Ascent Guidance Trajectory Optimization Using Evolutionary Algorithm Considering Engine Gimbal and Aerodynamic Control

To achieve high-range capability, reusability, and aircraft-like operability in spaceplanes, the latter have been investigated actively. One of the critical technologies for spaceplanes is the flexible guidance methodology, which can accommodate various mission requirements and constraints. The application of an evolutionary algorithm to the real-time optimization of longitudinal ascent guidance trajectories is presented herein. The combination of the engine gimbal and aerodynamic control surfaces is considered to improve the design flexibility of the trajectories and mitigate the elevator hinge moment. The range of guidance commands for the engine gimbal angle and the angle of attack that satisfy the longitudinal trim condition are identified in advance and stored as tabular data. The performance of the proposed guidance algorithm is evaluated via a flight simulation of a subscale flight demonstrator.