阅读说明：本技术 一种无人机起落架减震结构 (Unmanned aerial vehicle undercarriage shock-absorbing structure ) 是由 张先忙 于 2020-09-21 设计创作，主要内容包括：本发明公开了一种无人机起落架减震结构,涉及无人机部件技术领域。包括横板和支撑杆,所述横板的下方设置有支撑杆,所述横板的上表面固定连接有固定板,所述固定板的内部开设有定位孔,所述横板的两端固定连接有套筒,所述横板的下方设置有连接板,所述连接板的左右两端滑动连接有插板,所述插板之间固定连接有复进弹簧；通过设置一号转动轴和二号转动轴将支撑杆、套管和连接杆活动连接,组成对与支撑杆所处平面平行的方向上的缓冲结构,通过横板、连接板和连接块组成在垂直于支撑杆平面的方向上的缓冲结构,从而形成在各个方向上的缓冲结构,从而达到起落架在各个方向上对无人机降落进行缓冲的作用。(The invention discloses an unmanned aerial vehicle undercarriage damping structure and relates to the technical field of unmanned aerial vehicle components. The spring-loaded type automatic feeding device comprises a transverse plate and supporting rods, wherein the supporting rods are arranged below the transverse plate, a fixing plate is fixedly connected to the upper surface of the transverse plate, positioning holes are formed in the fixing plate, sleeves are fixedly connected to two ends of the transverse plate, a connecting plate is arranged below the transverse plate, inserting plates are slidably connected to the left end and the right end of the connecting plate, and a re-feeding spring is fixedly connected between the inserting plates; through setting up a axis of rotation and No. two axis of rotation with bracing piece, sleeve pipe and connecting rod swing joint, constitute to the buffer structure in the direction parallel with the plane that the bracing piece is located, constitute the buffer structure in the planar direction of perpendicular to bracing piece through diaphragm, connecting plate and connecting block to form the buffer structure in all directions, thereby reach the landing gear and carry out the effect of buffering to unmanned aerial vehicle descending in all directions.)

1. The utility model provides an unmanned aerial vehicle undercarriage shock-absorbing structure, includes diaphragm (1) and bracing piece (2), its characterized in that: a support rod (2) is arranged below the transverse plate (1),

the upper surface of the transverse plate (1) is fixedly connected with a fixing plate (11), a positioning hole (12) is formed in the fixing plate (11), two ends of the transverse plate (1) are fixedly connected with sleeves (13), a connecting plate (14) is arranged below the transverse plate (1), the left end and the right end of the connecting plate (14) are connected with inserting plates (15) in a sliding mode, and a re-feeding spring (16) is fixedly connected between the inserting plates (15);

blotter (21) has been cup jointed to the outside of bracing piece (2), axis of rotation (22) of both ends fixedly connected with of bracing piece (2), bracing piece (2) rotate through axis of rotation (22) and are connected with sleeve pipe (23), the inside sliding connection of sleeve pipe (23) has connecting rod (24), fixedly connected with supporting spring (25) between connecting rod (24) and sleeve pipe (23) inner wall, axis of rotation (26) No. two of the upper end fixedly connected with of connecting rod (24), connecting rod (24) rotate through axis of rotation (26) No. two and are connected with connecting block (27).

2. The unmanned aerial vehicle landing gear shock-absorbing structure of claim 1, wherein: the utility model discloses a support rod, including bracing piece (2), blotter (21), bracing piece (2) are the U style of calligraphy, blotter (21) are cylindricly cup jointed at bracing piece (2) horizontal part both ends, and blotter (21) rotate with bracing piece (2) to be connected.

3. The unmanned aerial vehicle landing gear shock-absorbing structure of claim 1, wherein: connecting block (27) are the V type, the both ends of connecting block (27) rotate with sleeve (13) and picture peg (15) respectively and are connected, the flex point and No. two axis of rotation (26) fixed connection of connecting block (27), and No. two axis of rotation (26) and sleeve (13) and picture peg (15) set up the opposite side at connecting block (27).

4. The unmanned aerial vehicle landing gear shock-absorbing structure of claim 1, wherein: when the recoil spring (16) is in an initial state, the support rod (2) is in a vertical state.

5. The unmanned aerial vehicle landing gear shock-absorbing structure of claim 1, wherein: the first rotating shaft (22) and the second rotating shaft (26) have the same rotating direction, and the rotating direction of the first rotating shaft is perpendicular to the rotating direction of the connecting block (27) on the lateral surfaces of the transverse plate (1) and the inserting plate (15).

6. The unmanned aerial vehicle landing gear shock-absorbing structure of claim 1, wherein: the support rod (2) is made of metal pipes, the bending part of the support rod (2) is smooth and arc-shaped, the cushion pad (21) is made of rubber materials, and arc surfaces are arranged at two ends of the cushion pad.

