Defining Ablative Thermal Protection System Margins for Planetary Entry Vehicles
Defining Ablative Thermal Protection System Margins for Planetary Entry Vehicles
复制标题
定义行星进入飞行器的烧蚀热保护系统裕度
DOI：
10.2514/6.2011-3757
复制
发表时间：
2011
影响因子：
2.6
通讯作者：
Lockheed Martin
中科院分区：
文献类型：
--
作者：
I. Cozmuta;M. Wright;B. Laub;W. Willcockson;Lockheed Martin
经过50多年的航天飞行，计算进入航天器的热防护系统的必要裕度仍然是一个主要由工程判断决定的临时（战术意义上的）过程。在过去几年中，美国航天局通过将统计得出的因素应用于设计的各个要素，探索了一种更有条理的技术。本文首先回顾了从阿波罗到火星探测漫游者的几次NASA任务的保证金应用历史，然后讨论了一种新的概率保证金过程，该过程是为火星科学实验室和猎户座计划开发的。该过程非常依赖数据，需要通过精心制作和执行的测试程序进行验证，包括地面和飞行数据。这个概率过程的应用的例子给出了火星探路者，星尘，和火星科学实验室。这一进程仍在进行中，本文件讨论了其中的一些关键要素，沿着讨论了改进总体方法的可能途径。最终的目标是在TPS热裕度过程和相应的对整体热屏蔽可靠性的贡献之间建立严格的联系。
After over 50 years of spaceflight, the calculation of the necessary margin on the thermal protection system of an entering spacecraft remains a largely ad-hoc (in a tactical sense) process governed by engineering judgment. Over the past several years, NASA has explored a more methodical technique through the application of statistically derived factors to various elements of the design. The current paper first reviews the history of margin application for several prior NASA missions ranging from Apollo to the Mars Exploration Rovers, then discusses a new probabilistic margin process, which was developed for the Mars Science Laboratory and Orion programs. The process is very data-dependent, and requires validation via a carefully crafted and executed test program including both ground and flight data. Examples of the application of this probabilistic process are given for Mars Pathfinder, Stardust, and the Mars Science Laboratory. This process is still a work in progress, and the paper discusses some of the key elements of it, along with potential ways by which the overall methodology could be improved. The eventual goal is the development of a rigorous link between TPS thermal margin process and the corresponding contribution to the overall heatshield reliability.