V/STOL Aircraft

• US 4,469,294 A
• Filed: 05/20/1982
• Issued: 09/04/1984
• Est. Priority Date: 05/20/1982
• Status: Expired due to Fees

• Current Assignee: Clifton, Robert T.
• Original Assignee: Clifton, Robert T.
• Inventors: Clifton, Robert T.
• Primary Examiner(s): Blix, Trygve M.
• Assistant Examiner(s): Shum, Ivy M.
• Application Number:
  US06/380,480
• Time in Patent Office: 838 Days
• Field of Search: 244/12.1, 244/12.3, 244/6.7 A, 244/8, 244/10, 244/21, 244/23 B, 244/60, 244/45
• US Class Current: 244/12.3
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 39/08 having multiple wings
• CPC Class Codes: B64C 39/12 Canard-type aircraft

Abstract

A V/STOL aircraft comprising a fuselage, having three sets of wings that are offset lengthwise and vertically. The center set of relatively small relatively thick wings 34 between the canard 14 and the rear relatively thin relatively large aerodynamic lift wings 18 are equipped with identical lift fans 36 enclosed in the wing by upper and lower movable slotted deflectors 40. The attitude of the slatted deflectors may be varied to transition the present invention from hovering to forward flight, and vice versa. The present invention'"'"'s lift fans are interconnected by a balanced power distribution system, to insure constant, efficient use of total power and provide symmetrical lift about the aircraft'"'"'s center of gravity resistibility. In the event of an engine failure, the remaining lift is still properly distributed to maintain symmetrical lift, so as to maintain balance and operational control of the aircraft in the lift mode.

Claims

1. A vertical and short take-off and landing aircraft comprising:

a fuselage made of foamed core material;

a set of canard wings attached to said fuselage forward of the center of gravity of said aircraft, said canard wings including elevator members pivotally attached thereto for controlling pitch of said aircraft;

a second set of lift fan wings, having relatively thick cross-section, attached to said fuselage at about the center of gravity of said aircraft, each one of said second set of lift fan wings comprises;

a generally circular duct extending vertically through said wing;

a multi-bladed fan mounted for free rotation axially in said duct;

prime mover means for selectively applying rotational torque to said fan, said prime mover means arranged so as to drive said fans in contrarotation to each other;

said prime mover means comprising at least two engines driving a central shaft, said engines capable of producing in excess of one horsepower per pound of engine weight;

means for selectively applying the rotation of the center shaft to the lift fans;

second shaft transmission means for selectively applying rotation of said central shaft to a pusher propeller located aft of said lift wings; and

fan control means for controlling the inflow and outflow of gas through said circular duct comprising;

pivoted openable forward opening inlet control vanes in the duct inlet, the upper surface of said vanes being shaped so that they form an airfoil when the vanes are closed, the forward end of one of said vanes being adapted to be received in flush mating engagement with the rearward portion of an adjacent vane, said forward opening inlet control vanes for causing forward motion of said aircraft to produce a ram air effect in said duct;

pivoted discharge vanes on the underside of said duct to direct the discharge of fluid through said duct; and

at least one control arm connected to said vanes for causing the simultaneous movement of said vanes;

a third set of relatively thin main lift wings attached to said fuselage aft of the center of gravity of said aircraft, said third set of lift wings including ailerons pivotally connected thereto; and

orthogonal working surfaces arranged aft of said pusher propeller.