跨大气层飞行器爬升段飞行仿真研究  

Conceptual Design of Flight Control Law for Climbing Phase

作　　者：周欲晓[1] 张子彦[2] 明晓[3] 

机构地区：[1]南京航空航天大学无人机研究院,江苏南京210016 [2]成都飞机设计研究所,四川成都610041 [3]南京航空航天大学航空宇航学院,江苏南京210016

出　　处：《计算机仿真》2006年第10期23-26,共4页Computer Simulation

摘　　要：跨大气层飞行器在爬升过程中飞行参数及质量特性变化剧烈,因而飞行器的操纵稳定特性也相应迅速变化。各种干扰因素的影响对飞行控制系统设计起着不可忽视的作用。对此进行了分析研究,仿真结果表明分离时刻载机与飞行器之间的干扰气流影响飞行安全;点火时机合理地选择、缓和拉起爬升动作对爬升初始阶段飞行参数稳定合理地变化也很重要;无动力爬升段结束后姿态控制对稳定飞行器横侧特性起着关键的作用。爬升过程中出现发动机停车状况,只要控制合理,也可以将飞行器安全着陆。During the climbing phase, the flight parameters and weight of Trans - Aerosphere Vehicle（TAV） change so much, thus the vehicle＇s controllability and stability vary very quickly. The disturbing factors play important roles on flight control system design. Simulating results show that the disturbing airflow between the carrier and vehicle affect the safety of TAV. Reasonable igniting time selection and slow pulling - up maneuver are also important to flight parameters of preliminary phase. The attitude angle control is the key for stabilizing lateral parameters of vehicl after the power - off climbing. If the engine curts off during the climbing phase, the TAV would land safely so long as the control is reasonable.

关 键 词：跨大气层飞行器 爬升段 飞行仿真 干扰因素分析 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]