Time-Delay Control for Integrated Missile Guidance and Control

Numerical SDRE Approach for Missile Integrated Guidance - Control

Numerical state-dependent Riccati equation based integrated guidance-control formulation is developed for an internally actuated missile. The dynamic system under consideration is of tenth order, making it tedious to algebraically manipulate the equations of motion into the state-dependent coefficient form central to the design methodology. A numerical approach based on previous research is dev...

Missile Guidance and Control Systems

New Principle for Missile Guidance and Control

ted to allow efficient ballistic missiles , the paper describes a recently developed ted estimation/guidance design paradigm n several innovative concepts that provides satisfactory homing performance against ly maneuvering targets. The new paradigm veloped and tested first by using a simplified constant speed interception scenario model. paper the integrated estimation/guidance m is validated ...

A New Method for Time-Delay Compensation in Control Systems

In this paper a new method is introduced and investigated for removing the destabilizing effects of time-delay parameter in control loops. The concept of the method is taken from the knowledge concerning the dynamic behaviour of irrational transfer functions (Ir-TF), which is discussed and investigated elswhere in frequency response domain and is explained briefly here. Ir-TFs, which are we...

Missile Interceptor Guidance and Control Using Second Order Sliding Modes

Abstract: The missile interceptors integrated guidance and control technology for achieving the hit-to-kill accuracy against targets performing evasive maneuvers including spiraling motion is developed on the basis of high (second) order sliding mode control (HOSM). The integration of guidance and flight control systems is achieved in a two-loop guidance and flight control system designed in th...