VTOL ROTOR WING DRONE AIRCRAFT

• US 3,794,273 A
• Filed: 09/25/1972
• Issued: 02/26/1974
• Est. Priority Date: 09/25/1972
• Status: Expired due to Term

• Current Assignee: Peter F. Girard
• Original Assignee: Peter F. Girard
• Inventors: Girard, Peter F.
• Primary Examiner(s): Reger, Duane A.
• Assistant Examiner(s): Reese, Randolph A.
• Application Number:
  US05/291,582
• Time in Patent Office: 519 Days
• Field of Search: 244/2,6,7R,7A,7B,7C,8,15,17.11,17.19,39,45R,46,47,48 416/143,121,130,171,120
• 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 capable of vertical take-off and landing and high speed cruising flight, utilizing a combine rotary and fixed wing. The wing has a large center body with three radial arms which are pivotal and controllable in the manner of helicopter rotor blades in the wing rotating operation, and incorporate spoilers to minimize center of pressure shift during transition between rotary and fixed modes. In fixed position the wing is stopped with one arm forward in a modified delta configuration, the lateral arms being movable for roll control in cruising flight. Propulsion is by means of a turbojet providing cruising thrust and also wing rotating thrust through tip nozzles in a beam mounted below the wing. In stopped position, the beam is streamlined in alignment with the forward arm, and for rotary wing mode the beam is rotationally displaced relative to the wing to clear the movable arm.

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 three radially extending airfoil sectioned arms, each pivotally attached to the center body for pitch change motion about a substantially radial axis;

control means coupled to said wing arms for pitch change operation thereof;

means for locking said wing with one of said arms extending longitudinally forwardly over the airframe;

a beam mounted below said wing for limited rotation, relative to said wing, about the wing rotational axis, and having oppositely directed propulsion nozzles at opposite ends thereof;

actuating means for moving said beam between a fixed wing position in longitudinal alignment below said one wing arms, and an offset position clear of the wing arms;

a power souce of compressed gases mounted in said airframe;

gas conducting means connected to said power source, including a rearwardly directed tailpipe and a branch duct communicating with said nozzles; and

a diverter valve in said gas conducting means for directing gases slectively to said tailpipe and said nozzles.

2. An aircraft according to claim 1, wherein said beam fits closely against the underside of said wing and is streamlinEd therewith in the fixed wing position.

3. An aircraft according to claim 2, wherein said beam has a plenum chamber coaxial with the axis of rotation, with ducts extending from the plenum chamber to said nozzles;

said branch duct having a sealed rotary connection to said plenum chamber.

4. An aircraft according to claim 1, and including a control unit in the rear portion of said airframe, with a gas bleed connection to said branch duct;

said control unit having directional control nozzles opening to opposite sides of the airframe; and

a directional control valve in said control unit, with actuating means for varying the proportion of gas flow through said directional control nozzles.

5. An aircraft according to claim 4, and including modulating valve means in said control unit for varying the total gas flow through the directional control nozzles.

6. An aircraft according to claim 1, wherein each of said wing arms has a lift spoiler hinged in the upper surface thereof;

and spoiler actuating means in the wing for moving said spoilers between extended and retracted positions.

7. An aircraft according to claim 6, wherein said spoiler actuating means includes means for retracting the spoiler in said one wing arm independently of the other spoilers.

8. An aircraft according to claim 1, wherein said aerodynamic surfaces include a fin extending downwardly from the rear portion of said airframe;

a pair of landing gear legs extending from opposite sides of the forward portion of the airframe;

said fin having a lower tip portion comprising a third supporting element of the landing gear.