CN116750234A

CN116750234A - Unmanned aerial vehicle undercarriage

Info

Publication number: CN116750234A
Application number: CN202311053970.3A
Authority: CN
Inventors: 叶成海; 郝树奇; 高文文; 任航
Original assignee: Shaanxi Dexin Intelligent Technology Co ltd
Current assignee: Shaanxi Dexin Intelligent Technology Co ltd
Priority date: 2023-08-21
Filing date: 2023-08-21
Publication date: 2023-09-15
Anticipated expiration: 2043-08-21
Also published as: CN116750234B

Abstract

The application relates to the technical field of landing gears, in particular to an unmanned aerial vehicle landing gear, which comprises a cabin door assembly and a landing gear. The cabin door assembly comprises a cabin body and a cabin door hinged with the cabin body, a storage cavity is formed in the cabin body, a driven assembly is arranged on the cabin door, and the driven assembly is used for driving the cabin door to open or close; the landing gear is folded and stored into the Chu Naqiang, the landing gear comprises a retraction motion assembly, one end of the retraction motion assembly is hinged to the cabin body, chu Naqiang is used for storing the retraction motion assembly, a torsion preventing arm is arranged on the retraction motion assembly and used for driving the driven assembly to move, and the retraction motion assembly is stored to drive the cabin door to be closed. The application has the effect of simplifying the retraction operation of the landing gear and the cabin door of the unmanned aerial vehicle.

Description

Unmanned aerial vehicle undercarriage

Technical Field

The application relates to the technical field of landing gears, in particular to an unmanned aerial vehicle landing gear.

Background

At present, the unmanned aerial vehicle comprises a body, the landing gear and a landing gear cabin door are respectively arranged on the body, and the landing gear cabin door is a key structure for keeping the aerodynamic appearance of the body after the landing gear is retracted. The landing gear and the landing gear cabin door are generally independent of each other, namely, the retraction and the opening and closing of the landing gear and the cabin door are required to be completed by two independent action structures. When the unmanned aerial vehicle takes off, the landing gear is required to be folded and stored, and then the cabin door is closed. When the landing gear needs to be released, the cabin door needs to be opened first, and then the landing gear is driven to stretch.

For the related art in the above: the opening and closing of the landing gear cabin door of the unmanned aerial vehicle and the retraction process of the landing gear are mutually independent, so that the retraction operation of the landing gear and the cabin door of the unmanned aerial vehicle is complicated.

Disclosure of Invention

In order to simplify the retraction operation of an unmanned aerial vehicle landing gear and a cabin door, the application provides the unmanned aerial vehicle landing gear.

The application provides an unmanned aerial vehicle landing gear, which adopts the following technical scheme:

an unmanned aerial vehicle landing gear, comprising:

the cabin door assembly comprises a cabin body and a cabin door hinged with the cabin body, a storage cavity is formed in the cabin body, a driven assembly is arranged on the cabin door, and the driven assembly is used for driving the cabin door to open or close;

the landing gear, the landing gear is folded and is accomodate to Chu Naqiang is interior, the landing gear includes receive and releases action subassembly, receive and release action subassembly's one end with the cabin body is articulated, chu Naqiang is used for accomodating receive and release action subassembly, be provided with the anti-torsion arm on the receive and release action subassembly, the anti-torsion arm is used for driving driven assembly removes, in order to realize receive and release action subassembly is accomodate and is driven the hatch door is closed.

By adopting the technical scheme, when the retraction motion assembly is used for carrying out retraction, the retraction motion assembly drives the anti-torsion arm to move, and the anti-torsion arm drives the driven assembly to move, so that the cabin door is conveniently driven to be closed; when the retraction motion assembly is put down, the retraction motion assembly drives the anti-torsion arm to move, so that the anti-torsion arm does not apply thrust to the driven assembly any more, the driven assembly is convenient to drive the cabin door to open, and retraction operation of the landing gear and the cabin door of the unmanned aerial vehicle is simplified to a certain extent.

