CN210853002U

CN210853002U - Buffer box for spacecraft separation device

Info

Publication number: CN210853002U
Application number: CN201921880838.9U
Authority: CN
Inventors: 王志勇; 唐占文; 张鹏; 刘千; 刘含洋; 金�一; 丁常方; 王非; 李超
Original assignee: Beijing Mechanical And Electrical Engineering General Design Department; Tianjin Aisida New Material Technology Co ltd
Current assignee: Beijing Mechanical And Electrical Engineering General Design Department; Tianjin Aisida New Material Technology Co ltd
Priority date: 2019-11-04
Filing date: 2019-11-04
Publication date: 2020-06-26
Anticipated expiration: 2029-11-04

Abstract

An embodiment of the utility model provides a cushion box for spacecraft separator, include: the buffer box body is provided with a hole for the connecting piece to pass through, the inside of the buffer box body is provided with an accommodating space, and the bottom of the buffer box body is an inclined plane; the buffer block is positioned in the accommodating space, arranged on the inclined plane and fixedly connected with the inclined plane. The utility model discloses a bolt wastes material that produces after the connecting piece separation when the scheme can effectively collect spacecraft separator separation device separation.

Description

Buffer box for spacecraft separation device

Technical Field

The utility model relates to a space flight device technical field especially indicates a buffering box for separator.

Background

In a spacecraft system, a separation system is an important system and plays a role in interstage separation, booster separation, fairing separation, satellite separation and other product separation during the process of the rocket. The explosion bolt is the most widely applied product in the separation system, and has the advantages of simple and reliable structure, but the defect of large separation impact. Therefore, how to reduce the impact of the bolt on the structure of the spacecraft after the explosive bolt is separated and collect the broken two-section bolt product is a problem which must be considered by designers.

The impact load transmission is not reduced, on one hand, the structure of the carrier can be damaged, and on the other hand, the impact overload is too large, so that the electronic equipment in the carrier is damaged and even fails.

Not collecting the two sections of bolts after disconnection would create an excess in the vehicle, with possible serious consequences. Therefore, a shock reduction and bolt waste collection design of the explosive bolt separation method is necessary.

The traditional buffering structure for collecting the bolts after explosion separation is that a metal box directly connected by explosion bolts resists impact load hard, and meanwhile, the metal box is used as a collector for the bolts after separation. The structure has the defects that the weight of the metal box is heavy (the wall thickness of the structure is thick for resisting extremely high impact), the impact load is not reduced, and a control instrument is influenced, and the like.

SUMMERY OF THE UTILITY MODEL

The utility model provides a buffering box for spacecraft separator. Bolt wastes generated after the connecting piece is separated when the spacecraft separating device is separated can be effectively collected.

In order to solve the above technical problem, an embodiment of the present invention provides the following solutions:

a buffer box for a spacecraft separation device, comprising:

the buffer box body is provided with a hole for the connecting piece to pass through, the inside of the buffer box body is provided with an accommodating space, and the bottom of the buffer box body is an inclined plane;

the buffer block is positioned in the accommodating space, arranged on the inclined plane and fixedly connected with the inclined plane.

Optionally, the inclined plane angle of the inclined plane is the same as the inclined plane angle of the buffer block.

Optionally, the inclined plane angle of the inclined plane and the inclined plane angle of the buffer block are both 15 degrees to 35 degrees.

Optionally, the buffer block is an aluminum honeycomb body.

Optionally, the buffer block is bonded to the inclined plane through structural adhesive.

Optionally, the buffer box body is provided with a flange connected with the cabin base body of the spacecraft.

Optionally, the buffer box for the spacecraft separation device further includes: and the opening cover is connected with the buffer box body.

Optionally, the connecting piece is a bolt connected with a cabin base body of the spacecraft.

Optionally, the bolt penetrates through the hole in the buffer box body and then the connecting end in the accommodating space is connected with the nut.

The above technical scheme of the utility model at least include following beneficial effect:

the above technical scheme of the utility model, after the separation of the separator spare of the spacecraft that the connecting piece is connected, as the bolt and the nut separation of connecting piece, the buffer block in this buffer box can effectively reduce explosion bolt explosion impact load, can effectively collect the separation back bolt wastes material, effectively prevents to separate the anti-former connecting hole that rebounds of bolt to have light in weight, energy-absorbing and fall and strike obvious, with low costs, easily make.

Drawings

FIG. 1 is a schematic view of an assembly structure of the buffer box and the collection box of the present invention;

fig. 2 is a schematic view of a buffer block in the buffer box of the present invention;

FIG. 3 is another schematic structural view of the assembly structure of the buffer box and the collecting box of the present invention;

fig. 4 is a schematic diagram of the separation of the bolt and the nut in the assembly structure of the buffer box and the collection box of the present invention.

