CN210063376U

CN210063376U - Automatic ejection parachute of four shaft air vehicle

Info

Publication number: CN210063376U
Application number: CN201920959382.9U
Authority: CN
Inventors: 常江峰; 李玉刚; 崔书铭; 王超磊
Original assignee: Shenyang Ligong University
Current assignee: Shenyang Ligong University
Priority date: 2019-06-25
Filing date: 2019-06-25
Publication date: 2020-02-14
Anticipated expiration: 2029-06-25

Abstract

The utility model relates to the technical field of parachutes, in particular to an automatic ejection parachute of a four-axis aircraft, which comprises an aircraft body, a battery box and a parachute box, wherein both sides of the aircraft body are fixedly provided with a connecting shaft, the other side of the connecting shaft is fixedly provided with a screw, the inside of the screw is fixedly provided with a motor, the inside of the aircraft body is fixedly provided with a 51-chip microcomputer, the top of the aircraft body is fixedly provided with the parachute box, a lacing is fixedly arranged between the parachute box and a supporting leg, the top of the parachute box is fixedly provided with a protective cover, the left side of the top of the parachute box is fixedly provided with a buckle, the left bottom inside of the parachute box is fixedly provided with a micro motor, the inside of the parachute box is fixedly provided with a mounting box, the inside of the mounting, the two sides of the bottom of the supporting plate are fixedly provided with compression springs, and the device is simple in structure, low in cost and more flexible.

Description

Automatic ejection parachute of four shaft air vehicle

Technical Field

The utility model relates to a parachute technical field specifically is a four shaft air vehicle's automatic ejection parachute.

Background

The quadcopter is also called a quadrotor and a quadrotor helicopter, and is called a quadcopter and a quadrotor for short. The quadoror is a multi-rotor aircraft. Four propellers of the four-axis aircraft are simple mechanisms with directly connected motors, and the cross-shaped layout allows the aircraft to obtain the force for rotating the aircraft body by changing the rotating speed of the motors, so that the self posture of the aircraft can be adjusted. Specific technical details are described in the "basic motion principle". Because of its inherent complexity, historically there have never been large commercial quadrotors. In recent years, due to the development of micro-electromechanical control technology, the stable four-axis aircraft has attracted extensive attention, and the application prospect is very considerable. Compared with a helicopter, the four-axis aircraft can realize fewer flight attitudes, but basic states of advancing, retreating, translating and the like can be realized. However, the mechanical structure of the four-axis aircraft is far simpler than that of a helicopter, and the maintenance and replacement cost is very small, so that the four-axis aircraft has greater application advantages than the helicopter.

The parachute is a deployable aerodynamic speed reducer which is inflated and deployed relative to the air movement by utilizing the principle of air resistance. Modern parachutes are aerial vehicles that safely descend persons or things from the air to the ground. Mainly made of flexible fabric. The air-drop flight training device is equipment for air-drop soldier combat and training, lifesaving and training of aerospace personnel, training, competition and performance of parachutists, air-drop supplies and aircraft recovery.

Most of the existing four-axis aircrafts use a CO2 compression bottle as ejection power, are large in size, need to be checked regularly, cannot be reused, and cannot meet the current requirements.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a four shaft air vehicle's automatic parachute that launches to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme:

an automatic ejection parachute of a four-axis aircraft comprises an aircraft body, a battery box and an umbrella box, wherein connecting shafts are fixedly mounted on two sides of the aircraft body, a screw is fixedly mounted on the other side of each connecting shaft, a motor is fixedly mounted inside the screw, the battery box is fixedly mounted at the bottom of the aircraft body, a storage battery is fixedly mounted inside the battery box, supporting legs are fixedly mounted at the bottom of the battery box, a 51 single chip microcomputer is fixedly mounted inside the aircraft body, the umbrella box is fixedly mounted at the top of the aircraft body, a lacing is fixedly mounted between the umbrella box and the supporting legs, a protective cover is fixedly mounted at the top of the umbrella box, a buckle is fixedly mounted at the left side of the top of the umbrella box, a micro motor is fixedly mounted at the left bottom inside the umbrella box, and a rotating shaft is, the utility model discloses a parachute box, including umbrella box, mounting box, backup pad, the top fixed mounting of backup pad has the parachute, the equal fixed mounting in both sides of backup pad bottom has compression spring.