Optionally, receive and release action subassembly includes driving piece and hydraulic buffer pillar, the one end of driving piece articulates on Chu Naqiang's the inner wall, the other end of driving piece with hydraulic buffer pillar articulates, hydraulic buffer pillar is close to the one end of driving piece articulates there is the mounting, the mounting is used for fixing on the fuselage, the torsion-proof arm sets up on the hydraulic buffer pillar.

Through adopting above-mentioned technical scheme, the driving piece can drive the hydraulic buffer pillar and remove, and the one end of hydraulic buffer pillar is fixed through the mounting to make the driving piece can drive the hydraulic buffer pillar and change the horizontality into by vertical, and then be convenient for accomodate hydraulic buffer pillar and torque proof arm into storing up and receive the intracavity.

Optionally, the hydraulic buffer support post include the connecting piece and with the connecting piece rotates the buffer module of being connected, the connecting piece keep away from the one end of buffer module respectively with the output of driving piece with the mounting is articulated, the buffer module is kept away from the one end of connecting piece is provided with the organic wheel, the connecting piece is close to the one end of buffer module is provided with steering engine, steering engine is used for the drive buffer module rotates.

Through adopting above-mentioned technical scheme, steering rudder can drive buffer assembly and take place to rotate on the connecting piece, and buffer assembly can drive the wheel and rotate to the direction of movement of the control wheel of being convenient for, and then be favorable to carrying out tracking control to unmanned aerial vehicle take off and land the route when running, with adjust unmanned aerial vehicle's route in real time.

Optionally, the buffer module includes sleeve and bracing piece, the one end of bracing piece is inserted and is established in the sleeve and with sleeve fixed connection, the other end of bracing piece with the wheel is connected, the sleeve is kept away from the one end rotation of bracing piece is connected on the connecting piece, steering engine with telescopic joint, the torsion-preventing arm is including first linking arm and the second linking arm of mutual articulated, first linking arm is kept away from the one end of second linking arm with the bracing piece is articulated, the second linking arm is kept away from the one end of first linking arm with the sleeve is articulated.

Through adopting above-mentioned technical scheme, first linking arm and second linking arm mutually support, can carry out spacingly to sleeve and bracing piece for the bracing piece is difficult for rotating for the sleeve, thereby is favorable to steering engine stable and accurate drive sleeve and bracing piece to rotate. And the sleeve can limit the supporting rod, so that the supporting rod is not easy to swing, and further the anti-swing and anti-torsion capabilities of the hydraulic buffer support column are improved.

Optionally, the first connecting arm is provided with a pushing member, the driven component includes two connecting rods hinged to each other, one ends of the two connecting rods, which are away from each other, are respectively hinged to the inner wall of the cabin door and the inner wall of the Chu Naqiang, and the pushing member is used for pushing one of the two connecting rods hinged to the inner wall of the Chu Naqiang to move.

Through adopting above-mentioned technical scheme, when the hydraulic buffer pillar moved to storing up the intracavity, first linking arm drove the impeller and removes for articulated one connecting rod on storing up the inner wall of storing up the chamber in impeller and two connecting rods contradicts, thereby be convenient for drive the connecting rod of articulated on storing up the inner wall of storing up the chamber through the impeller and remove, so that articulated connecting rod on storing up the inner wall of storing up the chamber drives another connecting rod and removes, and then be convenient for utilize the connecting rod to drive the hatch door and close.

Optionally, a guide groove is formed in a side wall, close to the driving piece, of the cabin body, the guide groove is communicated with the Chu Naqiang, a guide piece is arranged on the driving piece, and the guide piece is inserted into the guide groove.

Through adopting above-mentioned technical scheme, the guide way can play the guide effect to the guide piece, and the guide piece can play the guide effect to the driving piece to make the driving piece can stably drive hydraulic buffer pillar and fold or extend.

Optionally, a yielding groove is formed on a side, close to the fixing piece, of the cabin body, the yielding groove is communicated with the Chu Naqiang, and the yielding groove is used for yielding for rotation of the hydraulic buffering support column.

