Addressing the challenge of controlling impact angle and time during the terminal guidance phase of gliding-guided projectiles,a scheme was proposed to simplify the guidance law design process and facilitate engineering applications.This scheme extends existing high-performance,non-time-critical guidance laws to accommodate time constraints.Based on a nonlinear guidance model and using the projectile's flight trajectory under existing guidance laws as a reference,the proposal divided the terminal guidance phase into two stages.In the first stage,the projectile flies under the extended guidance law,adjusting the reference trajectory's curvature and extending flight time to converge the impact time error to zero within a finite period.In the second stage,the original guidance law takes over until the target is hitted,ensuring compliance with miss distance and impact angle constraints.Extensive simulations were carried out under various conditions.The impact of design parameter ranges on the convergence performance of impact time error in the first stage was studied.The derivation of this extended scheme does not require an explicit expression of the existing guidance laws,offering a degree of universality.The results indicate that with appropriate parameter settings,the extended scheme can achieve impact time control on the basis of existing guidance laws,with smooth guidance commands and minimal required overload,meeting the operational requirements.
gliding-guided projectileterminal guidancetime-varying velocityimpact time controlimpact angle constraintstrajectory prediction
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