CN113184173B - Vertical take-off and landing fixed wing unmanned aerial vehicle with damping device - Google Patents
Vertical take-off and landing fixed wing unmanned aerial vehicle with damping device Download PDFInfo
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- CN113184173B CN113184173B CN202110632235.2A CN202110632235A CN113184173B CN 113184173 B CN113184173 B CN 113184173B CN 202110632235 A CN202110632235 A CN 202110632235A CN 113184173 B CN113184173 B CN 113184173B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
- B64C25/64—Spring shock-absorbers; Springs using rubber or like elements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Vibration Prevention Devices (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses a vertical take-off and landing fixed wing unmanned aerial vehicle with a damping device, which comprises a machine body, a hinge element, a first elastic element, a first supporting part and a second supporting part, wherein the first supporting part is provided with a first limiting element, and the second supporting part is provided with a second limiting element. The second supporting part is of a telescopic structure. Utilize first elastic component to provide elastic support to first supporting part, cooperate each other between first locating part and the second locating part for unmanned aerial vehicle can carry out the position to between first supporting part and the second supporting part when being in the state of flight and prescribe a limit to, avoid first supporting part to take place to rock, and then influence unmanned aerial vehicle's stability, and at unmanned aerial vehicle parking in-process, the prescribe a definite state self-determination of first supporting part and second supporting part is removed, rely on the scalability of first elastic component and second supporting part, realize unmanned aerial vehicle's dual shock attenuation, avoided unmanned aerial vehicle to park the in-process because of vibrations too big and damage.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a vertical take-off and landing fixed wing unmanned aerial vehicle with a damping device.
Background
In recent years, with the rise of unmanned aerial vehicles and the rapid development of related aeromodelling and unmanned aerial vehicle field technologies, unmanned aerial vehicles are also applied in more and more occasions. The unmanned aerial vehicle is an unmanned aerial vehicle which is operated by using a radio remote control device and a self-contained program control device. Unmanned aerial vehicles can be divided into a plurality of types from the technical perspective, wherein the unmanned fixed wing aircraft and the unmanned vertical take-off and landing aircraft. In the prior art, two technologies are often combined for use, such as a vertical take-off and landing fixed-wing unmanned aerial vehicle.
At present, the vertical take-off and landing fixed wing unmanned aerial vehicle is required to be subjected to damping treatment in the stopping and landing process so as to prevent damage caused by overlarge speed of the unmanned aerial vehicle when the unmanned aerial vehicle stops and falls. In the prior art, a group of connecting rod structures are hinged to the lower portion of an unmanned aerial vehicle body, the connecting rod structures are connected with the unmanned aerial vehicle body through damping springs, when the unmanned aerial vehicle stops descending, the connecting rod structures touch the ground to drive the damping springs to compress, and therefore the unmanned aerial vehicle is damped, but when the unmanned aerial vehicle flies, the connecting rod structures are prone to being subjected to air resistance to shake, and therefore the unmanned aerial vehicle flies unstably, and the safety is poor.
Disclosure of Invention
The invention aims to provide a vertical take-off and landing fixed wing unmanned aerial vehicle with a damping device, which can solve the problems of unstable flight and poor safety of the unmanned aerial vehicle caused by shaking of a connecting rod structure when the unmanned aerial vehicle stops and falls in the prior art.
The invention aims at realizing the following technical scheme:
a vertical take-off and landing fixed wing unmanned aerial vehicle with a damping device comprises a machine body, a hinge element, a first elastic element, a first supporting part and a second supporting part;
one end of the hinge element is fixedly arranged on one side of the machine body;
one end of the first supporting part is rotationally connected with the other end of the hinge piece; the first supporting part is also connected with the machine body through a first elastic piece;
the second supporting part is a telescopic mechanism, one end of the second supporting part is fixedly connected with the machine body, and the other end of the second supporting part extends along the direction vertical to the machine body;
a first limiting piece is arranged on one side, facing the second supporting part, of the first supporting part, a second limiting piece is arranged on one side, facing the first supporting part, of the second supporting part, and the second limiting piece is matched with the first limiting piece to lock the first supporting part and the second supporting part; when the first limiting piece and the second limiting piece are matched with each other, the distance between one end of the second supporting portion, which is far away from the machine body, and the machine body is greater than the distance between one end of the first supporting portion, which is far away from the machine body, and the machine body.
