亚轨道飞行器着陆段控制系统研究

Research into Control System for Landing Phase of Suborbital Vehicle

亚轨道飞行器的着陆轨迹分四段给出。根据航迹倾角的变化律及动压变化得出迎角的变化律,并以此作为制导律。控制系统的纵向系统采用比例积分控制的自动驾驶仪,通过操纵升降舵控制迎角变化实现。侧向控制系统通过操纵方向舵和副翼来确保系统稳定。最后,在Matlab/Simulink中对亚轨道飞行器控制系统进行了系统仿真。仿真结果表明,该系统可以满足亚轨道飞行器进场着陆段的要求,具有良好的控制效果。

The trajectory of landing phase of a suborbital vehicle is divided to four phases. The guidance system can be explained by the change rules of attack of angle which can be examined from flight path angle changes and dynamic pressure. The control system is devoted to lengthways and transverse controls. The lengthways control system is a proportional and integral system. Attack angle control rules are manipulated by elevator. Rudder and aileron are controlled to ensure the stability of transverse control system. The control system for landing phase of the suborbital vehicle is simulated in the Simulink tool box of Matlab.