CN107264842B

CN107264842B - Space debris emergency avoidance system based on shock waves

Info

Publication number: CN107264842B
Application number: CN201710386961.4A
Authority: CN
Inventors: 袁建平; 陈诗瑜; 朱战霞; 袁源; 孙冲
Original assignee: Northwest University of Technology
Current assignee: Northwest University of Technology
Priority date: 2017-05-26
Filing date: 2017-05-26
Publication date: 2020-01-10
Anticipated expiration: 2037-05-26
Also published as: CN107264842A

Abstract

The invention discloses a shock wave-based space debris emergency avoidance system which comprises a spacecraft main body, wherein shock wave injection hole surfaces are symmetrically arranged on the front surface and the rear surface of the spacecraft main body, a compressed gas cabin is arranged in the spacecraft main body, the shock wave injection hole surfaces comprise porous panels, horn-shaped joints are arranged below the porous panels, the horn-shaped joints are connected with the compressed gas cabin through Laval pipes, shock waves are generated through high-pressure gas release in the compressed gas cabin, the shock waves are emitted through the porous panels on a satellite, high-speed gas flow can blow away debris or temporarily block the movement of the debris, and meanwhile, the spacecraft main body can leave a dangerous position through strong reaction force. The invention can emergently deal with space debris which moves rapidly and is difficult to capture, so that the body avoids the threat of the debris.

Description

Space debris emergency avoidance system based on shock waves

Technical Field

The invention belongs to the technical field of spaceflight, and particularly relates to a space debris emergency evasion system based on shock waves.

Background

Intensive space tasks and complex space environments increase the on-orbit failure rate of the spacecraft, resulting in the occurrence of a batch of failed or partially failed spacecraft; meanwhile, in deep space oriented exploration missions, the spacecraft may encounter asteroid and celestial body debris. These space fragments pose a serious threat to the safety of the spacecraft and the astronauts. Due to the diversification of the generation reasons of the space debris, the space debris is not fixed in size and shape, and besides objects which are discarded satellite components and the like and are relatively suitable for being caught in a configuration or motion state, some space debris which are irregular in shape, relatively high in speed or tumbling exist. Such debris 1) does not have obvious beacons or obvious features (such as solar sailboards, nozzles, etc.) for catching, and the common rigid machinery is difficult to catch; 2) the possibility of impacts or accidents generally occurs due to the high speed of operation and the rolling, which require the spacecraft to handle it urgently, at which time the usual rigid arrest is not suitable, while the flexible arrest, such as a flying net, is also difficult to exert its effectiveness in the face of such delicate space debris due to its complex dynamics. 3) The size is moderate, the small fragments cannot pose a threat, the orbit of the large fragments is clearly calibrated, and the space fragments between the large fragments cannot be ignored and are not easy to monitor.

In summary, for the space debris which is not suitable for front grabbing and processing and can threaten the spacecraft and the astronaut, an emergency avoidance method or an emergency avoidance device is needed to quickly and effectively avoid the interference of the space debris on the space mission and ensure the mission safety.

Disclosure of Invention

The invention aims to overcome the defects and provide an emergency space debris avoidance system based on shock waves, which can quickly pull the distance between space debris and a spacecraft, so that the spacecraft has time to change the orbit/posture and avoid collision with the space debris.

In order to achieve the purpose, the spacecraft comprises a spacecraft main body, shock wave injection hole surfaces are symmetrically arranged on the front surface and the rear surface of the spacecraft main body, a compressed gas cabin is arranged in the spacecraft main body, the shock wave injection hole surfaces comprise porous panels, horn-shaped joints are arranged below the porous panels, and the horn-shaped joints are connected with the compressed gas cabin through Laval pipes.

The spacecraft body comprises an attitude and orbit control system, a power supply system and a payload required by on-orbit operation.

Two solar sailboards are symmetrically arranged on two sides of the spacecraft main body.

The solar sailboard is fixed on the spacecraft main body through the telescopic support rod, and the top of the telescopic support rod is provided with two sub-boards.

Two sub-boards of the solar energy sailboard that opens and shuts before the expansion coincide with the top of scalable cradling piece, and two sub-boards of the solar energy sailboard that opens and shuts after the expansion are rotatory the amalgamation and are circular, and two sub-boards can be around 360 degrees rotations of scalable cradling piece axis.

And a hatch valve is arranged between the compressed gas cabin and the Laval pipe.

The main body of the spacecraft is hexagonal prism-shaped.

Compared with the prior art, the invention has the following beneficial effects: the high-pressure gas in the compressed gas cabin is released to generate shock waves, the shock waves are emitted through the porous panel on the satellite, high-speed gas flow can blow away fragments or temporarily block the fragments from moving, and meanwhile strong reaction force can enable the spacecraft main body to leave a dangerous position. The invention can emergently deal with space debris which moves rapidly and is difficult to capture, so that the body avoids the threat of the debris.

