VTOL AIRCRAFT WITH CRUCIFORM ROTOR WING

• US 3,792,827 A
• Filed: 11/10/1972
• Issued: 02/19/1974
• Est. Priority Date: 11/10/1972
• Status: Expired due to Term

• Current Assignee: Peter F. Girard
• Original Assignee: Peter F. Girard
• Inventors: Girard, Peter F.
• Primary Examiner(s): Halvosa, George E. A.
• Assistant Examiner(s): Frankfort, Charles E.
• Application Number:
  US05/305,261
• Time in Patent Office: 466 Days
• Field of Search: 244/7R,7A,17.11 416/20
• US Class Current: 244/7.00A
• CPC Class Codes: B64C 27/026 Devices for converting a fixed wing into an autorotation rotor and viceversa

Abstract

An aircraft having a combined rotary and fixed wing providing aerodynamic support in vertical take-off and landing and in high speed cruising flight. The wing is cruciform in configuration, with four similar arms extending radially from a center body, the outer portions of the arms being pivotal and controllable in the manner of helicopter rotor blades in the rotating mode of the wing. In fixed wing mode the wing is locked with two arms longitudinal to the aircraft and the other two extending laterally, one or both of the lateral arm portions being used for roll control in forward flight. The wing arms may have air brakes to slow rotation and stop the wing in proper alignment. A common turbojet power source provides propulsion for wing rotation and cruising flight.

Claims

1. An aircraft, comprising:

an airframe having aerodynamic control surfaces thereon;

a wing mounted above said airframe for rotation about a substantially vertical axis;

said wing having a center body and four radially extending airfoil sectioned arms in cruciform configuration, each arm having a tip portion pivotally attached thereto for pitch change motion about a substantially radial axis;

control means coupled to said tip portions for pitch change actuation thereof;

means for locking the wing with two of said arms extending longitudinally over the airframe and the remaining two arms fixed transverse to the airframe for maintaining horizontal cruising flight;

a power source of compressed gases in said airframe and having a rearwardly opening tailpipe extending therefrom;

a pair of nozzles mounted below said two longitudinally extending arms inboard of the tip portions, said nozzles being oppositely directed substantially chordwise of the arms;

a branch duct connecting said tailpipe to said nozzles; and

a diverter valve at the junction of said tailpipe and branch duct, for directing gases selectively to said tailpipe and nozzles.

2. An aircraft according to claim 1, and including a control unit in the rear of said airframe, and a gas bleed pipe connecting said control unit to said branch duct;

said control unit having nozzles opening to opposite sides of the airframe, and valve means in the control unit for collective and proportional control of gas flow through the nozzles.

3. An aircraft according to claim 1, wherein said branch duct has a plenum chamber coaxial with the wing axis of rotation, and substantially radial ducts between the plenum chamber and said nozzles along the underside of said two arms.

4. An aircraft according to claim 1, wherein each of said tip portions has an air brake hinged in the underside to swing downwardly therefrom, and actuating means for selectively extending and retracting the air brakes.

5. An aircraft according to claim 1, wherein said aerodynamic surfaces include a fin extending downwardly below the rear portion of the airframe and having a shock absorbing lower tip;

said airframe having landing gear legs extending on opposite sides of the forward portion thereof and providing, with said shock absorbing tip, three point support for the aircraft.