Robust Nonlinear Control Technology for High-Agility Missile Interceptors

Development and application of robust nonlinear control techniques for synthesizing high-agility missile interceptor flight control systems is proposed. Proposed design methods will be capable of handling strong nonlinearities and coupling effects that can arise during high angle of attack flight, and can deliver guaranteed performance under parameter uncertainties and disturbances. Nonlinear flight control system performance will be assessed in a high fidelity missile simulation. Design methods and algorithms developed in Phase I work will be used to synthesize flight control systems for a NAVY specified missile interceptor configuration during Phase II research. Nonlinear flight control laws will be implemented on a missile interceptor flight control computer for further evaluations and flight test.