Abstract
This paper proposes a biased proportional navigation guidance (PNG) law to control the impact time, that can be used for salvo attacks or cooperative missions of missiles. To derive the guidance command of the proposed law, we introduce a polynomial function of the command with two coefficients, one of which is to achieve zero miss-distance and the other is to satisfy the terminal impact time constraint. Since the proposed guidance law has an arbitrary guidance gain, it is possible to shape the homing trajectory and acceleration command profile by choosing a proper guidance gain in consideration of the missile's capability and operational conditions. Numerical simulations for the various forms of the guidance command are performed to investigate the characteristics and performance of the proposed law.