Through adopting above-mentioned technical scheme, the groove of stepping down can provide the shift position for hydraulic buffer support to the driving piece drives hydraulic buffer support and accomodates completely to storing in the chamber.

Optionally, the driven subassembly includes torsional spring and locating part, first spacing groove has been seted up on Chu Naqiang's the inner wall, the second spacing groove has been seted up on the hatch door, the locating part slides respectively and inserts and establish first spacing groove with in the second spacing groove, the locating part is used for right the hatch door is spacing, be provided with first magnetism on the torque arm and inhale the piece, first magnetism is inhaled the piece and is used for driving the locating part first spacing groove with remove in the second spacing groove, the torsional spring sets up the hatch door with between the cabin body, the torsional spring is used for driving the hatch door is closed.

Through adopting above-mentioned technical scheme, when driving piece and hydraulic buffer pillar all are located and store up the intracavity, the locating part is not inserted and is established in the second spacing inslot, and at this moment, the torsional spring can drive the hatch door and close.

When the driving piece drives the hydraulic buffering pillar to move outside the storage cavity, the hydraulic buffering pillar pushes the cabin door to open and drives the anti-torsion arm to move, the anti-torsion arm drives the first magnetic attraction piece to move, and the first magnetic attraction piece drives the limiting piece to move, so that one end of the limiting piece is inserted into the second limiting groove from the first limiting groove, the limiting piece is convenient to limit the cabin door, the cabin door is in an open state, further the follow-up driving piece and the hydraulic buffering pillar are further contained in the storage groove again, and the retraction operation of the landing gear and the cabin door of the unmanned aerial vehicle is simplified to a certain extent.

Optionally, a second magnetic attraction piece is arranged on one side, away from the first limiting groove, of the limiting piece, and the second magnetic attraction piece and the first magnetic attraction piece are attracted mutually.

Through adopting above-mentioned technical scheme, the piece is inhaled to the second magnetism can inhale a mutual attraction with first magnetism to make first magnetism inhale a stable drive locating part removal through the second magnetism.

Optionally, the cross section of first spacing groove the second spacing groove the locating part is the dovetailed setting.

Through adopting above-mentioned technical scheme for the locating part is difficult for breaking away from first spacing groove and second spacing groove.

In summary, the present application includes at least one of the following beneficial technical effects:

1. through the mutual matching of the driven component, the retraction motion component and the torsion-preventing arm, the retraction motion component can drive the cabin door to move so as to drive the cabin door to close when the landing gear is stored, thereby being beneficial to simplifying the retraction operation of the landing gear and the cabin door of the unmanned aerial vehicle;

2. through the mutual matching of the driving piece, the hydraulic buffer support, the fixing piece, the first connecting arm, the second connecting arm, the pushing piece and the connecting rod, the pushing piece can push the connecting rod to move in the process that the driving piece drives the hydraulic buffer support to be converted into a horizontal state from vertical, so that the connecting rod drives the cabin door to move, and the cabin door is driven to be closed when the driving piece and the hydraulic buffer support are accommodated in the storage cavity;

3. through driving piece, hydraulic buffer pillar, hatch door, locating part, torsional spring, anti-torsion arm, first magnetism inhale the piece and the second magnetism inhale the piece mutually support for when driving piece and hydraulic buffer pillar accomodate into storing up and hold the intracavity, the torsional spring can drive the hatch door and close, and when making driving piece and hydraulic buffer pillar stretch out to store up and hold the chamber outward, the locating part can restrict the hatch door in open state all the time, thereby is convenient for simplify the receive and release operation of unmanned aerial vehicle undercarriage and hatch door.

Drawings

Fig. 1 is a schematic overall structure of a landing gear for an unmanned aerial vehicle according to embodiment 1 of the present application.

Fig. 2 is a schematic view of the cabin interior and landing gear of embodiment 1 of the present application.

Fig. 3 is a schematic overall structure of an unmanned aerial vehicle landing gear in a stowed state according to embodiment 1 of the present application.

Fig. 4 is a bottom view of fig. 3.

Fig. 5 is a schematic view showing the structure of the landing gear of embodiment 1 of the present application during storage.

