Optimal Gliding Guidance of Vertical Plane for Standoff Released Guided Bomb Unit

Optimal gliding guidance for a guided bomb unit in the vertical plane is studied based on nonlinear dynamics and kinematics. The guidance law is designed under minimum energy loss index. To avoid the complexity in solving two-point-boundary-value problems, the steady-state solutions of the adjoint states in regular equations are suggested to be used. With these considerations, a quasi-closed, optimal gliding guidance law is obtained. The guidance law is described by the angle of attack in a simple nonlinear equation. An iterative computation method can be easily used to get the optimal angle of attack. The further simplified direct computation algorithm for the optimal angle of attack is also given. The guidance properties are compared with those of maximum lift-to-drag angle of attack control. The simulation results demonstrate that the quasi-closed, optimal gliding guidance law can improve the gliding phase terminal performance with significant increase in the altitude and much little decrease in the speed.