System for destroying ballistic missiles

• US 6,209,820 B1
• Filed: 07/19/1999
• Issued: 04/03/2001
• Est. Priority Date: 07/22/1998
• Status: Expired due to Term

• Current Assignee: Ministry of Defense
• Original Assignee: Ministry of Defense Armament Development Authority
• Inventors: Rom, Hanan, Golan, Oded M., Yehezkely, Oded
• Primary Examiner(s): Gregory, Bernarr E.
• Application Number:
  US09/356,986
• Time in Patent Office: 624 Days
• Field of Search: 244/3.1, 244/3.11, 244/3.14-3.19, 244/3.13, 244/3.24-3.29
• US Class Current: 244/3.15
• CPC Class Codes: F41G 7/2206 using a remote control station
• CPC Class Codes: F41G 7/34 based on predetermined target position data

Abstract

A system for intercepting targets having predictable flight trajectory, the system comprising a platform carrying an interceptor missile which includes a seeker unit, propulsion system steering system and destruction capability system, all communicating with a processor device. The processor device is further coupled to a data link for communicating with the platform. In response to launching of the intercepting missile, the processor device controls the steering system and propulsion system for steering the missile in one of the following flight modes: (a) approach mode, wherein said intercepting missile closes on said target; (b) trajectory matching mode wherein the interceptor velocity vector is modified to bring the trajectory of the interceptor to match the predicted trajectory of the target so that the interceptor moves in the same direction as the target in a relatively small closing velocity with respect to the target; and (c) end game mode wherein the interceptor is maneuvered to a distance sufficiently close to the target whereby the target destruction capability can be activated efficiently.

Claims

1. A system for intercepting targets having predictable flight trajectory, comprising:

(i) a platform carrying at least one interceptor missile;

the interceptor missile includes a seeker unit, propulsion system, steering system, and target destruction capability system all communicating with a processor device;

said processor device is further coupled to a data link for communicating with at least said platform;

(ii) the processor device, in response to launching of said interceptor missile, for controlling said steering system and propulsion system for steering said missile in at least the following flight modes;

(a) approach mode, wherein said interceptor missile closes on said target;

(b) trajectory matching mode wherein a velocity vector of the interceptor missile is modified to substantially match a predicted trajectory of the target so that the interceptor missile moves in the same direction as the target in a relatively small closing velocity with respect to the target; and

(c) end game mode wherein the interceptor missile is maneuvered to a distance sufficiently close to the target whereby said target destruction capability system will destroy the target on activation.

2. The system according to claim 1, wherein said interceptor missile moves in the direction of the target and is positioned ahead of the target and moves at slower velocity than the target.

3. The interceptor of claim 2, wherein the seeker is operational during the end-game mode and is mounted on the interceptor such that its axis is pointing opposite to the direction of the motion of the interceptor, to observe the target, which is approaching from behind.

4. The system according to claim 2, wherein said processor controls said steering system and said propulsion system and activates said target destruction capability system also on the basis of commands received from said platform or other source.

5. The system according to claim 1, wherein said interceptor missile moves in the direction of the target and is positioned behind the target and moves at faster velocity than the target.

6. The system of claim 1, wherein said processor is further capable of pre-planning the flight trajectory of said interceptor missile in order to determine the time of launch of the interceptor missile, as stipulated in (ii).

7. The system of claim 6, wherein said processor device further communicates through said data-link with an early warning system.

8. The system of claim 6, wherein said pre-planning includes:

selecting an intercepting zone;

determining approach flight mode parameters;

determining trajectory matching mode parameters,

to obtain said interception timing.

9. The system of claim 8, wherein said approach flight parameters include:

interception plane, initial trajectory bending.

10. The system according to claim 8, wherein said trajectory matching flight parameters include:

initial missile position, thrust duration and thrust direction.

11. The system according to claim 1, wherein the target having predictable flight trajectory being a ballistic missile (BM).

12. The system according to claim 1, wherein said platform being a stationary platform.

13. The system according to claim 1, wherein said platform being an air vehicle.

14. The system according to claim 1, wherein said platform being a maritime vehicle.

15. The system according to claim 1, wherein said platform being a motorized land vehicle.

16. The system according to claim 1, wherein said platform being a space vehicle.

17. The system according to claim 1, wherein the processor device is configured to modify interception parameters during said modes in a closed loop fashion according to updated information about the target.

18. An intercepting missile including:

(i) a seeker unit, propulsion system, steering system and destruction capability system all communicating with a processor device;

said processor device is further coupled to a data link for communicating with at least said platform;

(ii) the processor device, in response to launching of said intercepting missile, for controlling said steering system and propulsion system for steering said missile in at least the following flight modes;

(a) approach mode, wherein said missile closes on a target;

(b) trajectory matching mode wherein a velocity vector of the missile is modified to bring a trajectory of the missile to substantially match a predicted trajectory of the target so that the missile moves in the same direction as the target in a relatively small closing velocity with respect to the target; and

(c) end game mode wherein the missile is maneuvered to a distance sufficiently close to the target whereby said target destruction capability system will destroy the target upon activation.