Further, the second supporting part comprises a guide sleeve, a second elastic piece and a top supporting rod, one end of the guide sleeve is fixedly connected with the machine body, and the second elastic piece is arranged in the guide sleeve and one end of the second elastic piece is fixedly connected with the machine body; one end of the top support rod extends into the guide sleeve and is fixedly connected with the other end of the second elastic piece, and the other end of the top support rod extends out of the guide sleeve.
Further, the second supporting part comprises a fixing part fixedly connected with the machine body and a top supporting rod slidingly connected with the fixing part; the fixed part is provided with a sliding block, and the top support rod is provided with a slideway matched with the sliding block; or the fixing part is provided with a slideway, and the top support rod is provided with a sliding block matched with the slideway.
Further, the limiting groove is formed in the side wall of the top supporting rod, the limiting block is fixedly arranged on the inner wall of the guide sleeve, and the limiting block extends to the inside of the limiting groove and is in sliding fit with the limiting groove.
Further, the first limiting piece comprises a first supporting piece and a first limiting protrusion, the first supporting piece is fixedly arranged on one side of the first supporting portion, facing the second supporting portion, and the first limiting protrusion is arranged at one end, far away from the first supporting portion, of the first supporting piece; the second limiting piece comprises a second supporting piece and a second limiting protrusion, the second supporting piece is fixedly arranged on one side, facing the first supporting portion, of the second supporting portion, the second limiting protrusion is arranged at one end, far away from the second supporting portion, of the second supporting piece, and the first limiting protrusion and the second limiting protrusion are clamped with each other.
Further, the first limiting piece comprises a first magnet, the second limiting piece comprises a second magnet, and the first magnet and the second magnet are attracted.
Further, one end of the first supporting portion, which is far away from the hinge member, is provided with a caster.
Further, a flexible body is arranged at one end of the second supporting part, which is far away from the machine body.
Further, the first supporting part is rotatably connected with the hinge member through a rotation pin.
Further, the first limiting protrusion and the second limiting protrusion are the same in shape and are of hook-shaped or wedge-shaped structures.
Compared with the prior art, the vertical take-off and landing fixed wing unmanned aerial vehicle with the damping device has the beneficial effects that:
through setting up the second supporting part in first supporting part one side, utilize first elastic component to provide elastic support to first supporting part, cooperate each other between first locating part and the second locating part for unmanned aerial vehicle can carry out the position to between first supporting part and the second supporting part when being in the flight state and prescribe a limit to, avoid first supporting part to take place to rock, and then influence unmanned aerial vehicle's stability, and at unmanned aerial vehicle parking process, the prescribe a limit to the state self-setting of first supporting part and second supporting part is removed, rely on first elastic component and second elastic component to realize unmanned aerial vehicle's dual shock attenuation, avoided unmanned aerial vehicle parking in-process to damage because of vibrations are too big.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments or the description of the prior art will be briefly described below, it will be obvious that the drawings in the following description are some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort to a person skilled in the art.
FIG. 1 is a schematic view of a vertical lift fixed wing unmanned aerial vehicle with a shock absorbing device according to the present invention;
fig. 2 is a schematic view of the internal structure of the second supporting part of the present invention;
FIG. 3 is an enlarged schematic view of area A of FIG. 1;
fig. 4 is an enlarged schematic view of region B in fig. 1.
The reference numerals are explained as follows: 1-fuselage, 2-articulated element, 21-swivel pin, 3-first elastic element, 4-first support, 41-first stop, 411-first support, 412-first stop projection, 42-caster, 5-second support, 51-guide sleeve, 52-second elastic element, 53-top stay, 54-second stop, 541-second support, 542-second stop projection, 55-flexible body, 56-stop, 57-stop slot.
