CN210212759U

CN210212759U - Unmanned aerial vehicle is with frame shock-absorbing structure that plays

Info

Publication number: CN210212759U
Application number: CN201920844064.8U
Authority: CN
Inventors: Wenjie Xu; 许文杰; Zesen Wu; 吴泽森
Original assignee: Shenzhen Anzela Technology Co ltd
Current assignee: Shenzhen Anzela Technology Co ltd
Priority date: 2019-06-05
Filing date: 2019-06-05
Publication date: 2020-03-31
Anticipated expiration: 2029-06-05

Abstract

The utility model discloses a landing gear shock-absorbing structure for unmanned aerial vehicle, which comprises a mounting plate, four groups of connecting rods are fixedly welded on the mounting plate, inflatable rubber is fixedly arranged in the mounting plate, an inflation inlet is fixedly arranged on one side of the mounting plate, a hydraulic shock absorber is movably connected on the connecting rods, spring shock absorbers are fixedly arranged at the bottom ends of the connecting rods, supporting legs are movably connected at the bottom ends of the connecting rods through pin shafts, and moving wheels are fixedly connected at the bottom ends of the supporting legs; the utility model adopts the rod structure to connect, support and damp, and prevents the plate structure from increasing the flight resistance of the unmanned aerial vehicle; the multi-group damping device is arranged, so that the transmission of the collision force of the landing gear when the unmanned aerial vehicle is lifted can be effectively reduced, and the inflatable rubber is arranged on the mounting plate to protect the collision between the power or control device of the unmanned aerial vehicle and the lifting frame; landing leg and removal wheel that are equipped with swing joint can remove and decompose unmanned aerial vehicle vertically power.

Description

Unmanned aerial vehicle is with frame shock-absorbing structure that plays

Technical Field

The invention belongs to the technical field of damping structures, and particularly relates to a landing frame damping structure for an unmanned aerial vehicle.

Background

An unmanned aircraft, simply "drone" ("UAV"), is an unmanned aerial vehicle that is operated by a radio remote control device and self-contained program control, or is operated autonomously, either completely or intermittently, by an onboard computer. Unmanned aerial vehicles are in fact a general term for unmanned aerial vehicles, and can be defined from a technical perspective as follows: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane, etc. The unmanned aerial vehicle has the advantages of small volume, low manufacturing cost and convenient use, and is more suitable for tasks too dull, dirty or dangerous compared with piloted aircrafts. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle and the industrial application are really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, and the application of the unmanned aerial vehicle is greatly expanded.

However, in the prior art, the unmanned aerial vehicle is fixedly provided with a lifting frame below the unmanned aerial vehicle for supporting the unmanned aerial vehicle and facilitating the lifting and landing of the unmanned aerial vehicle, but the existing unmanned aerial vehicle has only some rubber structures added on the landing gear for damping, however, the damping device often cannot meet the impact force generated when the unmanned aerial vehicle lands, and the existing unmanned aerial vehicle guides the wind flow downwards to lift when rising, the flight capability of the drone is greatly limited if the landing gear employs a plate connection structure, if the damping treatment is only carried out on the landing gear, the power device or the control device of the unmanned aerial vehicle can easily collide with the landing gear when landing, so that the unmanned aerial vehicle is damaged, damping device in prior art is single, and simple structure can't satisfy this impact force that unmanned aerial vehicle produced when descending.

Therefore, the undercarriage shock-absorbing structure for the unmanned aerial vehicle solves the problems in the prior art, has multiple shock-absorbing structures, can quickly and multiply reduce the impact force of the unmanned aerial vehicle, can reduce the impact force of different positions by different shock-absorbing devices, can protect corresponding structures from being damaged by collision even, can move when descending, decomposes vertical impact force into horizontal movement, and further protects the structure of the unmanned aerial vehicle from being damaged.

Disclosure of Invention

The invention aims to provide a shock absorption structure of an undercarriage for an unmanned aerial vehicle, which aims to solve the problems that the shock absorption mode proposed in the background technology is single, the structure is simple, the protection effect cannot be achieved, and the like.

