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An anti-heat insulation/protection integrated space debris protection structure and its application

A technology for protecting structures and space debris, applied in spaceflight vehicle heat protection devices, aerospace safety/emergency devices, etc., can solve problems such as limiting protection performance, increasing the burden on aircraft, and poor heat resistance

Active Publication Date: 2017-12-22
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the heat insulation material uses a multi-layer (N≤30) heat insulation material, which has a large mass and volume, which will increase the burden on the aircraft
In addition, the heat insulation material uses Kevlar fabric as a reinforcement material. Due to the poor heat resistance of Kevlar fabric, its protective performance at high temperatures is limited.

Method used

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  • An anti-heat insulation/protection integrated space debris protection structure and its application
  • An anti-heat insulation/protection integrated space debris protection structure and its application
  • An anti-heat insulation/protection integrated space debris protection structure and its application

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0034] like figure 1 As shown, an anti-heat insulation / protection integrated space debris protection structure is formed by stacking a front plate 2 and a filling layer 4; the filling layer 4 is composed of three layers of SiC fiber fabric 4-1 and three layers of alumina ceramics fiber reinforced SiO 2 The nano-airgel plates 4-2 are stacked alternately in pairs, the thickness of the filling layer 4 is 60mm, and the SiC fiber fabric 4-1 is close to the front plate 2.

[0035] In order to facilitate the performance test, a back plate 5 is installed on the other side of the front plate 2 on the filling layer 4, and the distance between the front plate 2 and the back plate 5 is 100 mm, and the filling layer 4 and the front plate 2 The distance from the rear plate 5 is 20 mm.

[0036] like figure 1 As shown, the assembly method of the protective structure test structure described in this embodiment is as follows: first, the front plate 2, the filling layer 4 (SiC fiber fabric 4-...

Embodiment 2

[0042] The difference between the anti-heat insulation / protection integrated space debris protection structure of this embodiment and embodiment 1 is that SiC fiber fabric 4-1 and alumina ceramic fiber reinforced SiO 2 The number of layers of the nano-airgel board 4-2 is five layers, and the thickness of the filling layer 4 is 100 mm; the distance between the filling layer 4 and the front plate 2 and the rear plate 5 is 0 mm.

[0043] The difference between the assembling method of the protection structure described in this embodiment and that of Embodiment 1 is only that the filling layer 4 is not separated from the front plate 2 and the rear plate 5 by a sleeve 3 with a diameter greater than that of the drilled hole, and the screws on the screw rod 1 are screwed. Fasten with nuts and you're done.

[0044] Under the conditions of impact velocity v≈6.8km / s and projectile diameter d=8.02mm, the anti-heat insulation / protection integrated space debris protection structure was use...

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Abstract

An anti-heat insulation / protection integrated space debris protection structure and its application, the protection structure is formed by stacking a front plate and a filling layer; the filling layer is formed of SiC fiber fabric and ceramic fiber reinforced SiO2 nano airgel plate Pairs are stacked alternately, one side of the SiC fiber fabric is close to the front plate. The protection structure is applied to the heat insulation and debris protection of the spacecraft, and the protection performance is significantly better than that of the Nextel / Kevlar filled protection structure under the same surface density. There is no breakdown damage, good heat resistance performance, and thermal conductivity ≤ 0.023 W / m·K; the quality of the filling layer of the protective structure is ≤1.08 kg. Compared with the traditional filled Whipple protective structure, with the same quality, it can play the role of heat insulation / protection integration at a higher temperature Function; By changing the thickness of the filling layer, different requirements for heat protection, debris protection and weight reduction can be met, and the designability is strong.

Description

technical field [0001] The invention relates to a space debris protection structure and its application, in particular to an anti-heat insulation / protection integrated space debris protection structure and its application. Background technique [0002] After the returnable spacecraft completes the orbital mission, it will use the return capsule to carry the payload or the astronauts to return to the ground. When the return capsule passes through the atmosphere at a very high speed, due to its compression of the air in front and friction with the surrounding air, part of the kinetic energy will be converted into heat energy of the air to heat the return capsule. Therefore, the shell of the return capsule will be installed Anti-heat insulation materials to protect the safety of astronauts or the normal work of equipment. In addition, the anti-heat insulation structure can also play the role of maintaining the shape of the spacecraft, bearing relevant loads, and maintaining th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/52B64G1/58
Inventor 王应德韩成冯坚姜勇刚
Owner NAT UNIV OF DEFENSE TECH
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