Observer-Based Optimal Zero-Sliding Midcourse Guidance for Missiles with TVC and DCS

Optimal Sliding-Mode Guidance Law for Fixed-Interval Propulsive Maneuvers

An optimal strategy based on minimum effort control and also with terminal positionconstraint is developed for an exoatmospheric interceptor with a fixed- interval guidance time. It isthen integrated with sliding-mode control theory to drive an optimal sliding-mode guidance law forfixed-interval guidance time. In addition, this guidance law is generalized for intercepting anarbitrarily time-var...

Modified Generalized Explicit Guidance for Midcourse with Near-Zero Lateral Acceleration in Terminal Phase

By appropriately modifying the generalized explicit guidance and developing it further, an optimal midcourse guidance law is proposed in this paper to ensure terminal impact angle constrained engagement of missiles with near-zero lateral acceleration in the terminal phase. This guidance law generates a desired intermediate point in space as well as the desired angles which needs to be achieved ...

Evolutionary Guidance for Multiple Missiles

A new approach to guiding a swarm of missiles using an on-line evolutionary algorithm to optimise the flight paths is introduced. The missiles are flown via intermediate points which are adjusted dynamically by the evolutionary algorithm, then towards the point of impact with the target, thus altering the trajectory shape. Evolutionary algorithms are robust global optimisation techniques and ar...

A Modified Midcourse Guidance Law Based on Genelarized Collision Course

Midcourse guidance law with neural networks

A dual neural network ‘adaptive critic approach’ is used in this study to generate midcourse guidance commands for a missile to reach a predicted impact point while maximizing its final velocity. The adaptive critic approach is based on approximate dynamic programming. The first network, called a ‘critic’, network, outputs the Lagrangian multipliers arising in an optimal control formulation whi...