Guidance law with time control and falling angle constraints
In order to meet the requirements of time control and falling angle constraint,a time falling angle control guidance law based on the improved proportional guidance method is proposed for the mission scenario of multiple missile salvo attack.The falling angle control term is derived by solving the optimal control problem based on Hamilton's principle,and an analytical expression for predicting the time-to-go estimation is obtained by using the small leading angle hypothesis.An optimal error dynamics is introduced to expedite convergence of time control error,and a time control term with adjustable time control gain coefficient is constructed.Simulation results demonstrate that increasing the time control gain coefficient can improve convergence speed of time error,but also increase the consumption of control resources.Compared with existing time falling angle control guidance laws,this proposed method can effectively improve the accuracy in hit position,falling angle and time control to achieve missile hit time and falling angle under different constraints.
multiple missile salvo attackproportional guidance methodHamilton principlefalling angle controlimpact time controltime-to-go estimationtime control gain coefficient
NETL
NSTL
万方数据
