一种弱气动弹/箭滚转控制方法  

A Roll Control Method for Missile and Rocket of Weak Aerodynamic Force

作　　者：赵红刚 潘涛 陈华兵 Zhao Honggang;Pan Tao;Chen Huabing(National Key Laboratory of Combustion, Flow and Thermo-structure, the 41st Institute of the Academy of China Aerospace Science and Technology Corporation, Xi＇ an 710025, China)

机构地区：[1]航天科技集团公司第四研究院第41研究所、燃烧、流动和热结构国家级重点实验室,西安710025

出　　处：《战术导弹技术》2018年第3期74-77,共4页Tactical Missile Technology

摘　　要：针对弱气动弹/箭滚转通道采用直接力控制执行机构结构复杂、成本高、可靠性低等缺点,基于动量矩定理提出了一种可用于低速飞行,稀薄大气环境弱气动弹/箭的滚转控制方法,通过理论推导和控制器设计,分析了干扰力矩与旋翼舵机最终转速的关系以及影响控制系统响应速度的因素,最后给出了合理的验证试验方案。试验结果表明,依靠旋翼的主动旋转产生反向的控制力矩来进行滚转控制的方案可行,稳态控制精度优于0.5°,能够满足此类飞行器对滚转控制的需求。The missile and rocket of weak aerodynamic using direct force control have some disadvantages such as complex structure,high cost and low reliability. A control method of low-speed,thin atmosphere environment,weak aerodynamic force missile and rocket was proposed based on theorem of kinetic energy. The relation between disturbance moment and the final rotational speed of rotor,and the factors influencing the response speed of the control system were analyzed through the theoretical derivation and controller design,and a reasonable verification experiment scheme was given. The results showed that the scheme of the roll control generated by the reverse rotation of the rotor was feasible. The steady control precision was better than 0. 5 °,which could meet the requirements of the roll control of the aircraft.

关 键 词：弱气动 动量矩定理 滚转控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]