Control of static unstable airframes  

作　　者：Junfang Fan Defu Lin Zhong Su Qing 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》2010年第6期1063-1071,共9页系统工程与电子技术（英文版）

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.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：missile control static instability optimal control BACKSTEPPING weight matrix unstable zero-pole pair. 

分 类 号：TP273.2[自动化与计算机技术—检测技术与自动化装置] TV51[自动化与计算机技术—控制科学与工程]