Fig. 6 is a schematic view showing the structure of the cabin interior and the landing gear of embodiment 2 of the present application.

Fig. 7 is a schematic structural view of a stopper according to embodiment 2 of the present application.

Reference numerals illustrate:

1. a hatch assembly; 11. a cabin body; 111. chu Naqiang; 112. a relief groove; 113. a guide groove; 114. a first limit groove; 12. a cabin door; 121. the second limit groove; 13. a driven assembly; 131. a connecting rod; 132. a torsion spring; 133. a limiting piece; 1331. a second magnetic attraction member; 2. landing gear; 21. a retraction motion assembly; 211. a driving member; 2111. a guide member; 212. a hydraulic buffer strut; 2121. a connecting piece; 2122. a sleeve; 2123. a support rod; 213. a fixing member; 22. anti-torsion arms; 221. a first connecting arm; 222. a second connecting arm; 223. a pushing member; 224. a first magnetic attraction member; 23. a fork; 24. a wheel; 25. steering engine.

Detailed Description

The application is described in further detail below with reference to fig. 1-7.

The embodiment of the application discloses an unmanned aerial vehicle landing gear.

Example 1

Referring to fig. 1 and 2, an unmanned aircraft landing gear includes a door assembly 1 and a landing gear 2. The cabin door assembly 1 comprises a cabin body 11 and a cabin door 12 hinged with the cabin body 11, the cabin body 11 is fixedly arranged on a machine body, chu Naqiang and Chu Naqiang 111 are arranged in the cabin body 11 and used for accommodating the landing gear 2, a driven assembly 13 is arranged on the cabin door 12, and the driven assembly 13 is used for driving the cabin door 12 to open or close; the landing gear 2 comprises a retraction motion assembly 21, one end of the retraction motion assembly 21 is hinged with the cabin 11, a torsion preventing arm 22 is arranged on the retraction motion assembly 21, and the torsion preventing arm 22 is used for driving the driven assembly 13 to move so as to realize that the retraction motion assembly 21 is retracted to drive the cabin door 12 to be closed.

The landing gear 2 in this embodiment is provided with three door assemblies 1, the number of which is equal to the number of landing gears 2, and each door assembly 1 corresponds to one landing gear 2. Three landing gears 2 are mounted on the fuselage in a front three-point distribution by means of the door assembly 1.

Referring to fig. 2, the retraction movement assembly 21 includes a driver 211 and a hydraulic buffer strut 212. One end of the driving member 211 is hinged to the inner wall of the Chu Naqiang and the other end of the driving member 211 is hinged to the hydraulic buffer post 212, so that the driving member 211 can drive the hydraulic buffer post 212 to move. The driving member 211 in this embodiment is a hydraulic cylinder.

The hydraulic damping strut 212 includes a link 2121 and a damping assembly rotatably coupled to the link 2121. Wherein, the end of the connecting piece 2121 away from the buffer assembly is hinged with the output end of the driving piece 211, and the end of the connecting piece 2121 away from the end of the buffer assembly is further hinged with the fixing piece 213.

Referring to fig. 2 and 3, the fixing member 213 is fixed to the body by a bolt, and the fixing member 213 can limit the connecting member 2121, so that the position of the connecting member 2121 near one end of the fixing member 213 is not easily deviated, and when the driving member 211 drives the connecting member 2121 to move, the connecting member 2121 can rotate around the fixing member 213, so that the driving member 211 drives the connecting member 2121 to switch between a vertical state and a horizontal state.

Referring to fig. 2 and 4, an end of the cabin 11 near the fixing member 213 is provided with a yielding groove 112, the yielding groove 112 is communicated with the Chu Naqiang 111, and the yielding groove 112 is used for providing a moving position for the connecting member 2121, so that the possibility of interference between the connecting member 2121 and the cabin 11 when the driving member 211 drives the connecting member 2121 to change from a vertical state to a horizontal state is reduced, and the connecting member 2121 enters the storage cavity 111 in the horizontal state for storage.

