MUNITION GUIDANCE SYSTEM AND METHOD OF ASSEMBLING THE SAME

• US 20140158814A1
• Filed: 07/18/2012
• Published: 06/12/2014
• Est. Priority Date: 07/19/2011
• Status: Active Grant

• Current Assignee: Elbit Systems Limited
• Original Assignee: Elbit Systems Limited
• Inventors: Elkayam, Ami, Azar, Zeev
• Granted Patent: US 9,157,702 B2
• Time in Patent Office: Days
• US Class Current: 244/3.16
• CPC Class Codes: F41G 7/20 based on continuous observation of target position
• CPC Class Codes: F41G 7/22 Homing guidance systems
• CPC Class Codes: F42B 10/64 of fins
• CPC Class Codes: F42B 15/01 Arrangements thereon for guidance or control steering arrangements F42B10/60; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]
• CPC Class Codes: F42B 33/00 Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor F42B5/188 takes precedence; manufacturing processes for hollow charges F42B1/036; manufacture of blasting cartridge initiators F42B3/195

Abstract

A munition guidance system is disclosed. The system comprises a generally tubular enclosure, having an internal cavity adapted for receiving a munition, wherein an outer diameter of the enclosure is at most the largest outer diameter of the munition; and a processing and control unit enclosed within the enclosure and being configured for controlling guidance wings so as to maneuver the munition while flying.

Claims

1-22. -22. (canceled)

23. A munition guidance system, comprising:

an generally tubular enclosure, having an internal cavity adapted for receiving a munition, wherein an outer diameter of said enclosure is at most the largest outer diameter of said munition;

a plurality of guidance wings enclosed within said enclosure and configured for being erected outwardly from said enclosure;

a target identification unit for identifying a target; and

a processing and control unit enclosed within said enclosure and being configured for erecting said wings based on at least one criterion, and for controlling said guidance wings so as to maneuver said munition while flying;

wherein said at least one criterion is at least one of;

(i) time of flight of said munition, (ii) positive identification signal received from said target identification unit, and (iii) relative location data received from said target identification unit.

25. The system according to claim 23, being in a separate packing from said munition.

26. The system according to claim 23, further comprising an adaptor device having a protruding member compatible with a recess in said munition and an outer surface compatible with an inner surface of said enclosure.

27. The system according to claim 23, wherein said processing and control unit is configured for signaling said wings to maneuver said munition during flight responsively to target identification data received from said target identification unit.

28. The system according to claim 23, wherein said target identification unit comprises an optical identification unit.

29. The system according to claim 23, further comprising a global positioning system (GPS) for determining a location of said munition during flight, said GPS being associated with a data interface for receiving from an external source location data pertaining to an expected location of a target, and being configured for calculating expected relative location data based on said location of said munition and said expected location of said target.

30. The system according to claim 29, further comprising said guidance wings, wherein said guidance wings are enclosed within said enclosure and configured for being erected outwardly from said enclosure, and wherein said processing and control unit is configured for signaling said wings to erect and maneuver said munition during flight toward said target based on said relative location data.

35. The system according to claim 23, further comprising an inertial measurement unit (IMU) configured for sensing kinematic data pertaining to motion of said munition, wherein said processing and control unit is configured for processing said kinematic data to estimate a location of said munition during flight.

36. The system according to claim 23, wherein said enclosure comprises an opening for allowing an operator to access a safety element in said munition.

37. The system according to claim 23, wherein said enclosure comprises a collapsing member for triggering an impact fuse in said munition upon impact.

38. The system according to claim 23, wherein said processing and control unit is configured for detonating a warhead in said munition when said munition approaches a target.

39. The system according to claim 23, wherein said munition is a mortar shell.

40. A method of assembling a guided munition, comprising mounting the system according to claim 23, on a munition.

24. A munition guidance system, comprising:

an generally tubular enclosure, having an internal cavity adapted for receiving a munition, wherein an outer diameter of said enclosure is at most the largest outer diameter of said munition;

a plurality of guidance wings enclosed within said enclosure and configured for being erected outwardly from said enclosure;

a target identification unit for identifying a target;

a global positioning system (GPS) for determining a location of said munition during flight, said GPS being associated with a data interface for receiving from an external source location data pertaining to an expected location of a target, and being configured for calculating expected relative location data based on said location of said munition and said expected location of said target; and

a processing and control unit enclosed within said enclosure and being configured for erecting said wings based on at least one criterion, and for controlling said guidance wings so as to maneuver said munition while flying;

wherein said at least one criterion comprises at least one of;

(i) time of flight of said munition, (ii) positive identification signal received from said target identification unit, (iii) (iii) relative location data received from said target identification unit, and (iv) relative location data received from said GPS.

31. The system according to claim 24, wherein said processing and control unit is configured for selecting a single guidance scenario from the group consisting of:

a first guidance scenario in which said erecting and said maneuvering is responsive to relative location data received from said target identification unit, and a second guidance scenario in which said erecting and said maneuvering is responsive to relative location data received from said GPS but not from said target identification unit.

32. The system according to claim 31, wherein said processing and control unit is configured for selecting said first guidance scenario if a positive identification signal is received from said target identification unit within a predetermined time of flight.

33. The system according to claim 31, wherein said processing and control unit is configured for selecting said first guidance scenario if a positive identification signal is received from said target identification unit while an estimated distance to said target is above a predetermined distance threshold.

34. The system according to claim 31, wherein said processing and control unit is configured for selecting said first guidance scenario if a positive identification signal is received from said target identification unit while an estimated remaining time until impact is above a predetermined impact time threshold.