Mark S Shander

US Patent:

6717786, Apr 6, 2004

Filed:

Oct 30, 2001

Appl. No.:

10/001636

Inventors:

Robert D. Holley - Shoreline WA
Mark S. Shander - Lynnwood WA

Assignee:

The Boeing Company - Chicago IL

International Classification:

H02H 308

US Classification:

361 931, 307 64

Abstract:

Methods and systems for selecting and connecting an electronics package to a power source from one or more of a plurality of possible power source paths. An embodiment of the invention uses inexpensive analog components to select a power path by testing the possible power source paths for a desired potential. The invention interrupts the alternate power path while maintaining the connection of the electronics package to the power source through the selected power path. An optional removal circuit removes the testing and selection circuitry once the alternate power path is interrupted. In actual embodiment of the invention, the methods and systems described are included in a reversible circuit breaker.

US Patent:

6822458, Nov 23, 2004

Filed:

Apr 17, 2003

Appl. No.:

10/417240

Inventors:

Mark S. Shander - Lynnwood WA

Assignee:

The Boeing Company - Chicago IL

International Classification:

G01R 3112

US Classification:

324536, 324509, 324424

Abstract:

An apparatus and method for simulating arcing events for use in testing arc fault circuit interrupters. The apparatus and method utilizes a plurality of motion sensitive switches, for example, mercury switches or ball-tilt switches, secured within the housing. When the apparatus is moved the switches interrupt a current flow mimicking arcing events.

US Patent:

7687927, Mar 30, 2010

Filed:

Nov 21, 2007

Appl. No.:

11/944199

Inventors:

Mark S. Shander - Mill Creek WA, US
Richard A. Cote - Mill Creek WA, US
Michael L. Drake - Bellevue WA, US
Howard Carter, III - Chesterfield MO, US
John T. Peters - Edmonds WA, US
Casey Y. K. Ng - Sammamish WA, US
Michael S. Hoag - Kent WA, US
John T. Paterson - Mukilteo WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

H02K 7/00

US Classification:

290 7

Abstract:

An electrical architecture for an aircraft is provided. The electrical architecture is particularly suitable for relatively small, compact, and lightweight aircraft. In one embodiment, the electrical architecture includes an electrical generator component coupled to the aircraft engine, and an air compression system coupled to the electrical generator component. The electrical generator component is configured to receive mechanical power from the engine and to generate a constant frequency AC electrical power from the engine mechanical power, and the air compression system is configured to receive the constant frequency AC power as an input and, in response thereto, produce a pressurized air output having variable characteristics (for example, a variable flow rate or a variable air pressure).

US Patent:

20060176625, Aug 10, 2006

Filed:

Feb 4, 2005

Appl. No.:

11/052505

Inventors:

Mark Shander - Mill Creek WA, US

International Classification:

H02H 3/00

US Classification:

361042000

Abstract:

A circuit protection apparatus having an integral grounding provision is disclosed. In one embodiment, the apparatus includes a circuit breaker having an integral over-current circuit that is responsive to a selected transient current condition. At least one conductive contact is positioned on an external portion of the circuit breaker that is coupled to the circuit. A barrier is positioned on the external portion of the breaker and configured to electrically couple to the at least one conductive contact to a selected electrical potential.

US Patent:

20130075530, Mar 28, 2013

Filed:

Sep 27, 2011

Appl. No.:

13/246470

Inventors:

Mark Stephen Shander - Mill Creek WA, US
Robert Thomas Johnson - Everett WA, US

International Classification:

B64C 1/00
B23P 17/04
H01R 43/00
H05K 1/14

US Classification:

244131, 361749, 29428, 29825

Abstract:

A method for interconnecting electronic equipment within an aircraft is described. The method includes installing a multi-dimensional backplane within the aircraft, the backplane including a plurality of connectors mounted thereon, contacts associated with the connectors interconnected by electrical conductors formed within the backplane, attaching shipside wiring to a first portion of the connectors on the backplane, and attaching electrical connectors of the electronic equipment to corresponding connectors on the backplane.

