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对未来 H-1运载火箭第三级采用低温推进系统进行了可行性研究。虽然LO_2/LH_2的第三级质量比率比现在的固体推进剂第三级小,但比推力提高50%的结果能使非常有意义的有效载荷提高。推荐的两个新推进系统的基本结构方案是:一个挤压式供给系统和二个泵式供给系统。第一个挤压式系统能在441s 比推力时提供700kg 的推力,且具有再起动能力。第二个泵式输送系统根据膨胀循环原理工作。小型涡轮泵有90000r/min 的轴转速,供给在比推力为471s 时能产生1t 推力的推力室所用推进剂。提出的第三个系统仍然是一个泵式供给系统方案,它采用独特的膨胀排放循环,且在比推力为470s 和涡轮泵转速为80000r/min 时能产生1t 的推力。发动机试验结果预示了各个推进系统方案性能的可行性。
Feasibility study on the third stage of H-1 launch vehicle adopting low-temperature propulsion system. Although the third mass ratio of LO_2 / LH_2 is smaller than the current third level of solid propellant, a 50% increase in thrust results in a very significant payload increase. The basic structural solution of the two proposed new propulsion systems is a squeeze supply system and two pump supply systems. The first squeeze system provides 700kg of thrust at 441s thrust and has a restart capability. The second pumping system operates on the principle of expansion cycles. The small turbocharger has a shaft speed of 90000 rpm and supplies the propellant used in the thrust chamber, which produces 1t of thrust at a thrust of 471s. The third proposed system remains a pump supply system with a unique expansion cycle that produces a 1t thrust at a thrust of 470s and a turbo pump speed of 80000rpm. Engine test results indicate the feasibility of each propulsion system program performance.