Rocket-boosted guided hard target penetrator

• US 6,276,277 B1
• Filed: 04/22/1999
• Issued: 08/21/2001
• Est. Priority Date: 04/22/1999
• Status: Active Grant

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Schmacker, Bruce E.
• Primary Examiner(s): Nelson, Peter A.
• Application Number:
  US09/295,594
• Time in Patent Office: 852 Days
• Field of Search: 102/518, 102/519, 102/384, 102/386, 102/374
• US Class Current: 102/384
• CPC Class Codes: F42B 10/00 Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding F42B6/00 takes precedence
• CPC Class Codes: F42B 12/06 with hard or heavy core; Kinetic energy penetrators F42B12/16, F42B12/74 take precedence
• CPC Class Codes: F42B 12/20 of high-explosive type F42B12/44 takes precedence
• CPC Class Codes: F42B 12/204 for attacking structures, e.g. specific buildings or fortifications, ships or vehicles
• 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
• CPC Class Codes: F42B 25/00 Fall bombs F42B10/00, F42B12/00 take precedence; for practice or training F42B8/12 ; gliding type bombs F42B15/105

Abstract

A target-penetrating aerial bomb includes a penetrator of hard steel or similar material that contains an explosive charge. A rocket motor is formed as an annular chamber and surrounds the penetrator. The bomb includes a guidance and control unit that guides the bomb on a glide path after release from the delivery aircraft, and steers the bomb onto a dive line. Once the bomb is aligned on the dive line, the guidance and control unit fires the rocket booster to accelerate the bomb to the target. A fuse ignites the explosive after target penetration.

Claims

1. A rocket-boosted penetrating bomb, comprising:

a penetrator having a hardened case with a hollow interior containing a payload;

a rocket booster motor mounted to the penetrator to accelerate the penetrator;

an outer skin enclosing at least the penetrator and providing an aerodynamic shape;

guiding means for guiding the bomb after release from an airborne vehicle in a glide phase and from the glide phase onto a guided dive line to a target;

controlling means for activating the rocket booster motor after the guiding means has guided the bomb onto the guided dive line; and

,

a fuze for initiating the payload after impact with a target.

2. The bomb as claimed in claim 1, wherein the rocket booster motor comprises an elongated, annular propellent chamber, wherein the penetrator is disposed in a central space defined by the annular chamber.

3. The bomb as claimed in claim 1, wherein the rocket booster motor comprises a plurality of individual rocket motors mounted about the circumference of the penetrator.

4. The bomb as claimed in claim 1, wherein the rocket motor comprises a propellant chamber and nozzle mounted in tandem to an aft end of the penetrator.

5. The bomb as claimed in claim 1, wherein the fuze including means for sensing movement of the penetrator through structural layers of a target and for activating the fuze responsive to movement through a predetermined number of layers.

6. The bomb as claimed in claim 1, wherein the fuze includes a delay timer for measuring a time interval after initial impact and delaying igniting the explosive until elapse of the measured time interval.

7. The bomb as claimed in claim 1, wherein the outer skin provides an outer shape that emulates an aerodynamic outer shape of a flight qualified bomb.

8. The bomb as claimed in claim 1, wherein said guidance means includes an inertial navigation system having means for communicating with a global positioning system.

9. The bomb as claimed in claim 1, wherein said guidance means includes a target seeker having means for sensing energy radiating from a target.

10. The bomb as claimed in claim 1, wherein said guidance means includes a plurality of air vanes and means for moving the air vanes to steer the bomb.

11. The bomb as claimed in claim 10, wherein the air vanes include wings attached at a middle portion of the bomb and fins attached at the aft end of the bomb.

12. The bomb as claimed in claim 1, wherein said guidance means includes thrust vector steering means for adjusting an angle of attack of the bomb, said thrust vector steering means being active during rocket boost.

13. The bomb as claimed in claim 1, wherein the rocket motor comprises a plurality of exhaust nozzles, the nozzles being canted with respect to a longitudinal axis of the bomb to produce a roll on the longitudinal axis.

14. The bomb as claimed in claim 1, wherein said controlling means includes means for sensing distance from a target and calculating a time duration before target impact, and responsive to said calculated time duration, activating the rocket motor to achieve a predetermined velocity at target impact.

15. The bomb as claimed in claim 1, wherein the payload comprises an explosive.

16. The bomb as claimed in claim 1, wherein the payload is selected from the group comprising fragmenting bomblets, chemicals, incendiaries, and radioactive material.

17. The bomb as claimed in claim 1, wherein an outer surface of the rocket booster motor forms at least a part of the outer skin.