Detailed Description
Embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present disclosure will become readily apparent to those skilled in the art from the following disclosure, which describes embodiments of the present disclosure by way of specific examples. It will be apparent that the described embodiments are merely some, but not all embodiments of the present disclosure. The disclosure may be embodied or practiced in other different specific embodiments, and details within the subject specification may be modified or changed from various points of view and applications without departing from the spirit of the disclosure. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art without inventive effort, based on the embodiments in this disclosure are intended to be within the scope of this disclosure.
The vertical take-off and landing fixed wing unmanned aerial vehicle with the damping device comprises a machine body 1, a hinge element 2, a first elastic element 3, a first supporting part 4, a first limiting element 41, a second supporting part 5 and a second limiting element 54, wherein one end of the hinge element 2 is fixedly arranged on one side of the machine body 1. One end of the first supporting part 4 is rotatably connected with the other end of the hinge 2. The first support 4 is also connected to the body 1 by a first elastic member 3. The second supporting part 5 is a telescopic mechanism, one end of the second supporting part 5 is fixedly connected with the machine body 1, and the other end extends along the direction vertical to the machine body. The first elastic member 3 provides an elastic supporting force for the first supporting portion 4, so as to drive the first supporting portion 4 to rotate towards the second supporting portion 5. The first limiting piece 41 is arranged on one side of the first supporting part 4 facing the second supporting part 5, the second limiting piece 54 is arranged on one side of the second supporting part 5 facing the first supporting part 4, the second limiting piece 54 is matched with the first limiting piece 41 to lock the first supporting part 4 and the second supporting part 5, when the first limiting piece 41 is matched with the second limiting piece 54, the distance between one end of the second supporting part 5 far away from the machine body 1 and the machine body 1 is L, the distance between one end of the first supporting part 4 far away from the machine body 1 is H, and the L value is larger than the H value.
The working principle of the technical scheme is as follows: when unmanned aerial vehicle is in the state of flight, first elastic component 3 provides the support for first supporting part 4, order about first supporting part 4 and rotate towards the direction of second supporting part 5, and then drive first locating part 41 deflection, until first locating part 41 and the cooperation of second locating part 54, form locking state between first supporting part 4 and the second supporting part 5, can guarantee this moment that first supporting part 4 stabilizes in fuselage 1 one side, thereby avoid first supporting part 4 to receive air resistance and take place to rock the phenomenon when flying along with unmanned aerial vehicle, and then influence unmanned aerial vehicle's flight stability. When unmanned aerial vehicle finishes the flight and needs to park, unmanned aerial vehicle descends downwards, because when forming locking state between first supporting part 4 and the second supporting part 5, the distance between the one end that fuselage 1 was kept away from to the second supporting part 5 and fuselage 1 is L, and the distance that fuselage 1 one end was kept away from to first supporting part 4 is H, and L numerical value is greater than H numerical value for second supporting part 5 can touch ground prior to first supporting part 4, and the fuselage continues to move downwards because of inertial reason this moment, leads to second supporting part 5 to be compression motion. The end of the second supporting part 5 far away from the machine body 1 moves towards the machine body 1, and then drives the second limiting piece 54 to move, so that the cooperation between the second limiting piece 54 and the first limiting piece 41 is released. And when the second supporting part 5 performs compression movement, preliminary shock absorption of the unmanned aerial vehicle is realized. When the matching state between the second limiting piece 54 and the first limiting piece 41 is released, the second supporting portion 4 can touch the ground, and the first elastic piece 3 is driven to compress under the action of gravity of the unmanned aerial vehicle, so that further shock absorption of the unmanned aerial vehicle is realized. When the unmanned aerial vehicle takes off again, the second supporting part 5 is stretched to move away from the machine body 1, and under the action of the first elastic piece 3, the first supporting part 4 rotates towards the second supporting part 5, so that the first limiting piece 41 and the second limiting piece 54 are matched again, locking between the first supporting part 4 and the second supporting part 5 is realized, and stability of the unmanned aerial vehicle during flight is guaranteed.
