Munition with integrity gated go/no-go decision

• US 6,896,220 B2
• Filed: 05/23/2003
• Issued: 05/24/2005
• 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): Luu, Teri Pham
• Assistant Examiner(s): Holzen, Stephen A
• Application Number:
  US10/444,937
• Publication Number:
  US 20040245369A1
• Time in Patent Office: 732 Days
• Field of Search: 244/3.1, 244/3.11, 244/3.13, 244/3.14, 244/3.15, 244/3.16, 244/3.17, 244/3.18, 244/3.19, 89/11.1
• 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 munition comprising:

a payload;

a steering component;

at least one guidance system in communication with said steering component, said guidance system capable of controlling said steering component to direct said munition to a predetermined target; and

an integrity verification system in communication with said guidance system, said integrity verification system performing the step of measuring an integrity of said munition, wherein, when an integrity threshold is not met, the step of aborting operation is executed.

2. The munition of claim 1 farther comprising an acceleration unit.

3. The munition of claim 1 further comprising an arm/disarm component coupled to said payload.

4. The munition of claim 1 wherein said at least one guidance system is selected from the group comprising a laser guidance system, an inertial guidance system, a seeker guidance system, and a Global Positioning System guidance system.

5. The munition of claim 4 wherein said Global Positioning System guidance system is coupled to a guidance integrity system.

6. The munition of claim 5 wherein said guidance integrity system comprises a Space Based Augmentation System (SBAS).

7. The munition of claim 6 wherein said SBAS comprises a Wide Area Augmentation System (WAAS).

8. The munition of claim 1 wherein said aborting operation step is executed by performing one of the group of steps consisting of self-destructing said munition, diverting said munition to a predetermined location, disarming said munition, and failing to arm said munition.

9. The munition of claim 1 wherein said integrity verification system measures the integrity of said munition at least once from a time said munition is launched until said munition engages said predetermined target.

10. The munition of claim 1 wherein said aborting operation step includes determining if the integrity error is recoverable and when the error is recoverable then not aborting the engagement of said munition with said predetermined target at this time, and when the error is not recoverable then aborting the engagement of said munition with said intended target.

11. The munition of claim 1 wherein said integrity verification system measures an integrity of said munition at a rate selected from the group consisting of continuously, at predetermined intervals, and on an interrupt basis.

12. The munition of claim 1 wherein a step of final measuring of the integrity of said munition occurs before said munition reaches a point of no return.