空天飞行器跨大气层再入建模及姿态控制

为满足空天飞行器ASV(aerospace vehicle)再入轨迹优化、姿态控制等问题的需要,研究了ASV再入跨大气层飞行时的数学模型。所建数学模型所涉及的气动力和力矩系数是迎角、马赫数及控制舵面偏角的函数;反作用控制系统RCS(reaction contrlsystem)推进器属于开关型的,控制量可近似为常值开关型的量。考虑ASV在空气稀薄、气动舵面低效或失效且推力系统关机不能提供推力矢量的情况,设计了ASV飞行姿态控制系统,并通过仿真验证了所设计的控制系统在一定条件下的合理性和有效性。

Modeling and flight attitude control for aerospace vehicle's reentry through atmosphere

To meet the demands for tr ajector y o pt imizat ion, at t itude cont rol and so o n of ASV ( aerospace vehicles) and the atmospher ic reent ry modeling o f reent ry through atmosphere w ere researched. Aerodynamic for ce and moment coef ficient s w ere presented as funct io ns of the attack angle, the Mach number and the cont rol surface def lect ions. The thruster of react ion cont ro l system ( RCS) w as of sw itch type and the co nt rol value w as an approx imate sw itching constant . Considering the air scarcity , the decreased eff iciency and the disabled thrust vector w ith the energy sy stem turned of f , the flig ht at t itude cont rol system for ASV was designed to solve this pro blem. The r easonableness and ef fect iveness of the co nt rol system are demo nstr ated by the simulat ion result s