亚轨道飞行器进场着陆段控制方法研究  

Study on Auto-landing Control Method for Suborbital Launch Vehicle

作　　者：王文星[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：《计算机仿真》2010年第3期35-38,共4页Computer Simulation

摘　　要：研究轨道系统在常用的飞行控制方法的基础上,进一步分析了亚轨道飞行器着陆段飞行的特点,为实现精确着陆,将进场着陆段分为纵向和侧向两个相互独立的运动来分别予以分析,并以内外回路的设计方法给出相应的控制规律,以X-34为模型,制定相应的控制策略,保证着陆时飞行器精确跟踪轨迹线。仿真结果证实方法可以对亚轨道飞行器进场着陆段进行有效的跟踪控制。大量仿真试验表明控制规律对于进场着陆是切实可行的。The auto- landing phase characteristics of Suborbital Reusable Launch Vehicle （SRLV） are analyzed in this paper based on the conventional flight vehicle method. During the research of auto - landing, the motion of SRLV is considered independently on the vertical and horizontal direction. The control law is also planned in the way of inner/outer loop. With the referenced model X - 34, the control strategy is designed to assure that the SRLV can track the planned trajectory. Conclusion is that this method is feasible and it is effective for SRLV＇ s tracking control during its auto-landing.

关 键 词：亚轨道飞行器 进场着陆段 内外回路控制 风干扰 大气紊流 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]