Control of static unstable airframes

查看全文 作　　者：Junfang [1]Fan;Defu [2]Lin;Zhong [1]Su;Qing [1]Li

机构地区：[1]School of Automation, Beijing Information Science and Technology University, Beijing 100101, E R. China;[2]School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, P. R. China

出　　处：《Journal of Systems Engineering and Electronics》索引2010年第21卷第6期,共9页

基　　金：supported by the National Natural Science Foundation of China (60972118);the Funding Project for Academic Human Resources Development in Institutions of Higher Learning under the Jurisdiction of Beijing Municipality (PHR200906131; PHR201006115) 摘　　要：The challenge and control problems of static unstable missiles are presented. The steady-state benefits of static instability are illustrated, while the corresponding control challenge is described both by the characteristic lag of airframe and the increment of necessary control usage. Control limitation led by unstable zero-pole pair is analyzed for preliminary design and evaluation. Linear control strategy is examined wherein two and three loop acceleration autopilots with different control usages are developed using an optimal control approach combined with frequency domain constraint. The weights selection and relation with system performance are detailed. Then the nonlinear backstepping recursive method is detailed to determine how well it is able to follow command and its engineering feasibility. The results show that a static unstable missile is controllable, while the actuator bandwidth is the crucial limited factor. There should be a compromise between overall performance and actuator payment. 关键词：静态控制静不稳定 BACKSTEPPING 机身最优控制方法自动驾驶仪工程可行性控制策略

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Control of static unstable airframes

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