Controlling rotor blades of a swashplateless rotor

Patent metadata

Field	Value
Publication number	US-9682771-B2
Application number	US-201313966951-A
Country	US
Kind code	B2
Filing date	Aug 14, 2013
Priority date	Aug 14, 2013
Publication date	Jun 20, 2017
Grant date	Jun 20, 2017

Abstract

Controlling rotor blades of a rotor assembly includes determining an azimuthal position of a rotor assembly and identifying a lateral control command value, a longitudinal control command value and a collective control command value of a rotor assembly control system. A sine value and a cosine value of the azimuthal position are calculated and separate blade commands signals are generated for each separate blade of the rotor assembly to control a position of each blade independent of each other blade. The blade command signals are generated based on combining the sine and cosine values of the azimuthal position with the lateral control command value, the longitudinal control command value and the collective control command value.

First claim

What is claimed is:

1. A method for controlling rotor blades of a rotor assembly, comprising:
determining an azimuthal position of a rotor assembly;
identifying a lateral command value, a longitudinal command value and a collective command value of a rotor assembly control system;
calculating a sine value and a cosine value of the azimuthal position;
generating a separate blade control signal for each separate blade of the rotor assembly to control a position of each blade independent of each other blade based on combining the sine value and cosine value of the azimuthal position with the lateral command value, the longitudinal command value and the collective command value, wherein the sine value of the azimuthal position is combined with the lateral command, and the cosine value of the azimuthal position is combined with the longitudinal command, and wherein each blade control signal is generated to be different from each other blade control signal; and
adjusting the position of one or more blades in response to the separate blade control signals generated.

2. The method of claim 1 , wherein the lateral command value, the longitudinal command value and the collective command value are generated by a flight control system.

3. The method of claim 2 , wherein the lateral command, longitudinal command and collective command of the flight control system are generated based on pilot-manipulated physical controls.

4. The method of claim 1 , wherein combining the sine and cosine values of the azimuthal position with the lateral, longitudinal and collective command values comprises:
generating a first blade control signal based on multiplying the sine of the azimuthal position by negative one (−1) to obtain a first result and combining the first result with the lateral command value, the longitudinal command value and the collective command value; and
generating a second blade control signal based combining the sine of the azimuthal position with the lateral command value, the longitudinal command value and the collective command value, without multiplying the sine of the azimuthal position by negative one (−1).

5. The method of claim 4 , wherein combining the first result with the lateral command value, the longitudinal command value and the collective command value comprises:
multiplying the first result by the lateral command value to obtain a second result;
adding the second result to the cosine of the azimuthal position to obtain a third result; and
adding the third result to the collective command value.

6. The method of claim 4 , wherein combining the sine of the azimuthal position with the lateral command value, the longitudinal command value and the collective command value, without multiplying the sine of the azimuthal position by negative one (−1), comprises:
multiplying the sine of the azimuthal position by the lateral command value to obtain a fourth result;
adding the fourth result to the cosine of the azimuthal position to obtain a fifth result; and
adding the fifth result to the collective command value.

7. The method of claim 1 , further comprising:
transmitting the separate blade control signals to separate blade positioning servos wherein the separate blade positioning servos control the positions of each separate blade.

8. A rotor blade position control assembly, comprising:
a rotor including a plurality of rotor blades;
first and second rotor blade control servos connected to separate first and second blades among the plurality of rotor blades to control the position of the first and second blades;
a flight control computer for transmitting command signals including a lateral command value, a longitudinal command value, a collective command value, and an azimuthal position signal, wherein the flight control computer operates at a first frequency; and
a rotor blade control computer configured to receive the command signals from the flight control computer, the rotor blade control computer operating at a second frequency, wherein the rotor blade control computer calculates a sine value and a cosine value of the azimuthal position, and generates a first rotor blade control signal for transmission to the first rotor blade control servo and a second rotor blade control signal for transmission to the second rotor blade control servo based on combining the sine value and cosine values of the azimuthal position with the lateral command value, the longitudinal command value and the collective command value, wherein the sine value of the azimuthal position is combined with the lateral command, and the cosine value of the azimuthal position is combined with the longitudinal command, and wherein the first rotor blade control signal is generated to be different than the second rotor blade control signal.

9. The rotor blade position control assembly of claim 8 , further comprising:
physical flight controls configured to be physically manipulated by a pilot to generate the lateral command, longitudinal command and collective command.

10. The rotor blade position control assembly of claim 8 , wherein combining the sine and cosine values of the azimuthal position with the lateral, longitudinal and collective command values comprises:
generating the rotor first blade control signal based on multiplying the sine of the azimuthal position by negative one (−1) to obtain a first result and combining the first result with the lateral command value, the longitudinal command value and the collective command value; and
generating the second rotor blade control signal based combining the sine of the azimuthal position with the lateral command value, the longitudinal command value and the collective command value, without multiplying the sine of the azimuthal position by negative one (−1).

11. The rotor blade position control assembly of claim 10 , wherein combining the first result with the lateral command value, the longitudinal command value and the collective command value comprises:
multiplying the first result by the lateral command value to obtain a second result;
adding the second result to the cosine of the azimuthal position to obtain a third result; and
adding the third result to the collective command value.

12. The rotor blade position control assembly of claim 10 , wherein combining the sine of the azimuthal position with the lateral command value, the longitudinal command value and the collective command value, without multiplying the sine of the azimuthal position by negative one (−1), comprises:
multiplying the sine of the azimuthal position by the lateral command value to obtain a fourth result;
adding the fourth result to the cosine of the azimuthal position to obtain a fifth result; and
adding the fifth result to the collective command value.

13. A rotor blade control computer for controlling rotor blades of a rotor assembly, comprising:
memory configured to store a rotor blade control program and one or more of an azimuthal position value, a lateral command value, a longitudinal command value and a collective command value; and
a processor configured to execute the rotor blade control program to perform a method for controlling the rotor blades of the rotor assembly, the method comprising:
obtaining the azimuthal position value of a rotor assembly;
obtaining the lateral command value, the longitudinal command value and the collective command value;
calculating a sine value and a cosine value of the azimuthal position;
generating a first rotor blade control signal to transmit to a first rotor blade control servo for controlling a first rotor blade of the rotor assembly and a second rotor blade control signal t

Assignees

• Sikorsky Aircraft Corp

Inventors

• Knag John
• Litwinowicz Anthony

Classifications

• B64C2027/7216

  using one actuator per blade · CPC title

• B64C27/04 Primary

  Helicopters · CPC title

• B64C27/54 Primary

  Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement · CPC title

• Y02T50/34

  Cross-Sectional Technologies · mapped topic

• Y02T50/30

  Wing lift efficiency · CPC title