# US 8,740,155 B2 · More electric flight control system onboard an aircraft

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 8,740,155 B2
- Document ID: US8740155B2
- Status: Granted
- Kind: B2
- Application number: 12/651,603
- Filed: 2010-01-04
- Published: 2010-07-08
- Granted: 2014-06-03
- Earliest claimed: 2009-01-08
- Assignees: Airbus Operations GmbH
- Applicants: Marc Fervel; Alexandre Gentilhomme
- Inventors: Marc Fervel; Alexandre Gentilhomme
- Web page: https://patentgrep.com/patent/US8740155B2

## CPC

- B64C 13/00: Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C 13/504: {using electro-hydrostatic actuators [EHA's]}
- Y02T 50/50: On board measures aiming to increase energy efficiency
- B64C: AEROPLANES; HELICOPTERS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

An electric flight control system onboard an aircraft provided with flight control surfaces and controllers for controlling these surfaces, that include at least one local electro-hydraulic generator to supply hydraulic servocontrols connected to flight control surfaces.

## Claims

### Claim 1

An electric flight control system for an aircraft provided with flight control surfaces, said system comprising:
at least one local electro-hydraulic generator to supply, from within a fuselage of the aircraft, hydraulic servocontrols located outside the fuselage and connected to flight control surfaces;
a trimmable horizontal stabilizer actuator (THSA) including at least one electric motor; and
an electronic module that commonly supplies power to each of the at least one local electro-hydraulic generator and to each of the at least one electric motor, wherein
each local electro-hydraulic generator is provided with a fixed frequency AC voltage with a constant rms, and comprises at least one electric motor which is an induction motor powered by said fixed frequency AC voltage with said constant rms value and configured to operate at a constant speed, and
the hydraulic servocontrols powered by the at least one electro-hydraulic generator from within the fuselage of the aircraft are located on at least one of a wing, an elevator, or a rudder of the aircraft.

### Claim 2 (depends on 1)

The system according to claim 1, comprising at least two electro-hydraulic generators located in an aft part of the fuselage of the aircraft.

### Claim 3 (depends on 1)

The system according to claim 1, wherein the flight control surfaces connected to the hydraulic servocontrols powered by the at least one electro-hydraulic generator comprise elevators and rudders.

### Claim 4 (depends on 3)

The system according to claim 3, wherein said flight control surfaces comprise a horizontal stabiliser.

### Claim 5 (depends on 1)

The system according to claim 1, wherein the flight control surfaces connected to the hydraulic servocontrols powered by the at least one electro-hydraulic generator comprise surfaces located on a wing of said aircraft.

### Claim 6 (depends on 5)

The system according to claim 5, wherein said surfaces located on the wing comprise ailerons and/or spoilers.

### Claim 7 (depends on 1)

The system according to claim 1, wherein said electronic module is housed in a pressurised zone.

### Claim 8 (depends on 1)

An aircraft comprising a system according to claim 1.

### Claim 9 (depends on 1)

The system according to claim 1, wherein said hydraulic servocontrols include servovalves that direct hydraulic pressure supplied via the at least one local electro-hydraulic generator to move pins of actuators connected to the flight control surfaces.

### Claim 10 (depends on 1)

The system according to claim 1, wherein the flight control surfaces are not connected to an electro-hydrostatic actuator.

### Claim 11 (depends on 1)

The system according to claim 1, wherein the electronic module is located within the fuselage of the aircraft.