Ceramic Matrix Composite (CMC) Thermal Protection Systems (TPS) and Hot Structures for Hypersonic Vehicles
Ceramic Matrix Composite (CMC) Thermal Protection Systems (TPS) and Hot Structures for Hypersonic Vehicles
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DOI：
10.2514/6.2008-2682
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发表时间：
2008-04
期刊：
影响因子：
--
通讯作者：
D. Glass
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文献类型：
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作者：
D. Glass
从弹道再入到高超声速巡航飞行器，在地球大气层和非地球大气层内，都需要热防护系统（TPS）和热结构。本文的重点是在地球大气层中的吸气式高超声速飞行器。这包括单级入轨（SSTO），两级入轨（TSTO）加速器，进入太空飞行器和高超音速巡航飞行器。本文将首先简要讨论气动加热和热管理技术，以解决高加热，其次是TPS的火箭发射和吸气式飞行器的概述。提出的论点是，当我们从火箭为基础的车辆到空气呼吸式车辆，我们需要从航天飞机轨道器上使用的隔热飞机的方法，以广泛的TPS和热结构的方法。本文的主要部分将讨论CMC TPS和热结构部件的问题和设计方案，包括前缘、面积TPS和操纵面。将简要讨论某些组件的当前最新技术水平。影响CMC热防护系统和高超声速飞行器热结构使用的两个主要技术挑战是环境耐久性和制造，下面将简要讨论。
Thermal protection systems (TPS) and hot structures are required for a range of hypersonic vehicles ranging from ballistic reentry to hypersonic cruise vehicles, both within Earth's atmosphere and non-Earth atmospheres. The focus of this paper is on air breathing hypersonic vehicles in the Earth's atmosphere. This includes single-stage to orbit (SSTO), two-stage to orbit (TSTO) accelerators, access to space vehicles, and hypersonic cruise vehicles. This paper will start out with a brief discussion of aerodynamic heating and thermal management techniques to address the high heating, followed by an overview of TPS for rocket-launched and air-breathing vehicles. The argument is presented that as we move from rocket-based vehicles to air-breathing vehicles, we need to move away from the insulated airplane approach used on the Space Shuttle Orbiter to a wide range of TPS and hot structure approaches. The primary portion of the paper will discuss issues and design options for CMC TPS and hot structure components, including leading edges, acreage TPS, and control surfaces. The current state-of-the-art will be briefly discussed for some of the components. The two primary technical challenges impacting the use of CMC TPS and hot structures for hypersonic vehicles are environmental durability and fabrication, and will be discussed briefly.