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This paper proposes integrated guidance and control design to intercept a target, which may execute various motions, at a pre-specified time of interception. The problem is addressed considering nonlinear engagement kinematics and the interceptor is steered using the combined effects of canard as well as tail configurations (dual-controlled interceptors). Different formulations of time-to-go, without the restrictive assumption of interceptor's small heading angle, have been used in deriving the guidance commands, allowing the proposed strategy to remain effective over a wide range of impact time values. A weighted effort allocation scheme, in canard and tail deflections, has been proposed to generate the required lateral acceleration. The overall design uses sliding mode control owing to its simplicity of design, while a nonlinear finite-time disturbance observer is used to estimate the target's maneuver. Finally, simulations are presented for various target motions, and time-constrained interception with an impaired actuator is also shown, vindicating the efficacy of the proposed technique. [ABSTRACT FROM AUTHOR]

This paper deals with nonsingular guidance and control design for an interceptor, using a decoupled approach, steered by the combined effects of both canard and tail, to intercept a moving but non-maneuvering target at a time specified a priori. First, interceptor's desired lateral acceleration, consisting of nominal and corrective components, is derived using deviated pursuit guidance. While the nominal component is the pursuit guidance law, the corrective component drives the time-to-go error to zero within a finite-time in an optimal manner. Using a desired error dynamics and a meaningful performance index, the lateral acceleration demand is minimized during the transient phase. With exact knowledge of time-to-go and the consideration of nonlinear kinematic model, the proposed design circumvents the errors arising out of any approximations. Interceptor's canard and tail deflection commands are derived using predefined-time convergent sliding mode control, which allows the autopilot to precisely track the commanded lateral acceleration within a time specified during design. Finally, simulations are presented for various cases to demonstrate the efficacy of the proposed design. [ABSTRACT FROM AUTHOR]

This paper addresses the problem of maximizing the warhead effectiveness, by achieving impact at the structurally vulnerable points of the targets. The impact direction is first defined using target frame, and then a unique relation between the desired impact angles and the desired line-of-sight angles is derived. Using this relation, two nonlinear guidance strategies, based on finite-time sliding mode and optimal control methods, are proposed to achieve interception of maneuvering targets at a pre-specified desired impact orientation. Unlike most of the existing three-dimensional guidance strategies, the proposed guidance strategies are derived without decoupling nonlinear coupled engagement kinematics into two mutually orthogonal planes and performing linearization, thereby avoiding possible performance deterioration for engagement with large heading errors. The performances of proposed guidance strategies are evaluated for various engagement geometries as well as constant speed and different realistic time-varying speed pursuer models subjected to aerodynamics parameter variations, and found to be satisfactory. [ABSTRACT FROM AUTHOR]