Missile stage ignition delay timing for axial guidance correctio

Details Missile stage ignition delay timing for axial guidance correctio Missile stage ignition delay timing for axial guidance correctio

1996-10-29

1998-08-04

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

244 314, 244 31, F41G 734, F41G 736, F41G 730

Patent

active

057881790

ABSTRACT:
An ignition delay timing system, and corresponding method, for adjusting the position of an in-flight missile during its boost phase along its flight path according to a pre-launch flight path solution. The ignition delay system of the present invention is applied by navigating missile position between burnout of a given booster stage and ignition of a subsequent booster stage, and modifying ignition time of the subsequent boost stage so that the missile position along its flight path follows a pre-launch solution after all booster stages are burned. Nominal missile coast phases, which occur between burnout of one booster stage and ignition of subsequent booster stage are either increased or decreased for earlier or later booster stage ignitions to maintain the missile position along its flight path in accordance with the pre-launch solution.

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Antitactical Ballistic Missile Global Effectiveness Model (AGEM) Intercept Algorithm, by Lawton and Byrum, NSWCDD/TR-92/527, NSWC Dahlgren, VA, Jul. 1994.
Cut-Off Insensitive Guidance with Variable Time of Flight, John E. White, Sandia National Laboratories, Jan. 1993.

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