Electric nose landing gear architecture

Inventors: Amir Fazeli (Mississauga, CA); Adnan Cepic (Mississauga, CA)

Assignee: Goodrich Corporation

B64C25/22 B64C25/24 B64C25/50

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Quick Facts

Patent No.: US 11,066,153
App. No.: 16/592,602
Granted: Jul 20, 2021
Kind: B2

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Abstract

A nose landing gear system is disclosed. In various embodiments, the nose landing gear system includes an electro-hydraulic actuator configured to raise and lower a nose shock strut assembly; a first electro-mechanical actuator configured to steer the nose shock strut assembly; and a second electro-mechanical actuator configured to open and close a fairing door.

Claims (34)

1. A nose landing gear system, comprising:

an electro-hydraulic actuator configured to raise and lower a nose shock strut assembly;

a first electro-mechanical actuator configured to steer the nose shock strut assembly; and

a second electro-mechanical actuator configured to open and close a fairing door,

wherein the first electro-mechanical actuator includes a first electric motor and a first gear box connected to a steering collar,

wherein the steering collar is connected to the nose shock strut assembly,

wherein the second electro-mechanical actuator includes a second electric motor and a second gear box connected to the fairing door,

wherein the electro-hydraulic actuator includes a third electric motor and a hydraulic pump connected to a locking actuator,

wherein the locking actuator includes a cylinder and a piston slidably disposed within the cylinder,

wherein the locking actuator includes a key configured to engage a first recess disposed within the cylinder while in a first locked position,

wherein the key is configured to engage a second recess disposed within the cylinder while in a second locked position,

wherein the locking actuator includes a first port fluidly coupling the hydraulic pump to the first recess and

wherein the hydraulic pump is configured to urge the key radially inward, against the force of a bias member disposed radially inward and in radial alignment with the key, and away from the first recess in order to disengage the key from the first recess and to unlock the locking actuator from the first locked position, thereby allowing the piston to slide within the cylinder.

2. The nose landing gear system of claim 1 , wherein the bias member is configured to bias the key radially outward toward the cylinder.

3. The nose landing gear system of claim 2 , wherein the cylinder defines a chamber fluidly coupled to the hydraulic pump, which is configured to provide a hydraulic fluid under pressure to the chamber in order to transition the piston from the first locked position to the second locked position.

4. The nose landing gear system of claim 1 , wherein the locking actuator includes a second port fluidly coupling the hydraulic pump to the second recess.

5. The nose landing gear system of claim 1 , wherein the first electro-mechanical actuator is connected to a power source via a first power cable; the second electro-mechanical actuator is connected to the power source via a second power cable and the electro-hydraulic actuator is connected to the power source via a third power cable.

6. A method of operating a nose landing gear system, comprising:

energizing an electro-hydraulic actuator configured to raise and lower a nose shock strut assembly;

energizing a first electro-mechanical actuator configured to steer the nose shock strut assembly; and

energizing a second electro-mechanical actuator configured to open and close a fairing door,