CN216546740U

CN216546740U - Aircraft protection device that falls convenient to assembly

Info

Publication number: CN216546740U
Application number: CN202123192195.9U
Authority: CN
Inventors: 李傲; 闫品; 徐子贺; 谢婷婷; 张天赐
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-12-19
Filing date: 2021-12-19
Publication date: 2022-05-17
Anticipated expiration: 2031-12-19

Abstract

The utility model relates to the technical field of unmanned aerial vehicle aircraft falling protection convenient to assemble, in particular to an aircraft falling protection device convenient to assemble. The aircraft comprises an aircraft body, three supporting foot frames are mounted on the lower surface of the aircraft body, a protection structure is arranged on the surface of the aircraft body and comprises an installation frame, the surface of the installation frame is connected with the aircraft body in a sliding mode, three first screw rods are evenly in threaded connection with the surface of the installation frame, the lower ends of the three first screw rods are respectively connected with a clamping plate in a rotating mode, six connecting rods are connected with the surface of the installation frame in a sliding mode, every two connecting rods form one group, three groups of connecting rods are evenly distributed on the surface of the installation frame, and the upper ends of the connecting rods in the same group are fixedly connected with a protection frame. The problem of exist among the prior art when the aircraft falls, the screw that rotates at a high speed bumps ground easily, causes the screw to damage is solved.

Description

Aircraft protection device that falls convenient to assembly

Technical Field

The utility model relates to the technical field of unmanned aerial vehicle aircraft falling protection convenient to assemble, in particular to an aircraft falling protection device convenient to assemble.

Background

Aircraft protection device that falls convenient to assembly is an aircraft protection device that falls for being convenient for installation and dismantlement, and the aircraft receives the influence of wind-force at the in-process of flight easily and loses balance, makes the aircraft fall, because the high-speed rotatory screw collides ground easily, causes the screw to damage.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the problem that in the prior art, when an aircraft falls, a propeller rotating at a high speed easily collides with the ground, so that the propeller is damaged, and provides an aircraft fall protection device convenient to assemble.

In order to achieve the purpose, the utility model adopts the following technical scheme: an aircraft falling protection device convenient to assemble comprises an aircraft body, wherein three support foot frames are mounted on the lower surface of the aircraft body, a protection structure is arranged on the surface of the aircraft body and comprises an installation frame, the surface of the installation frame is in sliding connection with the aircraft body, three first screw rods are in uniform threaded connection with the surface of the installation frame, the lower ends of the three first screw rods are in rotating connection with a clamping plate, six connecting rods are in sliding connection with the surface of the installation frame, every two connecting rods form a group, three groups of the connecting rods are uniformly distributed on the surface of the installation frame, a protection frame is fixedly connected to the upper ends of the connecting rods in the same group, a spring is fixedly connected to the surface of the protection frame, the lower end of the spring is fixedly connected with the installation frame, and the protection structure can be rapidly mounted on the aircraft body by rotating the first screw rods, can protect the screw of aircraft body through the protective frame, prevent that aircraft body screw from striking ground.

Preferably, the surface of the protective frame is uniformly and fixedly connected with three connecting plates, and the lower ends of the three connecting plates are fixedly connected with a round frame.

The effect that above-mentioned part reaches is: the area of protection can be promoted through the circle frame, further promotes the protective effect.

Preferably, the surface of the circular frame is fixedly connected with a sliding rod, the arc surface of the sliding rod penetrates through a fixing plate in a sliding mode, and the fixing plate is fixedly connected with the aircraft body through bolts.

The effect that above-mentioned part reaches is: can prevent the protection frame swing when striking ground, and then hoisting device's stability, the screw of better protection aircraft body.

Preferably, the arc surface of the connecting rod penetrates through a limiting plate in a sliding manner, and the upper end of the limiting plate is fixedly connected with the installation frame.

The effect that above-mentioned part reaches is: the connecting rod can be prevented from deflecting to cause the connecting rod to be stuck.

