Asymmetric penetration warhead

• US 6,012,393 A
• Filed: 12/02/1997
• Issued: 01/11/2000
• Est. Priority Date: 08/17/1995
• Status: Expired due to Fees

• Current Assignee: Rafael - Armament Development Authority Ltd.
• Original Assignee: State of Israel--Ministry of Defence Armament Development Authority Rafael
• Inventors: Tal, Zeev
• Primary Examiner(s): TUDOR, HAROLD JAY
• Application Number:
  US08/982,899
• Time in Patent Office: 770 Days
• Field of Search: 102/374, 102/382, 102/384, 102/390, 102/391, 102/398, 102/399, 102/436, 102/439, 102/473, 102/501, 102/514-519, 244/3.1
• US Class Current: 102/374
• CPC Class Codes: F42B 12/06 with hard or heavy core; Kinetic energy penetrators F42B12/16, F42B12/74 take precedence
• CPC Class Codes: F42B 30/08 Ordnance projectiles or missiles, e.g. shells

Abstract

A penetration warhead of a positively position-controlled roll-stabilized missile. The warhead has a main axis and includes a nose section which is asymmetric with respect to the main axis of the warhead, the asymmetry is selected such that upon impacting a target the forces acting on the nose section create a moment about the warhead'"'"'s center of gravity which directs the penetration warhead in a direction which is substantially toward the perpendicular, thereby increasing the warhead'"'"'s penetration depth.

Claims

1. A penetration warhead of a positively position-controlled roll-stabilized missile, the warhead having a main axis, the warhead comprising a nose section which is rigidly asymmetric with respect to said main axis of the warhead, said asymmetry is selected such that upon impacting and penetrating a target at an angle which deviates from a perpendicular to a surface of said target, the forces acting by said target on said nose section create a moment about the warhead'"'"'s center of gravity which directs the penetration warhead in a direction which is substantially toward the perpendicular, thereby increasing the warhead'"'"'s penetration depth into the target.

2. The warhead of claim 1, wherein said nose section includes a planar configuration at its anterior end.

3. The warhead of claim 1, wherein said nose section includes an oblique conical configuration at its anterior end.

4. The warhead of claim 1, wherein said nose section includes a convex configuration at its anterior end.

5. The warhead of claim 1, wherein said nose section includes a concave configuration at its anterior end.

6. A positively roll-stabilized position-controlled missile, comprising a generally cylindrical housing and a flight control system being implemented within and on said housing, said flight control system being for determining the trajectory and the roll position of the missile, said housing including:

(a) a guidance section being implemented on said housing for controlling said flight control system; and

(b) a penetration warhead having a main axis and a nose section, said warhead being characterized in that said nose section is rigidly asymmetric with respect to said axis of the warhead, said asymmetry is selected such that upon impacting and penetrating a target at an angle which deviates from a perpendicular to a surface of said target, the forces acting by said target on said nose section create a moment about the warhead'"'"'s center of gravity which directs the penetration warhead in a direction which is substantially toward the perpendicular, thereby increasing the warhead'"'"'s penetration depth into the target.

7. The missile of claim 6, wherein said nose section includes a planar configuration at its anterior end.

8. The missile of claim 6, wherein said nose section includes an oblique conical configuration at its anterior end.

9. The missile of claim 6, wherein said nose section includes a convex configuration at its anterior end.

10. The missile of claim 6, wherein said nose section includes a concave configuration at its anterior end.