Collective to elevator mixing of a rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-10654565-B2
Application number	US-201515501095-A
Country	US
Kind code	B2
Filing date	Sep 29, 2015
Priority date	Oct 1, 2014
Publication date	May 19, 2020
Grant date	May 19, 2020

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 horizontal stabilizer with a left elevator and right elevator positioned at the extending tail. A flight control computer to independently control one or more of the main rotor assembly and the elevator through a fly-by-wire control system. The flight control computer is configured to mix a collective pitch of the main rotor assembly and a deflection of the elevator.

First claim

What is claimed is:

1. An aircraft comprising:
an airframe including a longitudinal axis and a lateral axis;
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;
a horizontal stabilizer including a first actuator connected with a left elevator and a second actuator connected to a right elevator, the left and right elevators being positioned at the extending tail, one of the left elevator and the right elevator being offset relative the other of the left elevator and the right elevator along one of the longitudinal axis and the lateral axis; and
a flight control computer to independently control one or more of the main rotor assembly and the elevator through a fly-by-wire control system, wherein the left elevator and the right elevator are independently controllable through selective actuation of the first actuator and the second actuator by the flight control computer;
wherein the flight control computer is configured to mix a collective pitch of the main rotor assembly and a deflection of the elevator.

2. The aircraft of claim 1 further comprising:
a plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, the plurality of sensors providing the sensor data to the flight control computer.

3. The aircraft of claim 2 wherein:
in response to at least one control input, the flight control computer is configured to utilize algorithms based on the sensor data and the control input to mix the collective pitch of the main rotor assembly and the deflection of the elevator for load alleviation.

4. The aircraft of claim 3 wherein:
the loads are loads on the main rotor assembly.

5. The aircraft of claim 3 wherein:
the algorithms controlling the deflection of the elevator are configured to incorporate gain as function of airspeed and offset as a function of airspeed.

6. The aircraft of claim 2 wherein:
in response to at least one control input, the flight control computer is configured to utilize algorithms based on the sensor data and the control input to mix the collective pitch of the main rotor assembly and the deflection of the elevator to free up individual rotor longitudinal cyclic range.

7. The aircraft of claim 2 wherein:
in response to at least one control input, the flight control computer is configured to utilize algorithms based on the sensor data and the control input to mix the collective pitch of the main rotor assembly and the deflection of the elevator to improve performance.

8. The aircraft according to claim 1 , wherein one of the left elevator and the right elevator is larger than the other of the left elevator and the right elevator.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Eller Erez
• White Matthew A
• Luszcz Matthew T

Classifications

• B64C27/80

  for differential adjustment of blade pitch between two or more lifting rotors · CPC title

• B64C27/467

  Aerodynamic features · CPC title

• B64C27/52

  Tilting of rotor bodily relative to fuselage (of see-saw type construction B64C27/43) · CPC title

• B64C2027/004

  using actuators, e.g. active systems · CPC title

• B64C2027/8281

  comprising horizontal tail planes · CPC title