Fiber optic track/reaim system

• US 4,611,771 A
• Filed: 04/18/1985
• Issued: 09/16/1986
• Est. Priority Date: 04/18/1985
• Status: Expired due to Fees

• Current Assignee: United States Of America As Represented By The Secretary Of The Army (Government of the United States of America)
• Original Assignee: United States Of America As Represented By The Secretary Of The Army (Government of the United States of America)
• Inventors: Gibbons, John P., Powell, Rex B.
• Primary Examiner(s): Jordan, Charles T.
• Application Number:
  US06/724,432
• Time in Patent Office: 516 Days
• Field of Search: 244/3.12, 244/3.11
• US Class Current: 244/3.12
• CPC Class Codes: F41G 7/32 for wire-guided missiles

Abstract

In a missile tracking and guidance system, a fiber optic link is maintained between a missile and the launcher. Tracking after launch is via a video link between the missile seeker and a video imager at the launcher. Guidance signals are derived from the video signal input to the imager and transmitted back to the missile. Additionally, rate sensors and an interrupt or reaim circuit within the launcher allows an operator to reacquire the target for refining the missile seeker look axis toward a target during flight. After the target aimpoint is refined the operator can then release the interrupt circuit, allowing the system to continue tracking from the video input, with a newly established seeker heading established during the aimpoint refinement.

Claims

1. In a missile system wherein a missile is launched from a movable housing and directed toward a target, a missile guidance method comprising the steps of:

launching a missile along a selectable path,

generating azimuth and elevation guidance commands for said missile at a tracker station on said movable housing,

guiding said guidance commands along a confined optical path from the tracker station to the missile,

optically imaging a selectable field of view along and adjacent to said path ahead of said missile,

guiding a video signal of said optical imaging from said missile to said tracker station along said confined optical path for providing selectable missile azimuth and elevation guidance signals to the tracker,

directing said video signal to a video display on said movable housing for providing a visual image of optically imaged scenes,

measuring the angular rate of movement of said movable housing for providing azimuth and elevation signals indicative of changes in direction of movement of said tracker and said video display,

coupling the azimuth and elevation signals obtained from the measured angular rate of movement as a selectable input to said tracker station, and

controllably switching between said video signal azimuth and elevation input signals to the tracker station and said angular rate azimuth and evaluation input to the tracker station for controlling said generating of azimuth and elevation guidance commands.

2. A method of missile guidance as set forth in claim 1 and further comprising the steps of:

selecting said angular rate azimuth and elevation input to the tracker station during the step of controllably switching, and

selectably moving said housing to generate a desired change in azimuth and elevation signals for changing the azimuth and elevation guidance commands and thereby changing said optically imaged, selectable field-of-view.

3. A method of missile guidance as set forth in claim 1 and further comprising the steps of:

measuring the angular rate of movement of the movable housing by continuously sensing the movable platform angular motion,

providing variable electrical signal outputs in response to said sensing, and

integrating and shaping said electrical signal outputs to provide azimuth and elevation signals to the tracker station only in response to switching by said step of controllably switching said angular rate input to the tracker.

4. In a missile system wherein a missile having a video imaging seeker for scanning a selectable look angle is launched from a portable launcher comprising a launch tube, a missile tracker, a video display, a switching circuit for controlling the source of missile guidance commands, and angular rate sensors all supported on said portable launcher;

a missile guidance method comprising the steps of;

aiming and launching a missile from said launch tube along a selectable path,

directing azimuth and elevation guidance signals from said angular rate sensors to said tracker,

transmitting azimuth and elevation guidance commands from said tracker to said missile during and after launching of said missile,

optically imaging a video image signal from said imaging seeker in said video display of visual scenes ahead of said missile seeker,

confining said azimuth and elevation commands directed from the tracker to the missile and said video image signal to a common, meandering optical path between said tracker and said missile,

coupling said video image signal to said tracker,

processing said video image signal by said tracker to derive missile azimuth and elevation guidance signals indicative of missile trajectory coordinates and sensor look angle, and

releasably switching between the azimuth and elevation guidance signals from said angular rate sensors and the derived azimuth and elevation signals for providing alternatively selectable azimuth and elevation guidance commands.

5. A missile guidance method as set forth in claim 4 wherein said step of releasably switching for providing alternatively selectable azimuth and elevation guidance commands further comprises the steps of:

activating said switching circuit to activate said guidance commands from said angular rate sensors and to suppress said derived guidance signals, and

deactivating said switching circuit to deactivate said guidance commands from said angular rate sensors and to activate said derived guidance signals.

6. In a missile system wherein a missile is launched from a portable launcher, the improvement of a missile guidance system comprising:

a tracker mounted on said portable launcher, a fiber optic link coupled between said missile and said tracker for coupling tracking commands to and video signals from said missile, said tracker receiving said video signals and providing azimuth and elevation commands in response to said video signals, a television display mounted on said launcher and being further coupled to receive said video signals for displaying a video image from said missile on said display, angular rate sensing means mounted on said portable launcher for sensing angular motion of said launcher, and signal processing means coupled between said sensing means and said tracker for providing signals indicative of launcher azimuth and elevation aimpoint changes to said tracker.

7. A missile guidance system as set forth in claim 6 and further comprising switching means coupled to said tracker for controlling passage of said video signals through said tracker, and said switching means being further coupled to said signal processing means for controlling passage of said signals indicative of launcher azimuth and elevation aimpoint changes through said processing means.

8. A missile guidance system as set forth in claim 7 wherein said switching means has first and second operating states, said first state allows said video signal derived azimuth and elevation signals to be coupled as command outputs from said tracker for automatic guidance of said missile, and said switching means, when in said second state, suppresses video signal processing and activates processing of said signals indicative of launcher azimuth and elevation aimpoint changes as a command output.

9. A missile guidance system as set forth in claim 6 wherein said missile has a seeker therein for measuring the line-of-sight rate along a missile look angle, said missile seeker providing said video signals for coupling to said tracker and television display, and said tracker responding to said video signal input to generate azimuth and elevation commands for directing the missile flight path along the look angle.