Hydraulic system and method for an aircraft flight control system

Patent metadata

Field	Value
Publication number	US-10196131-B2
Application number	US-201615045237-A
Country	US
Kind code	B2
Filing date	Feb 16, 2016
Priority date	Feb 16, 2016
Publication date	Feb 5, 2019
Grant date	Feb 5, 2019

Abstract

A hydraulic system of an aircraft may include a system pump configured to provide hydraulic fluid to the hydraulic system at a first working pressure. The hydraulic system may further include a booster pump configured to supply hydraulic fluid to at least one boostable actuator at a second working pressure higher than the first working pressure. The boostable actuator may be operatively coupled to and configured to actuate at least one flight control surface of an aircraft.

First claim

What is claimed is:

1. A hydraulic system of an aircraft, comprising:
a plurality of non-boostable actuators and at least one boostable actuator each operatively coupled to a different flight control surface of an aircraft;
a system pump fluidly coupled to the plurality of non-boostable actuators via a nominal pressure supply line configured to transfer hydraulic fluid at a first working pressure, each non-boostable actuator acting under the first working pressure to actuate one of the flight control. surfaces;
a booster pump fluidly coupled only to the at least one boostable actuator via a boosted pressure supply line designed to withstand a higher pressure than the nominal pressure supply line, the nominal pressure supply line incapable of receiving hydraulic fluid at the higher pressure from the booster pump, the boosted pressure supply line transferring hydraulic fluid at a second working pressure higher than the first working pressure;
the booster pump fluidly coupled to the system pump via the nominal pressure supply line for receiving the hydraulic fluid at the first working pressure;
the non-boostable actuators excluded from receiving hydraulic fluid from the booster pump;
the booster pump switchable between a passivated state and an activated state;
the booster pump in the passivated state providing the hydraulic fluid to the at least one boostable actuator at the first working pressure, the boostable actuator acting under the first working pressure to actuate one of the flight control surfaces different than the flight control surfaces actuated by the non-boostable actuators;
the booster pump in the activated state increasing a pressure of the hydraulic fluid from the first working pressure to the second working pressure, and supplying the hydraulic fluid at the second working pressure to the at least one boostable actuator for actuating the at least one boostable actuator at the second working pressure.

2. The hydraulic system of claim 1 , further comprising:
a boost controller communicatively coupled to the booster pump, the boost controller programmed to:
identify when the aircraft is commanded to perform a maneuver;
switch the booster pump from the passivated state to the activated state to provide hydraulic fluid to the at least one boostable actuator at the second working pressure upon identifying that the aircraft is commanded to perform the maneuver; and
switch the booster pump from the activated state to the passivated state such that the pressure of the hydraulic fluid decreases from the second working pressure during or after the flight control surface has been actuated by the at least one boostable actuator causing the aircraft to perform the maneuver.

3. The hydraulic system of claim 2 , wherein:
the boost controller, upon identifying that the aircraft is commanded to perform the maneuver and prior to switching the booster pump from the passivated state to the activated state, further programmed to determine that the boostable actuator acting under the first working pressure is incapable of actuating the flight control surface causing the aircraft to perform the maneuver as commanded based upon at least one of aircraft state data and actuator state data.

4. The hydraulic system of claim 3 , wherein:
the aircraft state data comprises at least one of the following:
an aircraft environment; and
a control column input;

the actuator state data comprises at least one of the following:
a current actuator pressure of the boostable actuator is outside of a nominal actuator pressure range; and
a current actuator position of the boostable actuator is outside of a nominal actuator position range.

5. The hydraulic system of claim 1 , wherein:
the at least one flight control surface comprises an aileron of an aircraft wing.

6. The hydraulic system of claim 1 , wherein:
the first working pressure is approximately 3000 psi and the second working pressure is in a range of from approximately 5000-8000 psi.

7. A hydraulic system for an aircraft, comprising:
a plurality of non-boostable actuators each operatively coupled to a different flight control surface of an aircraft;
a first boostable actuator and a second boostable actuator operatively coupled to a common flight control surface excluded from the flight control surfaces of the non-boostable actuators, the common flight control surface comprising one of an aileron, a rudder, or an elevator;
a system pump fluidly coupled to the plurality of non-boostable actuators via a nominal pressure supply line configured to transfer hydraulic fluid to at a first working pressure, each non-boostable actuator acting under the first working pressure to respectively actuate one of the flight control surfaces;
a first booster pump and a second booster pump fluidly coupled respectively to only the first boostable actuator and the second boostable actuator via a boosted pressure supply line designed to withstand a higher pressure than the nominal pressure supply line, the nominal pressure supply line incapable of receiving hydraulic fluid at the higher pressure from the booster pump, the boosted pressure supply line transferring hydraulic fluid at a second working pressure higher than the first working pressure;
the first booster pump and the second booster pump fluidly coupled to the system pump via the nominal pressure supply line for receiving the hydraulic fluid at the first working pressure;
the non-boostable actuators excluded from receiving hydraulic fluid from either the first booster pump or the second booster pump;
the first booster pump and the second booster pump each switchable between a passivated state and an activated state; the first booster pump and the second booster pump in the passivated state providing the hydraulic fluid respectively to the first boostable actuator and the second boostable actuator at the first working pressure for actuating the common flight control surface comprising one of the aileron, the rudder, or the elevator; and
the first booster pump and the second booster pump in the activated state increasing the pressure of the hydraulic fluid to the second working pressure and providing the hydraulic fluid respectively to the first boostable actuator and the second boostable actuator at the second working pressure for actuating the common flight control surface of one of the aileron, the rudder, or the elevator.

8. A method of operating a hydraulic system of a flight control system of an aircraft having a plurality of non-boostable actuators and at least one boostable actuator each operatively coupled to a different flight control surface of the aircraft, the hydraulic system having a system pump fluidly coupled to the plurality of non-boostable actuators via a nominal pressure supply line configured to transfer hydraulic fluid at a first working pressure, the method comprising the steps of:
receiving, at a booster pump, the hydraulic fluid at the first working pressure from the system pump via the nominal pressure supply line, the booster supplying the hydraulic fluid only to the at least one boostable actuator via a boosted pressure supply line designed to withstand a higher pressure than the nominal pressure supply line, the nominal pressure supply line incapable of receiving hydraulic fluid at the higher pressure from the booster pump, the boosted pressure supply line transferring hydraulic fluid at a second working pressure higher than the first working pressure, the non-boostable actuators excluded from receiving hydraulic fluid from the booster pump;
identifying, using a boost controller communicatively coupled to the booster pump, when the aircraft is commanded to perform a maneuver;
activating, using the boost controller, the booster pu

Assignees

• Boeing Co

Inventors

• Mccormick Patrick J
• Huynh Neal V
• Overton Timothy G
• Marx Alan

Classifications

• B64C13/504

  using electro-hydrostatic actuators [EHA's] · CPC title

• B64C13/42 Primary

  having duplication or stand-by provisions · CPC title