Electronic controller with off-load and anti-stall capability for Ram air turbine variable displacement hydraulic pump

Patent metadata

Field	Value
Publication number	US-11820528-B2
Application number	US-202217705528-A
Country	US
Kind code	B2
Filing date	Mar 28, 2022
Priority date	Mar 28, 2022
Publication date	Nov 21, 2023
Grant date	Nov 21, 2023

Abstract

An aircraft hydraulic control system includes a pump system, a fluid circuit, and a controller. The pump system includes a hydraulic pump and a ram air turbine assembly. The fluid circuit delivers hydraulic fluid to the hydraulic pump and receives the hydraulic fluid output from the hydraulic pump. The controller is in signal communication with the hydraulic pump. The controller determines a rotational frequency of a ram air turbine included in the ram air turbine assembly, and controls the hydraulic pump so as to control the flow of hydraulic fluid in the fluid circuit. The flow of hydraulic fluid in the fluid circuit controls a fluid pressure of the aircraft.

First claim

What is claimed is:

1. An hydraulic control system included in an aircraft, the hydraulic control system comprising:
a pump system including a hydraulic pump and a ram air turbine assembly, the ram air turbine assembly comprising a permanent magnet generator (PMG) rotatably coupled to the ram air turbine, the PMG configured to generate a voltage signal in response to the rotation of the ram air turbine;
a fluid circuit configured to deliver hydraulic fluid to the hydraulic pump and to receive the hydraulic fluid output from the hydraulic pump; and
a controller in signal communication with the hydraulic pump, the controller configured to determine a rotational frequency of a ram air turbine included in the ram air assembly, and to control the hydraulic pump so as to control the flow of hydraulic fluid in the fluid circuit,
wherein the flow of hydraulic fluid in the fluid circuit controls a fluid pressure of the aircraft, and
wherein the controller is in signal communication with the PMG and is powered in response to receiving the voltage signal output from the PMG, and wherein the controller determines a rotation signal based on the voltage signal generated in response to rotating the PMG.

2. The aircraft hydraulic control system of claim 1 , wherein the hydraulic pump comprises:
a swash plate configured to operate according to a plurality of different adjustable plate positions that vary the flow of the hydraulic fluid output from the hydraulic pump; and
a plate actuator coupled to the swash plate and configured to adjust the plate position to control the flow of the hydraulic fluid in the fluid circuit.

3. The aircraft hydraulic control system of claim 2 , wherein the controller outputs a command signal that controls the plate actuator to adjust the plate position of the swash plate.

4. The aircraft hydraulic control system of claim 1 , further comprising:
a pressure sensor in fluid communication with the fluid circuit, the pressure sensor configured to output a pressure signal indicative of the fluid pressure based on the hydraulic fluid,
wherein the controller actively adjusts the plate position based at least in part on the pressure signal to control the flow of the hydraulic fluid in the fluid circuit.

5. The aircraft hydraulic control system of claim 4 , wherein the controller compares the fluid pressure indicated by the pressure signal to a target fluid pressure and adjusts the plate position such that the fluid pressure meets the target fluid pressure.

6. The aircraft hydraulic control system of claim 5 , wherein the controller continuously compares the fluid pressure to the target fluid pressure and actively adjusts the plate position to maintain the fluid pressure at the target fluid pressure.

7. The aircraft hydraulic control system of claim 4 , wherein the controller compares the rotational frequency to a targeted operational frequency and controls the hydraulic pump based on the comparison between the rotational frequency to the targeted operational frequency.

8. The aircraft hydraulic control system of claim 7 , wherein in response to the rotational frequency falling below the targeted operational frequency, the controller outputs a plate control signal to control the plate actuator and adjust the plate position to reduce the flow of hydraulic fluid output from the hydraulic pump thereby increasing the rotational frequency toto meet or exceed the targeted operational frequency.

9. A method of controlling an hydraulic control system included in an aircraft, the method comprising:
delivering, via a fluid circuit, hydraulic fluid to a hydraulic pump;
outputting, from the hydraulic pump the hydraulic fluid to the fluid circuit;
driving a rotation of a permanent magnet generator (PMG) using a ram air turbine included in a ram air assembly;
generating a voltage signal from the PMG in response to the rotation of the ram air turbine;
powering a controller using the voltage signal output from the PMG;
determining, using the controller, a rotational frequency of the ram air turbine included in the ram air assembly;
determining, by the controller, a rotation signal based on the voltage signal generated in response to rotating the PMG; and
controlling, using the controller, the hydraulic pump so as to control a flow of the hydraulic fluid in the fluid circuit to control a fluid pressure of the aircraft.

10. The method of claim 9 , further comprising:
operating a swash plate according to a plurality of different adjustable plate positions that vary the flow of the hydraulic fluid output from the hydraulic pump; and
adjusting a plate actuator coupled to the swash plate so as to adjust the plate position to control the flow of the hydraulic fluid in the fluid circuit.

11. The method of claim 10 , further comprising outputting, from a controller, a command signal that controls the plate actuator to adjust the plate position of the swash plate.

12. The method of claim 9 , further comprising:
outputting a pressure signal from a pressure sensor that is in fluid communication with the fluid circuit, the pressure signal indicative of the fluid pressure based on the hydraulic fluid; and
actively adjusting the plate position using the controller based at least in part on the pressure signal to control the flow of the hydraulic fluid in the fluid circuit.

13. The method of claim 12 , further comprising:
comparing, by the controller, the fluid pressure indicated by the pressure signal to a target fluid pressure; and
outputting from the controller a plate control signal to adjust the plate position such that the fluid pressure meets the target fluid pressure.

14. The method of claim 13 , further comprising continuously comparing, by the controller, the fluid pressure to the target fluid pressure; and
actively adjusting, by the controller, the plate position to maintain the fluid pressure at the target fluid pressure.

15. The method of claim 14 , further comprising comparing, by the controller, the rotational frequency to a targeted operational frequency.

16. The method of claim 15 , further comprising:
determining, by the controller, the rotational frequency falling below the targeted operational frequency; and
in response to the rotational frequency falling below the targeted operational frequency, controlling, by the controller the plate actuator to adjust the plate position to reduce the flow of hydraulic fluid output from the hydraulic pump thereby increasing the rotational frequency to meet or exceed the targeted operational frequency.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Reinhard Paul
• Horihan Gregory E
• Behling David S

Classifications

• B64D41/007 Primary

  Ram air turbines · CPC title

• B64C13/40

  using fluid pressure · CPC title

• F03D9/28

  the apparatus being a pump or a compressor · CPC title

• F03D9/32

  on moving objects, e.g. vehicles · CPC title

• F05B2220/31

  in ram-air turbines ("RATS") · CPC title