Mark S Gardner

US Patent:

6719106, Apr 13, 2004

Filed:

Dec 17, 2002

Appl. No.:

10/321960

Inventors:

Mark J. Gardner - Snohomish WA

Assignee:

The Boeing Company - Chicago IL

International Classification:

B60T 712

US Classification:

188134, 188 715, 192 7014

Abstract:

A skewed-roller brake assembly is provided, including a first rotor disc and a second rotor disc. A stator disc , positioned between the first and second rotor discs , includes a plurality of skewed-roller slots formed through the stator disc. A pair of roller elements are positioned within each of the plurality of skewed-roller slots such that a first of the pair of roller elements protrudes from the stator disc in the direction of the first rotor disc and a second of said pair of roller elements protrudes from the stator disc in the direction of the second rotor disc. When the first and second rotor discs are moved towards the stator disc , the first of the pair of roller elements and the second of the pair of roller elements rotate in concert while transmitting frictional torque to the first rotor disc and the second rotor disc respectively.

US Patent:

7945425, May 17, 2011

Filed:

Oct 17, 2008

Appl. No.:

12/253747

Inventors:

Alan D. Marx - Shoreline WA, US
Gary A. Emch - Arlington WA, US
Mark J. Gardner - Snohomish WA, US
Richard I. Apfel - Seattle WA, US
Michael E. Renzelmann - Woodinville WA, US
Christopher D. Feet - Marysville WA, US
Michael R. Finn - Kirkland WA, US
Mark S. Good - Seattle WA, US
Gregory J. Seehusen - Seattle WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G06F 11/30

US Classification:

702183, 244213

Abstract:

A method for detecting freewheeling skew failures in the wing flaps of an aircraft includes measuring the outputs of flap skew sensors when the aircraft is in flight (IF) and the flaps are extended to a selected position, and when the aircraft is next on the ground (OG) and the flaps are extended to the selected position. The respective differences between the IF and OG outputs of symmetrical pairs of the flap skew sensors are computed, and then the respective difference between the computed IF output difference and the computed OG output difference of each symmetrical pair of the sensors is computed. The computed IF and OG difference of each symmetrical pair of the sensors is then compared with each of predetermined maximum and minimum threshold value to determine whether a freewheeling skew failure exists in any of the flaps of the aircraft.

US Patent:

8115649, Feb 14, 2012

Filed:

Apr 30, 2009

Appl. No.:

12/433021

Inventors:

George Moy - Seattle WA, US
Peter Angel Padilla - Mill Creek WA, US
Michael Edward Renzelmann - Woodinville WA, US
Mark J. Gardner - Snohomish WA, US
Charles E. Jokisch - Lynnwood WA, US
William Suhail Hanna - Bellevue WA, US
Eric J. Selby - Lake Stevens WA, US
Mark A. Barr - Seattle WA, US
Stephen Roger Amorosi - Seattle WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G08B 21/00

US Classification:

3406861, 340945, 3406862, 244194, 244203, 244213

Abstract:

An apparatus comprises a sensor system, a flexible line, and a sensor. The sensor system is capable of detecting skew in at least some of a plurality of control surfaces for a vehicle. The flexible line extends across a number of interfaces for a portion of the plurality of control surfaces. The sensor is connected to the flexible line and is capable of detecting the skew in the portion of the plurality of control surfaces in response to a selected amount of movement of the flexible line.

US Patent:

20140033909, Feb 6, 2014

Filed:

Aug 3, 2012

Appl. No.:

13/566807

Inventors:

Robert M. Murphy - Everett WA, US
Kelly T. Jones - Snohomish WA, US
Robert E. Fisher - Everett WA, US
Mark J. Gardner - Snohomish WA, US

International Classification:

F15B 15/00

US Classification:

91 27

Abstract:

Methods and apparatus to control movement of a component are disclosed herein. An example apparatus includes a housing defining a bore and a piston disposed inside the bore. The piston is to be coupled to a movable component disposed outside of the bore. The example apparatus further includes a fluid flowline in fluid communication with a first chamber of the bore and a second chamber of the bore. The first chamber is on a first side of the piston, and the second chamber on a second side of the piston. The example apparatus also includes a valve to control fluid flow through the fluid flowline. The valve is to be in a first state to enable the piston to dampen movement of the component, and the valve is to be in a second state to enable the piston to hold the component substantially stationary.

