基于运载能力评估的固体运载火箭推力向量控制方案比较  

Comparison of Thrust Vector Control Scheme for Solid Launch Vehicle Based on Launching Capability Evaluation

作　　者：杨希祥[1] 江振宇[1] 张为华 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2010年第1期16-21,共6页Journal of National University of Defense Technology

基　　金：国家部委基金资助项目(2007AAX02503)

摘　　要：从对运载能力影响角度开展固体运载火箭发动机推力向量控制系统比较分析研究。设计了三种采用不同发动机推力向量控制系统的多级固体运载火箭方案,将增广乘子法与共轭方向法相结合,对固体运载火箭上升段弹道进行了优化设计,给出运载能力评估结果。研究表明,起飞质量均为50 000kg,目标轨道均为300km太阳同步轨道时,采用栅格舵和侧喷流作为推力向量控制系统方案,比采用燃气舵和侧喷流作为推力向量控制系统方案,运载能力提高70kg,比各级固体发动机全部采用摆动喷管控制方案,运载能力提高115kg,为固体运载火箭总体方案论证提供理论依据。The thrust vector control schemes for solid launch vehicle were compared from the view of launching capability. Three multiple-stage solid launch vehicle schemes with different thrust vector control systems were designed, the ascent trajectory of launch vehicle was optimized by combining augmented lagrangian method with Powell method, and the evaluation results of launching capability were provided. Research results show that, with the same take-off mass of 50000 kg and object orbit of 300km SSO, the scheme using jet thrusts and grid vane achieved heavier lauching capability, 115 kg bigger than the scheme using vectored nozzle, and 70 kg bigger than the scheme using jet thrusts and jet vane, respectively. All the above can provide theoretic reference for scheme demonstration of solid launch vehicle.

关 键 词：固体运载火箭 推力向量控制方案 运载能力 弹道优化 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] V412