Referring to fig. 2, a guide groove 113 is formed in a side wall of the cabin 11 adjacent to the driving member 211, and the guide groove 113 is communicated with the Chu Naqiang 111. The guide groove 113 is arranged in an arc shape in this embodiment.

Fixedly connected with guide 2111 on the driving piece 211, guide 2111 slides and inserts and establish in guide slot 113 to make guide slot 113 play the guide effect to driving piece 211 through guide 2111, make driving piece 211 can steadily take place to rotate around the articulated department of self and the inner wall of storing and holding chamber 111, and then make driving piece 211 can steadily drive connecting piece 2121 and rotate.

The buffering component comprises a sleeve 2122 and a supporting rod 2123, wherein the sleeve 2122 is rotationally connected with one end, far away from the fixing piece 213, of the connecting piece 2121, the sleeve 2122 can rotate on the connecting piece 2121 around the axis of the sleeve, one end of the supporting rod 2123 is inserted into the sleeve 2122 and fixedly connected with the sleeve 2122, and accordingly the sleeve 2122 can limit the supporting rod 2123, the supporting rod 2123 is not prone to swing relative to the sleeve 2122, and the sleeve 2122 is convenient to drive the supporting rod 2123 to rotate.

One end of the support rod 2123, which is far away from the sleeve 2122, is fixedly connected with a fork 23, and the fork 23 is rotatably connected with an organic wheel 24. The support rod 2123 and the sleeve 2122 in the embodiment adopt a hydraulic buffering mode, so that energy generated during parking and landing of the unmanned aerial vehicle can be effectively absorbed, and the possibility of accidental damage of the unmanned aerial vehicle is reduced.

One end fixedly connected with steering engine 25 that connecting piece 2121 is close to sleeve 2122, steering engine 25 still is connected with sleeve 2122, and steering engine 25 can drive sleeve 2122 and take place to rotate, and sleeve 2122 drives bracing piece 2123 and rotates, and bracing piece 2123 passes through fork 23 and drives the rotation of wheel 24 to be convenient for adjust the direction of movement of wheel 24, and then be favorable to carrying out tracking control to the route when unmanned aerial vehicle takes off and land to roll, in order to adjust unmanned aerial vehicle's route in real time.

The anti-torsion arm 22 comprises a first connecting arm 221 and a second connecting arm 222, the first connecting arm 221 and the second connecting arm 222 are fixedly connected through a quick-release pin, one end, away from the second connecting arm 222, of the first connecting arm 221 is hinged with the supporting rod 2123, one end, away from the first connecting arm 221, of the second connecting arm 222 is hinged with the sleeve 2122, and accordingly the first connecting arm 221 and the second connecting arm 222 can limit the supporting rod 2123 and the sleeve 2122, the sleeve 2122 can conveniently and stably drive the supporting rod 2123 to rotate, and further the steering engine 25 can stably and accurately drive the sleeve 2122 and the supporting rod 2123 to rotate.

When the quick release pin is detached from between the first connecting arm 221 and the second connecting arm 222, the first connecting arm 221 and the second connecting arm 222 are not fixed, so that the sleeve 2122 and the support rod 2123 can rotate, and ground traction is facilitated for the unmanned aerial vehicle.

Through the mutual cooperation of the sleeve 2122, the support rod 2123, the first connecting arm 221 and the second connecting arm 222, the anti-swing and anti-torsion capabilities of the hydraulic buffer strut 212 are improved to a certain extent, so that the landing gear 2 can stably support the fuselage.

Referring to fig. 2 and 5, a pushing member 223 is fixedly connected to the first connection arm 221, and one end of the pushing member 223 extends in a direction away from the first connection arm 221.

The driven assembly 13 in this embodiment comprises two mutually hinged connecting rods 131 and a torsion spring 132. The torsion spring 132 is arranged at the hinge joint of the cabin door 12 and the cabin body 11, and the torsion spring 132 is in a pre-tightening state when the cabin door 12 is in a closed state and is used for driving the cabin door 12 to open; the torsion of the torsion spring 132 is fully released when the door 12 is completely opened.

