Design Of Guidance And Control System For A Guided Rocket

This article takes a certain type of guided rocket as the research object and takes the design of the rocket control guidance system as the main content.The research on the design of autopilot,guidance law and ballistic simulation of rockets are conducted.In this process,the numerical analysis of the aerodynamic characteristics of the rocket is also performed.The specific research content is as follows:The common coordinate system of the rotating rocket is established,and the conversion relations and common angles between the coordinate systems are given.The forces and moments of the projectile during the flight are analyzed,and a mathematical model for accurately describing the movement of the projectile is established to simulate the six-degrees of freedom of the rocket projectile.Based on the Fluent computing platform,the numerical calculation of the aerodynamic force of the rocket and the numerical simulation of the missile under various flight conditions are completed using the CFD method.The variations of aerodynamic parameters such as lift coefficient and drag coefficient at different Mach numbers and angles of attack are studied and compared with the results of wind tunnel tests.Finally,the aerodynamic characteristics and surface pressure distribution of guided rockets during flight are summarized.Introduce the function and design index of the autopilot and give the derivation process of the missile transfer function.According to the problem of the uncorrected projectile,the autopilot is designed using the analytical method and the pole assignment method.And the steady state performance is verified.The equation of relative motion of the missile is established.The gravity PN guidance law,bias proportional navigation guidance law based on terminal impact position and angle constraint are all derived.The different guidance schemes are simulated and verified.A full trajectory simulation of guided rockets is performed by using Matlab simulation software.The simulation results are analyzed,and the validity and rationality of the design scheme for the guided rocket guidance and control system is verified.