Technical Field

The invention relates to the technical field of unmanned aerial vehicle components, in particular to a damping structure of an unmanned aerial vehicle undercarriage.

Background

The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar. Can be repeatedly used for many times. The method is widely used for aerial reconnaissance, monitoring, communication, anti-submergence, electronic interference and the like.

Disclosure of Invention

The invention provides a damping structure of an unmanned aerial vehicle undercarriage, which has the advantage of buffering effect and solves the problem of lack of buffering capacity.

In order to realize the purpose with the buffering effect, the invention provides the following technical scheme: a damping structure of an unmanned aerial vehicle undercarriage comprises a transverse plate and a support rod, wherein the support rod is arranged below the transverse plate,

the upper surface of the transverse plate is fixedly connected with a fixed plate, a positioning hole is formed in the fixed plate, two ends of the transverse plate are fixedly connected with sleeves, a connecting plate is arranged below the transverse plate, the left end and the right end of the connecting plate are connected with inserting plates in a sliding mode, and a re-feeding spring is fixedly connected between the inserting plates;

the blotter has been cup jointed to the outside of bracing piece, axis of rotation No. one of both ends fixedly connected with of bracing piece, the bracing piece rotates through an axis of rotation and is connected with the sleeve pipe, sheathed tube inside sliding connection has the connecting rod, fixedly connected with supporting spring between connecting rod and the intraductal wall of sleeve, the axis of rotation No. two of upper end fixedly connected with of connecting rod, the connecting rod rotates through axis of rotation No. two and is connected with the connecting block.

As a preferable technical scheme of the invention, the supporting rod is U-shaped, the buffer pads are sleeved at two ends of the horizontal part of the supporting rod in a cylindrical shape, and the buffer pads are rotatably connected with the supporting rod.

As a preferable technical scheme of the invention, the connecting block is V-shaped, two ends of the connecting block are respectively and rotatably connected with the sleeve and the inserting plate, the inflection point of the connecting block is fixedly connected with the second rotating shaft, and the second rotating shaft, the sleeve and the inserting plate are arranged on the opposite sides of the connecting block.

As a preferable technical solution of the present invention, when the recoil spring is in an initial state, the support rod is in a vertical state.

As a preferable technical scheme of the invention, the first rotating shaft and the second rotating shaft have the same rotating direction, and the rotating direction of the first rotating shaft and the second rotating shaft is perpendicular to the rotating direction of the connecting block on the lateral surfaces of the transverse plate and the inserting plate.

As a preferable technical scheme of the invention, the support rod is made of a metal pipe, the bent part of the support rod is in a smooth arc shape, the cushion pad is made of a rubber material, and arc surfaces are arranged at two ends of the cushion pad.

Compared with the prior art, the invention provides an unmanned aerial vehicle undercarriage damping structure, which has the following beneficial effects:

this unmanned aerial vehicle undercarriage shock-absorbing structure through setting up an axis of rotation and No. two axes of rotation with bracing piece, sleeve pipe and connecting rod swing joint, constitutes to the ascending buffer structure in the direction parallel with the plane that the bracing piece is located, through diaphragm, connecting plate and connecting block constitution in the ascending buffer structure of the planar direction of perpendicular to bracing piece to form the ascending buffer structure in all directions, thereby reach the landing gear and descend to unmanned aerial vehicle in all directions and carry out the effect of buffering.

Drawings

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

FIG. 2 is a schematic view of a support bar according to the present invention;

fig. 3 is a top view of the fixation plate of the present invention.

In the figure: 1. a transverse plate; 11. a fixing plate; 12. positioning holes; 13. a sleeve; 14. a connecting plate; 15. inserting plates; 16. a spring is re-entered; 2. a support bar; 21. a cushion pad; 22. a first rotating shaft; 23. a sleeve; 24. a connecting rod; 25. a support spring; 26. a second rotating shaft; 27. and (4) connecting the blocks.

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. 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.

Referring to fig. 1-3, the invention discloses a damping structure for an undercarriage of an unmanned aerial vehicle, comprising a transverse plate 1 and a support rod 2, wherein the support rod 2 is arranged below the transverse plate 1,

the upper surface of the transverse plate 1 is fixedly connected with a fixing plate 11, a positioning hole 12 is formed in the fixing plate 11, two ends of the transverse plate 1 are fixedly connected with sleeves 13, a connecting plate 14 is arranged below the transverse plate 1, the left end and the right end of the connecting plate 14 are connected with inserting plates 15 in a sliding mode, and a recoil spring 16 is fixedly connected between the inserting plates 15;

blotter 21 has been cup jointed to the outside of bracing piece 2, axis of rotation 22 of both ends fixedly connected with of bracing piece 2, bracing piece 2 rotates through an axis of rotation 22 and is connected with sleeve pipe 23, the inside sliding connection of sleeve pipe 23 has connecting rod 24, fixedly connected with supporting spring 25 between connecting rod 24 and the sleeve pipe 23 inner wall, No. two axis of rotation 26 of upper end fixedly connected with of connecting rod 24, connecting rod 24 rotates through No. two axis of rotation 26 and is connected with connecting block 27.

