Ilya A. Shkolnikov

Brief paper: Smooth second-order sliding modes: Missile guidance application

A new smooth second-order sliding mode control is proposed and proved using homogeneity-based technique for a system driven by sufficiently smooth uncertain disturbances. The main target application of this technique-the missile-interceptor guidance system against targets performing evasive maneuvers is considered. The smooth second-order sliding mode control-based guidance law is designed and compared with augmented proportional navigation guidance law via computer simulations of a guided missile intercepting a maneuvering ballistic target.

Guidance and Control of Missile Interceptor using Second-Order Sliding Modes

A new smooth second-order sliding mode control (SSOSM) is proposed and proved for a system driven by uncertain sufficiently smooth disturbances. The main target application of this technique, the missile interceptor guidance-control system against targets performing evasive maneuvers, is considered to demonstrate benefits of this design for a two-loop integration of guidance and flight control systems. The designed guidance-control system performance is verified via computer simulations using a miniature hypervelocity kinetic energy endo-atmospheric interceptor planar model.

Brief Tracking in a class of nonminimum-phase systems with nonlinear internal dynamics via sliding mode control using method of system center

A method of asymptotic output tracking in a class of causal nonminimum-phase uncertain nonlinear systems is considered. Local asymptotic stability of output tracking-error dynamics are provided for the specified class of systems with the nonlinear hyperbolic at the origin internal dynamics forced by a reference output profile and external disturbances defined by a known linear exosystem. The nonlinear vector field of the internal dynamics is expanded in a power series, obtained at a selected operational point in the internal dynamics state space. The presented technique employs some linear algebraic methods and sliding mode control approach. The solution is a complete constructive algorithm.

Aircraft Nonminimum Phase Control in Dynamic Sliding Manifolds

The approximate causal nonminimum phase output tracking problem is considered for an F-16 nonlinear sixdegree-of-freedom modelandaddressed via sliding modecontrol.Asymptoticoutputtracking-errordynamicswith desired eigenvalue placement are provided in case of tracking causal reference output proe le with a e nite number of nonzero time derivatives (piecewise polynomial spline model ) in the presence of unmatched disturbances of the same kind. A complete constructive algorithm for tracking controller design is built for a class of uncertain nonlinear multi-input/multi-output systems with known linear unstable internal dynamics. An analysis is made of the issue that the given nonlinear aircraft model yields to the approach developed.

Brief Sliding mode control of boost and buck-boost power converters using method of stable system centre

Nonminimum phase tracking control is studied for boost and buck-boost power converters. The sliding mode controller is designed to track directly a causal voltage tracking profile given by an exogenous system. The nonminimum phase output tracking problem is reduced to a state tracking problem. Bounded state tracking profiles are generated by equations of stable system centre. Numerical examples demonstrate the effectiveness of the sliding mode control design.

Missile Controlled by Lift and Divert Thrusters Using Nonlinear Dynamic Sliding Manifolds

A new approach to the design of a kinetic-kill longitudinal autopilot steering the missile trajectory by the combination of aerodynamic lift and divert thrusters (dual-thrusters control) and with its attitude oriented by attitude thrusters is presented. The proposed approach may increase the total divert acceleration capability by up to 100%, improving the end-game intercept accuracy, when such capability is required. The pitch plane autopilot design is based on second-order sliding mode control using a nonlinear dynamic sliding manifold technique. A robust high-accuracy tracking of the missile normal acceleration guidance command is achieved in the presence of considerable model uncertainties created by the interactions between the airflow and the thrusters jets. Results of the computer simulation demonstrate excellent, robust, high-accuracy tracking performance of the proposed design.

Autopilot for Missiles Steered by Aerodynamic Lift and Divert Thrusters using Nonlinear Dynamic Sliding Manifolds

A new approach to the design of a kinetic-kill longitudinal autopilot steering the missile trajectory by the combination of aerodynamic lift and divert-thrusters (dual-thrusters control) and with its attitude oriented by attitude-thrusters is presented. The proposed approach may increase the total divert acceleration capability by up to 100%, improving the “end-game” intercept accuracy, when such capability is required. The pitch plane autopilot design is based on second order sliding mode control using nonlinear dynamic sliding manifold technique. A robust, high accuracy tracking of the missile normal acceleration guidance command is achieved in presence of considerable model uncertainties created by the interactions between the airflow and the thrusters jets. Results of the computer simulation demonstrate excellent, robust, high accuracy tracking performance of the proposed design.

Parameter identification of non-linear system using traditional and high order sliding modes

Identification problem of a non-linear system with constant coefficients is addressed via traditional and high-order sliding mode parameter observer based on the least-squares continuous-time technique. Measurement noise effects on the parameter estimation algorithm are analyzed. The effectiveness of the proposed method is verified via the parameter estimation in a second-order system with noisy measurement

Sliding mode parameter identification of systems with measurement noise

Identification problem in a nonlinear system with constant coefficients is addressed via traditional and high-order sliding mode parameter observer based on the least-squares continuous-time technique. Measurement noise effects on the parameter estimation algorithm are analyzed. The effectiveness of the proposed method is verified via the parameter estimation in a second-order system with noisy measurement.

Nonminimum phase tracking in MIMO systems with square input–output dynamics via dynamic sliding manifolds

Abstract The approximate causal output tracking problem in nonlinear multi-input/multi-output (MIMO) nonminimum phase systems is addressed via sliding mode control. A class of MIMO nonlinear systems with matched nonlinearities as well as matched and unmatched disturbances, where the number of inputs, outputs, and the total relative degree are equal, is considered. The output tracking problem is solved using dynamic sliding manifold technique. The linear bounded error dynamics with desired eigenvalue placement forced by unmatched disturbance and causal reference output profile are provided. Addressing nonminimum phase condition, the sliding mode controller (SMC) joins features of a conventional SMC (insensitivity to matched nonlinearities and disturbances) and a conventional dynamic compensator (accomodation to unmatched disturbances). Theoretical results are demonstrated on a numerical example.