助推-滑行式燃料最优真空飞行轨迹的设计方法  

A method of multi-burn propellant-optimal vacuum flight trajectory design

作　　者：王炀[1] 唐硕[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《飞行力学》2011年第5期69-72,共4页Flight Dynamics

摘　　要：建立了飞行器助推-滑行式燃料最优真空飞行轨迹的最优控制模型,给出了一种更为简单、直观的内点约束条件和横截条件的推导方法,讨论了高效且更为稳定的数值计算方法,提出了两种应用模式,通过与连续推力式和脉冲式飞行方案的比较,说明这种设计方法在节省燃料方面具有优势。This paper develops the optimal control formulation for multi-burn propellant-optimal vacuum flight trajectory.An alternative simple method for handling the inner constraints and transversality conditions has been developed.A more effective and stable numerical method has been employed to solve the problem.Two typical applications have been given to validate the superiority of multi-burn flight in propellant assumption compared with single-burn and impulsive flight.

关 键 词：助推-滑行 最优控制 轨道转移 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]