Helicopters with coaxial rotors, of convertible type in particular

• US 4,123,018 A
• Filed: 05/16/1977
• Issued: 10/31/1978
• Est. Priority Date: 01/12/1976
• Status: Expired due to Term

• Current Assignee: Rene C. A. Tassin De Montaigu
• Original Assignee: Rene C. A. Tassin De Montaigu
• Inventors: Tassin de Montaigu, Rene C. A.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US05/797,486
• Time in Patent Office: 533 Days
• Field of Search: 244/17.13, 244/17.23, 244/7 R, 244/83 F, 244/7 A, 244/7 B, 244/17.11, 244/23 C, 244/82, 416/23, 416/40, 416/115, 416/117, 416/152, 416/130, 416/124, 416/127, 416/128, 416/129, 416/41, 416/24, 416/226
• US Class Current: 244/17.23
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded

Abstract

The invention relates to improvements to helicopters with coaxial rotors, of convertible type in particular, consisting of at least two contra rotative rotors carrying blades for lifting and propelling, the fuselage having an axis parallel to the axes of the rotors and wherein each rotor consists of a nave carrying arms radially arranged, the arms carrying a coating with a propeller blade section, movable in incidence through whirling on to said arms. The naves are axially displaced along and rotatably supported about a shaft coaxial with the fuselage axis and comprising a structural support member of the fuselage.

Claims

1. Improvements to helicopters with coaxial rotors of convertible type in particular, consisting of at least two contra rotative rotors carrying blades having a coating for lifting and propelling, the fuselage having an axis common with the axes of the rotors and rocking jointly with the latter between substantially vertical and horizontal positions, improvements wherein each rotor consists of a nave carrying blades radially arranged, and said blades being movable in incidence and cyclically controlled and further comprising,

a shaft coaxial with said fuselage axis inside said fuselage forming a structural member of said fuselage,

and means for supporting the rotor naves axially displaced along and rotatable about said shaft,

said helicopter being free of fixed wings with said rotors being the sole means for providing lift when said fuselage is vertical and horizontal in flight,

propulsive transmissions and flight control systems external to said shaft,

engine means axially displaced from said shaft inside said fuselage embracing the common axis of said shaft and fuselage coupled to said propulsive transmission for providing driving power to said rotors,

wherein the incidence of the blades coating is driven by two cyclic plates located between the rotors and related to each of said rotors.

2. Improvements according to claim 1, wherein the two cyclic plates are fitted rotating one of them inside the other, the internal plate being arranged on a swivel-joint coaxial to the fuselage and movable axially.

3. Improvements according to claim 1, wherein the contra rotative rotors are driven through a differential carrying a variation speed device constituting the control of the rotation of the fuselage.

4. Improvements according to claim 1 wherein each nave of each rotor carries rigid arms radially arranged,

said arms being provided with a coating with a propeller blade section, movable in incidence, through whirling onto said arms.

5. Improvements according to claim 4 wherein each rotor has blades with each blade having a rigid central member extending substantially the full length of the blade surrounded by said coating and having means for relatively displacing said coating about said member as said rotors rotate for varying collective and cyclic pitch of the rotors.

6. Improvements according to claim 1 wherein said rotors are the sole means for propulsion and control.

7. Improvements according to claim 1 wherein said rotors are alike.

8. Improvements according to claim 1 wherein said means for supporting the rotor naves comprises first and second nave ball bearings coaxially mounted on said first and second naves respectively and rotatable about said shaft and further comprising,

means for driving the rotor naves contra rotatively,

said rotors being mounted rigidly on a respective nave and located axially along said shift in the vicinity of the gravity center of said helicopter.

9. Improvements to helicopters with coaxial rotors of convertible type in particular, consisting of at least two contra rotative rotors carrying blades for lifting and propelling, the fuselage having an axis common with the axes of the rotors and rocking jointly with the latter wherein each rotor consists of a nave carrying arms radially arranged, said arms being provided with a coating with a propeller blade section, movable in incidence through whirling on to said arms,

a shaft coaxial with said fuselage axis inside said fuselage forming a structural member of said fuselage,

means for supporting the rotor naves axially displaced along and rotatable about said shaft,

wherein the incidence of the blades coating is driven by two cyclic plates located between the rotors and related to each of said rotors with the two cyclic plates being fitted rotating one of them inside the other, the internal plate being arranged on a swivel-joint coaxial to the shaft and movable axially and is integral with a bell connected to the handle-bar of the helicopter by a ball-bearing for simultaneously driving the two cyclic plates.

10. Improvements according to claim 9, wherein the cyclic control handle-bar acting onto the bell carries a stabilizing speed and direction anemometer.

11. Improvements to helicopters with coaxial rotors of convertible type in particular, consisting of at least two contra rotative rotors carrying blades for lifting and propelling, the fuselage having an axis common with the axes of the rotors and rocking jointly with the latter wherein each rotor consists of a nave carrying arms radially arranged, said arms being provided with a coating with a propeller blade section, movable in incidence through whirling on to said arms,

a shaft coaxial with said fuselage axis inside said fuselage forming a structural member of said fuselage,

means for supporting the rotor naves axially displaced along and rotatable about said shaft,

wherein the incidence of the blades coating is driven by two cyclic plates located between the rotors and related to each of said rotors with the two cyclic plates being fitted rotating one of them inside the other, the internal plate being arranged on a swivel-joint coaxial to the shaft and movable axially and the axial displacement of the swivel-joint for driving the collective pitch is driven from the motion of the rotors.

12. Improvements according to claim 11, wherein the swivel-joint is integral in rotation with one of the rotors and secured by means of screws, themeselves integral with the rollers, said rollers internally and externally engaging rings turning freely, said rings selectively co-operating with braking means.

13. Improvements to helicopters with coaxial rotors of convertible type in particular, consisting of at least two contra rotative rotors carrying blades for lifting and propelling, the fuselage having an axis common with the axes of the rotors and rocking jointly with the latter between substantially vertical and horizontal positions, improvements wherein each rotor consists of a nave carrying blades radially arranged, said blades being movable in incidence and cyclically controlled and further comprising,

a shaft coaxial with said fuselage axis inside said fuselage forming a structural member of said fuselage,

and means for supporting the rotor naves axially displaced along and rotatable about said shaft,

said rotors being the sole means for providing lift when said fuselage is vertical and horizontal in flight and,

means for increasing the angular velocity of one of said rotors while decreasing the angular velocity of the other rotor to alter the differential velocity therebetween without substantially increasing the energy dissipated for controlling the rotation of the fuselage.