# US 2025/0145280 A1 · Strut for aircraft landing gear equipped with an accumulator, landing gear comprising such a strut, and aircraft comprising at least one such landing gear

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- Number: US 2025/0145280 A1
- Document ID: US20250145280A1
- Status: Published application
- Kind: A1
- Application number: 18/836,970
- Filed: 2023-02-08
- Published: 2025-05-08
- Earliest claimed: 2022-02-08
- Assignees: Safran Landing Systems
- Applicants: Safran Landing Systems
- Inventors: Aurélien DOUX; David FRANK
- Web page: https://patentgrep.com/patent/US20250145280A1

## CPC

- B64C 25/001: {Devices not provided for in the groups B64C25/02 - B64C25/68}
- B64C 25/22: fluid
- B64C 25/24: electric
- B64C 25/34: wheeled type, e.g. multi-wheeled bogies
- B64C 25/62: Spring shock-absorbers; Springs
- B64D 41/00: Power installations for auxiliary purposes
- B64C: AEROPLANES; HELICOPTERS
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT

## Abstract

A strut for an aircraft landing gear is provided. The strut includes a casing configured to absorb landing forces applied to the aircraft landing gear. The casing includes a cavity in which an energy accumulator is housed. The energy accumulator can be a removable cartridge which can be inserted in the cavity. An aircraft landing gear comprising such a strut is also provided. An aircraft comprising at least one such landing gear having such a strut is also provided. A method for emergency deployment of such a landing gear, using energy stored in the energy accumulator integrated in the strut of the landing gear to deploy the landing gear is also provided.

## Claims

### Claim 1

A strut for an aircraft landing gear, the strut comprising a casing configured to absorb landing forces applied to the aircraft landing gear, the casing having a cavity in which an energy accumulator is housed, wherein the energy accumulator is a removable cartridge which can be inserted in the cavity.

### Claim 2 (depends on 1)

The strut according to claim 1, wherein the energy accumulator is hydraulic.

### Claim 3 (depends on 1)

The strut according to claim 1, wherein the energy accumulator is an electrochemical battery.

### Claim 4 (depends on 1)

The strut according to claim 1, further comprising a rod forming a damper slidable into the casing, wherein an end of the rod carries at least one wheel.

### Claim 5 (depends on 1)

The strut according to claim 1, further comprising a rocker arm articulable on the casing and a damper connecting the rocker arm to the casing, wherein an end of the rocker arm carries at least one wheel.

### Claim 6 (depends on 1)

An aircraft landing gear comprising a strut according to claim 1.

### Claim 7 (depends on 1)

An aircraft comprising at least one landing gear comprising a strut according to claim 1.

### Claim 8 (depends on 7)

The aircraft according to claim 7, wherein the casing of the landing gear is articulable on a structure of the aircraft.

### Claim 9 (depends on 1)

A method for emergency deployment of a landing gear comprising a strut according to claim 1, the method comprising using energy stored in the energy accumulator integrated in the strut of the landing gear to deploy the landing gear.