This patent application relates generally to guidance techniques and more particularly to a method of guiding an in-flight vehicle from its initial flight path at target acquisition to a desired flight path prior to target interception. A method of using two diverts in combination to guide an in-flight vehicle from its initial flight path at target acquisition to a desired flight path prior to target interception is provided. The two diverts are of known and different magnitudes. The magnitude of an initial projected miss at a closest approach to the target is used to determine the order and timing of the two diverts. At the completion of the second divert, the vehicle is on the desired flight path which may be either a collision or offset course trajectory as required by the vehicle's terminal guidance law.
Method of Guiding an In-Flight Vehicle to a Designed Flight Path
1991
17 pages
Report
Keine Angabe
Englisch
Missile Guidance & Control Systems , Missile Trajectories & Reentry Dynamics , Ordnance , Flight paths , Guidance , Inflight , Interception , Patent applications , Target acquisition , Targets , Terminal guidance , Vehicles , Intercept trajectories , Guided missile trajectories , Interceptors , Liquid propellant rocket engines , Solid propellant rocket engines , Divert motors , Course corrections , Corrections , Flight maneuvers
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