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Helicopter integrated fire and flight control having constraint limiting control

  • US 5,310,136 A
  • Filed: 05/19/1992
  • Issued: 05/10/1994
  • Est. Priority Date: 05/19/1992
  • Status: Expired due to Term
First Claim
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1. An aircraft flight control system for providing control surface command signals to the aircraft control surfaces thereby controlling the yaw, pitch, roll and lift attitude axes of the aircraft in flight, comprising:

  • means for providing a constraint limit in a given attitude axis with respect to an aircraft reference axis, said constraint limit being indicative of a limit relative to said reference axis for a given aircraft subsystem;

    means for providing a signal for constraint limiting for said given attitude axis, said signal for constraint limiting being indicative of a current operating position of said given aircraft subsystem in said given attitude axis relative to said reference axis;

    means responsive to said signals for constraint limiting and said constraint limit for providing constraint limiting axis command signals indicative of an amount the magnitude of said signal for constraint limiting exceeds said constraint limit for said given attitude axis;

    constraint limiting mode indicating means for providing a constraint limiting signal in response to activation of a flight control system constraint limiting mode; and

    signal processing means responsive to the presence of said constraint limiting signal for providing control surface command signal for driving the magnitude of said constraint limiting axis command signals to zero.

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