GUIDED MISSILE

• US 20090230234A1
• Filed: 03/12/2009
• Published: 09/17/2009
• Est. Priority Date: 03/13/2008
• Status: Active Grant

• Current Assignee: Diehl BGT Defence GmbH & Company KG (Diehl VA Systeme Stiftung & Company KG)
• Original Assignee: Diehl BGT Defence GmbH & Company KG (Diehl VA Systeme Stiftung & Company KG)
• Inventors: Fisch, Peter Gerd, Gross, Michael
• Granted Patent: US 7,893,390 B2
• Time in Patent Office: Days
• US Class Current: 244/3.110
• CPC Class Codes: F42B 15/10 Missiles having a trajectory only in the air

Abstract

A guided missile has a sensor unit, a propulsion unit, and a payload unit. A missile casing forms the outer contour, extends along a longitudinal direction, and accommodates the sensor unit, the propulsion unit, and the payload unit. At least two of the units can be fitted alongside one another in the longitudinal direction. In comparison to conventional guided missiles, the guided missile is distinguished by increased modularity and thus by increased flexibility with regard to different operational scenarios.

Claims

1. A guided missile, comprising:

a missile casing defining an outer contour of the missile and extending along a longitudinal direction;

a plurality of units accommodated in said missile casing, said units including a sensor unit, a propulsion unit, and a payload unit;

wherein said missile casing is configured to accommodate at least two of said units fitted alongside one another in the longitudinal direction.

2. The guided missile according to claim 1, wherein said propulsion unit and said payload unit are fitted alongside one another in said missile casing.

3. The guided missile according to claim 1, wherein said payload unit is disposed at an overall center of gravity of the missile.

4. The guided missile according to claim 1, wherein at least one of said units is an interchangeable module.

5. The guided missile according to claim 4, wherein said interchangeable module is configured for placement in said missile casing such that a position of the overall center of gravity remains substantially constant when a module is replaced.

6. The guided missile according to claim 1, wherein said sensor unit is an electro-optical, infrared, radar or ladar seeker head.

7. The guided missile according to claim 6, wherein said sensor unit is manufactured in modular form.

8. The guided missile according to claim 1, wherein said sensor unit comprises GPS navigation.

9. The guided missile according to claim 1, wherein said sensor unit is a remotely controllable unit.

10. The guided missile according to claim 1, wherein said propulsion unit is a turbine motor, a solid-fuel motor, or a gel-fuel motor.

11. The guided missile according to claim 10, wherein said propulsion unit is manufactured in modular form.

12. The guided missile according to claim 1, wherein said propulsion unit is disposed substantially centrally within said missile casing.

13. The guided missile according to claim 1, wherein said propulsion unit is a turbine motor, and a fuel module is connected to said turbine motor, and said missile casing is configured to accommodate said fuel module substantially close to a center of gravity of the missile.

14. The guided missile according to claim 10, wherein said motor is a solid-fuel motor having a motor structure formed from a fiber composite material.

15. The guided missile according to claim 10, wherein said motor structure of said solid-fuel motor is formed of a plastic reinforced with carbon fibers.

16. The guided missile according to claim 1, wherein said payload unit is a shape-charged unit or an HPMW unit.

17. The guided missile according to claim 16, wherein said payload unit is manufactured in modular form.

18. The guided missile according to claim 1, wherein said missile casing is manufactured from a fiber composite material.

19. The guided missile according to claim 18, wherein said missile casing is formed of a plastic reinforced with carbon fiber.

20. The guided missile according to claim 1, wherein said missile casing is configured to minimize a reflective cross section for electromagnetic radiation.

21. The guided missile according to claim 20, wherein said missile casing is configured to minimize a reflective cross section with regard to radar detection.

22. The guided missile according to claim 1, wherein said missile casing is formed with an accommodation area for accommodation of said units, and wherein said accommodation area is movably disposed in the longitudinal direction.

23. The guided missile according to claim 1, formed to have an overall mass of less than 70 kg.

24. The guided missile according to claim 23, formed to have an overall mass between 50 and 60 kg.

25. The guided missile according to claim 1, wherein said missile casing is configured for the attachment of wings manufactured in a modular form.

26. The guided missile according to claim 25, wherein said wings are retractable wings.