Dual actuator hydraulic pitch-lock propeller system

Patent metadata

Field	Value
Publication number	US-11097832-B2
Application number	US-201916566023-A
Country	US
Kind code	B2
Filing date	Sep 10, 2019
Priority date	Sep 10, 2019
Publication date	Aug 24, 2021
Grant date	Aug 24, 2021

Abstract

A system is provided. The system includes a dual piston actuator and valves. The dual piston actuator includes a primary actuator and a protection actuator. The primary and protection actuators move to increase and decrease a pitch of propellers of an aircraft with respect to a supply of first and second mediums. The valves include a first check valve, a second check valve, and a third valve. The third valve operates between a first mode and a protection mode. The second medium is directed to the primary and protection actuators through the first and second check valves by the third valve when the third valve is operating in a protection mode.

First claim

What is claimed is:

1. A system comprising:
a dual piston actuator comprising a primary actuator and a protection actuator,
wherein the primary and protection actuators move to increase and decrease a pitch of propellers of an aircraft with respect to a supply of first and second mediums; and
a plurality of valves comprising a first check valve, a second check valve, and a third valve,
wherein the third valve, based on a signal from a sensor, operates between a first mode and a protection mode, wherein when operating in the first mode, the second medium is sent directly to the primary and protection actuators without passing through the first and second check valves, respectively, wherein when operating in the protection mode, the second medium is directed to the primary and protection actuators through the first and second check valves, respectively.

2. The system of claim 1 , wherein the protection mode comprises a hydraulic pitch-lock condition with a capability to increase the pitch of the propellers.

3. The system of claim 1 , wherein the first medium comprises a hydraulic force used to decrease the pitch of the propellers.

4. The system of claim 1 , wherein the second medium comprises a hydraulic force used to increase the pitch of the propellers.

5. The system of claim 1 , wherein a connection of the protection actuator receives atmospheric pressure or the first medium.

6. The system of claim 1 , wherein the third valve comprises a solenoid operated valve that generates a controlled magnetic field that provides a force acting on the third valve.

7. The system of claim 1 , wherein the third valve comprises a biasing spring that selects that the protection mode during a power loss.

8. The system of claim 1 , wherein the sensor monitors the dual piston actuator for latent fault detection.

9. The system of claim 1 , wherein the system is incorporated into a rotating side of the propellers of the aircraft.

10. A method comprising:
operating a dual piston actuator in a first mode, the dual piston actuator comprising a primary actuator and a protection actuator that move to increase and decrease a pitch of propellers of an aircraft with respect to a supply of first and second mediums without the first and second mediums moving through a first check valve or a second check valve;
detecting a control loss with respect to the second medium and a third valve switching between operating in the first mode and the protection mode based on the control loss,
wherein, when operating the dual piston actuator in the protection mode, the second medium is directed to the primary and protection actuators through the first and second check valves.

11. The method of claim 10 , wherein a sensor monitors the dual piston actuator for the control loss.

12. The method of claim 10 , wherein the protection mode comprises a hydraulic pitch-lock condition with a capability to increase the pitch of the propellers of the aircraft.

13. The method of claim 10 , wherein the primary and protection actuators control the propellers of the aircraft in accordance with the supply of the first and second mediums and the first medium comprises a hydraulic force used to decrease the pitch of the propellers.

14. The method of claim 10 , wherein the primary and protection actuators control the propellers of the aircraft in accordance with the supply of the first and second mediums and the second medium comprises a hydraulic force used to increase the pitch of the propellers.

15. The method of claim 10 , wherein the third valve comprises a solenoid operated valve that generates a controlled magnetic field that provides a force acting on the third valve.

16. The method of claim 10 , wherein the third valve comprises a biasing spring that selects that the protection mode during a power loss.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Maver Timothy

Classifications

• B64C11/44

  electric · CPC title

• B64C11/38 Primary

  fluid, e.g. hydraulic · CPC title

• B64C11/385

  comprising feathering, braking or stopping systems · CPC title