Further, in a preferred embodiment of the present application, the second supporting portion 5 includes a guide sleeve 51, a second elastic member 52, and a top stay 53, one end of the guide sleeve 51 is fixedly connected to the body 1, and the second elastic member 52 is disposed in the guide sleeve 51 and one end thereof is fixedly connected to the body 1. One end of the top supporting rod 53 extends into the guide sleeve 51 and is fixedly connected with the other end of the second elastic piece 52, and the other end of the top supporting rod 53 extends out of the guide sleeve 51. The guiding sleeve 51 is used for guiding the movement of the top supporting rod 53, so that the top supporting rod 53 can move towards the machine body 1 stably when touching the ground.
When one end of the top stay 53 of the second support part 5 far from the machine body touches the ground, the top stay 53 can move towards the inside of the guide sleeve 51, so as to squeeze the second elastic piece 52, drive the second elastic piece 52 to compress, and provide a guiding effect for the movement of the top stay 53 through the telescopic fit between the top stay 53 and the guide sleeve 51.
Further, in another embodiment of the present application, the second supporting portion 5 may further include a fixing portion fixedly connected to the body 1 and a top supporting rod slidingly connected to the fixing portion, where the fixing portion is provided with a slider, and the top supporting rod is provided with a slideway matched with the slider; or the fixed part is provided with a slideway, and the top support rod is provided with a sliding block matched with the slideway. Through the sliding fit between the sliding block and the guide rail, the guide support can be provided when the top stay bar moves, so that the top stay bar can move stably.
Further, in a preferred embodiment of the present application, referring to fig. 2 and 3, in order to ensure that the second limiting member 54 can be smoothly matched with the first limiting member 41 when the unmanned aerial vehicle flies, the side wall of the top supporting rod 53 is provided with a limiting groove 57, and the inner wall of the guiding sleeve 51 is fixedly provided with a limiting block 56, and the limiting block 56 extends into the limiting groove 57 and is slidably matched with the limiting groove 57.
When the unmanned aerial vehicle takes off, the top stay 53 moves towards the outer direction of the guide sleeve 51, so that the limiting block 56 slides relative to the limiting groove 57, and the second limiting piece 54 just moves to a position capable of being matched with the first limiting piece 41 until the limiting block 56 slides to one end of the limiting groove 57.
Further, in a preferred embodiment of the present application, referring to fig. 4, the first limiting member 41 includes a first supporting member 411 and a first limiting protrusion 412, the first supporting member 411 is fixedly disposed on a side of the first supporting portion 4 facing the second supporting portion 5, and the first limiting protrusion 412 is disposed on an end of the first supporting member 411 away from the first supporting portion 4. The second limiting member 54 includes a second supporting member 511 and a second limiting protrusion 512, the second supporting member 511 is fixedly disposed on one side of the second supporting portion 5 facing the first supporting portion 4, the second limiting protrusion 512 is disposed on one end of the second supporting member 511 away from the second supporting portion 5, and the first limiting protrusion 412 and the second limiting protrusion 512 can be mutually clamped.
When unmanned aerial vehicle takes off, second supporting part 5 and first spacing portion 4 break away from ground, first elastic component 3 orders about first supporting part 4 to second supporting part 5 direction rotation to drive first supporting part 411 and first spacing protruding 412 rotation, until first spacing protruding 412 rotates to second spacing protruding 512 one side, make first spacing protruding 412 and the mutual block of second spacing protruding 512, and then carry out spacingly to first supporting part 4, avoid first supporting part 4 to receive air resistance's influence and take place to rock when flying along with unmanned aerial vehicle, stability when guaranteeing unmanned aerial vehicle. When unmanned aerial vehicle stops flying, unmanned aerial vehicle descends, and second supporting part 5 touches ground and removes to fuselage 1 direction, and second supporting part 5 drives second support piece 511 and the spacing protruding 512 of second this moment and removes for spacing protruding 512 of second removes from spacing protruding 412 one side of first, until first supporting part 4 touches ground, under unmanned aerial vehicle self gravity action, first supporting part 4 drives first support piece 411 and the spacing protruding 412 reverse movement of first.
