Optimization Design of the Trajectory about Gun-launched Missile Based on SQP
The trajectory optimization problems of maximum impact angle about gun-launched missile which beam-riding guidance and homing guidance composite guidance program was used were studied in this paper.The flight trajectory of the missile was divided into four main phases: the climb phase,the turning phase,the search phase,the terminal guidance phase.Maximum impact angle was set as the optimization objective,the horizontal distance of the climb phase and the trajectory inclination angle of the search phase as well as engine ignition timing were set as optimization variables,the angle between the beam centerline and the receiver and overload were set as the main constraints.Whole trajectory optimization with the given range was executed under the sequential quadratic programming.The simulation results show that the optimized trajectory is smooth and the impact angle is large enough to meet the need of top strike attack.
Gun-launched Missile Beam-riding Guidance Trajectory Optimization Sequential Quadratic Programming
JIANG Huchao MEI Yuesong YU Jianqiao LI Jingxu CHEN Xi
School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081 Beijing Institute of Electronic System Engineering,Beijing 100854 Department of Research & Development,China North Industries Group,Beijing 100053
国际会议
The 33th Chinese Control Conference第33届中国控制会议
南京
英文
7555-7560
2014-07-28（万方平台首次上网日期，不代表论文的发表时间）