Detailed Description

Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

As shown in fig. 1 to 4, an embodiment of the present invention provides a buffer box for a spacecraft separation device, including:

the buffer box body 1 is provided with a hole for a connecting piece to pass through, an accommodating space is arranged in the buffer box body 1, and the bottom of the buffer box body 1 is an inclined plane B;

and the buffer block 2 is positioned in the accommodating space, arranged on the inclined plane B and fixedly connected with the inclined plane B. Optionally, the buffer block 2 is bonded to the inclined plane B through structural adhesive.

In this embodiment, the connection is a bolt 3 for connecting the nacelle base of the spacecraft. The bolt 3 passes through the hole on the buffering box body 1 and then is positioned at the connecting end in the accommodating space and is connected with the nut 6. After the separator separation of the spacecraft that the connecting piece is connected, as the bolt 3 and the nut 6 separation of connecting piece, on the buffer block 2 in this buffer box was strikeed to nut 6, buffer block 2 can effectively reduce explosion bolt explosion impact load, can effectively collect the separation back bolt waste, effectively prevent the separation bolt from rebounding original connecting hole.

In an optional embodiment of the present invention, the inclined plane angle of the inclined plane B is the same as the inclined plane angle of the buffer block 2. Preferably, the inclined plane angle of the inclined plane B and the inclined plane angle of the buffer block 2 are both 15 degrees to 35 degrees.

In an alternative embodiment of the present invention, the buffer block 2 is an aluminum honeycomb body, so that the buffer box is light in importance.

In an optional embodiment of the present invention, the buffer box body 1 is provided with a flange connected to the cabin base of the spacecraft.

The utility model discloses an in an optional embodiment, a cushion box for spacecraft separator still includes: and the opening cover is connected with the buffering box body 1, so that the box body is a closed space, and the separated nut 6 can be conveniently and effectively collected into the buffering box body 1.

The working process of the buffer box is described below with reference to fig. 1 to 4:

the buffer box body 1 is arranged on one side of a separating device (cabin) of the spacecraft, the collecting box 5 is arranged on one side of the other cabin of the spacecraft, the two cabins are butted on the surface A, and the connecting piece is a bolt 3. The bolt 3 is fixed in the collecting box 5 through the fixing block 4, when the bolt 3 explodes during working, the bolt 3 can be exploded in the middle of the structure, the nut end 6 can directly fly out, and the two cabin sections of the spacecraft are separated on the surface A (the structure loses bolt restraint). After flying out at a high speed, the nut 6 firstly impacts the buffer block 2, and the buffer block 2 absorbs the kinetic energy of the nut 6 through the plastic deformation of materials and structures, thereby achieving the purposes of energy absorption and impact reduction.

The bottom of the buffer box body 1 is arranged to be an inclined plane, so that when the flying-out kinetic energy of the nut 6 is far greater than the limit of the energy absorption of the buffer block 2, the nut 6 can rebound and cannot return to the original structure connecting hole, and the separation reliability is guaranteed.

Simultaneously, the flap is all installed in buffering box body 1, the 5 outsides of collection box, all forms enclosed construction in inside, collects box 5 and can directly collect bolt 3, the buffering box body 1 after the separation and can collect nut 6 after the separation, effectively protects the safety of equipment such as other electrical apparatus of spacecraft.

The foregoing is a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of improvements and decorations can be made without departing from the principle of the present invention, and these improvements and decorations should also be regarded as the protection scope of the present invention.

Claims

1. A buffer box for a spacecraft separation device, comprising:

the buffer box body (1) is provided with a hole for a connecting piece to pass through, an accommodating space is arranged in the buffer box body (1), and the bottom of the buffer box body (1) is an inclined plane (B);

and the buffer block (2) is positioned in the accommodating space, arranged on the inclined plane (B) and fixedly connected with the inclined plane (B).

2. A buffer magazine for spacecraft separation devices according to claim 1, wherein the ramp angle of the ramp (B) is the same as the ramp angle of the buffer block (2).

3. A buffer magazine for spacecraft separation devices according to claim 2, wherein the ramp angle of the ramp (B) and the ramp angle of the buffer block (2) are both 15 ° to 35 °.

4. The surge tank for spacecraft separation devices according to claim 1, wherein the surge block (2) is an aluminum honeycomb.

5. A buffer magazine for spacecraft separation devices according to claim 1, wherein the buffer block (2) is bonded to the ramp (B) by structural glue.

6. A buffer magazine for spacecraft separation devices according to claim 1, wherein the buffer magazine body (1) has a turn-up for connection to a nacelle base of a spacecraft.

7. A buffer box for a spacecraft separation device according to claim 1, further comprising: and the opening cover is connected with the buffer box body (1).

8. A buffer box for a spacecraft separation device according to claim 1, wherein the connection is a bolt (3) connecting the nacelle base of a spacecraft.

9. The buffer box for spacecraft separation equipment according to claim 8, wherein the bolt (3) passes through a hole on the buffer box body (1) and then the connecting end in the accommodating space is connected with a nut (6).