Preferably, the take-off structure is arranged on the surface of the supporting foot rest and comprises a sliding ring, the arc surface of the sliding ring is fixedly connected with the supporting foot rest, a telescopic rod is sleeved on the inner wall of the sliding ring, and the arc surface of the telescopic rod is connected with a fixed base in a sliding mode.

The effect that above-mentioned part reaches is: can restrict the aircraft body through above-mentioned part, stably do not deflect when conveniently taking off, stability when promoting to take off.

Preferably, three threaded holes are uniformly formed in the surface of the fixing base, and the inner walls of the three threaded holes are in threaded connection with second screws.

The effect that above-mentioned part reaches is: the second screw rod can block the telescopic link, prevents telescopic link roll-off unable adjustment base.

Preferably, the surface of the fixed base is provided with a groove, the surface of the groove is fixedly connected with three storage sleeves, and the size of each storage sleeve is matched with that of the telescopic rod.

The effect that above-mentioned part reaches is: the telescopic rod can be stored in the storage sleeve, the telescopic rod is convenient to store, and occupied space is reduced.

In view of the above, it is desirable to provide,

according to the installation method, through arrangement of the protection structure, when the protection structure needs to be installed on the aircraft body, the first screw rod is firstly rotated to move in the direction away from the installation frame until the first screw rod is adjusted to a proper position, then the protection structure is sleeved on the aircraft body, the clamping plate is rotated to enable the clamping plate to rotate again close to the lower end of the aircraft body, when the clamping plate is located at the lower end of the aircraft body, the first screw rod is rotated again to enable the first screw rod to drive the clamping plate to move in the direction close to the aircraft body, and installation can be completed until the aircraft body is clamped.

When the propeller of the aircraft body is weak and needs to be additionally protected, when the aircraft body loses balance and the propeller impacts the ground, the protective frame can firstly cushion the force vertical to the aircraft body by using the spring, so as to reduce the impact pressure of the aircraft body, meanwhile, the protective frame can enable the propeller to be far away from the ground as far as possible, so as to prevent the propeller from contacting the ground to damage the propeller, the slide rod can enhance the stability of the protective frame, the protective cover is prevented from deforming and deflecting to enable the propeller to contact the ground, the limiting plate can prevent the connecting rod from deflecting, so as to further improve the stability of the device, the circular frame can increase the protective area of the protective frame and improve the protective effect, and by using the protective structure, the aircraft is easily affected by wind power and loses balance in the flying process of the aircraft body, and the propeller is easily damaged due to the fact that the propeller easily impacts the ground when rotating at high speed, through protective structure, can protect the screw, and then promote the security that the screw used.

Drawings

FIG. 1 is a schematic perspective view of a crash protection system for aircraft according to the present invention, the crash protection system being readily assembled;

FIG. 2 is a schematic structural view of a crash protection system for aircraft in accordance with the present invention, as disclosed herein, which is readily assembled;

FIG. 3 is a schematic structural view of a takeoff structure for an aircraft crash protection device as provided herein, which is easy to assemble;

fig. 4 is a partial schematic structural view of a takeoff structure of an aircraft crash protection device according to the present invention, which is easy to assemble.

Illustration of the drawings: 1. an aircraft body; 2. a supporting foot rest; 3. a protective structure; 301. a mounting frame; 302. a first screw; 303. a splint; 304. a connecting rod; 305. a spring; 306. a protective frame; 307. a connecting plate; 308. a round frame; 309. a slide bar; 310. a fixing plate; 311. a limiting plate; 4. a takeoff structure; 41. a slip ring; 42. a telescopic rod; 43. a fixed base; 44. a groove; 45. a second screw; 46. a storage sleeve.

Detailed Description

Referring to fig. 1, the present invention provides a technical solution: the utility model provides an aircraft protection device that falls convenient to assembly, includes aircraft body 1, and three supporting leg 2 is installed to the lower surface of aircraft body 1, and the surface of aircraft body 1 is equipped with protective structure 3, and the surface of supporting leg 2 is equipped with take-off structure 4.

