Modular rocket boosted penetrating warhead

• US 6,494,140 B1
• Filed: 04/22/1999
• Issued: 12/17/2002
• Est. Priority Date: 04/22/1999
• Status: Expired due to Fees

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Webster, Frank F.
• Primary Examiner(s): TUDOR, HAROLD JAY
• Application Number:
  US09/295,595
• Time in Patent Office: 1,335 Days
• Field of Search: 102/293, 102/374, 102/393, 102/473, 102/489, 244/3.11, 244/3.12
• US Class Current: 102/374
• CPC Class Codes: F42B 12/625 a single submissile arranged in a carrier missile for being launched or accelerated coaxially; Coaxial tandem arrangement of missiles which are active in the target one after the other with shaped or hollow charges F42B12/16
• CPC Class Codes: F42B 15/00 Self-propelled projectiles or missiles, e.g. rockets; Guided missiles F42B10/00, F42B12/00, F42B14/00 take precedence; for practice or training F42B8/12; rocket torpedoes F42B17/00; marine torpedoes F42B19/00; cosmonautic vehicles B64G; jet-propulsion plants F02K

Abstract

A modular boosted penetrator (BPEN) is disclosed that includes a penetrating warhead in tandem with a booster motor. The modular BPEN can also include suitable guidance and control systems. The configuration of the modular BPEN is such that it can function as either a direct strike weapon, or as a launchable submunition, without substantial modification.

Claims

1. A warhead assembly comprising:

a penetrating warhead comprising a symmetric nose, and a hollow interior configured to carry a payload material extending from a rear end of the warhead to substantially the nose, the penetrating warhead having a weight of approximately 500-650 lbs;

a booster mounted in tandem with said warhead, said booster configured to drive the warhead into a target at a velocity of 2,000 ft./sec., or greater;

a plurality of collapsable vanes configured to lie close to the booster in a first position, and be expandable from the first position to a second expanded position;

a guidance system for guiding said penetrating warhead toward a target object; and

a control system for steering said penetrating warhead;

wherein said penetrating warhead, said booster, said guidance system, and said control system being configured such that said warhead assembly can function as a direct-launch weapon and as a launchable submunition, without substantial modification.

2. The system of claim 1, comprising:

means for activating said payload material after said warhead has been driven into said target.

3. The system of claim 1, wherein said booster is a rocket motor powered by a material in a form chosen from the group consisting of:

a liquid, a solid, a gel, or a combination thereof.

4. The system of claim 1, wherein said booster comprises a rocket motor powered by solid fuel.

5. The system of claim 1, wherein said guidance system comprises:

a combined Inertial Navigation System/Global Positioning System.

6. The system of claim 1, wherein said guidance system comprises:

a target seeker.

7. The system of claim 1, wherein said control system comprises the collapsable air vanes which are moveable.

8. The system of claim 1, wherein said control system comprises:

a thrust vector control device.

9. A two-stage guided missile assembly comprising:

an unmanned, guided air vehicle; and

a submunition carried within said air vehicle, said submunition including;

a penetrating warhead comprising a symmetric nose, and a hollow interior configured to carry a payload material extending from a rear end of the warhead to substantially the nose, the penetrating warhead having a weight of approximately 500-650 lbs;

a booster mounted in tandem with said warhead, said booster configured to drive the warhead into a target object at a velocity of 2,000 ft./sec., or greater;

comprising a plurality of collapsable vanes configured to lie close to the booster in a first position, and be expandable from the first position to a second expanded position;

a guidance system for guiding said submunition toward a target object;

a control system for steering said submunition; and

means for ejecting said submunition from said air vehicle when said air vehicle reaches a predetermined distance from a said target;

wherein said penetrating warhead, said booster, said guidance system, and said control system being configured such that said submunition can function as a direct launch weapon and as a launchable submunition, without substantial modification.

10. The two-stage guided missile assembly of claim 9, wherein said means for ejecting comprises:

a destruct mechanism that creates an opening in a forward portion of the air;

vehicle, and an eject pressurization system that pushes said submunition forward toward said opening.

11. The two-stage guided missile assembly of claim 9, wherein said air vehicle is a cruise missile.

12. The two-stage guided missile assembly of claim 9, comprising:

means for activating said payload material after said warhead has been driven into said target.

13. The two-stage guided missile assembly of claim 9, wherein said booster is a rocket motor powered by a material in a form chosen from the group consisting of:

a liquid, a solid, a gel, or a combination thereof.

14. The two-stage guided missile assembly of claim 9, wherein said booster comprises:

a rocket motor powered by solid fuel.

15. The two-stage guided missile assembly of claim 9, wherein said guidance system comprises:

a combined Inertial Navigation System/Global Positioning System.

16. The two-stage guided missile assembly of claim 9, wherein said guidance system comprises:

a target seeker.

17. The two-stage guided missile assembly of claim 9, wherein said control system comprises the collapsable air vanes which are moveable.

18. The two-stage guided missile assembly of claim 9, wherein said control system comprises:

a thrust vector control device.