Generalized optimal impact-angle-control guidance with terminal acceleration response constraint

Abstract

To study the optimal impact-angle-control guidance problem with multiple terminal constraints, a generalized optimal impact-angle-control guidance law with terminal acceleration response constraint (GOIACGL-TARC) is proposed. In the deriving, a time-to-go − nth power weighted object function is adopted to derived the GOIACGL-TARC and a general expression of GOIACGL-TARC is presented. Based on the general expression of GOIACGL-TARC, three guidance laws, GOIACGL-TARC1/TACC0/TACC1 are proposed and the inheritance relationship between GOIACGL-TACC0/TACC1/TARC1 and the conventional optimal guidance law with impact angle constraint is demonstrated. Performance analysis of the proposed guidance laws shows that in the case of GOIACGL-TACC0, the terminal acceleration is not zero at n = 0 and only as n > 0, the terminal acceleration converges to zero; in the case of GOIACGL-TACC1 and GOIACGL-TARC1, GOIACGL-TARC1 can guarantee the acceleration response to reach the exactly zero value but GOIACGL-TACC1 cannot, which can only guarantee the acceleration command to reach the exactly zero value. It is pointed out that compared with the biased proportional navigation guidance law, GOIACGL-TARC1 has an outstanding guidance performance in acceleration response, miss distance, and terminal impact angle error.

Direct impact angle control guidance for passive homing missiles

“…In Chen and Wang, 6 the optimal guidance law for an impact angle control is derived under small heading error assumption, which forms a biased proportional navigation guidance (PNG) law with the navigation constant N = 4. In Wang et al., 7 a generalized optimal guidance law with an impact angle constraint is investigated considering terminal acceleration response as a first-order autopilot lag system. Lee and Ryu 8 propose a general solution of the weighted optimal guidance law for an impact angle control with arbitrary weighting functions in the presence of the dynamic lag effect as well as velocity variation.…”

Adaptive back-stepping sliding mode guidance laws with autopilot dynamics and acceleration saturation consideration

“…30 In Dong et al., 31 a new guidance strategy was proposed for missile-guided maneuvering targets in the presence of towed bait interference using terminal sliding mode and adaptive control. In Wang et al., 32 an optimal guidance law with impact-angle and terminal acceleration response constraint was designed, which can achieve acceleration response, miss distance, and terminal impact angle error to reach the exactly zero value. In He et al., 33 an adaptive dynamic surface guidance law with impact angle constraints was designed by using the adaptive technique and dynamic surface method, which can solve acceleration saturation constraint efficiently by using the hyperbolic tangent function.…”