One of the two connecting rods 131 is hinged with the cabin door 12, the other connecting rod 131 is hinged with the inner wall of the Chu Naqiang 111, and the rotation of the two connecting rods 131 can drive the cabin door 12 to be closed.

When the driving member 211 drives the connecting member 2121 to be in a horizontal state, the connecting member 2121 drives the supporting rod 2123 to move through the sleeve 2122, and the sleeve 2122 and the supporting rod 2123 drive the first connecting arm 221 and the second connecting arm 222 to move, so as to drive the pushing member 223 to move, and the extending end of the pushing member 223 can abut against one connecting rod 131 hinged on the cabin 11. At this time, the pushing member 223 drives the connecting rod 131 to rotate, and the pushing member 223 and the connecting rod 131 slide, so that the first connecting arm 221 collides with the connecting rod 131 hinged on the cabin body 11, and the connecting rod 131 is limited between the first connecting arm 221 and the pushing member 223, so that the first connecting arm 221 drives the connecting rod 131 hinged on the cabin body 11 to rotate, and the connecting rod 131 hinged on the cabin body 11 drives the other connecting rod 131 to rotate, thereby achieving the effect of driving the cabin door 12 to close when the landing gear 2 is folded and stored in the storage cavity 111.

The implementation principle of the embodiment 1 is as follows: when the landing gear 2 needs to be folded and stored, the driving member 211 is started, the driving member 211 contracts, the connecting member 2121 is driven to rotate around the fixing member 213, the connecting member 2121 drives the sleeve 2122, the supporting rod 2123, the fork 23 and the wheel 24 to rotate towards the storage cavity 111, the sleeve 2122 and the supporting rod 2123 drive the first connecting arm 221 and the second connecting arm 222 to rotate, and the first connecting arm 221 drives the pushing member 223 to rotate, so that the pushing member 223 firstly collides with one connecting rod 131 hinged on the cabin 11 and drives the connecting rod 131 to move towards the storage cavity 111.

In this process, the pushing member 223 and the connecting rod 131 slide, so that the first connecting arm 221 abuts against the connecting rod 131 hinged on the cabin 11, and the connecting rod 131 is limited between the first connecting arm 221 and the pushing member 223, so that the first connecting arm 221 drives the connecting rod 131 to rotate, and the connecting rod 131 hinged on the cabin 11 drives the other connecting rod 131 to rotate, so as to drive the cabin door 12 to rotate in a direction approaching to the cabin 11.

When the landing gear 2 is completely converted into a horizontal state and is stored in the storage cavity 111, the cabin door 12 is closed to seal the storage cavity 111, so that the effect of driving the landing gear 2 to fold and store by using the driving piece 211 and driving the cabin door 12 to close is achieved.

When the landing gear 2 needs to be dropped from the storage cavity 111, the driving piece 211 is started, the driving piece 211 stretches, and the hydraulic buffer support column 212 is driven to rotate outside the storage cavity 111. At this time, the pushing member 223 no longer applies a force to the connecting rod 131 hinged to the cabin 11, so that the torsion force of the torsion spring 132 in the pre-tightening state is released, and the cabin door 12 is driven to move in a direction away from the cabin 11, so as to open the storage cavity 111, thereby facilitating the landing gear 2 to drop.

Example 2

Example 2 differs from example 1 in that: the driven component 13 includes a limiting member 133, and the torsion spring 132 in the present embodiment is used to drive the door 12 to close.

Referring to fig. 6 and 7, the torsion spring 132 in the present embodiment is in a pre-tensioned state when the door 12 is in an open state, and the torsion force of the torsion spring 132 is all released when the door 12 is in a closed state.

The hinge joint of the first connecting arm 221 and the second connecting arm 222 is fixedly connected with a first magnetic attraction piece 224, the limiting piece 133 is fixedly connected with a second magnetic attraction piece 1331, and the first magnetic attraction piece 224 and the second magnetic attraction piece 1331 attract each other.

