Aircraft propeller electric blade pitch change and control

Patent metadata

Field	Value
Publication number	US-11312477-B2
Application number	US-201916522869-A
Country	US
Kind code	B2
Filing date	Jul 26, 2019
Priority date	Jul 26, 2019
Publication date	Apr 26, 2022
Grant date	Apr 26, 2022

Abstract

A propeller assembly of an aircraft includes a hub, a plurality of propeller blades extending from the hub and secured thereto and a propeller blade pitch change system located at at least one propeller blade of the plurality of propeller blades. The propeller blade pitch change system includes a pitch change actuator located in the propeller blade, and a drive mechanism operably connected to the pitch change actuator and to the propeller blade to urge rotation of the propeller blade about a propeller blade axis.

First claim

What is claimed is:

1. A propeller assembly of an aircraft, comprising:
a hub;
a plurality of propeller blades extending from the hub and secured thereto;
a propeller blade pitch change system disposed at at least one propeller blade of the plurality of propeller blades, the propeller blade pitch change system including:
a pitch change actuator disposed in the propeller blade;
a drive mechanism operably connected to the pitch change actuator and to the propeller blade to urge rotation of the propeller blade about a propeller blade axis; and
a shaft operably connected to and driven by the drive mechanism, the shaft connected to the hub via an anti-rotation feature;
wherein the drive mechanism is a planetary gear train.

2. The propeller assembly of claim 1 , wherein the pitch change actuator is disposed in a blade pocket of the propeller blade.

3. The propeller assembly of claim 1 , wherein the pitch change actuator is one of a closed loop servomotor or a stepper motor.

4. The propeller assembly of claim 1 , further comprising one or more blade pitch sensors to detect a pitch angle of the propeller blade.

5. The propeller assembly of claim 4 , wherein the one or more blade pitch sensors are operably connected to a pitch change controller to provide feedback of propeller blade pitch to the pitch change controller.

6. The propeller assembly of claim 1 , further comprising a power supply configured to provide electrical power to the pitch change actuator via the hub.

7. A propeller blade pitch change system, comprising:
a pitch change actuator positioned in a blade pocket of a propeller blade;
a drive mechanism operably connected to the pitch change actuator and to the propeller blade to urge rotation of the propeller blade about a propeller blade axis; and
a shaft operably connected to and driven by the drive mechanism, the shaft connected to an anti-rotation feature of a hub of a propeller system;

wherein the drive mechanism is a planetary gear train.

8. The propeller blade pitch change system of claim 7 , wherein the pitch change actuator is one of a closed loop servomotor or a stepper motor.

9. The propeller blade pitch change system of claim 7 , further comprising one or more blade pitch sensors to detect a pitch angle of the propeller blade.

10. The propeller blade pitch change system of claim 9 , wherein the one or more blade pitch sensors are operably connected to a pitch change controller to provide feedback of propeller blade pitch to the pitch change controller.

11. A method of pitch change of a propeller blade of a propeller, comprising:
activating a pitch change actuator, the pitch change actuator disposed in a propeller blade pocket of the propeller blade;
driving a drive mechanism operably connected to the pitch change actuator via activation of the pitch change actuator; and
changing a pitch of the propeller blade via driving of the drive mechanism, the drive mechanism operably connected to the propeller blade; and
driving a shaft via the drive mechanism, the shaft secured to an anti-rotation feature of a hub of a propeller assembly;
wherein the drive mechanism is a planetary gear train.

12. The method of claim 11 , wherein the pitch change actuator is one of a servomotor or a stepper motor.

13. The method of claim 11 , further comprising detecting the pitch of the propeller blade via one or more blade pitch sensors.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Corley Thomas G

Classifications

• B64U40/10

  for adjusting control surfaces or rotors · CPC title

• B64U30/20

  Rotors; Rotor supports · CPC title

• B64C11/30 Primary

  Blade pitch-changing mechanisms · CPC title

• F05D2260/75

  the adjusting mechanism not using auxiliary power sources, e.g. by "servos" · CPC title

• F05D2260/76

  the adjusting mechanism using auxiliary power sources · CPC title