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A solar wing aerodynamic thermal protection device

A protective device and aerodynamic heat technology, which are applied in aerospace vehicle heat protection devices, aerospace safety/emergency devices, aerospace vehicle power supply systems, etc., can solve the problem of the long flight distance of deep space probes and the limitation of the total weight of the probes, etc. problem, to achieve the effect of good high temperature resistance and high infrared emissivity

Active Publication Date: 2014-10-08
BEIJING INST OF SPACECRAFT SYST ENG
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The flying distance of the deep space probe is so long that the total weight of the probe is strictly limited

Method used

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  • A solar wing aerodynamic thermal protection device
  • A solar wing aerodynamic thermal protection device
  • A solar wing aerodynamic thermal protection device

Examples

Experimental program
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Effect test

Embodiment

[0033] Such as figure 2 As shown, a solar wing aerodynamic thermal protection device, the aerodynamic thermal protection device includes a base film 9, a spacer layer 10, a surface film 7, a subsurface film 8 from bottom to top, and also includes peripheral equipment pins 3 and solar wing pressure Tight point embedded parts 6; base film 9, spacer layer 10, surface film 7, and subsurface film 8 are fixed by sewing line 11, and surface film 7 is flanged to the lower surface of the pneumatic thermal protection device, and The bottom film 9 is flanged to the upper surface of the aerodynamic heat protection device; the aerodynamic heat protection device is provided with a pin hole and a penetration hole for the embedded part of the pressing point of the solar wing.

[0034] Wherein, the thickness of the bottom film 9 , the surface film 7 and the subsurface film 8 are all 50 μm, and the thickness of the spacer layer 10 is 100 μm.

[0035] The material of the bottom film 9 is polyi...

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Abstract

The invention discloses a solar wing pneumatic thermal protection device, which belongs to the technical field of spacecraft thermal control, and comprises a bottom film, a spacer layer, a surface layer surface film and a secondary surface layer surface film from bottom to top, and is fixed through sewing threads. The solar wing pneumatic thermal protection device is provided with a pin hole and a solar wing compaction point embedded part through hole. The invention further discloses a solar wing pneumatic thermal protection method, wherein the solar wing pneumatic thermal protection device is arranged on the back surface of a solar wing, and the top portion of a pin is provided with a pressing plate after the pin passes through from a pin hole which is obligated on the solar wing pneumatic thermal protection device, thereby preventing the solar wing pneumatic thermal protection device from falling off from the pin. Relative to a traditional mode adopting a naked solar wing, the solar wing pneumatic thermal protection device can space pneumatic heat in a certain degree during the pneumatic deceleration process, thereby leading the temperature of a solar wing to be kept in a tolerable range.

Description

technical field [0001] The invention relates to an aerodynamic thermal protection device for a solar wing, in particular to an aerodynamic thermal protection device for a solar wing during the aerodynamic deceleration process of a deep space probe, and belongs to the technical field of spacecraft thermal control. Background technique [0002] In order to explore the unknown areas of the universe, human beings launch deep space probes to the space beyond the earth, including probes for orbiting and landing detection of various planets. The flying distance of deep space probes is so long that the total weight of the probes is strictly limited. The probe must not only ensure sufficient load weight to achieve scientific detection purposes, but also carry sufficient propellant to achieve orbital maneuvers such as probe attitude maintenance and orbit capture. In the case of limited rocket carrying capacity, when detecting planets with atmospheres, such as Mars and Venus, the aero...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/58B64G1/44
Inventor 苏生向艳超宋馨马巨印斯东波陈阳
Owner BEIJING INST OF SPACECRAFT SYST ENG
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