The specific arrangement and function of the protective structure 3 and the takeoff structure 4 will be described in detail below.

Referring to fig. 2, in the present embodiment: the protective structure 3 comprises a mounting frame 301, the surface of the mounting frame 301 is connected with the aircraft body 1 in a sliding manner, the surface of the mounting frame 301 is uniformly in threaded connection with three first screws 302, the lower ends of the three first screws 302 are rotatably connected with a clamping plate 303, the surface of the mounting frame 301 is connected with six connecting rods 304 in a sliding manner, every two of the six connecting rods 304 form a group, the three groups of connecting rods 304 are uniformly distributed on the surface of the mounting frame 301, the upper end of the same group of connecting rods 304 is fixedly connected with a protective frame 306, the size of the protective frame 306 is slightly larger than that of a propeller, the propeller rotating at high speed can be prevented from impacting the ground, the surface of the protective frame 306 is fixedly connected with a spring 305, the lower end of the spring 305 is fixedly connected with the mounting frame 301, the protective structure 3 can be rapidly mounted on the aircraft body 1 by rotating the first screws 302, and the propeller of the aircraft body 1 can be protected by the protective frame 306, prevent that 1 screw of aircraft body from striking ground, the three connecting plate 307 of the even fixedly connected with in surface of protective frame 306, the lower extreme fixedly connected with circle frame 308 of three connecting plate 307, can promote the area of protection through circle frame 308, further promote the guard effect, the fixed surface of circle frame 308 is connected with slide bar 309, the arc surface of slide bar 309 slides and runs through there is fixed plate 310, fixed plate 310 is with the help of bolt and aircraft body 1 fixed connection, can prevent protective frame 306 swing when striking ground, and then hoisting device's stability, better protection aircraft body 1's screw, the arc surface of connecting rod 304 slides and runs through there is limiting plate 311, the upper end and the installation frame 301 fixed connection of limiting plate 311, can prevent that connecting rod 304 from deflecting and causing connecting rod 304 to block.

Referring to fig. 3 and 4, specifically, the takeoff structure 4 includes a slip ring 41, an arc surface of the slip ring 41 is fixedly connected with the support leg 2, an expansion link 42 is sleeved on an inner wall of the slip ring 41, the arc surface of the expansion link 42 is slidably connected with a fixed base 43, the aircraft body 1 can be limited through the above parts, the aircraft can conveniently take off without deflection, the stability during takeoff is improved, three threaded holes are uniformly formed in the surface of the fixed base 43, the inner walls of the three threaded holes are all in threaded connection with a second screw 45, the expansion link 42 can be clamped by the second screw 45, the expansion link 42 is prevented from sliding out of the fixed base 43, a groove 44 is formed in the surface of the fixed base 43, three receiving sleeves 46 are fixedly connected to the surface of the groove 44, the receiving sleeves 46 are soft sleeves, the friction force can be improved, the expansion link 42 can be conveniently taken up, and the winding size of the receiving sleeves 46 is matched with the size of the expansion link 42, the storage sleeve 46 can store the telescopic rod 42, the telescopic rod 42 is convenient to store, and the occupied space is reduced.