Further, in another embodiment of the present application, the first limiting member 41 may further include a first magnet disposed on a side of the first supporting portion 4 facing the second supporting portion 5, and the second limiting member 54 may further include a second magnet disposed on a side of the second supporting portion 5 facing the first supporting portion 4, where the first magnet attracts the second magnet.
In this way, the supporting force of the first elastic member 3 is overcome by the mutual attraction between the first magnet and the second magnet, so that the stability of the first supporting portion 4 when flying along with the unmanned aerial vehicle is ensured.
Further, the first support 4 is rotatably connected to the hinge 2 by a rotation pin 21.
Preferably, the end of the first support 4 remote from the hinge 2 is provided with casters 42.
Through the setting of truckle 42 for can roll with between the ground when first supporting part 4 touches ground, thereby guarantee that first supporting part 4 can better deflection, with the supporting effect that improves first elastic component 3, improve shock attenuation effect.
In the above embodiment, the hinge 2, the first supporting portion 4 and the second supporting portion 5 are all rod-shaped structures, the first elastic member 3 and the second elastic member 52 are all springs or metal elastic sheets, and the first limiting protrusion 412 and the second limiting protrusion 512 are all hook-shaped or wedge-shaped structures.
Preferably, the second supporting part 5 is far away from the one end of fuselage 1 is provided with flexible body 55, through the setting of flexible body 55 for can with the ground between the flexible contact when second supporting part 5 touches ground, still can increase the friction effect with between the ground when carrying out further shock attenuation to unmanned aerial vehicle, guarantee that unmanned aerial vehicle is steadily parked.
In the above embodiment, the flexible body 55 is a rubber pad or a silica gel pad.
In the embodiment of the invention, the second supporting part 5 is arranged on one side of the first supporting part 4, the first elastic piece 3 is utilized to provide elastic support for the first supporting part 4, and the first limiting piece 41 and the second limiting piece 54 are matched with each other, so that the position between the first supporting part 4 and the second supporting part 5 can be limited when the unmanned aerial vehicle is in a flying state, the shaking of the first supporting part 4 is avoided, the stability of the unmanned aerial vehicle is further influenced, in the unmanned aerial vehicle parking process, the limiting state of the first supporting part 4 and the second supporting part 5 is automatically and fixedly removed, and the double shock absorption of the unmanned aerial vehicle is realized by virtue of the first elastic piece 3 and the second elastic piece 52, so that the damage caused by overlarge shock in the unmanned aerial vehicle parking process is avoided.
In the description of the present invention, it should be understood that the terms "middle," "length," "upper," "lower," "front," "rear," "vertical," "horizontal," "inner," "outer," "radial," "circumferential," and the like indicate an orientation or a positional relationship based on that shown in the drawings, merely for convenience of description and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the invention.
In the present invention, unless expressly stated or limited otherwise, a first feature "on" a second feature may be that the first and second features are in direct contact, or that the first and second features are in indirect contact via an intervening medium. The meaning of "a plurality of" means at least two, e.g., two, three, etc., unless explicitly defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
The above description is for the purpose of illustrating the embodiments of the present invention and is not to be construed as limiting the invention, but is intended to cover all modifications, equivalents, improvements and alternatives falling within the spirit and principles of the invention.
