Aircraft predictor-corrector guidance based on online constraint limit enforcement

In view of current research situation that the ballistic performance and constraints are unable to be guaranteed by traditional prediction correction algorithm in the reentry process, a new reentry guidance method was proposed, which combines the offline trajectory optimization based on simple parameterization of bank angle profile and the online prediction and correction. Process constraints were analyzed through equilibrium glide condition and the monotonic property of range to bank angle profile was proved. For offline section, control model was built through control variable parameterization (CVP) and the trajectory was optimized through sequence quadratic program (SQP) to improve the ballistic performance greatly. For online section, the solution of bank angle profile was obtained in real time, which satisfied terminal constraints through trajectory iteration based on Gauss-Newton method. Gauss-Newton method has fast convergence speed and high precision for solving trajectory. Finally, a constraint limit method was proposed to cope with the problems that high L/D aircraft would make equilibrium glide condition hard to be established and that strong interference would make constraints be violated, which provided powerful protection to process constraints in reentry. The simulation results show that this method is adaptable to uncertain factors such as throwing deviation, aircraft parameters and atmospheric model, and is of engineering application value for trajectory performance guarantee.