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从理论上探讨了单室双推力固体火箭发动机中影响其两级推力的主要因素。建立了导弹/发动机一体化设计的优化模型,对一种推进剂实现双推力,双燃速推进剂实现双推力两种情况分别进行了计算和分析。求出了使导弹射程达到最大,又能够在设计中实现的最佳推力方案。
The main factors affecting the two-stage thrust in single-chamber double-thrust solid rocket motor are theoretically discussed. The optimization model of missile / engine integrated design was established. The calculation and analysis were carried out for two situations: one for propellant and the other for twin thrust. The best thrust scheme that maximizes the range of a missile and achieves it in the design is obtained.