Claims (6)
1. The vertical take-off and landing fixed wing unmanned aerial vehicle with the damping device is characterized by comprising a machine body, a hinge element, a first elastic element, a first supporting part and a second supporting part;
one end of the hinge element is fixedly arranged on one side of the machine body;
one end of the first supporting part is rotationally connected with the other end of the hinge piece; the first supporting part is also connected with the machine body through a first elastic piece;
the second supporting part is a telescopic mechanism, one end of the second supporting part is fixedly connected with the machine body, and the other end of the second supporting part extends along the direction vertical to the machine body;
a first limiting piece is arranged on one side, facing the second supporting part, of the first supporting part, a second limiting piece is arranged on one side, facing the first supporting part, of the second supporting part, and the second limiting piece is matched with the first limiting piece to lock the first supporting part and the second supporting part; when the first limiting piece and the second limiting piece are matched with each other, the distance between one end of the second supporting part far away from the machine body and the machine body is larger than the distance between one end of the first supporting part far away from the machine body and the machine body;
the first limiting piece comprises a first supporting piece and a first limiting protrusion, the first supporting piece is fixedly arranged on one side, facing the second supporting portion, of the first supporting portion, and the first limiting protrusion is arranged on one end, far away from the first supporting portion, of the first supporting piece; the second limiting piece comprises a second supporting piece and a second limiting protrusion, the second supporting piece is fixedly arranged on one side, facing the first supporting portion, of the second supporting portion, the second limiting protrusion is arranged on one end, far away from the second supporting portion, of the second supporting piece, and the first limiting protrusion and the second limiting protrusion are mutually clamped;
the first limit bulge and the second limit bulge have the same shape and are of hook-shaped or wedge-shaped structures;
the first limiting piece comprises a first magnet, the second limiting piece comprises a second magnet, and the first magnet and the second magnet are attracted;
the first supporting part is rotationally connected with the hinge piece through a rotation pin.
2. The vertical take-off and landing fixed wing unmanned aerial vehicle with a damping device according to claim 1, wherein the second supporting part comprises a guide sleeve, a second elastic member and a top stay, one end of the guide sleeve is fixedly connected with the fuselage, and the second elastic member is arranged in the guide sleeve and one end of the second elastic member is fixedly connected with the fuselage; one end of the top support rod extends into the guide sleeve and is fixedly connected with the other end of the second elastic piece, and the other end of the top support rod extends out of the guide sleeve.
3. The vertical take-off and landing fixed wing unmanned aerial vehicle with a damping device according to claim 1, wherein the second supporting part comprises a fixed part fixedly connected with the fuselage and a top stay rod slidingly connected with the fixed part; the fixed part is provided with a sliding block, and the top support rod is provided with a slideway matched with the sliding block; or the fixing part is provided with a slideway, and the top support rod is provided with a sliding block matched with the slideway.
4. The vertical take-off and landing fixed wing unmanned aerial vehicle with the damping device according to claim 2, wherein a limit groove is formed in the side wall of the top supporting rod, a limit block is fixedly arranged on the inner wall of the guide sleeve, and the limit block extends into the limit groove and is in sliding fit with the limit groove.
5. The fixed wing aircraft with damping device according to any one of claims 1 to 4, wherein the end of the first support portion remote from the hinge is provided with casters.
6. The fixed wing aircraft with damping device according to any one of claims 1 to 4, wherein the end of the second support portion remote from the fuselage is provided with a flexible body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110632235.2A CN113184173B (en) | 2021-06-07 | 2021-06-07 | Vertical take-off and landing fixed wing unmanned aerial vehicle with damping device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110632235.2A CN113184173B (en) | 2021-06-07 | 2021-06-07 | Vertical take-off and landing fixed wing unmanned aerial vehicle with damping device |
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| CN113184173B true CN113184173B (en) | 2023-04-21 |
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| CN114104286A (en) * | 2021-11-22 | 2022-03-01 | 国网福建省电力有限公司南平供电公司 | AI front end algorithm-based autonomous intelligent inspection device for power transmission line unmanned aerial vehicle |
| CN114524087A (en) * | 2022-02-28 | 2022-05-24 | 北京博瑞翔伦科技发展有限公司 | Unmanned aerial vehicle detection interference system's unmanned aerial vehicle protective structure |
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