# US 2014/0197276 A1 · Aircraft landing gear and method of operating the same

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- Number: US 2014/0197276 A1
- Document ID: US20140197276A1
- Status: Published application
- Kind: A1
- Application number: 14/154,415
- Filed: 2014-01-14
- Published: 2014-07-17
- Earliest claimed: 2013-01-16
- Assignees: Otto Aviation Group
- Inventors: William M. OTTO
- Web page: https://patentgrep.com/patent/US20140197276A1

## CPC

- B64C 25/20: mechanical
- B64C 1/00: Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C 1/065: {Spars}
- B64C 1/069: {Joining arrangements therefor}
- B64C 1/10: Bulkheads
- B64C 3/185: {Spars}
- B64C 3/26: Construction, shape, or attachment of separate skins, e.g. panels
- B64C 3/58: provided with fences or spoilers (adjustable for control purposes B64C9/00)
- B64C 5/02: Tailplanes
- B64C 5/16: about spanwise axes
- B64C 9/02: Mounting or supporting thereof
- B64C 9/16: at the rear of the wing
- B64C 9/20: by multiple flaps
- B64C 25/02: Undercarriages
- B64C 25/10: retractable, foldable, or the like
- B64C 25/12: sideways
- B64C 25/14: fore-and-aft
- B64C 25/18: Operating mechanisms
- B64D 33/10: Radiator arrangement
- B64D 37/04: Arrangement thereof in or on aircraft
- B64C 2025/125: {into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage}
- F02B 37/001: {using exhaust drives arranged in parallel}
- Y02E 30/30: Nuclear fission reactors
- Y02T 50/30: Wing lift efficiency
- Y02T 50/40: Weight reduction
- Y02T 50/80: Energy efficient operational measures, e.g. ground operations or mission management
- 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
- F02B: INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL (gas-turbine plants F02C; hot-gas or combustion-product positive-displacement engine plants F02G)
- Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A front landing gear system for an aircraft including a swing arm rotatively coupled to a wheel, a forward link arm rotatively coupled to the swing arm, a oleopneumatic cylinder rotatively coupled to the swing arm, second extension arm and a bulkhead, a plate rotatively coupled to the bulkhead, an actuation device rotatively coupled to the bulkhead and to the plate, where refraction of the linear actuation device causes the plate and extension arms to move upward towards the bulkhead.

## Claims

### Claim 1

A front landing gear system for an aircraft including:
a swing arm rotatively coupled to a wheel;
a forward link arm rotatively coupled to the swing arm;
a oleopneumatic cylinder rotatively coupled to the swing arm, second extension arm and a bulkhead;
a plate rotatively coupled to the bulkhead;
an actuation device rotatively coupled to the bulkhead and to the plate,
wherein retraction of the linear actuation device causes the plate and extension arms to move upward towards the bulkhead.

### Claim 2 (depends on 1)

The landing gear of claim 1, wherein the axle of the wheel is behind a centerline of the bulkhead.

### Claim 3 (depends on 1)

The landing gear of claim 1, wherein the first extension arm is rotatively affixed to the second extension arm by a pin.

### Claim 4 (depends on 1)

The landing gear of claim 1, wherein the piston is rotatively coupled to the first extension arm at approximately the center of the first extension arm.

### Claim 5 (depends on 1)

The landing gear of claim 1, wherein the first extension arm consists of two parallel plates coupled to the axle of the wheel.

### Claim 6 (depends on 1)

The landing gear of claim 1, wherein the linear actuator includes a base portion coupled to the bulkhead and an extension portion coupled to each plate.

### Claim 7 (depends on 1)

The landing gear of claim 1, wherein the piston is a hydraulic actuator.

### Claim 8 (depends on 1)

The landing gear of claim 1, wherein the cylinder is an oleopneumatic shock.

### Claim 9 (depends on 1)

The landing gear of claim 1, wherein the actuation device is a linear actuator.

### Claim 10 (depends on 1)

The landing gear of claim 1, wherein the actuation device is a hydraulic actuator.

### Claim 11

A method of retracting a front landing gear for an aircraft including:
rotating a base plate towards a bulkhead by actuating an actuator rotatively coupled to the bulkhead and the base plate;
rotating a piston coupled to the base plate and rotatively coupled to the bulkhead towards the bulkhead as the actuator retracts;
rotating a wheel coupled to the piston by a first extension arm and second extension arm towards the plate thereby moving the wheel into the position it would occupy if the oleopneumatic cylinder were compressed.

### Claim 12 (depends on 11)

The method of claim 11, wherein the axle of the wheel is behind a centerline of the bulkhead when the landing gear is fully extended.

### Claim 13 (depends on 11)

The method of claim 11, wherein the first extension arm is rotatively affixed to the second extension arm by a pin.

### Claim 14 (depends on 11)

The method of claim 11, wherein the piston is rotatively coupled to the first extension arm at approximately the center of the first extension arm.

### Claim 15 (depends on 11)

The method of claim 11, wherein the first extension arm consists of two parallel plates coupled to the axle of the wheel.

### Claim 16 (depends on 11)

The method of claim 11, wherein the linear actuator includes a base portion coupled to the bulkhead and an extension portion coupled to the plate.

### Claim 17 (depends on 11)

The method of claim 11, wherein the piston is a hydraulic actuator.

### Claim 18 (depends on 11)

The method of claim 11, wherein the actuation device is a linear actuator.

### Claim 19 (depends on 11)

The method of claim 11, wherein the actuation device is a hydraulic actuator.