to close; when the electric push rod stretches, the electric push rod drives the landing gear to be lowered, the deflector rod moves along with the landing gear and away from the landing gear cabin body, the limiting effect of the deflector rod on the stop block disappears, and the landing gear cabin door is opened under the action of gravity.
Further, the landing gear retraction and door linkage also includes a hinge assembly through which the landing gear door is rotatably coupled to the landing gear bay.
Further, the landing gear retraction and door linkage mechanism also includes a spring assembly positioned on the axis of rotation of the hinge assembly, the spring assembly configured to urge the landing gear door open and to maintain the landing gear door in an open position.
Further, the hinge assembly comprises a plurality of hinges, the elastic assembly comprises a plurality of elastic pieces, and the hinges and the elastic pieces are arranged in one-to-one correspondence.
Further, the elastic member includes a torsion spring.
Further, the landing gear retracting and cabin door linkage mechanism further comprises an electric push rod mounting shaft, and the electric push rod is fixed on the landing gear cabin body through the electric push rod mounting shaft.
By the technical scheme, the landing gear retracting and opening and cabin door linkage mechanism for the small fixed wing unmanned aerial vehicle is provided, the landing gear retracting and opening and closing of the landing gear cabin door along with the retracting and opening of the landing gear can be realized through the mutual matching of the deflector rod and the stop dog, the linkage mechanism can realize the controllable retracting and opening of the landing gear on the premise of not sacrificing excessive structural weight, and meanwhile, the cabin door can realize the automatic closing and opening along with the retracting and opening of the landing gear. Compared with the prior art, the technical scheme of the invention can solve the technical problems that the landing gear 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 landing gear folding and unfolding and cabin door linkage mechanism cannot be suitable for a small fixed wing unmanned aerial vehicle.
Drawings
The accompanying drawings, which are included to provide a further understanding of 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 evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
Fig. 1 shows a schematic structural view of a landing gear retraction and door linkage for a small fixed wing unmanned aerial vehicle provided in accordance with a specific embodiment of the present invention;
Figure 2 shows a schematic view of door installation provided in accordance with a specific embodiment of the present invention;
FIG. 3 illustrates a schematic view of a landing gear retraction process provided in accordance with an embodiment of the present invention;
Fig. 4 shows a schematic view of the structure of a landing gear according to an embodiment of the present invention in a stowed state.
Wherein the above figures include the following reference numerals:
10. A landing gear bay; 20. landing gear bay doors; 30. landing gear; 40. a deflector rod; 50. an electric push rod; 60. a stop, 70, a hinge assembly; 71. a hinge; 80. an elastic component; 81. an elastic member; 90. the electric push rod is provided with a shaft.
Detailed Description
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
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 exemplary embodiments according to the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one 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 specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
As shown in fig. 1 to 4, there is provided a landing gear retraction and door linkage for a small fixed wing unmanned aerial vehicle according to an embodiment of the present invention, the landing gear retraction and door linkage comprising: landing gear bay 10, landing gear bay door 20, landing gear 30, toggle lever 40, electric push rod 50, and stop 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 bay 10. A lever 40 is connected to landing gear 30. The electric push rod 50 is connected with the landing gear cabin 10 and the landing gear 30 respectively, 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 10. The stop 60 is located at the connection between the landing gear cabin 10 and the landing gear door 20, and is fixedly connected to the landing gear door 20, and the stop 60 is used for cooperating with the deflector 40 to enable the landing gear door 20 to be closed and opened along with the retraction 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 deflector rod 40 moves towards the landing gear cabin body 10 along with the landing gear 30, and the deflector rod 40 drives the stop block 60 to drive the landing gear cabin door 20 to close; when the electric push rod 50 is extended, the electric push rod 50 drives the landing gear 30 to be lowered, the deflector 40 moves along with the landing gear 30 away from the landing gear cabin 10, the limit action of the deflector 40 on the stop block 60 disappears, and the landing gear cabin door 20 is opened under the action of gravity.
By applying the configuration mode, the landing gear retracting and cabin door linkage mechanism for the small fixed wing unmanned aerial vehicle is provided, the landing gear retracting and cabin door linkage mechanism realizes the retracting and the retracting of the landing gear 30 through the electric push rod 50, and can realize the closing and the opening of the landing gear cabin door 20 along with the retracting and the retracting of the landing gear 30 through the mutual matching of the deflector rod 40 and the stop block 60, the linkage mechanism can realize the controllable retracting and the retracting of the landing gear 30 on the premise of not sacrificing excessive structural weight, and simultaneously, the cabin door can realize the automatic closing and the opening along with the retracting and the retracting of the landing gear 30. Compared with the prior art, the technical scheme of the invention can solve the technical problems that the landing gear 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 landing gear folding and unfolding and cabin door linkage mechanism cannot be suitable for a small fixed wing unmanned aerial vehicle.
