Mitchell W Ray

US Patent:

20120211600, Aug 23, 2012

Filed:

Feb 21, 2011

Appl. No.:

13/031525

Inventors:

Mitchell Loren Ray Mellor - Bothell WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64C 25/02
G06F 15/00
G01M 17/00
B64D 45/00

US Classification:

244100 R, 702150, 738658

Abstract:

A method and apparatus for air-ground detection. A truck beam of a semi-levered landing gear is mounted on a pivot pin. The truck beam is configured to rotate about the pivot pin between a toes down position and a toes up position. A positioning mechanism is connected to a locking mechanism that secures an angle of the truck beam in the toes up position. The locking mechanism is secured in a steady state and configured to change from the steady state to a locked state in response to an initial ground contact. A sensor is connected to the locking mechanism. The sensor is configured to detect a change from the steady state to the locked state.

US Patent:

20130119196, May 16, 2013

Filed:

May 17, 2012

Appl. No.:

13/474332

Inventors:

Gary M. Lindahl - Newcastle WA, US
Eric Howard Nelson - Bothell WA, US
Mitchell Loren Ray Mellor - Bothell WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64C 25/02
F15B 13/00

US Classification:

244100 R, 91520

Abstract:

A hydraulic strut assembly, for use in a semi-levered landing gear in an aircraft, comprising an actuator and a manifold associated with the actuator. The actuator comprises a housing, a first piston, a second piston, and a third piston. The first piston is positioned between outer and inner cylindrical structures of the housing. The outer and inner cylindrical structures and first piston form an outer chamber that receives a first fluid. The inner cylindrical structure, the first piston, and the second piston, which is nested within the first piston, form an inner chamber, which holds a second fluid comprising a gas. A volume of the inner chamber changes when at least one of the first and second pistons moves. The third piston is positioned between the outer cylindrical structure and the first piston. The first, second, and third pistons move in a direction parallel to an axis through the housing.

US Patent:

20120126055, May 24, 2012

Filed:

Nov 22, 2010

Appl. No.:

12/951861

Inventors:

Gary M. Lindahl - Newcastle WA, US
Mitchell Loren Ray Mellor - Bothell WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64C 25/22

US Classification:

244104FP

Abstract:

A device including a first hydraulic piston, a second hydraulic piston disposed within the first hydraulic piston, and a third hydraulic piston disposed within both the first hydraulic piston and the second hydraulic piston. The first, second, and third hydraulic pistons are contained within a common outer wall. A manifold is connected to the first, second, and third hydraulic pistons. The manifold is disposed relative to the first, second, and third hydraulic pistons such that a fluid moving in the manifold can control positions of the first, second, and third hydraulic pistons.

US Patent:

20230107810, Apr 6, 2023

Filed:

Oct 1, 2021

Appl. No.:

17/491699

Inventors:

- Chicago IL, US
Mitchell Loren Ray Mellor - Bothell WA, US

International Classification:

F16H 25/22
F16H 25/20
F15B 15/06
B64C 13/36

Abstract:

Ball screw rotary actuator with independent ball paths. In one embodiment, a ball screw rotary actuator includes an outer cylinder including a fluid port, a piston configured to translate within the outer cylinder due to fluid pressure, helical grooves disposed between the outer cylinder and the piston, and outer ball bearings configured to travel in the helical grooves to rotate the piston within the outer cylinder as the piston translates. The ball screw rotary actuator also includes an inner shaft situated radially inward of the piston, straight grooves disposed between the piston and the inner shaft, and inner ball bearings configured to travel in the straight grooves, and to rotate the inner shaft as the piston rotates.

