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使神号航天飞机再入大气层的防热系统(TPS)对设计者是个新挑战。和美国的轨道器相比,使神号体积小、横向飞行距离大,相应地使工作温度升高,再入热过程时间延长。因此,防热系统的总重量比美国轨道器的要求更严格。另一方面,自提出轨道器方案以来,研制了许多新材料(即陶瓷复合材料),因而可能会出现更有效的TPS方案。在对使神号TPS系统进行的初步研究中曾考虑了多种可能的方案,其中包括外部被动TPS、热结构、主动TPS等。选择的方案最后缩简为三个基本方案,一些不同的或备用的方案仍在研究中: 1.陶瓷复合材料热结构:用于头部、前缘、尾翼和控制面。 2.外部绝热:陶瓷复合材料瓦表面涂以轻质绝缘层(或以刚性表面绝热层(瓦)作备用方案),用于高温下表面和部分上表面。 3.柔性表面绝热:用于较低温度的上表面。本文介绍了所研究方案的具体内容、优化方法和方案选择标准。
The thermal system (TPS) that makes the space shuttle Rex into the atmosphere is a new challenge for designers. Compared with the orbiter in the United States, the God size is small and the horizontal flight distance is large, correspondingly, the working temperature is increased and the reheating time is prolonged. Therefore, the total weight of the heat-protection system is more stringent than that required by the U.S. Orbital Orbiter. On the other hand, many new materials (ie, ceramic composites) have been developed since the orbital solution was proposed and hence a more efficient TPS scheme may emerge. A number of possible solutions have been considered in a preliminary study of the TPS system, including external passive TPS, thermal structures, active TPS and others. The solution chosen is finally reduced to three basic solutions, some of which are still under study: 1. Ceramic composite thermal structure: for the head, leading edge, tail and control surfaces. 2. External Insulation: The surface of the ceramic composite tile is coated with a lightweight insulation layer (or with a rigid surface insulation (tile) as a backup solution) for the high temperature surface and part of the upper surface. 3. Flexible surface insulation: for the lower temperature of the upper surface. This article describes the specific content of the study program, optimization methods and program selection criteria.