Rotorcraft rotor and propeller speed

Patent metadata

Field	Value
Publication number	US-10640203-B2
Application number	US-201515504250-A
Country	US
Kind code	B2
Filing date	Oct 1, 2015
Priority date	Oct 1, 2014
Publication date	May 5, 2020
Grant date	May 5, 2020

Abstract

An aircraft includes an airframe having an extending tail, a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail and providing translational thrust to the airframe, the translational thrust system including a propeller. A gearbox system is operably connected to the main rotor assembly and the propeller to drive rotation of the main rotor assembly and the propeller. The gearbox is configured to maintain a main rotor assembly tip speed below Mach 0.9 and a propeller helical tip speed below Mach 0.88.

First claim

What is claimed is:

1. An aircraft comprising:
an airframe having an extending tail;
a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly having a first plurality of rotor blades and a lower rotor assembly having a second plurality of rotor blades; and
a translational thrust system positioned at the extending tail and providing translational thrust to the airframe, the translational thrust system including a propeller;
a gearbox system operably connected to the main rotor assembly and the propeller to drive rotation of the main rotor assembly and the propeller;
a flight control computer (FCC); and
a flight control system operably coupled to the main rotor assembly and the propeller, the flight control system having a rotor interface for controlling a rotational speed of the main rotor assembly and a translational thrust interface for controlling a rotational speed of the propeller, wherein during operation of the counter rotating, coaxial main rotor system and the propeller, the flight control system is operable to determine a threshold speed based on the speed of sound at a sensed air temperature and control the main rotor system to limit the tip speed of each of the first plurality of rotor blades and the second plurality of rotor blades to below the threshold speed that is below Mach 0.9 and to limit the tip speed of the propeller helical tip speed to the threshold speed that is below Mach 0.88, wherein the FCC issues commands to the flight control system to limit the propeller helical tip speed to be between Mach 0.76 and Mach 0.80 during cruise speeds of between 200 knots to 250 knots.

2. The aircraft of claim 1 , wherein the gearbox is configured to maintain the main rotor assembly tip speed between Mach 0.57 and Mach 0.68 during hover operation of the aircraft.

3. The aircraft of claim 1 , wherein the gearbox is configured to maintain the propeller helical tip speed between Mach 0.72 and Mach 0.84 during hover operation of the aircraft.

4. The aircraft of claim 1 , wherein the FCC limits the main rotor assembly tip speed to Mach 0.9 during cruise speeds of between 200 knots to 250 knots.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Eadie William J
• Boyle Patrick

Classifications

• B64C2027/8227

  comprising more than one rotor · CPC title

• F05D2270/021

  to prevent overspeed · CPC title

• B64C27/33

  having flexing arms · CPC title

• B64C27/14

  Direct drive between power plant and rotor hub · CPC title

• B64C27/12

  Rotor drives · CPC title