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Stephen R Amorosi

from Seattle, WA
Age ~65
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Also known as:
Steve R Amorosi, Antonio Morosi
Phone and address:
8712 Jones Pl NW, Seattle, WA 98117
(206) 355-8078
Related to:
Jane E AmorosiGayle F Amorosi, 67Clara Amorosi, 32
Connected to:
Andy Amorosi, 87Maria I Amorosi, 61Mary T Amorosi, 64Patricia A Amorosi, 56Thomas D Amorosi, 61Antoinette J Amoroso, 94Antonino D Amoroso, 71Barbara R Amoroso, 74Carlo A Amoroso, 88Carmela R Amoroso, 77

Stephen Amorosi Phones & Addresses

  • 8712 Jones Pl NW, Seattle, WA 98117 (206) 355-8078
  • Lorain, OH
  • 8712 Jones Pl NW, Seattle, WA 98117 (206) 841-6977

Work

Company: Boeing Position: Senior design engineer

Education

Degree: Bachelor's degree or higher

Industries

Aviation & Aerospace

Resumes

Resumes

Stephen Amorosi Photo 1

Senior Design Engineer

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Location:
Seattle, WA
Industry:
Aviation & Aerospace
Work:
Boeing
Senior Design Engineer

Publications

Us Patents

Leading Edge Flap Apparatuses And Associated Methods

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US Patent:
7264206, Sep 4, 2007
Filed:
Sep 30, 2004
Appl. No.:
10/955686
Inventors:
James M. Wheaton - Seattle WA, US
Stephen R. Amorosi - Seattle WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 3/50
US Classification:
244214, 244210, 244215, 244216
Abstract:
The present invention is directed generally toward leading edge flap apparatuses and corresponding methods. One aspect of the invention is directed toward an aircraft system having an airfoil, an actuator driver, and a leading edge device with two flow surfaces and six links. In a further aspect of the invention, the flow surfaces of the leading edge device are at least approximately located in the same position when the actuator driver is in two different positions. Another aspect of the invention is directed toward an aircraft system having an airfoil and a leading edge device movable between at least a retracted position and an extended position along a motion path having two segments. The second flow surface can be positioned generally behind and/or generally above the first flow surface when the first and second flow surfaces are located in the first segment of the motion path.

Aircraft Leading Edge Apparatuses And Corresponding Methods

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US Patent:
7270305, Sep 18, 2007
Filed:
Jun 15, 2004
Appl. No.:
10/868234
Inventors:
Scott N. Rampton - Seattle WA, US
Stephen R. Amorosi - Seattle WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 3/50
US Classification:
244214, 244213
Abstract:
Aircraft and leading edge apparatuses and corresponding methods are disclosed. In one embodiment, an aircraft system includes an airfoil with a leading edge device that is movable among a retracted position, at least one first extended position, and a second extended position. A first actuator can be operatively coupled to the leading edge device to move the flow surface between the retracted and the at least one first extended position. A second actuator can be operatively coupled to the leading edge device to move the flow surface between the at least one first extended position and the second extended position.

Leading Edge Flap Apparatuses And Associated Methods

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US Patent:
7828250, Nov 9, 2010
Filed:
Jul 17, 2007
Appl. No.:
11/778995
Inventors:
James M. