CN211568292U

CN211568292U - Special undercarriage of small-size reconnaissance unmanned aerial vehicle

Info

Publication number: CN211568292U
Application number: CN201922064904.1U
Authority: CN
Inventors: 郑文锋
Original assignee: Hubei Chutiantong Survey Planning And Design Co ltd
Current assignee: Hubei Chutiantong Survey Planning And Design Co ltd
Priority date: 2019-11-26
Filing date: 2019-11-26
Publication date: 2020-09-25
Anticipated expiration: 2029-11-26

Abstract

The utility model provides a special undercarriage of small-size reconnaissance unmanned aerial vehicle, including the instrument case, the fixed surface of instrument case top is connected with the radar board, all fly the lifter through spliced pole fixedly connected with around the instrument case, fly the one end fixedly connected with motor fixed block that the spliced pole was kept away from to the lifter, the brushless DC motor of top fixedly connected with of motor fixed block, brushless DC motor's output shaft fixedly connected with power rotary vane, the fixed undercarriage of both sides fixedly connected with H type of instrument case bottom, the equal fixedly connected with shock attenuation pole that falls in both sides of the fixed undercarriage bottom of H type, the both ends of two shock attenuation poles that fall all articulate through the elasticity articulated elements has the bracing piece, the equal fixedly connected with rubber block in bottom of. The utility model discloses, when spring part 14 stretches, then can play the striking that the buffering fell to the ground, use safelyr, through can pivoted elastic hinged element 10, can make this kind of small-size reconnaissance unmanned aerial vehicle fall to the not position of co-altitude.

Description

Special undercarriage of small-size reconnaissance unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field especially relates to a special undercarriage of small-size reconnaissance unmanned aerial vehicle.

Background

An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. 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 + the industry application is 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, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology.

The multi-purpose environment that the topography is complicated of current small-size reconnaissance unmanned aerial vehicle owing to do not have flat road surface and better landing place, damages reconnaissance unmanned aerial vehicle easily during the use, leads to the condition such as tumble injury and blade fracture to appear, so need a special undercarriage that can guarantee unmanned aerial vehicle safety of rising and falling urgently.

SUMMERY OF THE UTILITY MODEL

Objects of the invention

For solving the technical problem who exists among the background art, the utility model provides a special undercarriage of small-size reconnaissance unmanned aerial vehicle has solved among the environment that current small-size reconnaissance unmanned aerial vehicle multi-purpose topography is complicated, owing to there is not flat road surface and better landing point, leads to the cracked problem of tumble injury unmanned aerial vehicle and blade during the use easily.

(II) technical scheme

The utility model provides a special undercarriage of small-size reconnaissance unmanned aerial vehicle, including the instrument case, the fixed surface of instrument case top is connected with the radar board, all fly the lifter through spliced pole fixedly connected with around the instrument case, fly the one end fixedly connected with motor fixed block that the spliced pole was kept away from to the lifter, the brushless DC motor of top fixedly connected with of motor fixed block, brushless DC motor's output shaft fixedly connected with power spiral leaf, the fixed undercarriage of both sides fixedly connected with H type of instrument case bottom, the equal fixedly connected with shock attenuation pole that falls in both sides of the fixed undercarriage bottom of H type, the both ends of two shock attenuation poles all articulate through the elasticity articulated elements has the bracing piece, the equal fixedly connected with rubber block in bottom of four bracing pieces.

Preferably, just be located and be equipped with the spring part between two bracing pieces under the shock attenuation lifting rod, one side fixedly connected with arc ring of bracing piece, one side of arc ring is fixed mutually through the one end of fixed cable and spring part.

Preferably, the spring part includes the spring body, and the equal fixedly connected with locking hook in both ends of spring body, one side of locking hook rotate and are connected with the card, the surface of locking hook and the one end fixed connection of fixed cable.

Preferably, the bottom of the instrument case is fixedly connected with a stabilizing disc, and four corners of the stabilizing disc are provided with adjusting grooves.

Preferably, the middle part of the adjusting groove is fixedly connected with a supporting piece through a clamping ring, and the top of the supporting piece is fixedly connected with the bottom of the instrument case.

Preferably, the elastic hinge member comprises a first elastic metal arc-shaped half ring, and one side of the first elastic metal arc-shaped half ring is fixedly connected with one end of the shock absorption lifting rod.

Preferably, the bottom of the first elastic metal arc semi-ring is rotatably connected with a second elastic metal arc semi-ring through a rotating block, and the bottom of the second elastic metal arc semi-ring is fixedly connected with the top end of the supporting rod.

