Integrated boost phase and post boost phase missile guidance sys

Details Integrated boost phase and post boost phase missile guidance sys Integrated boost phase and post boost phase missile guidance sys

1996-10-29

1998-09-22

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Remote control

244 314, F41G 730

Patent

active

058117881

ABSTRACT:
An integrated system and method for guiding an inflight missile during its boost phase to increase the accuracy of the missile flight and increase the probability that the missile reaches its intended target. The system includes four sub-systems that each perform a separate missile guidance function, but that each are integrated to form a single guidance system. The system includes a position rectified velocity wire guidance sub-system for steering the missile to maintain the same trajectory as determined in a prelaunch solution through measuring velocity error at a given position along the path of the missile. The system also includes an ignition delay sub-system for correcting missile position along the flight path by navigating position between burnout of the given missile stage and ignition of the subsequent stage, and modifying the ignition time to correct the missile position after all missile stages are burned. The system also includes a multi-node Lambert guidance sub-system for steering the missile through a multi-node Lambert guidance control that arrives at independent solutions based on desired conditions at the target point and one or more way points; then merges the independent solutions. In addition, the system of the present invention includes a post-boost guidance sub-system for guiding the missile through post-boost guidance correction to correct residual velocity error through either a post-boost trans-stage capability or through the inherent capability of the missile.

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