The inner wall of Chu Naqiang 111 is provided with a first limiting groove 114, and the limiting piece 133 is slidably inserted into the first limiting groove 114. A second limiting groove 121 is formed in one side, close to Chu Naqiang 111, of the cabin door 12. When the cabin door 12 is opened, the first limiting groove 114 is communicated with the second limiting groove 121, and the limiting pieces 133 are respectively inserted into the first limiting groove 114 and the second limiting groove 121, so as to limit the cabin door 12.

In this embodiment, the cross sections of the first limiting groove 114, the second limiting groove 121 and the limiting member 133 are all in a dovetail shape, so that the limiting member 133 is not easy to separate from the first limiting groove 114 and the second limiting groove 121.

The second magnetic piece 1331 is located at one side of the limiting piece 133 away from the first limiting groove 114, so that the first magnetic piece 224 can drive the limiting piece 133 to move between the first limiting groove 114 and the second limiting groove 121 through the second magnetic piece 1331.

In other embodiments, the cross sections of the first limiting groove 114, the second limiting groove 121 and the limiting member 133 may be T-shaped.

The implementation principle of the embodiment 2 is as follows: when the landing gear 2 needs to be dropped from the storage cavity 111, the driving piece 211 is started, the driving piece 211 stretches to drive the hydraulic buffering support column 212 to rotate towards the outside of the storage cavity 111, the hydraulic buffering support column 212 drives the first magnetic attraction piece 224 to move, the first magnetic attraction piece 224 drives the limiting piece 133 to move through the second magnetic attraction piece 1331, and meanwhile the hydraulic buffering support column 212 pushes the cabin door 12 to rotate towards a direction away from the cabin body 11. When the hydraulic buffer strut 212 pushes the cabin door 12 to the fully opened state, the first limiting groove 114 is communicated with the second limiting groove 121, and the limiting pieces 133 are respectively inserted into the first limiting groove 114 and the second limiting groove 121, so that the cabin door 12 is limited to the opened state, at this time, the torsion spring 132 is in the pre-tightening state, and the driving piece 211 continues to work, so that the landing gear 2 is completely dropped from the Chu Naqiang.

When the landing gear 2 needs to be folded and stored, the driving piece 211 is started, and the driving piece 211 drives the hydraulic buffer support column 212 to move so as to realize folding and storage of the landing gear 2. In this process, the first magnetic attraction piece 224 drives the limiting piece 133 to separate from the second limiting groove 121 through the second magnetic attraction piece 1331, so that the torsion force of the torsion spring 132 in the pre-tightening state is released, and the cabin door 12 is driven to move towards the direction close to the cabin body 11, so that when the landing gear 2 is completely contained in the storage cavity 111, the cabin door 12 can be closed, and the storage cavity 111 is blocked.

The above embodiments are not intended to limit the scope of the present application, so: all equivalent changes in structure, shape and principle of the application should be covered in the scope of protection of the application.

Claims

1. An unmanned aerial vehicle landing gear, comprising:

the cabin door assembly (1), the cabin door assembly (1) comprises a cabin body (11) and a cabin door (12) hinged with the cabin body (11), a storage cavity (111) is formed in the cabin body (11), a driven assembly (13) is arranged on the cabin door (12), and the driven assembly (13) is used for driving the cabin door (12) to be opened or closed;

landing gear (2), landing gear (2) fold take in to Chu Naqiang (111) are interior, landing gear (2) are including receiving and releasing action subassembly (21), receive and release action subassembly (21) one end with cabin body (11) are articulated, chu Naqiang (111) are used for accomodating receive and release action subassembly (21), be provided with on receive and release action subassembly (21) and prevent torsion arm (22), prevent torsion arm (22) are used for driving driven subassembly (13) remove, in order to realize receive and release action subassembly (21) are accomodate and are driven hatch door (12) are closed.

2. The unmanned aerial vehicle landing gear of claim 1, wherein: the folding and unfolding action assembly (21) comprises a driving piece (211) and a hydraulic buffer support (212), one end of the driving piece (211) is hinged to the inner wall of the Chu Naqiang (111), the other end of the driving piece (211) is hinged to the hydraulic buffer support (212), one end, close to the driving piece (211), of the hydraulic buffer support (212) is hinged to a fixing piece (213), the fixing piece (213) is used for being fixed to a machine body, and the torsion preventing arm (22) is arranged on the hydraulic buffer support (212).