Preferably, the connecting shafts are four in number and are uniformly distributed at the corners of the side walls on the two sides of the aircraft body.

Preferably, the storage battery is electrically connected with the 51 single chip microcomputer, the motor and the micro motor.

Preferably, the rotating shaft is in transmission connection with the buckle, and the buckle is fixedly installed at the connection position between the protective cover and the umbrella box.

Preferably, the support plate is inserted into the mounting box.

Preferably, the umbrella box is sleeved on the supporting legs through the tying belts so as to be fixedly installed on the top of the aircraft body.

Compared with the prior art, the beneficial effects of the utility model are that:

1. the utility model discloses in, through setting up 51 singlechips, the electric pulse signal that the accessible sent turns into micro motor's rotation to open the buckle through the pivot, make compression spring bounce from the mounting box, realize triggering of parachute, the cost is reduced and more nimble.

2. The utility model discloses in, through setting up the backup pad, can effectually drive the backup pad through compression spring and pop out the parachute, can carry out recycle after using the completion simultaneously, practiced thrift a large amount of costs, very practical.

3. The utility model discloses in, through setting up the frenulum, can be more stable fix the umbrella box on the aircraft body, not only more firm, also made things convenient for the dismantlement, overhauld the mechanism of umbrella box inside, prevent that the parachute from going wrong and leading to the aircraft to break.

Drawings

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

FIG. 2 is a schematic view of the internal structure of the present invention;

FIG. 3 is a schematic view of the internal structure of the umbrella case of the present invention;

FIG. 4 is a top view of the umbrella case of the present invention;

in the figure: 1. an aircraft body; 2. a connecting shaft; 3. a propeller; 4. an umbrella box; 5. a tie strap; 6. a battery case; 7. supporting legs; 8. a motor; 9.51 single-chip microcomputer; 10. a storage battery; 11. a micro motor; 12. a rotating shaft; 13. buckling; 14. a protective cover; 15. a parachute; 16. a support plate; 17. a compression spring; 18. and (5) mounting the box.

Detailed Description

The technical solution 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 some embodiments of the present invention, rather than all embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative work belong to the protection scope of the present invention based on the embodiments of the present invention.

Referring to fig. 1-4, the present invention provides a technical solution:

an automatic ejection parachute of a four-axis aircraft comprises an aircraft body 1, a battery box 6 and a parachute box 4, wherein connecting shafts 2 are fixedly mounted on two sides of the aircraft body 1, the connecting shafts 2 are four in number and are evenly distributed at corners of side walls on two sides of the aircraft body 1, a propeller 3 is fixedly mounted on the other side of the connecting shafts 2, a motor 8 is fixedly mounted inside the propeller 3, the battery box 6 is fixedly mounted at the bottom of the aircraft body 1, a storage battery 10 is fixedly mounted inside the battery box 6, supporting legs 7 are fixedly mounted at the bottom of the battery box 6, a 51 single chip microcomputer 9 is fixedly mounted inside the aircraft body 1, a fastener 13 can be opened through a sent electric pulse signal to convert the electric pulse signal into rotation of a micro motor 11, a compression spring 17 can be ejected from a mounting box 18, triggering of a parachute 15 is achieved, cost is reduced, the top of the aircraft body 1 is fixedly provided with an umbrella box 4, a lacing 5 is fixedly arranged between the umbrella box 4 and the supporting leg 7, the umbrella box 4 can be more stably fixed on the aircraft body 1, the umbrella box is firmer and is convenient to disassemble, a mechanism in the umbrella box 4 is overhauled to prevent the problem of the parachute 15 from causing the aircraft to break, the umbrella box 4 is sleeved on the supporting leg 7 through the lacing 5 so as to be fixedly arranged on the top of the aircraft body 1, the top of the umbrella box 4 is fixedly provided with a protective cover 14, the left side of the top of the umbrella box 4 is fixedly provided with a buckle 13, the bottom of the left side in the umbrella box 4 is fixedly provided with a micro motor 11, the storage battery 10 is electrically connected with the 51 single chip microcomputer 9, the motor 8 is electrically connected with the micro motor 11, the top of the micro motor 11 is fixedly provided with a rotating shaft 12, the rotating shaft 12 is in transmission connection, the inside fixed mounting of umbrella box 4 has mounting box 18, and the inside fixed mounting of mounting box 18 has backup pad 16, can effectually drive backup pad 16 through compression spring 17 and pop out parachute 15, can carry out recycle after using the completion simultaneously, has practiced thrift a large amount of costs, and is very practical, and backup pad 16 pegs graft in the inside of mounting box 18, and the top fixed mounting of backup pad 16 has parachute 15, and the equal fixed mounting in both sides of backup pad 16 bottom has compression spring 17.

