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Low cost flight instrumentation system

  • US 9,057,627 B2
  • Filed: 03/14/2006
  • Issued: 06/16/2015
  • Est. Priority Date: 03/15/2005
  • Status: Expired due to Fees
First Claim
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1. A backup display system for use in a general aviation aircraft, said backup display system configured to provide flight condition information in the event of partial or complete inoperability of a primary flight instrument system on said general aviation aircraft, said backup display system comprising:

  • a source of electrical power situated on said general aviation aircraft;

    a plurality of sensors situated on said general aviation aircraft and configured to collect flight data;

    a processor situated on said general aviation aircraft and cooperative with said source of electrical power and signally coupled to said plurality of sensors such that said processor operates on said collected flight data to generate at least a portion of said flight condition information without need for input from neither a global positioning system nor an inertial navigation system to said display system, said generated flight condition information comprising at least flight path angle, turn rate, and lateral acceleration; and

    a display situated on said general aviation aircraft and signally coupled to said processor such that said display conveys said generated flight condition information in such a way as to provide a pilot with a reduced cognitive workload, wherein said flight condition information conveyed by said display further comprises bank angle information that is estimated in said processor according to the following formula;


    sin((φ

    )=(−

    r{dot over (γ

    )}+q


    {square root over (r2+q2

    {dot over (γ

    )}2)})/(r2+q2)for situations where r≧

    0,and by the following formula;


    sin(φ

    )=−

    r{dot over (γ

    )}−

    q


    {square root over (r2)}+q2

    {dot over (γ

    )}2)/(r2+q2)for situations where r<

    0,where φ

    represents said bank angle information, γ

    represents said flight path angle, {dot over (γ

    )} is the rate of change in flight path angle, q represents aircraft pitch rate and r represents aircraft yaw rate,
    sin((φ

    )=(−

    r{dot over (γ

    )}+q


    {square root over (r2+q2

    {dot over (γ

    )}2)})/(r2+q2)for situations where r≧

    0,and by the following formula;


    sin(φ

    )=−

    r{dot over (γ

    )}−

    q


    {square root over (r2+q2

    {dot over (γ

    )}2)})/(r2+q2)for situations where r<

    0,where φ

    represents said bank angle information, γ

    represents said flight path angle, {dot over (γ

    )} is the rate of change in flight path angle, q represents aircraft pitch rate and r represents aircraft yaw rate.

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