Rate aided tracking for launch transient survivability

• US H455 H
• Filed: 10/28/1987
• Issued: 04/05/1988
• Est. Priority Date: 10/28/1987
• Status: Abandoned Application

• Current Assignee: Monte K. Helton
• Original Assignee: Monte K. Helton
• Inventors: Helton, Monte K.
• Primary Examiner(s): Jordan, Charles T.
• Application Number:
  US71/171,61
• Time in Patent Office: 160 Days
• CPC Class Codes: F41G 7/2213 maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro

Abstract

Rate aiding tracking prevents or dampens the effect of large scale target tion on a missile borne tracker during transition of a missile from prelaunch tracking to post launch tracking. Rate aided tracking includes a feedback network responsive to existing stable platforms for combining a tracker output signal with a rate signal that is itself responsive to torques present on a stable platform due to target sensor motion. The feedback network includes an integrator and a transformation circuit and is active only during the missile launching phase of operation when transient effects are manifest.

Claims

1. In a target tracking system wherein a target sensor on a missile is directed by a tracker to maintain track of a target position by summing the line-of-sight deviation of the target from the reference axis of a stable platform on the missile, the improvement comprising:

a rate aiding circuit coupled between the stable platform and the tracker for stabilizing the tracker input signals during the missile launching transition period, said rate aiding circuit having at least first and second inputs and an output for receiving input signals from the stable platform and from the tracker respectively and providing a maximum output signal to the tracker during the launching transition period and a minimum output signal thereafter.

2. In a target tracking system as set forth in claim 1 said rate aiding circuit comprising:

an integrator coupled to receive a signal indicative of changes occurring in stable platform position and for providing an integrated signal output, a disable circuit having an input coupled to the integrator output for providing a maximum gain output; and

a summing circuit having first and second inputs and an output, said first input being coupled to the output of said disable circuit, said second input being coupled to receive the output from said tracker, and said output being coupled to provide an input to said tracker during missile launch.