The working principle is that by arranging the protective structure 3, when the protective structure 3 needs to be installed on the aircraft body 1, the first screw 302 is rotated to move the first screw 302 in a direction away from the installation frame 301 until the protective structure 3 is adjusted to a proper position, then the protective structure 3 is sleeved on the aircraft body 1, the clamp plate 303 is rotated to enable the clamp plate 303 to rotate again close to the lower end of the aircraft body 1, when the clamp plate 303 is positioned at the lower end of the aircraft body 1, the first screw 302 is rotated to enable the first screw 302 to drive the clamp plate 303 to move in a direction close to the aircraft body 1 until the aircraft body 1 is clamped, the installation can be completed, the propeller of the aircraft body 1 is fragile and needs to be protected additionally, when the aircraft body 1 loses balance and the propeller impacts the ground, the protective frame 306 firstly contacts the ground, the protective frame 306 can buffer the force vertical to the aircraft body 1 by using the spring 305, further reducing the impact pressure of the aircraft body 1, simultaneously enabling the propeller to be far away from the ground as far as possible by the protective frame 306, preventing the propeller from being damaged by contacting with the ground, enabling the slide bar 309 to enhance the stability of the protective frame 306, preventing the protective cover from deforming and deflecting to enable the propeller to contact with the ground, enabling the connecting rod 304 to deflect by the limiting plate 311, further improving the stability of the device, enabling the round frame 308 to increase the protective area of the protective frame 306, improving the protective effect, enabling the aircraft body 1 to lose balance easily due to small ascending speed at the moment of taking off, through using the taking-off structure 4, when the aircraft body 1 needs to take off, firstly taking out the telescopic rod 42 from the storage sleeve 46, then extending the telescopic rod 42, inserting the three telescopic rods 42 into the fixed base 43, rotating the second screw rod 45 to enable the second screw rod 45 to move towards the direction close to the telescopic rod 42 until the telescopic rod 42 is supported, and then the sliding rings 41 on the supporting foot frames 2 are respectively sleeved into the telescopic rods 42, the aircraft body 1 slides towards the direction close to the fixed base 43 until the supporting foot frames 2 contact the fixed base 43, the fixed base 43 is placed on the flat ground to prepare for taking off, and the second bolts can place the telescopic rods 42 to slide out of the fixed base 43.

Claims

1. An aircraft crash protection device convenient to assemble, comprising an aircraft body (1), characterized in that: the lower surface mounting of aircraft body (1) has three supporting leg (2), the surface of aircraft body (1) is equipped with protective structure (3), protective structure (3) include installation frame (301), the surface and aircraft body (1) sliding connection of installation frame (301), the even threaded connection in surface of installation frame (301) has three first screw rod (302), three the lower extreme of first screw rod (302) all rotates and is connected with splint (303), the surface sliding connection of installation frame (301) has six connecting rods (304), six every two of connecting rod (304) are a set of, three set of connecting rod (304) evenly distributed is on the surface of installation frame (301), the upper end fixedly connected with protection frame (306) of connecting rod (304) is organized in the same way, the fixed surface of protection frame (306) is connected with spring (305), the lower end of the spring (305) is fixedly connected with the mounting frame (301).

2. An aircraft crash protection device as claimed in claim 1, wherein: the surface of the protective frame (306) is uniformly and fixedly connected with three connecting plates (307), and the lower ends of the three connecting plates (307) are fixedly connected with a round frame (308).

3. An aircraft crash protection device as claimed in claim 2, wherein: the surface of the round frame (308) is fixedly connected with a sliding rod (309), a fixing plate (310) penetrates through the arc surface of the sliding rod (309) in a sliding mode, and the fixing plate (310) is fixedly connected with the aircraft body (1) through bolts.

4. An aircraft crash protection device as claimed in claim 1, wherein: the arc surface of connecting rod (304) slides and runs through limiting plate (311), the upper end and installation frame (301) fixed connection of limiting plate (311).

5. An aircraft crash protection device as claimed in claim 1, wherein: the take-off structure is characterized in that a take-off structure (4) is arranged on the surface of the supporting foot rest (2), the take-off structure (4) comprises a sliding ring (41), an arc surface of the sliding ring (41) is fixedly connected with the supporting foot rest (2), a telescopic rod (42) is sleeved on the inner wall of the sliding ring (41), and a fixing base (43) is connected to the arc surface of the telescopic rod (42) in a sliding mode.

6. An aircraft crash protection device as claimed in claim 5, wherein: three threaded holes are uniformly formed in the surface of the fixing base (43), and the inner walls of the three threaded holes are in threaded connection with second screws (45).

7. An aircraft crash protection device as claimed in claim 5, wherein: the surface of the fixed base (43) is provided with a groove (44), the surface of the groove (44) is fixedly connected with three storage sleeves (46), and the size of each storage sleeve (46) is matched with that of the telescopic rod (42).