In order to achieve the purpose, the invention adopts the following technical scheme:

a landing frame damping structure for an unmanned aerial vehicle comprises a mounting plate, wherein four groups of connecting rods are fixedly welded on the mounting plate, inflation rubber is fixedly arranged in the mounting plate, an inflation inlet is fixedly arranged on one side of the mounting plate, a hydraulic damper is movably connected onto each connecting rod, a spring damper is fixedly installed at the bottom end of each connecting rod, a supporting leg is movably connected to the bottom end of each connecting rod through a pin shaft, a moving wheel is fixedly connected to the bottom end of each supporting leg, each hydraulic damper comprises a hydraulic cylinder, a telescopic rod, a first spring, a first limiting plate and a connecting seat, the connecting seat is fixedly welded with the top ends of the hydraulic cylinder and the telescopic rod, the telescopic rod is movably connected into the hydraulic cylinder, the first springs are fixedly sleeved outside the hydraulic cylinder and the telescopic rod, two ends of each first spring are fixedly connected onto the first limiting plates, the, the landing leg includes connecting portion, supporting part and flexion, connecting portion are through the inside of round pin axle swing joint at the connecting rod, the upper portion and the spring damper laminating of supporting part are connected, connecting portion swing joint has the removal wheel, the spring damper includes connecting plate, upper cover, fixed block, lower cover, second spring and rubber pad, the spring damper passes through connecting plate fixed mounting in the lower part of connecting rod, fixed welding has the upper cover on the connecting plate, swing joint has the lower cover in the upper cover, fixed welding has the fixed block in upper cover and the lower cover, cover fixedly connected with rubber pad down.

Preferably, the connecting seats at the two ends of the hydraulic damper are all arranged in a circular ring shape, and the connecting seats are respectively and fixedly connected with the unmanned aerial vehicle body and the connecting rod.

Preferably, the rotating groove has been seted up to the bottom of connecting rod, the rotating groove lateral wall sets to the arc, and rotates inslot portion and have connecting portion through round pin axle swing joint, and the top of connecting portion is equipped with solid fixed ring, gu fixed ring and round pin axle swing joint, connecting portion can rotate to the outside at the rotating groove.

Preferably, the supporting part is vertically connected with the connecting part, the bending part is fixedly welded with the supporting part, the supporting part is connected with the rubber pad on the spring damper in a fitting manner, and the bending part is arranged to bend towards the inner side.

Preferably, the bottom fixed welding of upper cover and lower cover has the fixed block, fixedly connected with second spring on the fixed block.

Preferably, the top of the upper cover and the bottom cover are respectively provided with an inward clamping part and an outward clamping part, and the inward clamping part and the outward clamping part are connected with each other in a fitting manner.

Preferably, the bottom of flexion is equipped with the spring groove, through fixed block fixedly connected with third spring in the spring groove, the one end fixed connection of third spring is on branch, branch fixed weld is on removing the wheel.

Preferably, the fixed welding has the second limiting plate on the branch, second limiting plate upper portion and third spring fixed connection, the activity of second limiting plate is in the spring inslot, and the size of second limiting plate is greater than the opening part size in spring groove.

Preferably, the top of aerifing rubber is connected with the power device of unmanned aerial vehicle body or the laminating of controlling means.

The invention has the technical effects and advantages that: compared with the prior art, the landing frame damping structure for the unmanned aerial vehicle has the following advantages that:

1. according to the invention, the damping frame is connected, supported and damped by adopting a rod structure, so that the use of a plate structure below the unmanned aerial vehicle is reduced as much as possible, and the plate structure is prevented from increasing the flight resistance of the unmanned aerial vehicle;

2. according to the invention, the landing gear damping structure is connected with the unmanned aerial vehicle through the hydraulic damper, so that the transmission of collision force of the landing gear when the unmanned aerial vehicle is lifted can be effectively reduced, and the pneumatic rubber is arranged on the mounting plate, so that the collision between the power and control device of the unmanned aerial vehicle and the lifting frame due to the damping effect when the unmanned aerial vehicle is lifted and landed can be prevented;

3. the landing leg is movably connected, namely the connecting part is movably connected with the connecting rod through the pin shaft and can move outwards when the landing leg is stressed;

4. according to the invention, the bottom ends of the supporting legs are movably connected with the moving wheels through the springs, and the moving wheels can decompose the collision force during vertical landing through moving displacement when the unmanned aerial vehicle collides with the ground suddenly during landing.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a top view of the present invention;

FIG. 3 is a schematic view of part A of the present invention;

FIG. 4 is a schematic view of part B of the present invention;

FIG. 5 is a schematic view of part C of the present invention.