Further, in the present invention, to achieve a rotatable connection of the landing gear door 20 with the landing gear bay body 10, the configurable landing gear retraction and door linkage also includes a hinge assembly 70, the landing gear door 20 being rotatably connected to the landing gear bay body 10 by the hinge assembly 70. The landing gear bay 10 is a physical space that accommodates the landing gear 30 as part of the structure of the machine, and the landing gear 30 acts to carry the weight of the machine. 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 door 20 and the landing gear bay 10. The number of hinges 71 may be adjusted according to the size and physical requirements of the landing gear door 20, for example, as shown in fig. 2, the hinge assembly 70 may include three hinges 71, and the stop 60 may be disposed at the middle hinge 71.
Furthermore, in the present invention, in order to avoid that the landing gear door 20 cannot be normally opened only under the action of gravity and that the landing gear door 20 is rocked during the flight of the unmanned aerial vehicle, the landing gear retraction and door linkage mechanism may further be configured to include an elastic assembly 80, where the elastic assembly 80 is located on the rotation axis of the hinge assembly 70, and the elastic assembly 80 is configured to urge the landing gear door 20 to open and keep the landing gear door 20 in the open 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 elastic members 81 can also be adjusted according to practical needs, for example, as shown in fig. 2, the elastic assembly 80 includes three elastic members 81.
Further, in the present invention, as shown in fig. 2, in order to achieve the open state control of the elastic member 81 to the landing gear door 20, 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 kept in the open state. In the present invention, other elastic members 81 that can urge the landing gear door 20 to open and hold the landing gear door 20 in an open state, other than torsion springs, are optional, and the electric push rod 50 is a power source for retraction of the landing gear 30.
In addition, in the present invention, in order to achieve the fixed mounting of the electric push rod 50, the landing gear retracting and door linkage may be further configured to include an electric push rod mounting shaft 90, the electric push rod 50 being fixed to the landing gear bay 10 by the electric push rod mounting shaft 90, the electric push rod mounting shaft 90 being a supporting member of the electric push rod 50.
As a specific embodiment of the present invention, the connection between the components, for example, between the landing gear 30 and the landing gear bay 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 stopper 60 and the landing gear bay door 20, etc., may be connected by bolts, pins or hinges, etc., to achieve the function of the entire system.
With the above configuration, under the control of the electrical instruction, when the electrical push rod 50 is retracted, the electrical push rod 50 drives the landing gear 30 to retract, the shift lever 40 moves along with the landing gear 30 towards the landing gear cabin 10, and when the shift lever 40 moves to the stop 60 position at the landing gear door hinge 71, the shift lever 40 shifts the stop 60 towards the landing gear cabin 10, and because the stop 60 is fixedly connected with the landing gear door 20, the stop 60 drives the landing gear door 20 to close towards the landing gear cabin 10. When the electric push rod 50 is extended, the electric push rod 50 drives the landing gear 30 to be lowered, the deflector 40 moves along with the landing gear 30 away from the landing gear cabin 10, the limit action of the deflector 40 on the stop block 60 disappears, and the landing gear cabin door 20 is opened under the action of gravity and the torsion spring and kept in an opened state under the action of the torsion spring. In the present invention, the tightening of the landing gear door 20 while the landing gear 30 is retracted and positioned can be achieved by a fine design of the cross-sectional shape of the stopper 60 and the position of the lever 40.
The landing gear retracting and cabin door linkage mechanism for the small fixed wing unmanned aerial vehicle can realize the controllable retracting and releasing of the landing gear 30 on the premise of not sacrificing excessive structural weight, and simultaneously enables the cabin door to realize automatic closing and opening along with the retracting and releasing of the landing gear 30.
For further understanding of the present invention, the landing gear retraction and door linkage for a small fixed wing unmanned aerial vehicle of the present invention will be described in detail below with reference to fig. 1 to 4.
As shown in fig. 1 to 4, there is provided a landing gear retraction and door linkage for a small fixed wing unmanned aerial vehicle according to an embodiment of the present invention, the landing gear retraction and door linkage comprising: landing gear bay 10, landing gear bay door 20, landing gear 30, toggle lever 40, electric push rod 50, stop 60, a plurality of hinges 71, a 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 10 by a plurality of hinges 71. The landing gear 30 is rotatably connected to the landing gear bay 10. A lever 40 is connected to landing gear 30. The electric push rod 50 is connected with the landing gear cabin 10 through the 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 cabin 10. The stop 60 is located at the connection between the landing gear cabin 10 and the landing gear door 20, and is fixedly connected to the landing gear door 20, and the stop 60 is used for cooperating with the deflector 40 to enable the landing gear door 20 to be closed and opened along with the retraction of the landing gear 30. A plurality of torsion springs are disposed on the rotation shaft of the hinge assembly 70, and a plurality of hinges 71 are disposed in one-to-one correspondence with the plurality of torsion springs, and the torsion springs are used to urge the landing gear door 20 to open and keep the landing gear door 20 in an open state.
