Tandem-rotor gyroplane

• US 6,089,501 A
• Filed: 06/22/1998
• Issued: 07/18/2000
• Est. Priority Date: 06/22/1998
• Status: Expired due to Fees

• Current Assignee: Stanley A. Frost
• Original Assignee: Stanley A. Frost
• Inventors: Frost, Stanley A.
• Primary Examiner(s): Carone, Michael J.
• Assistant Examiner(s): FRENCH, FREDRICK T
• Application Number:
  US09/102,485
• Time in Patent Office: 757 Days
• Field of Search: 244/8, 244/17.11, 244/17.23, 244/17.25
• US Class Current: 244/8
• CPC Class Codes: B64C 2027/8227 comprising more than one rotor
• CPC Class Codes: B64C 2027/8236 including pusher propellers
• CPC Class Codes: B64C 27/021 Rotor or rotor head construction for helicopters B64C27/32
• CPC Class Codes: B64C 27/028 Other constructional elements; Rotor balancing
• CPC Class Codes: B64C 27/08 with two or more rotors

Abstract

A tandem-rotor autogiro has a control system that facilitates operation of the tandem-rotor autogiro by fixed-wing aircraft pilots, without the requirement of extensive additional flight training. The autogiro includes forward and rearward non-powered rotors mounted in tandem on the fuselage of the aircraft. The forward rotor is controlled by manipulation of a control stick, and the rearward rotor is controlled by manipulation of foot operated pedals and trim control sticks. In a preferred embodiment the forward rotor is mounted in a plane vertically above a plane of the rearward rotor so as to facilitate an efficient aerodynamic air flow through the rotors.

Claims

1. An autogiro comprising:

a fuselage having forward, rearward, port and starboard regions;

a power unit capable of propelling said fuselage;

forward and rearward non-powered rotor units mounted in tandem on said fuselage, each rotor unit being capable of tilting movement with respect to said fuselage in any selected

a first control input device operatively connected to said forward rotor unit wherein manipulation of said first control input device causes tilting movement of said forward rotor unit in any selected azimuth with respect to said fuselage.

2. The autogiro of claim 1 wherein said first control input device comprises a control stick mounted within said fuselage and wherein forward manipulation of said control stick causes attendant forward tilting movement of said forward rotor unit with respect to said fuselage and wherein rearward manipulation of said control stick causes attendant rearward tilting movement of said forward rotor unit with respect to said fuselage.

3. The autogiro of claim 1 wherein said first control input device comprises a control stick mounted within said fuselage and wherein manipulation of said control stick toward the port region of the fuselage causes attendant tilting movement of said forward rotor unit toward the port region of the fuselage and wherein manipulation of said control stick toward the starboard region of the fuselage causes attendant tilting movement of said forward rotor unit toward the starboard region of the fuselage.

4. The autogiro of claim 1 further comprising a second control input device operatively connected to said rearward rotor unit wherein manipulation of said second control input device causes corresponding port and starboard tilting movement of said rearward rotor unit with respect to said fuselage.

5. The autogiro of claim 4 wherein said second control input device comprises first and second pedals mounted within said fuselage and wherein forward manipulation of said first pedal causes attendant tilting movement of said rearward rotor unit toward the port region of the fuselage and wherein forward manipulation of said second pedal causes attendant tilting movement of said rearward rotor unit toward the starboard region of the fuselage.

6. The autogiro of claim 1 further comprising a third control input device operatively connected to said rearward rotor unit wherein manipulation of said second control input device causes forward and rearward tilting movement of said rearward rotor unit with respect to said fuselage.

7. The autogiro of claim 6 wherein said third control input device comprises a trim control mounted within said fuselage.

8. An autogiro comprising:

an aircraft body;

a power unit capable of propelling said aircraft body;

fore and aft auto-rotating airfoils mounted on said aircraft body and being capable of tilting movement with respect to said aircraft body in any selected azimuth; and

a control input device capable of causing tilting movement of said aft auto-rotating airfoil in any selected azimuth with respect to said aircraft body so as to maneuver said aircraft body during flight.

9. The autogiro of claim 8 wherein said control input device comprises first and second pedals mounted within said aircraft body and wherein forward manipulation of said first pedal causes port tilting movement of said aft airfoil with respect to the aircraft body and wherein forward manipulation of said second pedal causes starboard tilting movement of said aft airfoil with respect to the aircraft body.