US Patent:

20230108051, Apr 6, 2023

Filed:

Oct 1, 2021

Appl. No.:

17/491720

Inventors:

- Chicago IL, US
Mitchell Loren Ray Mellor - Bothell WA, US

International Classification:

B64C 13/34
F16H 47/02
F15B 15/02

Abstract:

Ball screw rotary actuator with ball cage. In one embodiment, a ball screw rotary actuator includes an outer cylinder, a piston, and inner shaft. Outer ball bearings travel in helical groove between the outer cylinder and position to rotate the piston as it translates due to fluid pressure. The inner shaft is situated radially inward of the piston, and straight grooves are disposed between the piston and the inner shaft. Inner ball bearings travel in the straight grooves and rotate the inner shaft as the piston rotates. The ball screw rotary actuator also includes an outer ball cage to position the outer ball bearings in a spaced configuration, an outer indexing gear to control a position of the outer ball cage, an inner ball cage to position the inner ball bearings in a spaced configuration, and an inner indexing gear to control a position of the inner ball cage.

US Patent:

20200198773, Jun 25, 2020

Filed:

Feb 12, 2020

Appl. No.:

16/789190

Inventors:

- Chicago IL, US
Mitchell Loren Ray Mellor - Bothell WA, US
James E. Cusworth - Snohomish WA, US
Justin Cottet - Snohomish WA, US
Richard Kevin Johnson - Camano Island WA, US
George Sonnenburg - Mukilteo WA, US

International Classification:

B64C 25/20
B64C 25/10
B64C 25/60
B64C 25/34
B64C 25/26
B64C 25/14

Abstract:

An aircraft landing gear structure according to the present disclosure includes a strut assembly and a wheel assembly operatively coupled to the strut assembly. The strut assembly includes an upper tubular housing and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing such that the overall length of the strut assembly is transitioned between an extended configuration and a retracted configuration for stowage during flight. The wheel assembly includes a forward link pivotally coupled to the upper tubular housing and a truck beam that is pivotally coupled to the lower tubular housing such that translation of the lower tubular housing with respect to the upper tubular housing causes pivoting of the forward link and the truck beam with respect to one another, thereby tilting and/or raising a wheel of the wheel assembly with respect to the upper tubular housing.

US Patent:

20180244371, Aug 30, 2018

Filed:

Feb 28, 2017

Appl. No.:

15/445836

Inventors:

- Chicago IL, US
Mitchell Loren Ray Mellor - Bothell WA, US
James E. Cusworth - Snohomish WA, US
Justin Cottet - Snohomish WA, US

International Classification:

B64C 25/12
B64C 25/16
B64C 25/20

Abstract:

A strut assembly for an aircraft landing gear structure according to the present disclosure is transitioned between an extended configuration, corresponding to the aircraft being off the ground, and a retracted configuration, in which the strut assembly is shortened along its longitudinal axis with respect to the extended configuration, for stowage during flight. The strut assembly includes an upper bulkhead supported by an upper tubular housing, and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing. To transition the strut assembly to the retracted configuration, translation of the upper bulkhead with respect to the upper tubular housing mechanically causes translation of the lower tubular housing to a retracted position, such that the overall length of the strut assembly is reduced. In some examples, the strut assembly is an oleo strut assembly.

US Patent:

20180244372, Aug 30, 2018

Filed:

Feb 28, 2017

Appl. No.:

15/445652

Inventors:

- Chicago IL, US
Mitchell Loren Ray Mellor - Bothell WA, US
James E. Cusworth - Snohomish WA, US
Justin Cottet - Snohomish WA, US
Richard Kevin Johnson - Camano Island WA, US
George Sonnenburg - Mukilteo WA, US

International Classification:

B64C 25/20
B64C 25/26
B64C 25/14
B64C 25/34
B64C 25/60

Abstract:

An aircraft landing gear structure according to the present disclosure includes a strut assembly and a wheel assembly operatively coupled to the strut assembly. The strut assembly includes an upper tubular housing and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing such that the overall length of the strut assembly is transitioned between an extended configuration and a retracted configuration for stowage during flight. The wheel assembly includes a forward link pivotally coupled to the upper tubular housing and a truck beam that is pivotally coupled to the lower tubular housing such that translation of the lower tubular housing with respect to the upper tubular housing causes pivoting of the forward link and the truck beam with respect to one another, thereby tilting and/or raising a wheel of the wheel assembly with respect to the upper tubular housing.