Novel aeroassisted orbital transfer optimal guidance algorithm for reentry vehicle

A new optimal guidance algorithm for aeroassisted orbital transfer of reentry vehicle is presented. The complex aeroassisted orbital transfer guidance problem is translated into a trajectory optimization problem which is solved with optimal control theory. Based on the simplified dynamic equations, the Hamilton function and adjoint state equation for optimization is built. Sequentially, the problem is simplified with judicious selection of control variables and steering law, and all the constraints must be met. The accuracy under dispersed flight environment is enhanced with the use of c1oseloop real-time computation in the algorithm. The efficiency and faster convergence of the optimal algorithm is established through simulations, and the advantage of this arithmetic is validated in simulation. Thus, it is helpful to use this algorithm to solve the practical engineering trajectory optimization problems with complicated models. The proposed guidance algorithm is fairly generic and independent missions as well as vehicle configurations.