TY - GEN
T1 - Robust guidance law considering two-order dynamics of autopilot
AU - Guo, Jian Guo
AU - Zhou, Jun
PY - 2010
Y1 - 2010
N2 - For the case of a three-dimensional interception, a new continuous nonlinear H∞ guidance law with robustness is proposed. The mathematic model was built according to relationship between missile and target whose acceleration as disturbance was introduced and considering two-order autopilot dynamic. Based on the method of zeroing the rate of line-of-sight angle, a global nonlinear H∞ control strategy was contrived to obtain the continuous nonlinear guidance law. The asymptotic stability of guidance system was strictly proven by Lyapunov stability theory instead of solving the Hamilton-Jacobi-Isaacs(HJI) partial differential equation, at the same time the relative velocity was not controlled applying the method. Finally an illustrative example is given to show that new guidance law is more robust and suitable to the missile for intercepting the target with high velocity and high maneuver than proportional navigation law, and the better precision of guidance law is obtained.
AB - For the case of a three-dimensional interception, a new continuous nonlinear H∞ guidance law with robustness is proposed. The mathematic model was built according to relationship between missile and target whose acceleration as disturbance was introduced and considering two-order autopilot dynamic. Based on the method of zeroing the rate of line-of-sight angle, a global nonlinear H∞ control strategy was contrived to obtain the continuous nonlinear guidance law. The asymptotic stability of guidance system was strictly proven by Lyapunov stability theory instead of solving the Hamilton-Jacobi-Isaacs(HJI) partial differential equation, at the same time the relative velocity was not controlled applying the method. Finally an illustrative example is given to show that new guidance law is more robust and suitable to the missile for intercepting the target with high velocity and high maneuver than proportional navigation law, and the better precision of guidance law is obtained.
UR - http://www.scopus.com/inward/record.url?scp=79952171966&partnerID=8YFLogxK
U2 - 10.1109/ISSCAA.2010.5633041
DO - 10.1109/ISSCAA.2010.5633041
M3 - 会议稿件
AN - SCOPUS:79952171966
SN - 9781424460441
T3 - ISSCAA2010 - 3rd International Symposium on Systems and Control in Aeronautics and Astronautics
SP - 1506
EP - 1509
BT - ISSCAA2010 - 3rd International Symposium on Systems and Control in Aeronautics and Astronautics
T2 - 3rd International Symposium on Systems and Control in Aeronautics and Astronautics, ISSCAA2010
Y2 - 8 June 2010 through 10 June 2010
ER -