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Aircraft with improved aerodynamic performance

  • US 9,284,046 B2
  • Filed: 05/30/2011
  • Issued: 03/15/2016
  • Est. Priority Date: 02/14/2011
  • Status: Active Grant
First Claim
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1. An aircraft with improved aerodynamic performances, for maintaining direction stability and optimal aerodynamic behaviour with a medium-high incidence;

  • said aircraft comprising a fuselage to which wings are associated, at least one air intake and a nose with a tapered section, and at least one engine;

    wherein said aircraft comprises a control device of the vortex of a leading edge extension of the wing leading edge root extension, in which the ratio between the surface of one leading edge extension and a height of a corresponding control device is 2.35 m with a variable tolerance in a range from 100% and −

    50% of the ratio, comprising between 1.175 m and 4.70 m, said control device of the vortex generated by the edge, cooperates with a tail, obtained by coupling of a vertical tail with the wings whose leading edges penetrate trailing edges of each wing;

    an equipment comprising at least one dissipating device of incident radar waves which is removably applied on at least one hot portion of the aircraft;

    the at least one hot portion of the aircraft comprising;

    a piloting cabin or cockpit having at least one transparent portion;

    a fuselage frame;

    a plurality of leading edges of components, the components comprising wings, tail veils and air intakes of the at least one engine;

    at least one engine face;

    wherein to reduce radar marking from the at least one engine face, the equipment comprises at least one grid having an inner structure with a plurality of apertures, and a support structure having a plurality of rings securing said grid to the aircraft;

    each of the apertures comprises an internal surface coated with radar absorbing material adapted to absorb electromagnetic waves at high frequency;

    said grid is adapted to permit entry of air flow towards the at least one engine and reduce radar visibility of the at least one engine face of the aircraft.

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