Thermal insulation/protection integrated space debris protection structure and application thereof

A technology for protective structure and space debris, which is applied in the directions of aerospace vehicle heat protection device, aerospace safety/emergency device, etc., and can solve the problems of increasing aircraft burden, large mass and volume, and poor heat resistance.

Active Publication Date: 2015-12-02
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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  • Thermal insulation/protection integrated space debris protection structure and application thereof
  • Thermal insulation/protection integrated space debris protection structure and application thereof
  • Thermal insulation/protection integrated space debris protection structure and application thereof

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, the distance between the front plate 2 and the back plate 5 is 100 mm, and the filling layer 4 is connected to the front plate 2 and the back plate 5. The distances between the back plates 5 are all 20mm.

[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, t...

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 plate 4-2 is five, and the thickness of the filling layer 4 is 100mm; the distance between the filling layer 4 and the front plate 2 and the rear plate 5 is 0mm.

[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 used to cond...

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PUM

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Abstract

The invention discloses a thermal insulation / protection integrated space debris protection structure and an application thereof. The protection structure is formed by stacking a front plate and a filled layer, wherein the filled layer is formed by alternately stacking SiC fibre fabrics and ceramic fibre-reinforced SiO2 nanometre aerogel plates in pairs, and one side of each SiC fibre fabric is close to the front plate. The protection structure is applied to thermal insulation and debris protection for a spacecraft, the protection performance is obviously superior to the protection performance of a Nextel / Kevlar filled protection structure under the same surface density, puncture damages are avoided, the thermal insulation performance is good, and the thermal conductivity is not greater than 0.023W / m.K; the mass of the filled layer of the protection structure is not greater than 1.08kg, and the thermal insulation / protection integrated effect can be acted at a higher temperature in case of an equivalent mass compared with the traditional filled Whipple protection structure; and the different requirements of thermal insulation, debris protection and weight reduction can be met by changing the thickness of the filled layer, and the designability is high.

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 Applications(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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