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HYBRID STRAPDOWN GUIDANCE SYSTEM

  • US 3,746,281 A
  • Filed: 08/04/1971
  • Issued: 07/17/1973
  • Est. Priority Date: 08/04/1971
  • Status: Expired due to Term
First Claim
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1. A missile with an airframe and a guidance system comprising:

  • a space-stable platform in said missile;

    means mounted on said platform for sensing pitch and yaw acceleration and providing pitch and yaw acceleration signals;

    means mounted on said platform for sensing vertical acceleration of said platform and for providing a vertical acceleration signal;

    a guidance computer having inputs to which said pitch, yaw, and vertical acceleration signals are applied and having respective outputs for a missile engine cut-off signal, for pitch guidance signals and for yaw guidance signals;

    first and second transducers mounted between said stable platform and the airframe of said missile for respectively responding to the angles between said platform and pitch and yaw axes and for providing respective pitch and yaw angle signals;

    a signal processor having respective inputs for each of said pitch and yaw guidance signals, and said pitch and yaw angle signals, said processor also having respective outputs for pitch and yaw command signals;

    a sensor mounted on said missile airframe for sensing roll of said missile about its longitudinal axis and for providing a signal related to the roll angle;

    a plurality of aerodynamic control surfaces on said missile airframe; and

    a respective plurality of actuators for said control surfaces, with said pitch and yaw command signals applied to respective inputs of said actuators, and with said roll signal applied to inputs of said actuators.

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