High Precision Maneuver Guidance Law for High-Speed Flight Vehicles in the Dive Phase

Résumé fourni par la source

To address the inherent contradiction between maneuverability and impact accuracy during the dive phase of high-speed flight vehicles, a novel maneuver guidance law based on optimal control theory is proposed. Altitude-decaying S-shaped and sine maneuver signals are introduced into the line-of-sight angle to generate spiral and sinusoidal maneuver trajectories, respectively. The amplitude and frequency of these signals are modulated by altitude-dependent decay functions, which enable effective evasive maneuvers during flight while ensuring terminal guidance accuracy through the gradual attenuation of maneuver signals as the vehicle approaches the target. The guidance law is derived using Pontryagin's minimum principle under multiple constraints, including impact point, impact angle, overload, angle of attack, and control authority limits. Simulation results show that compared with non-maneuver optimal guidance, the proposed method significantly enhances vehicle maneuverability under multiple constraints. The average overload is increased to 3.98g and 7.35g for spiral and sine maneuvers, respectively. Monte Carlo simulations demonstrate that both maneuver guidance laws achieve sufficient robustness and accuracy, with miss distances and impact angle errors meeting engineering requirements. Furthermore, the influence of maneuver switching altitude on miss distance is analyzed, and it is revealed that the relationship is nonlinear and depends on the maneuver signal type.

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