When the electric push rod 50 is contracted, the electric push rod 50 drives the landing gear 30 to retract, the deflector rod 40 moves towards the landing gear cabin 10 along with the landing gear 30, and the deflector rod 40 drives the stop block 60 to drive the landing gear cabin door 20 to close; when the electric push rod 50 is extended, the electric push rod 50 drives the landing gear 30 to be lowered, the deflector 40 moves along with the landing gear 30 away from the landing gear cabin 10, the limit action of the deflector 40 on the stop block 60 disappears, and the landing gear cabin door 20 is opened under the action of gravity.
In summary, the invention provides a landing gear retracting and cabin door linkage mechanism for a small fixed wing unmanned aerial vehicle, which realizes the retraction of a landing gear through an electric push rod, and can realize the closing and opening of a landing gear cabin door along with the retraction of the landing gear through the mutual cooperation of a deflector rod and a stop block, and the linkage mechanism can realize the controllable retraction of the landing gear on the premise of not sacrificing excessive structural weight, and simultaneously, the cabin door can realize the automatic closing and opening along with the retraction of the landing gear. Compared with the prior art, the technical scheme of the invention can solve the technical problems that the landing gear 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 landing gear folding and unfolding and cabin door linkage mechanism cannot be suitable for a small fixed wing unmanned aerial vehicle.
Spatially relative terms, such as "above … …," "above … …," "upper surface on … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative 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 in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present invention.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. A undercarriage receive and releases and hatch door link gear for small-size fixed wing unmanned aerial vehicle, its characterized in that, undercarriage receive and releases 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 to the landing gear compartment body (10);
-a landing gear (30), the landing gear (30) being rotatably connected to the landing gear bay (10);
a deflector rod (40), the deflector rod (40) being connected to the landing gear (30);
The electric push rod (50) is respectively connected with the landing gear cabin (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 (10);
The stop block (60) is positioned at the joint of the landing gear cabin body (10) and the landing gear cabin door (20) and is fixedly connected with the landing gear cabin door (20), and the stop block (60) is used for being matched with the deflector rod (40) so as to realize that the landing gear cabin door (20) is closed and opened along with the retraction and the extension of the landing gear (30);
-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), the hinge assembly (70) comprising a plurality of hinges (71);
The elastic assembly (80) is positioned on the rotating shaft of the hinge assembly (70), the elastic assembly (80) is used for promoting the landing gear door (20) to be opened and keeping the landing gear door (20) in an opened state, the elastic assembly (80) comprises a plurality of elastic pieces (81), and the hinges (71) are arranged in one-to-one correspondence with the elastic pieces (81);
When the electric push rod (50) is contracted, the electric push rod (50) drives the landing gear (30) to retract, the deflector rod (40) moves towards the landing gear cabin body (10) along with the landing gear (30), and the deflector rod (40) drives the stop block (60) to drive the landing gear cabin door (20) to close; when the electric push rod (50) stretches, the electric push rod (50) drives the landing gear (30) to be lowered, the deflector rod (40) moves away from the landing gear cabin body (10) along with the landing gear (30), the limiting effect of the deflector rod (40) on the stop block (60) disappears, and the landing gear cabin door (20) is opened under the action of gravity.
2. Landing gear retraction and door linkage for a small fixed wing unmanned aerial vehicle according to claim 1, wherein the resilient member (81) comprises a torsion spring.
3. Landing gear retraction and door linkage for a small fixed wing unmanned aerial vehicle according to claim 1 or 2, wherein the landing gear retraction and door linkage further comprises an electric push rod mounting shaft (90), the electric push rod (50) being fixed to the landing gear bay (10) by means of the electric push rod mounting shaft (90).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010998907.7A CN114248912B (en) | 2020-09-22 | 2020-09-22 | Landing gear retracting and cabin door linkage mechanism for small fixed wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010998907.7A CN114248912B (en) | 2020-09-22 | 2020-09-22 | Landing gear retracting and cabin door linkage mechanism for small fixed wing unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114248912A CN114248912A (en) | 2022-03-29 |
| CN114248912B true CN114248912B (en) | 2024-06-11 |
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| CN202010998907.7A Active CN114248912B (en) | 2020-09-22 | 2020-09-22 | Landing gear retracting and cabin door linkage mechanism for small fixed wing unmanned aerial vehicle |
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| 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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| CN114248912A (en) | 2022-03-29 |
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