US Patent:

62447289, Jun 12, 2001

Filed:

Dec 13, 1999

Appl. No.:

9/459550

Inventors:

Richard A. Cote - Lake Forest Park WA
Mark S. Shander - Seattle WA
David F. King - Tukwila WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

F21Y10102
F21W10106

US Classification:

362249

Abstract:

A light emitting diode (LED) assembly is provided for use as an airplane position light which meets Federal Aviation Regulation lighting requirements and lasts longer than conventional incandescent and halogen position lights, while being relatively lightweight, cheap, and requiring relatively little power for operation. The LED assembly includes a first plurality of circuit boards in electrical communication with a base circuit board, wherein each circuit board of the first plurality of circuit boards is parallel to every other one of the first plurality of circuit boards, but is disposed at an acute angle to the base circuit board. The LED assembly also includes a second plurality of circuit boards in electrical communication with the base circuit board, wherein each circuit board of the second plurality of circuit boards is disposed at a different angle to the base circuit board such that the second plurality of circuit boards form a fan-shaped structure. In addition, the LED assembly includes a plurality of light emitting diodes electrically mounted to said first plurality of circuit boards and to said second plurality of circuit boards. The circuit boards and LEDs may be identical to facilitate construction and maintenance of the aircraft position light, and to decrease the cost of manufacturing the aircraft position light.

US Patent:

20180363560, Dec 20, 2018

Filed:

Aug 24, 2018

Appl. No.:

16/112495

Inventors:

- Chicago IL, US
Mark S. SHANDER - Mill Creek WA, US

International Classification:

F02C 7/24
F01D 25/00
F02C 7/00
F02C 7/32
F16L 57/00
B64D 13/00

Abstract:

Apparatus and system for containing a rupture of a duct. The apparatus includes an air-permeable sheet, such as a wide-weave fiberglass sheet. The air-permeable sheet includes a strap arranged on a first side of the sheet such that it forms diamond-shaped patterns along a longitudinal axis. The strap can be made of a tight-weave fiberglass. Laterally-spaced corners of the diamond-shaped patterns include connection members that can be engaged to affix the strap and the air-permeable sheet around a duct. Various aspects include an air-impermeable air barrier surrounding the wide-weave fiberglass sheet and strap. The air barrier can include a window that directs air from a ruptured duct. Various aspects can be used on a bleed-air duct of an aircraft. The window of the air barrier can be aimed at a temperature sensor. A valve can close the bleed-air duct if the temperature sensor detects a high temperature leak.

US Patent:

20160230670, Aug 11, 2016

Filed:

Feb 9, 2015

Appl. No.:

14/617640

Inventors:

- Chicago IL, US
Mark Stephen SHANDER - Mill Creek WA, US

International Classification:

F02C 7/24
B64D 41/00
F02C 7/32
F16L 59/14
B64C 3/18
F16L 9/10
F16L 9/14
B64D 27/12
B64C 3/32

Abstract:

Apparatus and system for containing a rupture of a duct. The apparatus includes an air-permeable sheet, such as a wide-weave fiberglass sheet. The air-permeable sheet includes a strap arranged on a first side of the sheet such that it forms diamond-shaped patterns along a longitudinal axis. The strap can be made of a tight-weave fiberglass. Laterally-spaced corners of the diamond-shaped patterns include connection members that can be engaged to affix the strap and the air-permeable sheet around a duct. Various aspects include an air-impermeable air barrier surrounding the wide-weave fiberglass sheet and strap. The air barrier can include a window that directs air from a ruptured duct. Various aspects can be used on a bleed-air duct of an aircraft. The window of the air barrier can be aimed at a temperature sensor. A valve can close the bleed-air duct if the temperature sensor detects a high temperature leak.