Single collective stick for a rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-11040770-B2
Application number	US-201515504227-A
Country	US
Kind code	B2
Filing date	Sep 30, 2015
Priority date	Oct 1, 2014
Publication date	Jun 22, 2021
Grant date	Jun 22, 2021

Abstract

An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A cockpit in the airframe, the cockpit including two seats and a single collective control input positioned between the two seats.

First claim

What is claimed is:

1. An aircraft comprising:
an airframe;
an extending tail;
a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly;
a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, the translational thrust system including a propeller; and
a cockpit in the airframe, the cockpit including two seats and a single collective control input positioned between the two seats, the single collective control including an ambidextrous grip supporting an input for heading adjustment, an input for differential cyclic adjustment, and an input for controlling the propeller.

2. The aircraft of claim 1 further comprising:
at least one flight control computer configured to independently control the main rotor assembly and the translational thrust system through a fly-by-wire control system.

3. The aircraft as in claim 1 wherein:
the seats further comprise a dedicated cyclic control input for each seat.

4. The aircraft as in claim 1 wherein:
the collective control input further comprises at least one of, an input for data recording, an input for controlling a pitch of a blade of the propeller, and an input for collective trim release.

5. The aircraft as in claim 1 wherein the propeller rotates about an axis substantially parallel to a longitudinal axis of the aircraft.

6. An aircraft comprising:
an airframe;
an extending tail;
a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly;
a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, the translational thrust system including a propeller;
at least one flight control computer configured to independently control the main rotor assembly and the translational thrust system through a fly-by-wire control system;
a single active collective control input including an ambidextrous grip supporting an input for heading adjustment, an input for differential cyclic adjustment, and an input for controlling the propeller; and
at least one servo configured to move the single active collective control input along a predefined schedule as a function of at least the airspeed of the aircraft;
wherein the predefined schedule is configured to initiate at a predefined airspeed.

7. The aircraft of claim 6 further comprising:
a cockpit in the airframe, the cockpit including two seats, wherein the single active collective control input is positioned between the two seats.

8. The aircraft as in claim 6 wherein the propeller rotates about an axis substantially parallel to a longitudinal axis of the aircraft.

9. A method of operating an aircraft comprising an airframe, a cockpit in the airframe, a translational thrust system including a propeller, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, the method comprising:
controlling, with a single collective control input, the main rotor assembly; and
controlling, with the single collective control input, the propeller;
wherein the single collective input is positioned between two seats in the cockpit, the single collective control including an ambidextrous grip supporting an input for heading adjustment, an input for differential cyclic adjustment, and an input for controlling the propeller.

10. The method according to claim 9 wherein:
the aircraft further comprising at least one flight control computer configured to independently control the main rotor assembly and the translational thrust system through a fly-by-wire control system.

11. The method according to claim 9 wherein:
the seats further comprise a dedicated cyclic control input for each seat.

12. The method according to claim 9 wherein:
the single collective control input further includes an input for data recording, an input for propeller control, and an input for collective trim release.

13. The aircraft as in claim 9 wherein the propeller rotates about an axis substantially parallel to a longitudinal axis of the aircraft.

14. A method of operating an aircraft comprising an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system including a propeller having a plurality of blades, the propeller providing translational thrust to the airframe, at least one flight control computer configured to independently control the main rotor assembly, and the translational thrust system through a fly-by-wire control system, a single active collective control input having an ambidextrous grip supporting an input for heading adjustment, an input for differential cyclic adjustment, an input for controlling the propeller, and at least one servo, the method comprising:
moving, with the servo, the single active collective control input along a predefined schedule as a function of at least the airspeed of the aircraft;
wherein the predefined schedule initiates at a predefined airspeed; and
controlling, with the single active collective control, a pitch of the blades of the propeller.

15. The method according to claim 14 wherein:
the aircraft further comprising a cockpit in the airframe, the cockpit including two seats, wherein the single active collective control input is positioned between the two seats.

16. The method according to claim 14 wherein:
the seats further comprise a dedicated cyclic control input for each seat.

17. The method according to claim 14 wherein:
the single active collective control input further includes an input for data recording, an input for propeller control, and an input for collective trim release.

18. The aircraft as in claim 14 wherein the propeller rotates about an axis substantially parallel to a longitudinal axis of the aircraft.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Bredenbeck Kevin L
• Fell William
• Eller Erez

Classifications

• B64U10/10

  Rotorcrafts · CPC title

• B64C27/08

  with two or more rotors · CPC title

• B64C1/0009

  Aerodynamic aspects · CPC title

• G05D1/0816

  to ensure stability · CPC title

• G05D1/0858

  specially adapted for vertical take-off of aircraft · CPC title