TY - GEN
T1 - An intercept guidance law with impact-angle-constrained based on linear gauss pseudospectral model predictive control
AU - He, Xingcai
AU - Chen, Wanchun
AU - Yang, Liang
N1 - Publisher Copyright:
© 2019 IEEE.
PY - 2019/7
Y1 - 2019/7
N2 - A nonlinear optimal guidance law with constraint on impact angle is proposed in this paper for interception of incoming high-speed ballistic missile targets. The guidance law is developed based on the recently developed linear gauss pseudospectral model predictive control (LGPMPC) method which is to solve the nonlinear optimal control problem with quadratic performance index and hard terminal constraints. The LGPMPC method combines the philosophies of linear quadrature optimal control, the Model Predictive Control and Gauss Pseudospectral Method. A design of engaging an incoming high-speed ballistic missile target with a specified impact angle in two dimensions is carried out to evaluate the performance of the proposed guidance law. In this work, the initial guess is produced by biased PN guidance law in the two dimensions. Simulation results show that the proposed guidance law has high computational efficiency in achieving ideal impact angles with high accuracy and the near-zero miss distance. And the generated lateral acceleration is small and smooth as expected. Moreover, performance of the proposed guidance law is superior to other guidance laws by comparative studies.
AB - A nonlinear optimal guidance law with constraint on impact angle is proposed in this paper for interception of incoming high-speed ballistic missile targets. The guidance law is developed based on the recently developed linear gauss pseudospectral model predictive control (LGPMPC) method which is to solve the nonlinear optimal control problem with quadratic performance index and hard terminal constraints. The LGPMPC method combines the philosophies of linear quadrature optimal control, the Model Predictive Control and Gauss Pseudospectral Method. A design of engaging an incoming high-speed ballistic missile target with a specified impact angle in two dimensions is carried out to evaluate the performance of the proposed guidance law. In this work, the initial guess is produced by biased PN guidance law in the two dimensions. Simulation results show that the proposed guidance law has high computational efficiency in achieving ideal impact angles with high accuracy and the near-zero miss distance. And the generated lateral acceleration is small and smooth as expected. Moreover, performance of the proposed guidance law is superior to other guidance laws by comparative studies.
KW - Gauss pseudospectral method
KW - Linear quadrature optimal control
KW - Model predictive control
KW - Optimal guidance LAW with impact angle Constraint
UR - https://www.scopus.com/pages/publications/85074834971
U2 - 10.1109/ICMAE.2019.8881042
DO - 10.1109/ICMAE.2019.8881042
M3 - 会议稿件
AN - SCOPUS:85074834971
T3 - 2019 IEEE 10th International Conference on Mechanical and Aerospace Engineering, ICMAE 2019
SP - 229
EP - 235
BT - 2019 IEEE 10th International Conference on Mechanical and Aerospace Engineering, ICMAE 2019
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 10th IEEE International Conference on Mechanical and Aerospace Engineering, ICMAE 2019
Y2 - 22 July 2019 through 25 July 2019
ER -