Optimal trajectory generation for the ascent phase of launch vehicle using θ-PSO approach

This paper proposes the application of a recently emerged variant of particle swarm optimization namely theta Particle Swarm Optimization (TH-PSO), in launch vehicle trajectory optimization problem. Constraint handling and accuracy of launch vehicle systems is a challenge for optimization researchers due to highly nonlinear nature .In this paper TH-PSO approach is implemented on the single stage of a multistage liquid propellant rocket, taking angle of attack as the control parameter. The objective is to reduce the terminal error within a constrained boundary by formulating it as a fixed time optimal control problem. It is shown that TH-PSO approach minimizes the shortcomings of other such type of optimization procedures in trajectory optimization scenario by providing better convergence and accuracy. Also to validate the effectiveness of the proposed approach it is compared with Adaptive Particle Swarm Optimization (APSO) in MATLAB simulation environment.