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Missile Jump Trajectory Planning And Navigation Technology

Posted on:2007-02-04Degree:MasterType:Thesis
Country:ChinaCandidate:H B ChenFull Text:PDF
GTID:2192360215970109Subject:Control Science and Engineering
Abstract/Summary:PDF Full Text Request
The hypersonic skip vehicle weapon which span the atmosphere ,is both a hot military research point all over the world and an important way to satisfy the demand of our army .Under the background of the research project of skip missile designed to attack the land target and slow moving sea-target ,this thesis studies and seeks after the way to realize the skipping volplane trajectory with fixed terminal restriction, by using suitable control method and efficient guidance law based on the air force.The missile is desired to do wave maneuver with a variable gunshot ,and hit the end point with a fixed velocity vector . Therefore, the main works are summarized as follows:We analysis the dynamics and trajectory equations of the hypersonic skip missile and the special demand to skip glide, bring forward the whole skipping ballistic trajectory scheme, divide the whole trajectory into the wave skip stage and terminal descend stage, choose the control method of each stage.Using the programmed flight, based on the method of controlling attack angle to provide vary lift force, we realize the wave maneuver trajectory of the missile, we also study the relation between attack angle and glide distance and solve the trajectory scheme and the control method of the missile which skip in the upaerosphere.In order to make a smooth transition to the vicinal stage,we analysis and frame the handing law between different guidance law of the stage and the handing over point between the wave maneuver trajectory and the terminal descend stage.In the terminal descend stage, according to the terminal restriction of the missile, based on constant LQ method, we propose a guidance law which can guaranty the terminal guidance accuracy,the direction and amplitude of the missile velocity by using a combination of optimal guidance law and ideal velocity curve approach.In the end,we make 3 DOF simulations to the skip trajectory of the missile and prove that the trajectory scheme and the guidance law are proper, efficient and easy for implementation.
Keywords/Search Tags:Missile, Trajectory, Guidance, Optimal guidance law, Maneuverable reentry, Programming, Attitude control, Simulation, Matlab
PDF Full Text Request
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