TY - GEN
T1 - Optimization design of the trajectory about gun-launched missile based on SQP
AU - Jiang, Huchao
AU - Mei, Yuesong
AU - Yu, Jianqiao
AU - Li, Jingxu
AU - Chen, Xi
N1 - Publisher Copyright:
© 2014 TCCT, CAA.
PY - 2014/9/11
Y1 - 2014/9/11
N2 - 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.
AB - 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.
KW - Beam-riding Guidance
KW - Gun-launched Missile
KW - Sequential Quadratic Programming
KW - Trajectory Optimization
UR - http://www.scopus.com/inward/record.url?scp=84907943532&partnerID=8YFLogxK
U2 - 10.1109/ChiCC.2014.6896258
DO - 10.1109/ChiCC.2014.6896258
M3 - Conference contribution
AN - SCOPUS:84907943532
T3 - Proceedings of the 33rd Chinese Control Conference, CCC 2014
SP - 7555
EP - 7560
BT - Proceedings of the 33rd Chinese Control Conference, CCC 2014
A2 - Xu, Shengyuan
A2 - Zhao, Qianchuan
PB - IEEE Computer Society
T2 - Proceedings of the 33rd Chinese Control Conference, CCC 2014
Y2 - 28 July 2014 through 30 July 2014
ER -