Noise modes for rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-10443674-B2
Application number	US-201515514115-A
Country	US
Kind code	B2
Filing date	Jul 27, 2015
Priority date	Oct 1, 2014
Publication date	Oct 15, 2019
Grant date	Oct 15, 2019

Abstract

A method of controlling noise of an aircraft includes storing a plurality of predefined noise modes; receiving a selection of a selected noise mode from the plurality of predefined noise modes, the selected noise mode identifying at least one operational parameter; and controlling the aircraft in response to the at least one operational parameter.

First claim

What is claimed is:

1. A method of controlling noise of an aircraft, the method comprising:
storing a plurality of predefined noise modes including one or more of a reduced noise cruise, a reduced noise approach, a reduced noise hover, and an unlimited noise mode;
receiving a selection from an operator of a selected noise mode from the plurality of predefined noise modes, the selected noise mode identifying at least one operational parameter; and
controlling the aircraft in response to the at least one operational parameter.

2. The method of claim 1 wherein:
the at least one operational parameter includes one or more of engine RPM, main rotor RPM, propeller RPM, propeller engage/disengage, propeller blade pitch, main rotor pitch and exhaust suppression.

3. The method of claim 2 wherein:
the main rotor pitch is at least one of collective pitch and cyclic pitch.

4. The method of claim 1 wherein:
the plurality of predefined noise modes includes a reduced noise cruise mode.

5. The method of claim 1 wherein:
the plurality of predefined noise modes includes a reduced noise approach mode.

6. The method of claim 1 wherein:
the plurality of predefined noise modes includes a reduced noise hover mode.

7. The method of claim 1 wherein:
the plurality of predefined noise modes includes an unlimited noise mode.

8. The method of claim 1 wherein:
the plurality of predefined noise modes includes a reduced noise cruise mode, a reduced noise approach mode, a reduced noise hover mode and an unlimited noise mode.

9. 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 including a propeller positioned at the extending tail, the translational thrust system providing translational thrust to the airframe;
a clutch for engaging and disengaging the propeller;
a flight control computer storing a plurality of predefined noise modes including one or more of a reduce noise cruise, a reduced noise approach, a reduced noise hover, and an unlimited noise mode; and
an input receiving a selection from an operator of a selected noise mode from the plurality of predefined noise modes, the selected noise mode identifying at least one operational parameter; and
the flight control computer controlling the aircraft in response to the at least one operational parameter.

10. The aircraft of claim 9 wherein:
the at least one operational parameter includes one or more of engine RPM, main rotor RPM, propeller RPM, propeller engage/disengage, propeller blade pitch, main rotor pitch and exhaust suppression.

11. The aircraft of claim 10 wherein:
the main rotor pitch is at least one of collective pitch and cyclic pitch.

12. The aircraft of claim 9 wherein:
the plurality of predefined noise modes includes at least one of a reduced noise cruise mode, a reduced noise approach mode, a reduced noise hover mode and an unlimited noise mode.

13. The aircraft of claim 9 wherein:
the plurality of predefined noise modes includes a reduced noise cruise mode, a reduced noise approach mode, a reduced noise hover mode and an unlimited noise mode.

14. The aircraft of claim 9 wherein:
the input for receiving the selection of the selected noise mode comprises a user interface for manual selection of the selected noise mode.

15. The aircraft of claim 9 wherein:
upon selecting a reduced noise mode as the selected noise mode, the flight control computer reduces engine RPM and main rotor assembly RPM to a reduced level based on aircraft parameters.

16. The aircraft of claim 15 wherein:
the aircraft parameters include at least one of weight of the aircraft, aircraft center of gravity, atmospheric conditions and airspeed.

17. The aircraft of claim 9 wherein:
the flight control computer controlling the aircraft includes controlling RPM of the propeller independently of RPM of the main rotor assembly.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Eller Erez
• Eadie William J
• Bredenbeck Kevin L
• Weiner Steven D

Classifications

• B64C2027/8227

  comprising more than one rotor · CPC title

• F16F15/02 Primary

  Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems ({F16F15/005 takes precedence } ; layered products B32B; suppression of vibration in ships B63; {relieving load on bearings, using magnetic means F16C39/06}) · CPC title

• F16H37/02

  comprising essentially only toothed or friction gearings · CPC title

• F16D13/74

  Features relating to lubrication · CPC title

• F16D13/72

  Features relating to cooling · CPC title