In the figure: 1. mounting a plate; 2. inflating rubber; 3. an inflation inlet; 4. a connecting rod; 5. a hydraulic shock absorber; 501. a hydraulic cylinder; 502. a telescopic rod; 503. a first spring; 504. a first limit plate; 505. a connecting seat; 6. a support leg; 601. a connecting portion; 602. a support portion; 603. a bending section; 7. a moving wheel; 8. a spring damper; 801. a connecting plate; 802. an upper cover; 803. a fixed block; 804. a lower cover; 805. a second spring; 806. a rubber pad; 9. a rotating groove; 10. a fixing ring; 11. a pin shaft; 12. a spring slot; 13. a third spring; 14. a strut; 15. and a second limiting plate.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The specific embodiments described herein are merely illustrative of the invention and do not delimit the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The invention provides a landing gear shock absorption structure for an unmanned aerial vehicle, which comprises a mounting plate 1, wherein four groups of connecting rods 4 are fixedly welded on the mounting plate 1, and the weight and flight resistance of the unmanned aerial vehicle can be reduced by setting the connecting rods 4; the mounting plate 1 is internally and fixedly provided with inflation rubber 2, one side of the mounting plate 1 is fixedly provided with an inflation inlet 3, and the inflation rubber 2 can prevent a power device and a control device of the unmanned aerial vehicle from colliding with an undercarriage and being damaged; the connecting rod 4 is movably connected with a hydraulic damper 5, and the hydraulic damper 5 at the position is used for connecting the unmanned aerial vehicle and the undercarriage and can slow down the impact force between the unmanned aerial vehicle and the undercarriage; the spring shock absorber 8 is fixedly installed at the bottom end of the connecting rod 4, and the spring shock absorber 8 at the position can support when the supporting leg 6 moves outwards, namely, the supporting leg 6 is prevented from being broken due to overlarge stress when the supporting leg 6 moves outwards under stress; the bottom end of the connecting rod 4 is movably connected with a supporting leg 6 through a pin shaft 11, the bottom end of the supporting leg 6 is fixedly connected with a moving wheel 7, and the moving wheel 7 can move when the supporting leg 6 moves outwards when the unmanned aerial vehicle lands and is subjected to impact force in the vertical direction, so that the impact force in the vertical direction is relieved; the hydraulic shock absorber 5 comprises a hydraulic cylinder 501, an expansion rod 502, a first spring 503, a first limiting plate 504 and a connecting seat 505, the top ends of the hydraulic cylinder 501 and the expansion rod 502 are fixedly welded on the connecting seat 505, the expansion rod 502 is movably connected in the hydraulic cylinder 501, the first spring 503 is fixedly sleeved outside the hydraulic cylinder 501 and the expansion rod 502, two ends of the first spring 503 are fixedly connected on the first limiting plate 504, the first limiting plate 504 is fixedly welded on the hydraulic cylinder 501 and the expansion rod 502, the connecting seat 505 can facilitate the fixed connection of the hydraulic shock absorber 5, and the first limiting plate 504 can play a role in fixing the first spring 503; the supporting leg 6 comprises a connecting part 601, a supporting part 602 and a bending part 603, the connecting part 601 is movably connected inside the connecting rod 4 through a pin shaft 11, the upper part of the supporting part 602 is connected with the spring damper 8 in an attaching manner, the connecting part 601 at the position is movably connected below the connecting rod 4, so that the connecting part 601 can rotate under stress, and the supporting part 602 can be connected with the spring damper 8 in an attaching manner when moving, so that the effect of reducing impact force is achieved; connecting portion 601 swing joint has movable wheel 7, spring damper 8 includes connecting plate 801, upper cover 802, fixed block 803, lower cover 804, second spring 805 and rubber pad 806, spring damper 8 passes through connecting plate 801 fixed mounting in the lower part of connecting rod 4, fixed welding has upper cover 802 on connecting plate 801, swing joint has lower cover 804 in upper cover 802, fixed welding has fixed block 803 in upper cover 802 and lower cover 804, fixedly connected with rubber pad 806 on lower cover 804, the setting of upper cover 802 and lower cover 804 of this department can prevent spring damper 8 from falling apart, and fixed block 803 is used for fixing second spring 805, prevent displacement or dislocation of second spring 805 in the atress, and rubber pad 806 can prevent that damaging striking takes place when supporting part 602 and spring damper 8 meet the department

Preferably, connecting seats 505 at both ends of hydraulic damper 5 are all set to be circular ring shape, and connecting seats 505 respectively with unmanned aerial vehicle body and connecting rod 4 carry out fixed connection.

