Arbitrary-Order Sliding-Mode-Based Homing-Missile Guidance for Intercepting Highly Maneuverable Targets

Abstract

This paper investigates the development and implementation of a new homing-missile guidance system for intercepting highly maneuverable targets using arbitrary features of the homogeneous high-order sliding-mode controllers and observers. The concept of this guidance system involves artificially increasing the orders of controllers and observers to enhance accuracy and robustness of future interceptors. Two advanced guidance laws, that is, augmented proportional navigation law and direct collision or hit-to-kill law, are considered to construct acceleration-based and velocity-based attractive sliding manifolds, respectively; and high-order robust exact differentiators are used to compute high-order time derivatives of these manifolds. Real-time estimation of target maneuver from measurements using these differentiators is also considered. The resulting guidance laws are implemented in computer simulation using nonlinear interceptor dynamics and engagement kinematics. The results prove that the guidance system achieves high-level performance and successfully meets direct collision guidance requirements. In addition, this system shows good adaptability and strong robustness to target evasive maneuvers, parameter uncertainties, and measurement noises.

Two-channel pitch/yaw missile autopilot design using arbitrary order sliding modes based pole placement

“…. (34) In this section, the results obtained through different simulation scenarios are discussed to evaluate the effectiveness, performance, and robustness of the proposed AOSM-based pole-placement scheme. The first sample simulation scenario is considered for effectiveness demonstration and for comparison with a recently developed HOSM-based pole-placement scheme [39].…”

Design of three-dimensional nonlinear guidance law with bounded acceleration command

“…[32,14,30,13,10]. However, in the design of these guidance laws, the closed-loop contour of an auto-piloted missile, normally briefly called missile autopilot, is treated as an ideal term.…”

Guidance and control laws design for a switched system with discontinuous actuators

“…Sliding mode control (SMC) exhibits strong robustness to system uncertainties; hence, it is used to design robust guidance laws against unknown target maneuvers, and performing restricted target acceleration estimations is not needed. In recent years, a number of SMC-based guidance laws have been presented, such as adaptive and optimal SMC-based guidance laws [17][18][19][20][21][22][23], higher-order SMC-based guidance laws [24][25][26][27][28], SMC-based guidance laws with impact angle constraints [29][30][31][32], and SMC-based integrated autopilot-guidance laws [24,27,[33][34][35]. The SMC-based guidance laws mentioned previously have discontinuous items in mathematical formulations, which are not suitable for continuous aero fins to realize.…”