Optimal reentry volte-face trajectory and control for hypersonic spacecraft

Volte-face trajectory and control of fly-back reusable spacecraft in hypersonic reentry are studied. The key technology of volte-face trajectory and control realized by adjusting aerodynamic force is analyzed. Three degree-of-freedom model of glide for spacecraft reentry is funded. Based on maximum principle and conjugate gradient method, the dynamic optimization problem of spacecraft reentry is resolved. With the constraint conditions of glide stage in reentry, optimal control variables, attack angle and roll angle, are gotten to minimize the distance between the stage end point and the launch station by means of simulation. The optimal volte-face trajectory characteristics are investigated. The laws of turning-time and roll angles during reentry acting to volte-face control characteristics are studied. Spacecraft control laws for volte-face reentry motion are explored.