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对三种空间站结构,提出了空间站上推进系统的设计方案,为便于比较,设计时必须确定系统的重量、体积和结构。系统的大小主要取决于保证270海里的轨道保持要求。推进系统的规模应在九十年代初期所预计的最坏(长期)大气密度下提供这种功能。假设补充供给的周期是三个月,万一一次补充供给的飞行不得不延期,也应保证三个月的应急贮备。表1列出了满足这种功能的总冲,同时还对三种空间站结构列出了初期工作能力及其发展所要求的相应推进剂需要量。
For the three kinds of space station structures, the design scheme of the propulsion system on the space station is proposed. For the sake of comparison, the weight, volume and structure of the system must be determined during the design. The size of the system depends mainly on the guaranteed orbital holding requirement of 270 nautical miles. The size of the propulsion system should provide this function at the worst (long-term) atmospheric densities expected in the early 1990’s. Assuming a three-month period of replenishment, in the unlikely event of a replenishment flight having to be postponed, a three-month emergency reserve should also be guaranteed. Table 1 shows the total impulse that meets this function. It also lists the initial capacity of the three space station structures and the corresponding propellant requirements for their development.