Through adopting above-mentioned technical scheme, the fixed connection to hydraulic damper 5 can be conveniently in the settlement of connecting seat 505.

Preferably, the bottom of the connecting rod 4 is provided with a rotating groove 9, the side wall of the rotating groove 9 is provided with an arc shape, the inside of the rotating groove 9 is movably connected with a connecting portion 601 through a pin 11, the top end of the connecting portion 601 is provided with a fixing ring 10, the fixing ring 10 is movably connected with the pin 11, and the connecting portion 601 can rotate towards the outside in the rotating groove 9.

By adopting the above technical scheme, the connecting portion 601 can move outwards when being stressed in the rotating groove 9, but cannot move inwards, and the portion 601 rubs when rotating.

Preferably, the support portion 602 is vertically connected to the connecting portion 601, the bending portion 603 is fixedly welded to the support portion 602, the support portion 602 is attached to the rubber pad 806 on the spring damper 8, and the bending portion 603 is configured to bend inward.

Through adopting above-mentioned technical scheme, supporting part 602 is connected with the perpendicular of connecting portion 601, can make things convenient for supporting part 602 and spring damper 8's contact, can effectually slow down the landing leg 6 when the atress impact force when outwards moving, and the flexion 603 is crooked to the inboard, can increase landing leg 6 stay area.

Preferably, the bottom ends of the upper cover 802 and the lower cover 804 are fixedly welded with a fixing block 803, the fixing block 803 is fixedly connected with a second spring 805, the top portions of the upper cover 802 and the lower cover 804 are respectively provided with an inward clamping portion and an outward clamping portion, and the inward clamping portion and the outward clamping portion are connected in a fitting manner.

By adopting the above technical solution, the setting of the fixing block 803 can prevent the second spring 805 from shifting and dislocating, so that the spring damper 8 cannot work normally, and the upper cover 802 and the lower cover 804 can stably fix the whole spring damper 8.

Preferably, the bottom of the bending portion 603 is provided with a spring groove 12, a third spring 13 is fixedly connected to the spring groove 12 through a fixing block 803, one end of the third spring 13 is fixedly connected to a supporting rod 14, the supporting rod 14 is fixedly welded to the moving wheel 7, a second limiting plate 15 is fixedly welded to the supporting rod 14, the upper portion of the second limiting plate 15 is fixedly connected to the third spring 13, the second limiting plate 15 is movably located in the spring groove 12, and the size of the second limiting plate 15 is larger than the size of an opening of the spring groove 12.

Through adopting above-mentioned technical scheme, connect through third spring 13 and remove wheel 7 for remove wheel 7 and can slow down the impact force in the atress, and third spring 13 establishes in the spring groove 12 of flexion 603, can prevent that third spring 13 from taking place to shift the dislocation and can not use, and the settlement of second limiting plate 15 can prevent droing of branch 14.

Preferably, the top of aerifing rubber 2 is connected with the power device of unmanned aerial vehicle body or the laminating of controlling means.

Through adopting above-mentioned technical scheme, aerify rubber 2 can protect and can not make power device and controlling means receive the collision of undercarriage and receive the damage when descending.

The structure principle is as follows: during use, the landing gear is fixedly connected with the unmanned aerial vehicle body through the hydraulic shock absorber 5, then the inflation rubber 2 is inflated through the inflation inlet 3, so that the inflation rubber 2 starts to swell, then the unmanned aerial vehicle can be started to take off, after the takeoff is finished, the unmanned aerial vehicle can be controlled to land on the ground when the landing gear at the lower end of the unmanned aerial vehicle body is in contact with the ground, because the impact force is larger when the unmanned aerial vehicle body flies, the moving wheel 7 at the bottom end of the bending part 603 of the supporting leg 6 is stressed, the third spring 13 connected with the supporting rod 14 on the moving wheel 7 is stressed to contract, then a part of buffer force is reduced, meanwhile, the supporting leg 6 can move outwards to reduce the impact force, and when the supporting leg 6 moves outwards, the supporting part 602 can be in fit connection with the rubber pad 806 of the spring shock absorber 8, then spring damper 8 can slow down certain impact force, and hydraulic damper 5 on the frame of taking off and land can contract, slow down partly impact force, and the unmanned aerial vehicle body can wholly remove downwards when hydraulic damper 5 contracts, this moment on the mounting panel 1 aerify rubber 2 can collide with power device or the controlling means of unmanned aerial vehicle body below, can effectually protect power device or controlling means can not receive the damage.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention.

