Design of quick parameter optimization guidance method for suborbital vehicle in reentry phase

A quick online predictive parameter optimization guidance method for sub-orbital vehicle in reentry phase was developed in this paper to adapt the complicated reentry aero environment. First the aero characteristic of vehicle was analyzed. Base on the result of aero glide ability and attitude maneuver ability, a logical attack angle and bank angle model was introduced to suit for the reentry aero environment. On the basis of this model a predictive parameter guidance method base on simplex method was developed to realize the self-adapting reentry of vehicle with high robustness and precision. Constringency speed of algorithm was guaranteed by elimination of restrictions in the phase of reentry, choice of logical initiate vertexes and weighting handle of central point in the step of echo. And the needs of voyage, altitude, velocity and process restrictions were all included into the performance index. The final simulation show the method in this paper can adapt to the varying of environment. Control parameter of guidance law can be optimized online quickly. High robustness and guidance precision also can be guaranteed. The final errors of altitude, velocity and voyage were respectively less than: 2500m, 16m/s and 8500m.