The utility model discloses work flow: during the use, when four shaft air vehicle goes wrong, 51 the electric pulse signal that 9 accessible of singlechip sent turns into micro motor 11's rotation, and open buckle 13 through pivot 12, make compression spring 17 bounce from the mounting box 18, realize triggering of parachute 15, the cost is reduced and more nimble, backup pad 16 can effectually drive backup pad 16 through compression spring 17 and pop out parachute 15, can carry out recycle after using the completion simultaneously, a large amount of costs have been practiced thrift, it is very practical, can be more stable fix parachute box 4 on aircraft body 1 through frenulum 5, not only more firm, also convenient the dismantlement, overhaul the mechanism inside parachute box 4, prevent that parachute 15 from going wrong and leading to the aircraft to break, the device simple structure, the cost is lower and more nimble.

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.

Claims

1. The utility model provides a four shaft air vehicle's automatic parachute that launches, includes aircraft body (1), battery case (6) and umbrella box (4), its characterized in that: the aircraft is characterized in that connecting shafts (2) are fixedly mounted on two sides of the aircraft body (1), screws (3) are fixedly mounted on the other sides of the connecting shafts (2), motors (8) are fixedly mounted inside the screws (3), a battery box (6) is fixedly mounted at the bottom of the aircraft body (1), a storage battery (10) is fixedly mounted inside the battery box (6), supporting legs (7) are fixedly mounted at the bottom of the battery box (6), a 51 single-chip microcomputer (9) is fixedly mounted inside the aircraft body (1), an umbrella box (4) is fixedly mounted at the top of the aircraft body (1), a lace (5) is fixedly mounted between the umbrella box (4) and the supporting legs (7), a protective cover (14) is fixedly mounted at the top of the umbrella box (4), and a buckle (13) is fixedly mounted at the top of the umbrella box (4), the utility model discloses an umbrella box, including umbrella box (4), the inside left bottom fixed mounting of umbrella box (4) has micro motor (11), the top fixed mounting of micro motor (11) has pivot (12), the inside fixed mounting of umbrella box (4) has mounting box (18), the inside fixed mounting of mounting box (18) has backup pad (16), the top fixed mounting of backup pad (16) has parachute (15), the equal fixed mounting in both sides of backup pad (16) bottom has compression spring (17).

2. The automatic ejection parachute of a quadcopter according to claim 1, wherein: the four connecting shafts (2) are arranged at the corners of the side walls of the two sides of the aircraft body (1).

3. The automatic ejection parachute of a quadcopter according to claim 1, wherein: the storage battery (10) is electrically connected with the 51 single chip microcomputer (9), the motor (8) and the micro motor (11).

4. The automatic ejection parachute of a quadcopter according to claim 1, wherein: the rotating shaft (12) is in transmission connection with the buckle (13), and the buckle (13) is fixedly arranged at the connection position between the protective cover (14) and the umbrella box (4).

5. The automatic ejection parachute of a quadcopter according to claim 1, wherein: the supporting plate (16) is inserted in the mounting box (18).

6. The automatic ejection parachute of a quadcopter according to claim 1, wherein: the umbrella box (4) is sleeved on the supporting legs (7) through the tying belts (5) and is fixedly installed on the top of the aircraft body (1).