New Iterative Guidance for Launch Vehicle with Quadratic Optimization

This paper investigates the iterative guidance mode for launch vehicle. In order to improve the precision of the guidance system and minimize the flight time, the iterative guidance mode derived from quadratic optimization method, to obtain minimal energy control for launch vehicle. At the same time, the optimal control vector of the guidance command is obtained based on the Hamiltonian equation, and the analytical solutions and the initial value of the adjoint variables are obtained by double integration. Finally, numerical simulation is demonstrated that the performance of the new iterative guidance mode for launch vehicle can achieve the desired performance. In addition, 500 times Monte-Carlo simulation results show the performance of the iterative guidance mode is better than the traditional iterative guidance.