Highly accurate long range optically-aided inertially guided type missile

• US 6,142,412 A
• Filed: 02/22/1999
• Issued: 11/07/2000
• Est. Priority Date: 02/22/1999
• Status: Expired due to Term

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: De Sa, Erwin M., Hanson, Clyde R.
• Primary Examiner(s): Gregory, Bernarr E.
• Application Number:
  US09/255,216
• Time in Patent Office: 624 Days
• Field of Search: 342/62, 342/63, 244/3.1, 244/3.11, 244/3.13, 244/3.14-3.17, 244/3.19, 244/3.2, 244/3.21, 244/3.22
• US Class Current: 244/3.16
• CPC Class Codes: F41G 7/306 for transmitting guidance signals; F41G7/308 takes precedence

Abstract

An optically-aided, inertially guided missile. The inventive missile includes a receiver for accepting guidance commands from a source located on an independent frame of reference relative to the missile and providing a first signal in response thereto. A filter is mounted on the missile for processing the first signal and providing a second signal in response thereto. The filter outputs commands to a navigation system which provides missile guidance commands in a conventional manner. In the illustrative implementation, the filter is a Kalman filter configured to eliminate the effects of gunner jitter and optical guidance system noise thereby significantly improving missile terminal performance at long ranges. In the illustrative implementation, the navigation system includes an inertial sensor assembly. The navigation system outputs a signal representative of missile-to-target cross track position and velocity in response to outputs from the sensor assembly and the filter. A guidance law is used by the system to compute missile acceleration commands in response to the missile-to-target cross track position and velocity. Thereafter, fin control commands are generated by an autopilot in response to the missile acceleration commands in a conventional manner.

Claims

1. An optically-aided, inertially guided type missile guidance system comprising:

receiver means located on the missile for receiving optically-aided commands from a source located on an independent frame of reference relative to the missile and providing a first signal in response thereto;

filter means mounted on said missile for processing said first signal and providing a second signal in response thereto; and

an inertial sensor assembly mounted on said missile for providing missile guidance commands in response to said second signal.

2. The invention of claim 1 wherein said receiver means is a radio frequency receiver.

3. The invention of claim 1 wherein said filter means is a Kalman filter.

4. The invention of claim 3 wherein said filter is configured to eliminate position error effects of gunner jitter.

5. The invention of claim 3 wherein said filter is configured to eliminate position error effects of optical guidance system noise.

6. The invention of claim 1 wherein said navigation means includes means responsive to said sensor assembly and said filter means for outputting a signal representative of missile-to-target cross track position.

7. The invention of claim 6 wherein said navigation means includes means responsive to said sensor assembly and said filter means for outputting a signal representative of missile-to-target cross track position and velocity.

8. The invention of claim 7 wherein said navigation means further includes means responsive to said signal representative of missile-to-target cross track position and velocity for generating missile acceleration commands.

9. The invention of claim 8 wherein said navigation means further includes an autopilot responsive to said missile acceleration commands for generating fin commands.

10. An optically-aided, inertially guided type missile comprising:

a frame adapted to carry a payload;

a propulsion mechanism mounted on said frame;

a guidance mechanism for changing a velocity vector of said missile; and

a guidance system, located on said frame for providing guidance commands to said guidance mechanism, said guidance system comprising;

receiver means for receiving commands from a source located on an independent platform and providing a first signal in response thereto;

a Kalman filter for processing said first signal and providing a second signal in response thereto; and

an inertial sensor assembly for providing missile guidance commands in response to said second signal.

11. The invention of claim 10 wherein said receiver means is a radio frequency receiver.

12. The invention of claim 10 wherein said navigation means includes means responsive to said sensor assembly and said filter for outputting a signal representative of missile-to-target cross track position.

13. The invention of claim 12 wherein said guidance system includes means responsive to said sensor assembly and said filter for outputting a signal representative of missile-to-target cross track position and velocity.

14. The invention of claim 13 wherein said guidance system further includes means responsive to said signal representative of missile-to-target cross track position and velocity for generating missile acceleration commands.

15. The invention of claim 14 wherein said guidance system further includes an autopilot responsive to said missile acceleration commands for generating fin commands.