Second-Order Sliding Mode Guidance Law considering Second-Order Dynamics of Autopilot

Abstract

Aiming at the requirement that some missiles need to meet certain impact angles when attacking targets, we consider the secondorder dynamic characteristics of autopilot, thereby proposing a second-order sliding mode guidance law with impact angle constraint. Firstly, based on the terminal sliding mode control, we design a fast nonsingular terminal sliding mode guidance law with impact angle constraint. Based on the second-order sliding mode control, a second-order sliding mode guidance law with impact angle constraint is proposed. We have proved its finite time convergence characteristics and presented the specific convergence time expression. Subsequently, the dynamic characteristics of the autopilot are approximated to the second-order link. Combined with the dynamic surface control theory, we proposed a second-order sliding mode guidance law considering the second-order dynamic characteristics of the autopilot and proved its finite-time convergence characteristics. Finally, the effectiveness and superiority of the proposed guidance law are verified by comparative simulation experiments.

Adaptive second order sliding mode guidance law for missile-target interception with fuzzy logic system

“…Table 2 gives three different scenarios that describe target accelerations and different disturbance levels. 29,30 These scenarios will be used to show the effectiveness and robustness of the presented guidance laws. Besides, the simulations are carried out in the presence of external disturbances in order to assess the performance of the guidance laws fairly.…”

Adaptive Super-Twisting Sliding Mode Forward Tracking Guidance Law Considering Missile Body Characteristics

“…First-order is used to approximate and express the physical characters of the projectile body and establishes the model to design the adaptive method for sliding mode guidance algorithm with progressive convergence and the characters of the projectile body [4] . The guidance problem of attacking maneuvering targets was studied and a new algorithm that considered the limitation of the Angle of attack constraint, the characters of the projectile body, and the convergence of fixed time were designed [5] . A guidance algorithm with the characters of the projectile body was obtained by using a nonlinear perturbation observer and integral slide mode method according to the finite time convergence theory [6] .…”