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本文分析了以火箭和火箭-冲压发动机为动力的垂直或水平起飞、水平降落、有翼单级入轨运载器的几种设计方案,并对这几种方案的性能和成本做了比较。为此,将原来的有效载荷和使用要求与航天飞机相似的液氢液氧火箭运载器做了一些改动,以便与氢燃料冲压发动机相配合。使用吸气式发动机使燃料消耗量明显地减小,但是重量却增加了,因为增加了冲压发动机,同时为了承受更大的气动载荷和热载荷,一些结构也需要加强。分析结果表明,在起飞重量相同的条件下,使用吸气式发动机的飞行器,整个系统的成本要比火箭系统高百分之十九。但是,由于有效载荷增加,使用吸气式发动机其单位运输成本仍然低于火箭系统。
In this paper, several designs of vertical or horizontal take-off, horizontal landing and single-stage orbited rail-bound carriers driven by rocket and rocket-ramjet engines are analyzed. The performances and costs of these schemes are compared. For this purpose, some modifications have been made to the original payload and payload requirements of a liquid hydrogen-oxygen liquid oxygen rocket carrier similar to a space shuttle for compatibility with a hydrogen-fuel ramjet engine. The use of aspirated engines leads to a significant reduction in fuel consumption but an increase in weight due to increased ramjet engines and some structures need to be strengthened in order to withstand greater aerodynamic and thermal loads. The results of the analysis show that using an aspirated aircraft at the same take-off weight would cost the entire system nineteen percent more than the rocket system. However, with the increase in payload, the unit cost of transporting a suction-type engine is still lower than that of a rocket system.