Abstract:
This project aims to devise a concise methodology for onboard computation for trajectory planning in launch vehicles. Our methodology is primarily based on optimal control theory; the framework would apply to multiphase-phase non-linear functional optimization problems. A 6-DOF multistage ascent case is presented with appropriate mission path & state-based constraints to perform the orbital insertion. A direct optimal control approach is taken to tract the non-linear control problem; further, the Radau-pseudospectral scheme is applied to formulate the computational equivalent of a continuous case. NLPs are accompanied by convex optimization techniques and successive convex optimization. The simulation result is provided to show the robustness of the algorithm despite inaccurate initial guesses.
