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未来大推力氢氧发动机方案初步探讨

Missiles and Space Vehicles(2012)

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Abstract
针对未来运载器对动力系统的需求,提出中国下一代大推力氢氧发动机的发展设想,对发动机系统方案、性能参数、动态特性和可靠性等方面进行了初步设计和分析比较。结果表明,所选择的发动机系统方案的可靠性、经济性和系统性能符合未来大推力氢氧发动机的技术发展趋势。
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Key words
Heavy-lift launch vehic1e,LOX/LH2 rocket engine,System design
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