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...

This paper considers application of L1 adaptive output feedback controller to a missile longitudinal autopilot design. The proposed adaptive controller has satisfactory performance in the presence of parametric uncertainties and time-varying disturbances. Simulations demonstrate the benefits of the control method and compare the results to Linear Quadratic Regulator (LQR) and Linear Quadratic G...

Situational awareness is essential for decision makers to efficiently manage their resources. Situational awareness has historically been associated with aviation security applications, such as air traffic control (ATC), fighter missions, and missile defence. However, the number of studies in the field of situational awareness for new applications has grown significantly in the past fifteen yea...

A visual simulation system of fragment warhead missile attacking F-16C ''Falcon'' battle plane based on simulation and virtual reality technology is put forward. Firstly, the overall design of visual simulation of missile attacking F16 battleplane is implemented, and all functions of each module are demonstrated in detailed. Then 3D models in virtual battle field are optimized by level of detai...

A new algorithm, advantage learning, is presented that improves on advantage updating by requiring that a single function be learned rather than two. Furthermore, advantage learning requires only a single type of update, the learning update, while advantage updating requires two different types of updates, a learning update and a normilization update. The reinforcement learning system uses the ...

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...

The feedforward path of an autopilot is designed for the longitudinal dynamics of a tactical missile. A linear parameter-varying model is used to synthesize a self-scheduled control law based on a parameter-dependent Lyapunov function. The controller is evaluated on a nonlinear model of industrial complexity both under nominal conditions and parametric uncertainty. Tracking performance is signi...

Aperture coupling is the main coupling mode through which electromagnetic pulse (EMP), ultra wideband (UWB) and high power microwave (HPM) can disturb or damage electronic equipments of the missile enclosure. To get knowledge of the coupling effects of apertures with different shapes and positions, coupling processes of HPM into the missile enclosure are investigated. The simulation results ind...

–A flight path rate demand modified three-loop lateral missile autopilot design methodology for a class of guided missile, based on state feedback, output feedback, reduced order Das & Ghosal observer (DGO) is proposed. The open loop undamped model of three-loop autopilot has been stabilized by using pole placement and state feedback. The non-minimum phase feature of rear controlled missile air...

This paper proposes a method to obtain a discrete-time LPV (Linear Parameter Varying) controller for a non-linear system represented with the LFT (Linear Fractional Transformation) framework. This synthesis can be integrated into a loop-shaping/LPV approach to obtain a discrete gain-scheduled control law. A detailed application of this method is here performed with a classical example of non-li...