TY - JOUR
T1 - New integrated guidance and control of homing missiles with an impact angle against a ground target
AU - Yang, Shengjiang
AU - Guo, Jianguo
AU - Zhou, Jun
N1 - Publisher Copyright:
© 2018 Shengjiang Yang et al.
PY - 2018
Y1 - 2018
N2 - A new integrated guidance and control (IGC) law is investigated for a homing missile with an impact angle against a ground target. Firstly, a control-oriented model with impact angle error of the IGC system in the pitch plane is formulated by linear coordinate transformation according to the motion kinematics and missile dynamics model. Secondly, an IGC law is proposed to satisfy the impact angle constraint and to improve the rapidity of the guidance and control system by combining the sliding mode control method and nonlinear extended disturbance observer technique. Thirdly, stability of the closed-loop guidance and control system is proven based on the Lyapunov stability theory, and the relationship between the accuracy of the impact angle and the estimate errors of nonlinear disturbances is derived from stability of the sliding mode. Finally, simulation results confirm that the proposed IGC law can improve the performance of the missile guidance and control system against a ground target.
AB - A new integrated guidance and control (IGC) law is investigated for a homing missile with an impact angle against a ground target. Firstly, a control-oriented model with impact angle error of the IGC system in the pitch plane is formulated by linear coordinate transformation according to the motion kinematics and missile dynamics model. Secondly, an IGC law is proposed to satisfy the impact angle constraint and to improve the rapidity of the guidance and control system by combining the sliding mode control method and nonlinear extended disturbance observer technique. Thirdly, stability of the closed-loop guidance and control system is proven based on the Lyapunov stability theory, and the relationship between the accuracy of the impact angle and the estimate errors of nonlinear disturbances is derived from stability of the sliding mode. Finally, simulation results confirm that the proposed IGC law can improve the performance of the missile guidance and control system against a ground target.
UR - http://www.scopus.com/inward/record.url?scp=85059096079&partnerID=8YFLogxK
U2 - 10.1155/2018/3968242
DO - 10.1155/2018/3968242
M3 - 文章
AN - SCOPUS:85059096079
SN - 1687-5966
VL - 2018
JO - International Journal of Aerospace Engineering
JF - International Journal of Aerospace Engineering
M1 - 3968242
ER -