A blended control strategy for intercepting high-speed target in high altitude

Abstract

To intercept target with high speed in high altitude, a blended control strategy is presented. The control strategy consists of two controls, one is the aerodynamic rudder control which is always switched on, another is the lateral jets control which is switched on only when the state variables' prediction at impact point suggests that the only aerodynamic rudder control is not enough to achieve interception. The objective of this strategy is to save consumption of lateral jets, which is necessary in the case of limited number of jets. The algorithm of state variables' prediction at impact point is summarized through recursive calculation using the analytic solutions of state variables of the kinematics with consideration of the dynamics of the interceptor (missile) by piecewise linearization and smart approximation. Considering the uncertain dynamics of the interceptor with blended control, a head pursuit robust guidance law is designed based on timescale separation and robust control, where, the nonlinear deviation dynamics of the relation that the lead angle of the interceptor changes in proportion with that of the target, and the uncertain acceleration dynamics, are treated as the slow subsystem, while the uncertain pitch angular rate dynamics is treated as the fast subsystem. Numerical simulations are performed to verify the performance of the proposed guidance law.

Study of Head-Pursuit Cooperative Guidance Law for Near-space Hypersonic Interceptor

“…For the purpose of improving the convergence rate of the guidance system, Si and Song (2017) proposed a head-pursuit guidance law based on fast double-power reaching law, which not only attenuated the system chattering, but also accelerated the convergence rate of the system. Since target maneuvering is unknown, Zhang et al (2018) used an adaptive algorithm to estimate the system disturbance and presented a headpursuit guidance law based on time-scale separation which can improve system intercept accuracy and have strong robustness.…”

Design of finite-time guidance law based on observer and head-pursuit theory

“…Si and Song 11 developed headpursuit guidance laws based on the fast double-power reaching law. Zhang et al 12 presented a head-pursuit guidance law taking into account the uncertain dynamics of the interceptor based on time-scale separation, which has strong robustness to system disturbance. Zhu and Mu 13 designed a head-pursuit guidance law based on the adaptive SMC theory to intercept targets with high speed.…”

Design of Head Pursuit Guidance Law Based on Fractional-Order Sliding Mode Theory

“…Si and Song (2017) introduced a fast double-power reaching law into the design of head pursuit guidance law, which can improve the approach speed of sliding mode variables. Taking into account the uncertain dynamics of missile, Zhang et al (2018) presented a head pursuit guidance law based on time-scale separation and varied the robustness to system disturbance. Zhu and Mu (2019) designed a head pursuit guidance law based on adaptive sliding mode control theory to intercept targets with high speed.…”