Specifically, bracing piece 2 is the U style of calligraphy, blotter 21 is cylindricly cup joints at 2 horizontal part both ends of bracing piece, and blotter 21 rotates with bracing piece 2 to be connected.

In this embodiment, blotter 21 rotates with bracing piece 2 to be connected, forms the gyro wheel structure, rolls along the unmanned aerial vehicle direction of sideslipping when descending, prevents to turn on one's side.

Specifically, connecting block 27 is the V type, connecting block 27's both ends rotate with sleeve 13 and picture peg 15 respectively and are connected, connecting block 27's inflection point and No. two axis of rotation 26 fixed connection, and No. two axis of rotation 26 and sleeve 13 and picture peg 15 set up the opposite side at connecting block 27.

In this embodiment, connecting rod 24 and diaphragm 1 and picture peg 15 are rotated to be connected to connecting block 27, and when connecting rod 24 passed through connecting block 27 and rotated at diaphragm 1 both ends, picture peg 15 slided in connecting plate 14 to drive recoil spring 16 and take place elastic deformation, play the cushioning effect to the side deviation that two bracing pieces 2 take place under the impact.

Specifically, when the recoil spring 16 is in the initial state, the support rod 2 is in the vertical state.

In this embodiment, when the recoil spring 16 is in the initial condition, bracing piece 2 is in the vertical state to guarantee that the landing gear keeps the support configuration under no exogenic action, play the supporting role to unmanned aerial vehicle.

Specifically, the first rotating shaft 22 and the second rotating shaft 26 rotate in the same direction, and the rotating direction is perpendicular to the rotating direction of the connecting block 27 on the lateral surface of the transverse plate 1 and the insertion plate 15.

In this embodiment, the horizontal plate 1, the connecting plate 14 and the connecting block 27 constitute a buffer structure in the direction perpendicular to the plane of the supporting rod 2, the rotating directions of the first rotating shaft 22 and the second rotating shaft 26 are perpendicular to the rotating directions of the connecting block 27 on the lateral surfaces of the horizontal plate 1 and the insertion plate 15, and the interference of the first rotating shaft 22 and the second rotating shaft 26 on the buffer structure constituted by the horizontal plate 1, the connecting plate 14 and the connecting block 27 is prevented.

Specifically, the support rod 2 is made of a metal pipe, the bending part of the support rod 2 is smooth and arc-shaped, the cushion pad 21 is made of a rubber material, and arc surfaces are arranged at two ends of the cushion pad.

In the embodiment, the arc surfaces on the supporting Pascal 2 and the buffer cushion 21 prevent sharp corner parts on the undercarriage from being blocked with the ground, so that the unmanned aerial vehicle is prevented from turning laterally.

The working principle and the using process of the invention are as follows: when using, through locating hole 12 on fixed plate 11 with undercarriage and unmanned aerial vehicle fixed connection, when unmanned aerial vehicle descends, when taking place with the bracing piece 2 on the parallel ascending pressure in direction in plane, bracing piece 2, sleeve pipe 23 and connecting rod 24 take place the wrench movement around a axis of rotation 22 and No. two axis of rotation 26, bracing piece 2 takes place to slide in sleeve pipe 23 during the wrench movement, supporting spring 25 takes place elastic deformation, and then cushion this ascending pressure in direction, when taking place with bracing piece on the perpendicular ascending pressure in plane vertically in direction, connecting rod 24 rotates around diaphragm 1, picture peg 15 takes place to slide in connecting plate 14, recoil spring 16 takes place elastic deformation, and then cushion this ascending pressure, thereby cushion landing gear pressure in all directions.

In conclusion, this unmanned aerial vehicle undercarriage shock-absorbing structure, through setting up a axis of rotation 22 and No. two axis of rotation 26 with bracing piece 2, sleeve pipe 23 and connecting rod 24 swing joint, constitute to the buffer structure in the direction parallel with bracing piece 2 place plane, through diaphragm 1, connecting plate 14 and connecting block 27 constitute the buffer structure in the 2 planar directions of perpendicular to bracing piece, thereby form the buffer structure in all directions, thereby reach the landing gear and descend the effect of buffering to unmanned aerial vehicle on all directions.

It should be noted that, in this document, terms such as "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.