Adaptive Constrained On-board Guidance Technology forPowered Glide Vehicle  

作　　者：Huang Rong Wei Changzhu Liu Yanbin Lu Yuping 

机构地区：[1]School of Astronautics,Harbin Institute of Technology,Harbin 150001,P.R.China [2]Beijing Institute of Control and Electronic Technology,Beijing 100038,P.R.China [3]College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,P.R.China

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2017年第2期125-133,共9页南京航空航天大学学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(No.61403100);Fundamental Research Funds for the Central Universities(HIT.NSRIF.2015037)

摘　　要：To make full use of expanded maneuverability and increased range,adaptive constrained on-board guidance technology is the key capability for a glide vehicle with a double-pulse rocket engine,especially under the requirements of desired target changing and on-line reconfigurable control and guidance.Based on the rapid footprint analysis,whether the new target is within the current footprint area is firstly judged.If not,the rocket engine ignites by the logic obtained from the analysis of optimal flight range by the method of hp-adaptive Gauss pseudospectral method(hp-GPM).Then,an on-board trajectory generation method based on powered quasi-equilibrium glide condition(QEGC)and linear quadratic regulator(LQR)method is used to guide the vehicle to the new target.The effectiveness of the guidance method consisted of powered on-board trajectory generation,LQR trajectory tracking,footprint calculation,and ignition time determination is indicated by some simulation examples.To make full use of expanded maneuverabili ty and increased range, adaptive constrained on-board guid-ance technology is the key capability for a glide vehicle with a double-pulse rocket engine？ especially under the requirements of desired target changing and on-line reconfigurable control and guidance. Based on the rapid footprint analysis, whether the new target is within the current footprint area is firstly judged. If not, the rocket engine ignites by the logic obtained from the analysis of optimal flight range by the method of hp-adaptive Gauss pseudospectral method （hp-GPM）. Then, an on-board trajectory generation method based on powered quasiequi-librium glide condition （QEGC） and linear quadratic regulator （LQR） method is used to guide the vehicle to the new target. The effectiveness of the guidance method consisted of powered on-board trajectory generation, LQR trajectory tracking, footprint calculation, and ignition time determination is indicated by some simulation examples.

关 键 词：adaptive constrained on-board guidance double-pulse rocket engine hp-adaptive Gauss pseudospectral method powered quasi-equilibrium glide condition linear quadratic regulator(LQR)trajectory tracking 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]