Claims

1. The utility model provides an unmanned aerial vehicle is with landing frame shock-absorbing structure, includes mounting panel (1), its characterized in that: fixed welding has four groups of connecting rods (4) on mounting panel (1), mounting panel (1) internal fixation is equipped with inflatable rubber (2), one side of mounting panel (1) is fixed and is equipped with inflation inlet (3), swing joint has hydraulic shock absorber (5) on connecting rod (4), the bottom fixed mounting of connecting rod (4) has spring shock absorber (8), the bottom of connecting rod (4) has landing leg (6) through round pin axle (11) swing joint, the bottom fixed connection of landing leg (6) removes wheel (7), hydraulic shock absorber (5) include pneumatic cylinder (501), telescopic link (502), first spring (503), first limiting plate (504) and connecting seat (505), the fixed welding of connecting seat (505) has the top of pneumatic cylinder (501) and telescopic link (502), telescopic link (502) swing joint is in pneumatic cylinder (501), and the first spring (503) is fixedly sleeved outside the hydraulic cylinder (501) and the telescopic rod (502), the two ends of the first spring (503) are fixedly connected to the first limiting plate (504), the first limiting plate (504) is fixedly welded on the hydraulic cylinder (501) and the telescopic rod (502), the support leg (6) comprises a connecting part (601), a supporting part (602) and a bending part (603), the connecting part (601) is movably connected inside the connecting rod (4) through a pin shaft (11), the upper part of the supporting part (602) is jointed and connected with the spring shock absorber (8), the connecting part (601) is movably connected with a moving wheel (7), the spring shock absorber (8) comprises a connecting plate (801), an upper cover (802), a fixing block (803), a lower cover (804), a second spring (805) and a rubber pad (806), the spring shock absorber (8) is fixedly installed at the lower part of the connecting rod (4) through the connecting plate (801), the connecting plate is characterized in that an upper cover (802) is fixedly welded on the connecting plate (801), a lower cover (804) is movably connected in the upper cover (802), fixing blocks (803) are fixedly welded in the upper cover (802) and the lower cover (804), and a rubber pad (806) is fixedly connected on the lower cover (804).

2. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: connecting seats (505) at two ends of the hydraulic damper (5) are all set to be circular rings, and the connecting seats (505) are fixedly connected with the unmanned aerial vehicle body and the connecting rod (4) respectively.

3. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: rotation groove (9) have been seted up to the bottom of connecting rod (4), it sets the arc to rotate groove (9) lateral wall, and rotates groove (9) inside through round pin axle (11) swing joint have connecting portion (601), and the top of connecting portion (601) is equipped with solid fixed ring (10), gu fixed ring (10) and round pin axle (11) swing joint, connecting portion (601) can rotate to the outside in rotation groove (9).

4. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the supporting portion (602) is vertically connected with the connecting portion (601), the bending portion (603) is fixedly welded with the supporting portion (602), the supporting portion (602) is attached to and connected with a rubber pad (806) on the spring damper (8), and the bending portion (603) is arranged to bend towards the inner side.

5. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the bottom fixed welding of upper cover (802) and lower cover (804) has fixed block (803), fixedly connected with second spring (805) on fixed block (803).

6. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the top of the upper cover (802) and the bottom cover (804) are respectively provided with an inward clamping part and an outward clamping part, and the inward clamping part and the outward clamping part are connected in a fitting manner.

7. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the bottom of flexion (603) is equipped with spring groove (12), through fixed block (803) fixedly connected with third spring (13) in spring groove (12), the one end fixed connection of third spring (13) is on branch (14), branch (14) fixed welding is on removing wheel (7).

8. The landing gear shock-absorbing structure for unmanned aerial vehicle of claim 7, wherein: the fixed welding has second limiting plate (15) on branch (14), second limiting plate (15) upper portion and third spring (13) fixed connection, second limiting plate (15) activity is in spring groove (12), and the size of second limiting plate (15) is greater than the opening part size of spring groove (12).

9. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the top of inflating rubber (2) is connected with the power device of the unmanned aerial vehicle body or the control device in an attaching mode.