Compared with the prior art, the above technical scheme of the utility model following profitable technological effect has: when this kind of small-size reconnaissance unmanned aerial vehicle falls to the ground, then the rubber block of bracing piece 11 bottom contacts to ground earlier, then under the instrument case 1 pressure at the top, make the shock attenuation pole of lifting 9 push down bracing piece 11, make bracing piece 11 bear pressure and drive elasticity articulated elements 10 and rotate, it is tensile to make bracing piece 11 drive spring part 14, when spring part 14 stretches, then can play the striking that the buffering fell to the ground, it is safer to use, through can pivoted elasticity articulated elements 10, can make this kind of small-size reconnaissance unmanned aerial vehicle fall to the not co-altitude position on, thereby solved current small-size reconnaissance unmanned aerial vehicle multi-purpose in the complicated environment of topography, because there is not flat road surface and better landing point, lead to falling injury unmanned aerial vehicle and the cracked problem of blade during the use easily.

Drawings

Fig. 1 is the utility model provides a structural schematic of special undercarriage of small-size reconnaissance unmanned aerial vehicle.

Fig. 2 is the utility model provides a schematic diagram of structure spring part in small-size reconnaissance special undercarriage of unmanned aerial vehicle.

Fig. 3 is an enlarged view of a structure at a in fig. 1.

Fig. 4 is an enlarged view of the structure at B in fig. 1.

Reference numerals: 1. an instrument chassis; 2. a radar plate; 3. connecting columns; 4. a fly-lift rod; 5. a motor fixing block; 6. a brushless DC motor; 7. a power rotary vane; 8. an H-shaped fixed landing gear; 9. a shock absorbing lifting bar; 10. an elastic hinge member; 11. a support bar; 12. a rubber block; 13. an arc-shaped ring; 14. a spring member; 15. fixing a stay cable; 16. locking the hook; 17. a card; 18. a spring body; 19. a stabilizing disc; 20. an adjustment groove; 21. a support member; 22. a snap ring; 23. a first elastic metal arc semi-ring; 24. rotating the block; 25. and the second elastic metal arc semi-ring.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings. It should be understood that the description is intended to be illustrative only and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.

As shown in fig. 1-4, the utility model provides a special undercarriage of small-size reconnaissance unmanned aerial vehicle, including instrument case 1, the fixed surface at instrument case 1 top is connected with radar board 2, all through spliced pole 3 fixedly connected with flight lifting rod 4 around instrument case 1, the one end fixedly connected with motor fixed block 5 of spliced pole 3 is kept away from to flight lifting rod 4, motor fixed block 5's top fixedly connected with brushless DC motor 6, brushless DC motor 6's output shaft fixed connection has power vane 7, the fixed undercarriage 8 of both sides fixedly connected with H type of instrument case 1 bottom, the equal fixedly connected with shock attenuation pole 9 in both sides of the fixed undercarriage 8 bottom of H type, the both ends of two shock attenuation poles 9 all articulate through elastic hinge spare 10 has bracing piece 11, the equal fixedly connected with rubber block 12 in bottom of four bracing pieces 11.

The utility model discloses in, when this kind of small-size reconnaissance unmanned aerial vehicle falls to the ground, then the rubber block of bracing piece 11 bottom contacts to earth earlier, then under the instrument case 1 pressure at top, make the shock attenuation pole 9 that plays push down bracing piece 11, make bracing piece 11 bear pressure and drive elasticity articulated elements 10 and rotate, it is tensile to make bracing piece 11 drive spring part 14, when spring part 14 stretches, then can play the striking that the buffering fell to the ground, it is safer to use, through can pivoted elasticity articulated elements 10, can make this kind of small-size reconnaissance unmanned aerial vehicle fall to the not position of co-altitude, thereby solved among the environment that current small-size reconnaissance unmanned aerial vehicle is used for the topography complicacy more, because there is not flat road surface and better landing point, lead to tumble unmanned aerial vehicle and the cracked problem of blade easily during the use.

In an alternative embodiment, a spring part 14 is arranged right below the shock-absorbing lifting rod 9 and between the two support rods 11, an arc-shaped ring 13 is fixedly connected to one side of each support rod 11, one side of each arc-shaped ring 13 is fixed to one end of each spring part 14 through a fixing cable 15, each spring part 14 comprises a spring body 18, locking hooks 16 are fixedly connected to two ends of each spring body 18, a clamping piece 17 is rotatably connected to one side of each locking hook 16, and the surface of each locking hook 16 is fixedly connected with one end of each fixing cable 15.