3. The unmanned aerial vehicle landing gear of claim 2, wherein: the hydraulic buffering support column (212) comprises a connecting piece (2121) and a buffering component rotationally connected with the connecting piece (2121), one end, away from the buffering component, of the connecting piece (2121) is hinged to the output end of the driving piece (211) and the fixing piece (213) respectively, one end, away from the connecting piece (2121), of the buffering component is provided with an organic wheel (24), one end, close to the buffering component, of the connecting piece (2121) is provided with a steering engine (25), and the steering engine (25) is used for driving the buffering component to rotate.

4. A unmanned aerial vehicle landing gear according to claim 3, wherein: the damping assembly comprises a sleeve (2122) and a supporting rod (2123), one end of the supporting rod (2123) is inserted into the sleeve (2122) and fixedly connected with the sleeve (2122), the other end of the supporting rod (2123) is connected with the machine wheel (24), one end of the supporting rod (2123) away from the sleeve (2122) is rotationally connected onto the connecting piece (2121), the steering engine (25) is connected with the sleeve (2122), the anti-torsion arm (22) comprises a first connecting arm (221) and a second connecting arm (222) which are mutually hinged, one end of the first connecting arm (221) away from the second connecting arm (222) is hinged with the supporting rod (2123), and one end of the second connecting arm (222) away from the first connecting arm (221) is hinged with the sleeve (2122).

5. The unmanned aerial vehicle landing gear of claim 4, wherein: the first connecting arm (221) is provided with a pushing piece (223), the driven component (13) comprises two connecting rods (131) hinged to each other, one ends, deviating from each other, of the two connecting rods (131) are hinged to the inner wall of the cabin door (12) and the inner wall of the Chu Naqiang (111) respectively, and the pushing piece (223) is used for pushing one connecting rod (131) hinged to the inner wall of the Chu Naqiang (111) in the two connecting rods (131) to move.

6. The unmanned aerial vehicle landing gear of claim 2, wherein: the cabin body (11) is close to the side wall of the driving piece (211) and is provided with a guide groove (113), the guide groove (113) is communicated with the Chu Naqiang (111), the driving piece (211) is provided with a guide piece (2111), and the guide piece (2111) is inserted into the guide groove (113).

7. The unmanned aerial vehicle landing gear of claim 2, wherein: and a yielding groove (112) is formed in one side, close to the fixing piece (213), of the cabin body (11), the yielding groove (112) is communicated with the Chu Naqiang (111), and the yielding groove (112) is used for yielding for rotation of the hydraulic buffer support column (212).

8. The unmanned aerial vehicle landing gear of claim 1, wherein: the driven component (13) comprises a torsion spring (132) and a limiting piece (133), a first limiting groove (114) is formed in the inner wall of the Chu Naqiang (111), a second limiting groove (121) is formed in the cabin door (12), the limiting piece (133) is respectively inserted in the first limiting groove (114) and the second limiting groove (121) in a sliding mode, the limiting piece (133) is used for limiting the cabin door (12), a first magnetic attraction piece (224) is arranged on the torsion preventing arm (22), the first magnetic attraction piece (224) is used for driving the limiting piece (133) to move in the first limiting groove (114) and the second limiting groove (121), the torsion spring (132) is arranged between the cabin door (12) and the cabin body (11), and the torsion spring (132) is used for driving the cabin door (12) to close.

9. The unmanned aerial vehicle landing gear of claim 8, wherein: one side of the limiting piece (133) deviating from the first limiting groove (114) is provided with a second magnetic attraction piece (1331), and the second magnetic attraction piece (1331) and the first magnetic attraction piece (224) are attracted mutually.

10. The unmanned aerial vehicle landing gear of claim 8, wherein: the cross sections of the first limiting groove (114), the second limiting groove (121) and the limiting piece (133) are all in a dovetail shape.