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早期的航天飞机轨道器的研究结果确认,某些结构件,如采用先进复合材料,将大大减轻轨道器的重量并提高它的性能。航天飞机的基本设计包含了许多的这类结构件,如石墨环氧(Gr/Ep)的有效载荷仓门。对其他构件,如垂直尾翼、升降副翼及后身部襟翼等,也开展了先进的高温可用于600℉结构的石墨/聚酰亚胺(Gr/Pi)复合材料的应用研究。Gr/Pi 的结构与基本设计采用的铝结构加防热系统(TPS)相比,其重量总共可以减轻20～30%。本文提出的先进结构及 TPS设计方案将给轨道器带来相应的效益。关于洛克威尔公司航天飞机轨道器分公司独立进行的以及按 NASA 合同开展的 Celion/LARC-160研制工作的技术状况将分下列几部分予以陈述:工艺开发、无损评价技术(NDE)和异常效应、材料性能及疲劳效应、Gr/Pi 身部襟翼段的设计、分析、制造及试验、修补工艺以及短石墨纤维模压件的研制。
The findings of earlier space shuttle orbiters confirm that certain structural components, such as the use of advanced composite materials, will greatly reduce the weight of the orbiter and improve its performance. The basic design of the space shuttle contains many of these structural elements, such as the graphite epoxy (Gr / Ep) payload door. For other components, such as vertical tail, lift aileron and back body flaps, advanced application of high temperature graphite / polyimide (GR / Pi) composites for 600 ℉ structures was also carried out. Gr / Pi structure and the basic design of the aluminum structure with anti-heat system (TPS) compared to the total weight can be reduced by 20 to 30%. The advanced structure and TPS design scheme proposed in this paper will bring corresponding benefits to the orbiter. The technical status of the Celion / LARC-160 development work independently and as per the NASA contract at Rockwell Aerospace Orbiter Company will be described in terms of process development, NDE and anomalous effects , Material properties and fatigue effects, design, analysis, manufacture and testing of Gr / Pi body flap sections, repair processes, and development of short graphite fiber molded parts.