The shock absorbing rising and falling rod 9 is engaged with the spring member 14 at the bottom to quickly absorb the impact force when falling to the ground, and the fixing cable 15 can be stably fixed by the engaging piece 17 on the side of the locking hook 16.

In an alternative embodiment, a stabilizing disc 19 is fixedly connected to the bottom of the instrument case 1, adjusting grooves 20 are formed at four corners of the stabilizing disc 19, a supporting member 21 is fixedly connected to the middle of each adjusting groove 20 through a clamping ring 22, and the top of each supporting member 21 is fixedly connected to the bottom of the instrument case 1.

It should be noted that, instrument case 1 can be with the required instrument of reconnaissance unmanned aerial vehicle stable installation, can adjust instrument case 1's position through the adjustment tank on stabilizer disc 19 surface, makes centrobaric regulation use more convenient.

In an alternative embodiment, the elastic hinge 10 includes a first elastic metal arc half ring 23, one side of the first elastic metal arc half ring 23 is fixedly connected to one end of the shock-absorbing lifting rod 9, the bottom of the first elastic metal arc half ring 23 is rotatably connected to a second elastic metal arc half ring 25 through a rotating block 24, and the bottom of the second elastic metal arc half ring 25 is fixedly connected to the top end of the supporting rod 11.

It should be noted that the elastic hinge 10 can adjust the position of the support rod 11, and together with the spring element 14, can play a role in surveying the buffering components of the drone.

It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.

Claims

1. The landing gear special for the small-sized reconnaissance unmanned aerial vehicle is characterized by comprising an instrument case (1), wherein a radar plate (2) is fixedly connected to the surface of the top of the instrument case (1), flying rods (4) are fixedly connected to the periphery of the instrument case (1) through connecting columns (3), a motor fixing block (5) is fixedly connected to one end, far away from the connecting columns (3), of the flying rods (4), a brushless direct current motor (6) is fixedly connected to the top of the motor fixing block (5), a power rotary vane (7) is fixedly connected to an output shaft of the brushless direct current motor (6), H-shaped fixed landing gears (8) are fixedly connected to two sides of the bottom of the instrument case (1), damping lifting rods (9) are fixedly connected to two sides of the bottom of the H-shaped fixed landing gears (8), and supporting rods (11) are hinged to two ends of the two damping lifting rods (9) through, the bottom ends of the four support rods (11) are fixedly connected with rubber blocks (12).

2. The landing gear special for the small-scale reconnaissance unmanned aerial vehicle as claimed in claim 1, wherein a spring part (14) is arranged under the shock-absorbing lifting rod (9) and between the two support rods (11), an arc-shaped ring (13) is fixedly connected to one side of each support rod (11), and one side of each arc-shaped ring (13) is fixed to one end of each spring part (14) through a fixing stay cable (15).

3. The landing gear special for the small-scale reconnaissance unmanned aerial vehicle as claimed in claim 2, wherein the spring member (14) comprises a spring body (18), locking hooks (16) are fixedly connected to both ends of the spring body (18), a clamping piece (17) is rotatably connected to one side of each locking hook (16), and the surface of each locking hook (16) is fixedly connected with one end of each fixing stay cable (15).

4. The landing gear special for small-scale reconnaissance unmanned aerial vehicle as claimed in claim 1, wherein the bottom of the instrument case (1) is fixedly connected with a stabilizing disc (19), and four corners of the stabilizing disc (19) are provided with adjusting grooves (20).

5. The landing gear for small-scale reconnaissance unmanned aerial vehicle as claimed in claim 4, wherein the middle part of the adjusting groove (20) is fixedly connected with a support member (21) through a snap ring (22), and the top of the support member (21) is fixedly connected with the bottom of the instrument case (1).

6. The landing gear for a small-sized reconnaissance unmanned aerial vehicle as claimed in claim 1, wherein the elastic hinge member (10) comprises a first elastic metal arc-shaped half ring (23), and one side of the first elastic metal arc-shaped half ring (23) is fixedly connected with one end of the shock-absorbing lifting rod (9).

7. The landing gear for small-scale reconnaissance unmanned aerial vehicle of claim 6, wherein the bottom of the first elastic metal arc-shaped semi-ring (23) is rotatably connected with a second elastic metal arc-shaped semi-ring (25) through a rotating block (24), and the bottom of the second elastic metal arc-shaped semi-ring (25) is fixedly connected with the top end of the support rod (11).