Design Of Autopilot On The Satellite-guided Rocket

This Papers uses satellite-guided rockets as a platform, focuses on the research of its guidance and control, provides a theoretical basis for our research and development of guided rockets.First of all, it takes an overview of the special background and working principles of the guided rockets, focuses on several domestic and foreign typical guided rockets, and summaries the key technologies and future trends of guided rocket development.It analyzes the forces and moments on the missile body and establishes dynamics and kinematics model of six degrees of freedom; According to the domestic atmosphere standard, chooses a realistic atmospheric model; References the Earth model and the northeast sky coordinate, and analyzes its conversion relationship between each other, then establish the contact of GPS receiver and the elastomer instruction data.Depending on the relative position of the target and the missile, it introduces proportional navigation guidance law and speed track guidance law; Under the effects of the error of initial direction, zero error of seeker, compares the proportional navigation, and two speed tracking guidance law on the ground guided performance when attacked. Analyzed according to whether consider or not the dynamics of the overload autopilot, and the velocity vector autopilot simplified to a closed-loop instrument with the dynamics of overload autopilot. The results shows that the effect of the initial direction error on the proportional navigation is small, but the impact is much more greater on the speed track guidance law; the effect of the zero error of seeker on the proportional navigation guidance law can be eliminated when the coefficient N≥3, but the impact on the velocity tracking guidance law can’t be eliminated, and it’s a constant.In order to improving the dynamic characteristics of the elastomer furtherly, designs the overload autopilot matched with the proportional navigation guidance law. With reasonable assumptions, establishes linear equations of the elastomer’s motion, designs two loop autopilot, two loop autopilot with PI correction circuit, three loop autopilot by using the pole configuration; compares the impact of a unit step input on the three autopilot, and its influences on the dynamics of missile body; analysis the impact on the pole-zero of the autopilot servos’ dynamics, inally verifies their abilities of inhibiting coupling and improving the robustness of the elastomer.