10. The autogiro of claim 9 wherein said control input device further comprises a control stick mounted within said aircraft body and wherein forward or rearward manipulation of said control stick causes attendant forward or rearward tilting movement of said fore airfoil with respect to said aircraft body.

11. The autogiro of claim 10 wherein said control stick is mounted within said aircraft body and wherein port or starboard manipulation of said control stick causes attendant port or starboard tilting movement of said fore airfoil with respect to the aircraft body.

12. The autogiro of claim 11 wherein said control input device further comprises a trim control mounted within said aircraft body and wherein manipulation of said trim control causes forward and rearward tilting movement of said aft airfoil with respect to said aircraft body.

13. An autogiro comprising:

an aircraft body;

a power unit capable of propelling said aircraft body;

first and second non-powered rotors mounted on said aircraft body and being capable of independently controlled tilting movement in any selected azimuth with respect to said aircraft body wherein the first rotor is mounted on the aircraft body forward of the second rotor.

14. The autogiro of claim 13 further comprising a control input device including a control stick and foot pedals, said control input device being capable of causing independent tilting movement of said first and second non-powered rotors with respect to said aircraft body so as to control the movement of said aircraft body during flight.

15. The autogiro of claim 14 wherein said control stick is mounted within said aircraft body and wherein forward or rearward manipulation of said control stick causes attendant forward or rearward tilting movement of said first rotor with respect to said aircraft body.

16. The autogiro of claim 14 wherein said control stick is mounted within said aircraft body and wherein port or starboard manipulation of said control stick causes attendant port or starboard tilting movement of said first rotor with respect to the aircraft body.

17. The autogiro of claim 14 wherein said foot pedals comprise first and second pedals mounted within said aircraft body and where in forward manipulation of said first pedal causes port tilting movement of said second rotor with respect to the aircraft body and wherein forward manipulation of said second pedal causes starboard tilting movement of said second rotor with respect to the aircraft body.

18. The autogiro of claim 14 wherein said control input device further includes a trim control mounted within said aircraft body and wherein manipulation of said trim control causes forward and rearward tilting movement of said second rotor with respect to said aircraft body.

19. An autogiro comprising:

a fuselage having forward, rearward, port and starboard regions;

a power unit capable of propelling said fuselage;

forward and rearward non-powered rotor units mounted in tandem on said fuselage, each rotor unit being capable of tilting movement in any selected azimuth with respect to said fuselage; and

a conventional rotary wing aircraft control system operatively connected to said non-powered rotor units;

said control system including;

a control stick mounted within said fuselage and wherein forward manipulation of said control stick causes attendant forward tilting movement of said forward rotor unit with respect to said fuselage and wherein rearward manipulation of said control stick causes attendant rearward tilting movement of said forward rotor unit with respect to said fuselage; and

wherein manipulation of said control stick toward the port region of the fuselage causes attendant tilting movement of said forward rotor unit toward the port region of the fuselage and wherein manipulation of said control stick toward the starboard region of the fuselage causes attendant tilting movement of said forward rotor unit toward the starboard region of the fuselage;

wherein said control system is operatively connected to said rearward rotor unit wherein manipulation of said conventional rotary wing aircraft control system causes corresponding port and starboard tilting movement of said rearward rotor unit with respect to said fuselage, and said control system includes first and second pedals mounted within said fuselage and wherein forward manipulation of said first pedal causes attendant tilting movement of said rearward rotor unit toward the port region of the fuselage and wherein forward manipulation of said second pedal causes attendant tilting movement of said rearward rotor unit toward the starboard region of the fuselage; and

wherein manipulation of said aircraft control causes corresponding forward and rearward tilting movement of said rearward rotor unit with respect to said fuselage, wherein said control system is operable to tilt said forward and rearward non-powered rotor units in any selected azimuth reactive to said fuselage.

20. The autogiro of claim 19 wherein said conventional rotary wing aircraft control system includes a trim control stick mounted within said fuselage.

21. The autogiro of claim 19 wherein the forward rotor unit is mounted on the fuselage forward of the rearward rotor unit and wherein the forward rotor unit is positioned generally in a plane vertically above a plane of the rearward rotor unit.