Evaluation of high-temperature multilayer insulation for inflatable ballute

被引：2

作者：

Kustas, FM

Rawal, SP

Willcockson, WH

Edquist, CT

Thornton, JM

Sandy, C

机构：

[1] Lockheed Martin Space Syst Co, Denver, CO 80201 USA

[2] ILC Dover Inc, Frederica, DE 19934 USA

来源：

JOURNAL OF SPACECRAFT AND ROCKETS | 2001年 / 38卷 / 04期

关键词：

D O I：

10.2514/2.3728

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

A high temperature-multilayer insulation (HT-MLI) thermal protection system (TPS) was designed for an inflatable ballute for spacecraft deceleration. The system was developed using analytical modelling and was fabricated for testing in a plasma-jet environment. The TPS consisted of ceramic, carbon fabric, metal foil, and metallized Kapton layers. Plasma-jet testing of a fabricated test article was performed to measure induced temperatures for comparison with analytical predictions. The measured temperature for the bladder was found to be lower than the predicetd bladder temperature.

引用

页码：630 / 631

页数：2

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