A missile guidance system is configured to estimate a time to go, the time to go comprising an amount of time until a missile would reach a closest point of approach to a target. The guidance system is also configured to estimate a zero-effort miss distance along a zero-effort miss vector, the zero-effort miss distance comprising a distance by which the missile would miss the target if the missile performs no future maneuvers. The guidance system is also configured to determine a tolerance for the zero-effort miss distance, the tolerance being a function of the time to go. The guidance system is further configured to modify a course of the missile by adjusting an expenditure of propellant such that the estimated zero-effort miss distance in excess of the tolerance is removed from future consideration.
This information is part of a study by Oasis Global, Inc. of all space inventions filed at the United States Patent and Trademark Office, and is provided for informational purposes only. It is not an endorsement of any particular assignee, inventor or invention. Although Peter A. Koziol represents inventors and assignees of space inventions he does not represent all of the inventors and assignees listed. The prosecuting attorney agent or firm for each patent is identified by the United States Patent and Trademark Office in the patent specfication, which can be viewed by clicking on the patent image or downloading the patent document. For more information regarding Mr. Koziol's background and experience, or to learn more about space inventions, please contact Mr. Koziol.
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