Stability control augmentation system and method

Patent metadata

Field	Value
Publication number	US-12179909-B2
Application number	US-202217950409-A
Country	US
Kind code	B2
Filing date	Sep 22, 2022
Priority date	Sep 27, 2021
Publication date	Dec 31, 2024
Grant date	Dec 31, 2024

Abstract

A stability control augmentation system and method for a flight control surface of an aircraft. The system includes s an actuator operable for actuating the flight control surface, and a control valve comprising a spool and an integrated augmentation mechanism. The spool and the actuation mechanism are both moveable to open and close a fluid flow path through the control valve to control the actuator.

First claim

The invention claimed is:

1. A stability control augmentation system for a flight control surface of an aircraft, comprising:
an actuator operable for actuating the flight control surface; and
a control valve comprising a spool and an integrated augmentation mechanism, wherein the spool is moveable to increase or decrease a cross-section of a fluid flow path through the control valve to thereby increase or decrease a flow of hydraulic fluid to the actuator during use, and wherein the integrated augmentation mechanism is operable to increase or decrease the cross-section of the fluid flow path to thereby adjust the flow of hydraulic fluid to the actuator;
wherein the control valve comprises a rocking pin connecting the spool and the augmentation mechanism, wherein the rocking pin is rotatable about two different points.

2. The stability control augmentation system as claimed in claim 1 , wherein the spool has a steady-state position in which the fluid flow path is closed, wherein the spool is axially moveable from the steady-state position in a first direction to thereby actuate the actuator in a first actuator direction, and wherein the spool is axially moveable from the steady-state position in a second direction to actuate the actuator in a second actuator direction.

3. The stability control augmentation system as claimed in claim 1 , wherein the augmentation mechanism comprises an intermediate sleeve that is axially movable to increase or decrease the cross-section of the fluid flow path through the control valve.

4. The stability control augmentation system as claimed in claim 1 , wherein the augmentation mechanism comprises a piezoelectric element operable to increase or decrease the cross-section of the fluid flow path.

5. The stability control augmentation system as claimed in claim 1 , further, comprising:
an input linkage operable to move the spool of the control valve.

6. The stability control augmentation system as claimed in claim 5 , comprising a feedback mechanism configured to adjust the input linkage based on the configuration of the actuator.

7. The stability control augmentation system as claimed in claim 6 , wherein the control valve comprises a summation sleeve movable by a lever head of the input linkage to move the spool.

8. The stability control augmentation system as claimed in claim 1 , wherein the control valve comprises a housing, and the spool and the augmentation mechanism are contained within the housing.

9. The stability control augmentation system as claimed in claim 1 , further comprising:
a controller configured to operate the integrated augmentation mechanism.

10. An aircraft comprising the stability control augmentation system as claimed in claim 1 , arranged to actuate a flight control surface of the aircraft.

11. A method of providing stability control augmentation to a flight control surface of an aircraft, comprising:
providing a control valve comprising a spool and an integrated augmentation mechanism;
increasing or decreasing a cross-section of a fluid flow path through the control valve by moving the spool to thereby increase or decrease a flow of hydraulic fluid to an actuator operable to actuate the flight control surface; and
increasing or decreasing the cross-section of the fluid flow path using the augmentation mechanism to thereby adjust the flow of hydraulic fluid to the actuator;
providing a rocking pin connecting the spool and the augmentation mechanism, and rotating the rocking pin about a first pivot to actuate the spool of the control valve and thereby increase or decrease the cross-section of the fluid flow path.

12. A method as claimed in claim 11 , further comprising:
actuating the augmentation mechanism and thereby rotating the rocking pin about a second pivot to increase or decrease the cross-section of the fluid flow path.

Assignees

• Microtecnica Srl

Inventors

• Mezzino Giacomo
• Tafuni Domenico

Classifications

• F15B13/0403

  a secondary valve member sliding within the main spool, e.g. for regeneration flow (F15B13/0418 takes precedence) · CPC title

• F16K31/5286

  comprising a sliding valve · CPC title

• F16K31/004

  actuated by piezoelectric means · CPC title

• F16K27/041

  cylindrical slide valves · CPC title

• F16K11/07

  with cylindrical slides · CPC title