Design of Impact Angle Control Guidance Law with Arbitrary Time Convergence

Abstract

Aiming at the problem of impact angle constrained guidance, an arbitrary time convergent impact angle constrained guidance (ATC-IACG) law against the stationary target is designed based on the pure proportion navigation (PPN) guidance law and the arbitrary time convergence control method. Firstly, the dynamic equation of impact angle error based on the PPN guidance law is derived. Then, the arbitrary time convergence control method is employed, and the ATC-IACG is designed, which could make the impact angle error converge to zero in a predefined convergent time. Finally, the guidance performance of the ATC-IACG law is demonstrated through numerical simulation results, and compared with that of the impact angle control guidance law based on optimal error dynamics. The simulation results show that the larger the expected impact angle, the smoother the change of the missile's guidance acceleration, also the less the missile's energy consumption. Under the guidance law, the missile can achieve the attack mission constrained by the expected convergence time and the terminal impact angle.

Keywords

• |guidance law|pure proportional navigation|arbitrary time convergence|impact angle constraint|stationary target|missile