A Guidance Method for Small Solid-Rocket Launch Vehicles

Abstract

This paper presents a guidance method for solid-rocket launch vehicles. A three-stage launch vehicle, as illustration, the guidance algorithm is designed for the second stage and the third stage. For the second stage, the guidance algorithm guides the vehicle to a transfer orbit, and high precision orbit injection is implemented by the guidance algorithm for the third stage. Numerical simulation results show that the proposed guidance method can achieve an adequate precision with the burnout shutdown.