使用固体火箭发动机的快速机动卫星质量矩控制研究  

Study on Satellite Mass Moment Control for Fast Orbit Maneuver Using Solid Rocket Motor

作　　者：陆正亮 张翔[1] 于永军 莫乾坤[1] 廖文和[1] 

机构地区：[1]南京理工大学机械工程学院,江苏南京210094

出　　处：《推进技术》2017年第5期1165-1172,共8页Journal of Propulsion Technology

基　　金：江苏省高校优势学科建设项目(高端装备与微纳器件)

摘　　要：针对使用固体火箭发动机进行卫星快速变轨机动时的姿态翻转问题,提出使用二维质量矩控制技术予以解决。首先分析了喷气阻尼力矩对三轴稳定卫星姿态的影响,随后建立了考虑推进剂燃烧过程的完整动力学模型,并从通道耦合以及扰动力矩角度对模型特性进行了分析;最后利用仿真手段对质量矩控制卫星姿态的可行性进行了仿真分析,同时考察了发动机不同装药形式以及外形尺寸对控制系统操纵性能的影响。结果表明:二维质量矩控制卫星姿态是切实可行的,且短粗型的发动机结构对控制系统设计更加有利。A two-dimensional mass moment control technique was proposed,on the issue of attitude turning when a satellite is carrying out a fast orbit maneuver using solid rocket motor. First jet-damping torque on the three-axis stabilized satellite attitude was analyzed. Next considering the burning process of propellant, the whole dynamic equations were derived,and deeply analyzed from the perspective of channel coupling and disturbance torques. At last the validity of mass moment control technique was verified,and at the same time the impacts on steering performance were assessed with different charge forms and outlines of solid rocket motor using simulations. Results indicate that it is feasible for attitude control using two-dimensional mass moment control technique,and a stubby outline of the motor structure has advantageous for system design.

关 键 词：固体火箭发动机 快速机动 质量矩 姿态控制 

分 类 号：V448.222[航空宇航科学与技术—飞行器设计]