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Method and guidance system for guiding a missile

Imported: 24 Feb '17 | Published: 06 Jan '04

Christer Regebro

USPTO - Utility Patents

Abstract

The present invention relates to a method and an arrangement for guiding a missile. In accordance with the prior art, the angle position of a target (

9) when the missile (

3) is expected to reach the target is predicted on the basis of the angular velocity determined in a preceding time period. In order to improve the strike accuracy, the operator, in a second subsequent time period, tracks the actual position of the missile in relation to the predicted angle position of the target. If a deviation is observed, a correction command is transmitted to the missile in order to correct the missile trajectory. For this purpose, a communications link is provided to transmit the correction command given by the operator.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

The invention will be described in greater detail below by way of example, and with reference to the attached drawings, in which:

FIG. 1 is a diagrammatic representation of a portable anti-tank weapon provided with a guidance system according to the invention.

FIG. 2 is a diagrammatic illustration showing a missile being guided towards an enemy tank with correction of the trajectory in accordance with the invention.

FIGS. 3

a-

3

c illustrate three different missile positions relative to an enemy tank.

FIG. 4 illustrates correction zones relative to an enemy tank in the case where correction can be done in two steps.

FIG. 5 is a diagrammatic representation of the transmit side of a communications link incorporated in a guidance system according to the invention.

FIG. 6 is a diagrammatic representation of the receive side of a communications link incorporated in a guidance system according to the invention.

Claims

1. A method for guiding a missile fired at a target, the method comprising:

2. The method according to claim 1, wherein upon receipt of the correction command the trajectory of the missile is corrected in steps in a direction counter to the deviation.

3. The method according to claim 2, wherein correction of the trajectory of the missile is carried out in at least one step.

4. The method according to claim 1, wherein a deviation of the determined angular velocity of the target is detected in the second time period, and wherein the trajectory of the missile is corrected stepwise in proportion to a firing distance in a direction counter to the deviation of the target angular velocity upon receipt of a correction command.

5. The method according to claim 1, wherein correction of the trajectory of the missile is carried out for target distances greater than 300 meters.

6. A missile guidance system, comprising:

7. The guidance system according to claim 6, wherein the communications link is connected to a firing mechanism of the missile, the system further comprising:

8. The guidance system according to claim 6, wherein the communications link comprises a receiver operative to receive the correction commands and a computer unit connected to the receiver.

9. The guidance system according to claim 8, wherein the communications link comprises an operator unit operative to use control algorithms to guide the missile in the desired trajectory, the guidance system further comprising:

10. The guidance system according to claim 9, wherein the control device comprises hot gas propulsion via valves.

11. The guidance system according to claim 9, wherein the control device comprises with aerodynamic control surfaces.

12. The guidance system according to claim 6, wherein the communications link operates with amplified coherent light.