New Guidance Law Design with Multiple Object Constraints for Guided Rocket-propelled Missile

摘要

A new approach is designed to the guidance of rocket-propelled missile with multiple object constraints. It allows the rocket-propelled missile to reach its target with a close to zero falling angle at a least time-of-flight (TOF). Instead of deriving the optimum guidance law by a series of linear quadratic optimization methods which results in guidance laws being complex, the new guidance law adopts a mixed framework composed of a modified PN guidance command and a TOF guidance command. The modified PN guidance is designed based on measured state information including missile position, flight-path angle and acceleration, which yields zero-miss-distance and zero-falling-angle. The TOF guidance command is determined in quadratic multinomial with respect to TOF error that is estimated with missile velocity reduction due to aerodynamic drag. Simulation results are presented to show that the proposed guidance law performs favorably in multiple object constraints.