Furthermore, the two solar sailboards are arranged and distributed on two sides of the spacecraft main body, each solar sailboard comprises a telescopic support rod connected with the spacecraft main body and a solar folding sailboard arranged at the top end of the telescopic support rod, the solar sailboards are used for providing an energy source for the spacecraft main body, the telescopic support rods are adopted to prevent the solar sailboards from being damaged or broken by strong reaction force when shock waves are sprayed, if the telescopic support rods extend out section by section when the spacecraft main body is used, the solar folding sailboards are retracted section by section when fragment early warning is carried out, the solar folding sailboards are unfolded to be circular, and the solar folding sailboards can rotate 360 degrees to adapt to different postures of the spacecraft main body.

Drawings

FIG. 1 is a schematic diagram of the working principle of the present invention;

FIG. 2 is a front view of the overall structure of the present invention;

FIG. 3 is a schematic side view of the overall structure of the present invention;

FIG. 4 is a schematic top view of the overall structure of the present invention;

FIG. 5 is a schematic view of a shock hole panel and a joint according to the present invention;

fig. 6 is a schematic view of a solar panel according to the present invention.

In the figure: 1. a spacecraft main body; 2. a porous panel; 3. a hatch valve; 4. a compressed gas compartment; 5. a solar array; 6. a horn-shaped joint; 7. a laval tube; 8. a telescoping mast; 9. a daughter board; 9-A, unfolding a solar folding sailboard before unfolding; and 9-B, unfolding the solar folding sailboard.

Detailed Description

The invention is further described below with reference to the accompanying drawings.

Referring to fig. 1 to 6, the invention includes a spacecraft main body 1, shock wave injection hole surfaces are symmetrically arranged on the front and back surfaces of the spacecraft main body 1, a compressed gas cabin 4 is arranged inside the spacecraft main body 1, the shock wave injection hole surfaces include a porous panel 2, a horn-shaped joint 6 is arranged below the porous panel 2, the horn-shaped joint 6 is connected with the compressed gas cabin 4 through a laval pipe 7, a hatch valve 3 is arranged between the compressed gas cabin 4 and the laval pipe 7, the porous panel 2 is used for expanding the shock wave injection range, and the laval pipe 7 is used for generating supersonic air flow.

Two solar sailboards 5 are symmetrically arranged on two sides of a spacecraft main body 1, the solar sailboards 5 are fixed on the spacecraft main body 1 through a telescopic support rod 8, two sub-boards 9 are arranged on the top of the telescopic support rod 8, the two sub-boards 9 of the solar folding sailboard 9-A are overlapped with the top of the telescopic support rod 8 before unfolding, the two sub-boards 9 of the solar folding sailboard 9-B are spliced into a circle in a rotating mode after unfolding, and the two sub-boards 9 can rotate 360 degrees around the axis of the telescopic support rod 8.

The spacecraft main body 1 comprises an attitude and orbit control system, a power supply system and a payload required by on-orbit operation, and the spacecraft main body 1 is in a hexagonal prism shape.

The working process of the invention is as follows: when emergency avoidance is needed, according to the position of fragments, a shock wave emitting device at the front part or the rear part of the spacecraft main body 1 is selected, a hatch valve 3 is opened, compressed gas is accelerated from a compressed gas cabin 4 through a Laval pipe 7 to form high-speed shock waves, and the high-speed shock waves are ejected through a horn-shaped joint 6 and a porous panel 2.

The invention takes the space debris moving at high speed as a target, the shape of the space debris is not required, the size of the space debris cannot be ignored, and the moving speed of the space debris makes the spacecraft difficult to capture and difficult to avoid. The invention can make the spacecraft avoid emergently when being threatened by space debris, the shock wave generating device in the main body 1 of the spacecraft generates shock waves to realize the deceleration of the debris and the reverberant acceleration of the spacecraft, and the porous panel 2 enlarges the shock wave action range and has stronger containment to the size and the shape of the debris.

Claims

1. A shock wave-based space debris emergency avoidance system is characterized by comprising a spacecraft main body (1), shock wave jet hole surfaces are symmetrically arranged on the front surface and the rear surface of the spacecraft main body (1), a compressed gas cabin (4) is arranged inside the spacecraft main body (1), the shock wave jet hole surfaces comprise a porous panel (2), a horn-shaped joint (6) is arranged below the porous panel (2), and the horn-shaped joint (6) is connected with the compressed gas cabin (4) through a Laval pipe (7);

two solar sailboards (5) are symmetrically arranged on two sides of the spacecraft main body (1);

the solar sailboard (5) is fixed on the spacecraft main body (1) through a telescopic support rod (8), and two sub-boards (9) are arranged at the top of the telescopic support rod (8);

the two sub-boards (9) of the solar folding sailboard (9-A) are overlapped with the top of the telescopic support rod (8) before being unfolded, the two sub-boards (9) of the solar folding sailboard (9-B) are spliced into a circle in a rotating mode after being unfolded, and the two sub-boards (9) can rotate 360 degrees around the axis of the telescopic support rod (8).

2. A shock wave based space debris emergency avoidance system according to claim 1, wherein the spacecraft body (1) comprises attitude and orbit control systems, power supply systems and payload required for in-orbit operation.

3. The shock wave-based space debris emergency avoidance system of claim 1, wherein a hatch valve (3) is arranged between the compressed gas cabin (4) and the Laval pipe (7).

4. Shock wave based space debris emergency avoidance system according to claim 1, characterized in that the spacecraft body (1) is hexagonal prism shaped.