Rapid Optimal Ascent Guidance for Multi-Engined Launch Vehicles

Considering the problem of rapid solution of optimal ascent trajectory of multi-engined launch vehicle, a fast numerical solution algorithm is proposed. Firstly, the optimal ascent guidance problem of multi-engined launch vehicle subject to terminal orbital constraints is converted into nonlinear algebraic equations. During the specific implementation process of the algorithm, a simplified multiple shooting method and modified Newton algorithm is put forward to enhance the robustness of convergence in the internal layer, and then external layer uses line search method to iteratively solve the cut-off time of main engine to minimum the fuel consumption. Finally, simulation tests are conducted and results demonstrate the effectiveness and adaptability of the propose method.