Rotorcraft state control

Patent metadata

Field	Value
Publication number	US-9944388-B2
Application number	US-201615248753-A
Country	US
Kind code	B2
Filing date	Aug 26, 2016
Priority date	Aug 27, 2015
Publication date	Apr 17, 2018
Grant date	Apr 17, 2018

Abstract

A method of rotorcraft state control includes receiving command input indicative of an intended state change in a rotorcraft. The method also includes issuing command output to a rotor actuation system to carry out the intended state change by varying drag and/or efficiency on one or more rotor blades of the rotorcraft. Issuing command output can include issuing a command output to the rotor actuation system to carry out the intended state change by increasing drag at a substantially constant thrust on one or more rotor blades of the rotorcraft.

First claim

What is claimed is:

1. An aircraft comprising
a rotor system including blades to provide thrust for the aircraft at a rotor efficiency level;
a power system which powers the rotor system at a power output level; and
a controller which selectively changes rotor efficiency of the rotor system to change a rotor system state of the aircraft without changing the power output level, wherein the controller issues command output to the rotor system to carry out the intended state change by adjusting drag and/or efficiency at a substantially constant thrust on one or more rotor blades of the rotorcraft.

2. The aircraft as recited in claim 1 , wherein the intended state change includes one or more of a horizontal translation of the rotorcraft, a change in speed of the rotorcraft, and/or a change in trim attitude of the rotorcraft, and wherein the controller issues command output to the rotor system to control rotor drag and/or efficiency as a function of azimuthal blade position cyclically to carry out the horizontal translation.

3. The aircraft as recited in claim 2 , wherein the controller issues command output to the rotor actuation system to control one or more of rotor pitch cyclically to counter aircraft rotation in any combination of roll and pitch induced by controlling rotor drag and/or efficiency and to control tail rotor thrust to account for the adjusted main rotor torque due to adjusted drag and/or efficiency of the main rotor.

4. The aircraft as recited in claim 3 , wherein countering aircraft rotation includes maintaining substantially constant heading and aircraft attitude in forward or rearward flight while laterally translating to a new track line.

5. The aircraft as recited in claim 3 , wherein countering aircraft rotation includes maintaining a substantially constant heading and aircraft attitude while translating to a new position in hover.

6. The aircraft as recited in claim 1 , wherein receiving command input includes receiving a command to enter drag translation mode prior to receiving command input indicative of an intended state change and issuing command output.

7. The aircraft as recited in claim 6 , wherein the controller receives a command to enter drag translation mode including selecting whether drag translation mode should be entered based on at least one of pilot input, auto-pilot input, and data regarding aircraft state.

8. The aircraft as recited in claim 1 , wherein the intended state change includes entering a power delivery response mode, and wherein the controller issues command output to the rotor actuation system to control rotor drag for an intended power delivery response.

9. The aircraft as recited in claim 8 , wherein the controller monitors power demand and rotor speed, wherein the controller issues command output to the rotor actuation system to vary rotor drag to maintain substantially constant power output from a power plant powering the rotor blades.

10. The aircraft as recited in claim 8 , wherein the controller monitors frequency and amplitude at which power is being demanded by the rotorcraft by monitoring at least one of power, torque, rotor speed, or power plant state parameters including speed, temperature or amperage, and actively manages fluctuations in power required by issuing command output to a rotor actuation system to vary drag and/or efficiency on one or more rotor blades of the rotorcraft to reduce the frequency and/or amplitude of power fluctuation demands from the power plant.

11. The aircraft as recited in claim 8 , wherein the controller monitors ambient conditions, determines whether the rotorcraft is in an ambient condition in which the power plant would have an unsatisfactory power-delivery response, and if so, commands extra steady state drag and/or reduced rotor system efficiency on the rotor to drive an increase in power required such that a combination of natural power plant power response rate and a rate at which drag power is shed can meet a satisfactory power-delivery response.

12. The aircraft as recited in claim 8 , wherein the controller monitors rotorcraft state parameters and a predefined minimum desired power plant state, commands an increase of rotor drag and/or reduced rotor system efficiency such that power plant state parameters do not fall below a predefined threshold.

13. The aircraft as recited in claim 1 , wherein the controller monitors at least one of rotor speed, aircraft pitch, and/or control commands and/or rates for cyclic and/or collective; and increases rotor drag and/or reduces rotor efficiency to prevent rotor overspeed in response to rotor speed approaching overspeed.

14. The aircraft as recited in claim 1 , wherein the controller issues command output to the rotor actuation system to apply differential cyclic to two coaxial, counter-rotating rotor systems in a coaxial rotorcraft.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Waltner Peter J

Classifications

• B64C27/57 Primary

  automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust · CPC title

• B64C27/32

  Rotors · CPC title

• B64C27/82

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• Y02T50/30

  Wing lift efficiency · CPC title

• B64C2027/7266

  actuated by actuators · CPC title