Hybrid semi-strapdown infrared seeker

• US 4,615,496 A
• Filed: 01/03/1985
• Issued: 10/07/1986
• Est. Priority Date: 01/03/1985
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Pinson, George T.
• Primary Examiner(s): Jordan, Charles T.
• Application Number:
  US06/688,532
• Time in Patent Office: 642 Days
• Field of Search: 244/3.16
• US Class Current: 244/3.16
• CPC Class Codes: F41G 7/008 Combinations of different guidance systems
• CPC Class Codes: F41G 7/2213 maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro
• CPC Class Codes: F41G 7/2226 comparing the observed data with stored target data, e.g. target configuration data
• CPC Class Codes: F41G 7/2253 Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
• CPC Class Codes: F41G 7/2293 using electromagnetic waves other than radio waves

Abstract

A hybrid semi-strapdown infrared seeker for mounting in a missile or the like. The seeker processing both imaged and non-imaged data available around a potential target area displayed on a vidicon and providing a level of target identification, target discrimination, target acquisition and attack at the target'"'"'s controid or other selected points on the target.

Claims

1. An infrared seeker adapted for gimballed or non-gimballed mounting in a missile and the like, the seeker comprising:

3. The seeker as described in claim 1 further including pitch, yaw and roll rate sensors having an input connected to the microprocessor for providing missile dynamic feedback and stabilization input for missile guidance control during target acquisition.

4. The seeker as described in claim 1 further including a target dynamic algorithm and a missile guidance and control algorithm connected to the microprocessor to provide missile guidance and control data to a missile control system, the target dynamics algorithm connected to a pointer and tracker controller for providing X and Y coordinates of the target to X axis and Y axis controls.

5. The seeker as described in claim 3 including drive motors connected to the X axis and Y axis controls for receiving the X and Y axis control data from the pointer and tracker controller, the drive motors used for orienting the vidicon toward the target field of view.

6. The seeker as described in claim 1 further including filters disposed in front of the vidicon for receiving infrared energy thereon and optics mounted in front of the filters.

8. The seeker as described in claim 6 further including a pointer and tracker controller connected to the target dynamics algorithm and the scan control for providing X and Y coordinates to drive motors used in orienting the vidicon toward the possible target.

10. The seeker as described in claim 6 further including pitch, yaw and roll rate sensors having an input connected to the microprocessor for providing missile dynamic feedback and stabilization input for missile guidance control during target acquisition.

2. a vidicon adapted for mounting on the missile and directed toward a target area, the vidicon having a vidicon controller connected thereto;

a threshold detector connected to the vidicon for receiving vidicon output therefrom, the threshold detector having a threshold control for providing a threshold setting to the detector, the vidicon output when in a non-imaging mode compared with the threshold setting and when the output exceeds the setting that area on the vidicon is considered a possible target;

an analog to digital converter connected to the detector for receiving the possible target data;

a video preprocessor connected to the converter for conditioning the target data;

a computer central processing unit having a microprocessor connected to the preprocessor, the unit having a target detector and acquisition algorithm for determining whether or not the potential target data meets a predetermined criteria, the microprocessor having an image processor; and

a scan control connected to the microprocessor and the vidicon controller, the scan control expanding the scan around the area of the potential target and if the potential target data meets the predetermined criteria the vidicon output from the expanded area is sent to the image processor for determination of the validity of the target.

7. An infrared seeker adapted for gimballed or non-gimballed mounting in a missile and the like, the seeker comprising:

a vidicon with vidicon face and appropriate filters and optics disposed in front thereof and directed toward a target area, the vidicon having a vidicon controller;

a threshold detector connected to the vidicon for receiving vidicon output therefrom, the threshold detector having a threshold control for providing a threshold setting to the detector, when the vidicon output when compared with the threshold setting exceeds the setting then that area on the vidicon face is considered a possible target;

an analog to digital converter connected to the detector for receiving the possible target data;

a video preprocessor connected to the converter for conditioning the target data;

a central processing unit having a microprocessor connected to the preprocessor, the unit having a target detector and acquisition algorithm for determining whether the potential target data meets a predetermined criteria, the microprocessor including an image processor, the unit further including target dynamics algorithms and missile guidance and control algorithms connected to a control system of the missile; and

a scan control connected to the microprocessor and the vidicon controller, the scan control also expanding the scan area of the potential target and if the potential target area meets the predetermined criteria the vidicon output of the expanded area is sent to the image processor for the determination of the validity of the target.

9. The seeker as described in claim 7 further including X axis and Y axis controls connected to the drive motors and the pointer and tracker controller.