US Patent:

62310127, May 15, 2001

Filed:

Nov 12, 1998

Appl. No.:

9/180778

Inventors:

Michael J. Cacciola - Seattle WA
Mark J. Gardner - Seattle WA
Stephen T. Steadman - Seattle WA

International Classification:

B64C 358
B64C 900
B64C 350
B64C 1334
B64C 1300

US Classification:

244213

Abstract:

Referring to FIG. 2, disclosed is an aircraft compound no-back/offset gearbox (2) with an integral load proportional safety (no-back) brake (50). The four gears are all 16 diametral pitch, involute external spur gears with 20 degree standard pressure angles. The two gear stages are interconnected with a mechanical fuse or shearout (40) designed to fail under excess shear loads and protect components downstream of the input shaft (10) from excess torque in the event of a system jam. The shearout (40) is essentially a quill shaft with external splines at both ends and an hourglass-shaped shear neckdown in the middle. The purpose of the no-back brake (50) is to prevent air loads from causing slat movement in the event of a torque tube disconnect. Referring to Figure, the no-back consists of a set of ball ramp (22) and brake plate components connected to the gearbox's output shaft. The ball ramp device converts part of the back driving torque into the axial force required to clamp the brake stack components (30) and restrain the output shaft.

US Patent:

20200189723, Jun 18, 2020

Filed:

Dec 18, 2018

Appl. No.:

16/224497

Inventors:

- Chicago IL, US
Mark J. Gardner - Snohomish WA, US
Jen-Shen Liu - Everett WA, US

International Classification:

B64C 13/32
F16D 59/02

Abstract:

Methods and systems according to one or more examples are provided for reducing chatter in a no-back brake during aiding load operations. In one example, an apparatus comprises a no-back brake, disposed within an actuator coupled to an aircraft, including a shaft, and a ball ramp plate, coupled to the shaft, to receive a force comprising an air loading force and is displaced responsive to the force. The apparatus further comprises a brake, coupled to the shaft and coupled to the ball ramp plate, and displaced by the ball ramp plate corresponding to a distance the ball ramp plate is displaced. The apparatus further comprises a modulating spring, coupled to the shaft and coupled to the brake, configured to compress in response to the brake being displaced, and the modulating spring is configured to apply a selective compressive force at the brake corresponding to a distance the brake is displaced.

US Patent:

20180312240, Nov 1, 2018

Filed:

Jul 6, 2018

Appl. No.:

16/029327

Inventors:

- Chicago IL, US
Matthew August Lassen - Seattle WA, US
Michael E. Renzelmann - Woodinville WA, US
Mark J. Gardner - Snohomish WA, US
Mark William Lesyna - Everett WA, US
Brian Curtis Hill - Everett WA, US
Nicholas Seth Tyler - Everett WA, US

International Classification:

B64C 3/56
B64C 13/50
B64C 13/40
B64C 13/42

Abstract:

A system and method for a number of backup systems in an aircraft. The apparatus comprises a movement system; a latch system; a lock system; and at least one of a backup valve, a backup actuator, or a backup power source connected to at least one of the movement system, the latch system, or the lock system. The movement system has a first number of actuators and is connected to a hydraulic power source. The latch system has a second number of actuators and is connected to the hydraulic power source. The lock system has a third number of actuators and is connected to the hydraulic power source.

US Patent:

20170349296, Dec 7, 2017

Filed:

Jun 7, 2016

Appl. No.:

15/175286

Inventors:

- Chicago IL, US
Charles E. Jokisch - Lynnwood WA, US
Mark Steven Good - Seattle WA, US
Mark John Gardner - Snohomish WA, US
Michael Edward Renzelmann - Woodinville WA, US
Jared Chung Houten - Mukilteo WA, US

International Classification:

B64D 45/00
G07C 5/08
B64C 3/56

Abstract:

A latch pin actuator comprises a primary lock, a spring, and a piston. The primary lock is attached to a primary lock cam and has a notch. The spring is biased to lock the primary lock. The piston is configured to unlock the primary lock.