Preliminary Thermal-Mechanical Sizing of a Metallic Thermal Protection System
Preliminary Thermal-Mechanical Sizing of a Metallic Thermal Protection System
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DOI：
10.2514/1.9174
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发表时间：
2004
影响因子：
1.6
通讯作者：
C. Poteet;H. Abu-Khajeel;S. Hsu
中科院分区：
文献类型：
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作者：
C. Poteet;H. Abu-Khajeel;S. Hsu
对NASA兰利研究中心开发的最新金属热防护系统进行了热分析、结构分析、尺寸确定和敏感性研究。定义的过程可用于确定适当的材料和大致厚度，并且是初始热保护系统重量估计的基础。金属热防护系统是降低可重复使用运载火箭成本的关键技术，与其他系统相比，它具有更高的耐用性和有竞争力的重量。金属热防护系统的精确尺寸需要结合热分析和结构分析。初步的灵敏度研究进行了瞬态一维有限元热分析，以确定各种设计和分析参数对热保护系统重量的影响。热分析模型结合热防护系统夹层板外表面的静态挠度和失效模式分析，以获得在一个代表性的可重复使用运载器的迎风中心线上的三个飞行器站的最小重量配置。耦合性质的分析需要一个迭代的分析过程，这是描述。从敏感性分析的结果报告，沿着与初步设计在三个汽车站考虑。
A process is developed to perform thermal and structural analysis and sizing and to perform sensitivity studies on the latest metallic thermal protection system developed at NASA Langley Research Center. The process defined can be used to determine appropriate materials and approximate thicknesses and is the basis for initial thermal protection system weight estimates. Metallic thermal protection systems are a key technology for reducing the cost of reusable launch vehicles, offering the combination of increased durability and competitive weights when compared to other Systems. Accurate sizing of metallic thermal protection systems requires combined thermal and structural analysis. Initial sensitivity studies were conducted using transient one-dimensional finite element thermal analysis to determine the influence of various design and analysis parameters on thermal protection system weight. The thermal analysis model was then used in combination with static deflection and failure mode analysis of the thermal protection system sandwich panel outer surface to obtain minimum weight configurations at three vehicle stations on the windward centerline of a representative reusable launch vehicle. The coupled nature of the analysis requires an iterative analysis process, which is described. Findings from the sensitivity analysis are reported, along with preliminary designs at the three vehicle stations considered.