Munition with integrity gated go/no-go decision

• US 7,367,525 B2
• Filed: 02/11/2005
• Issued: 05/06/2008
• Est. Priority Date: 05/23/2003
• Status: Expired due to Term

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Britigan, John D., McKendree, Thomas L., Habereder, Hans L.
• Primary Examiner(s): Gregory; Bernarr E.
• Application Number:
  US11/056,065
• Publication Number:
  US 20060108468A1
• Time in Patent Office: 1,180 Days
• Field of Search: 89/11.1, 244 31- 33, 342/62, 342/165, 342/166, 342/173, 34235701-35717, 342/175, 342/195, 701/200, 701/207, 701213-216, 701/218, 701/224, 701/300, 701 3- 18, 701 29- 35
• US Class Current: 244/3.15
• CPC Class Codes: F41G 7/007 Preparatory measures taken before the launching of the guided missiles
• CPC Class Codes: F41G 7/346 using global navigation satellite systems, e.g. GPS, GALILEO, GLONASS
• CPC Class Codes: F41G 7/36 using inertial references
• CPC Class Codes: F42C 13/00 Proximity fuzes; Fuzes for remote detonation F42C9/148 takes precedence; constructional details F42C19/00; mounting of antennas F42B30/006
• CPC Class Codes: F42C 15/40 wherein the safety or arming action is effected electrically
• CPC Class Codes: F42C 15/44 Arrangements for disarming, or for rendering harmless, fuzes after arming, e.g. after launch

Abstract

A munition is presented which includes an integrity verification system that measures the integrity of the munition. When an integrity threshold is not met, engagement of the munition with a predetermined target is aborted. Also presented is a methodology for gating the engagement of the munition with the target. The methodology includes performing an integrity check of the munition after it is deployed. The method further includes aborting the engagement of the target when the integrity check of the munition fails.

Claims

1. A method comprising:

deploying a munition to engage a target, the munition including a guidance system;

performing an integrity check of the munition, performing the integrity check comprising determining if the munition will not engage the target beyond an alert limit; and

if the integrity check fails, aborting the engagement of the target with the munition,

wherein aborting the engagement of the target includes determining if an integrity error is recoverable and when the error is recoverable then not aborting the engagement of the munition with the target, and when the integrity error is not ercoverable then aborting the engagement of the munition with the target.

2. The method of claim 1 wherein deploying a munition comprises deploying a precision guided missile (PGM).

3. The method of claim 1 wherein deploying a munition comprises deploying a munition having a Global Positioning System (GPS) guidance system adapted to receive signals from a Space Base Augmentation System (SBAS).

4. The method of claim 1 wherein aborting comprises performing one of the group consisting of self-destructing the munition, diverting the munition to a predetermined location, disarming the munition, and failing to arm the munition.

5. The method of claim 1 wherein performing the integrity check comprises performing the integrity check a plurality of times between the time the munition is deployed and a time before the munition engages the target.

6. The method of claim 1 wherein performing the integrity check comprises performing an integrity check at a rate selected from the group consisting of continuously, at predetermined intervals, and on an interrupt basis.

7. The method of claim 1 wherein performing the integrity check comprises performing a final integrity check before the munition reaches a point of no return.

8. The method of claim 7 wherein aborting the engagement of the target comprises performing one of the group consisting of self-destructing the munition, diverting the munition to a predetermined location, disarming the munition, and failing to arm the munition.