Trajectory Programming And Guidance Laws Design For Loiter Missiles Released By Airplane

A loitering missile is propelled to speed up to certain suitable velocity aftersafely launched by fighter plane, and synchronously adjusted to the schemingheight so as to execute multiple tasks, such as spying, attacking anddamage-evaluating, etc. So it is necessary to study on trajectory planning andguidance-law designing, which might provide technical support for furtherdevelopment of loitering missiles. The Dissertation’s primary work is listed asfollows:After reference frames and transforming formula are defined, the6DOF motionmodel is established for loitering missiles. Then a simplified trajectoryprogramming model is obtained for BTT guidance mode.In according with loitering missile’s working process in warfare, trajectoryplan is designed and trajectory constraints are analyzed during each phase, then theguidance laws are presented.Taking position and velocity as state variables, acceleration as control variables,path tracking model is established. And the decoupling controller is designed for thepitch/yaw channel of loitering missile by using variable structure control method.Then path tracking simulations are carried out, and the simulation results show theloitering missile is controlled to fly along the programming trajectory, which in turnprovide reference for the further design of path tracking.After the leader’s and followers’ models are deduced, trajectory planning forformation flight is put forward. In this plan, both compact formation mode andincompact formation mode are discussed by ballistic simulations. The resultsugguest the advantages and disadvantages of the two modes, which mayproviding important referrence for constituting scheme of multi-missles takingtasks in coordinated way, such as reconnaissance and campaign.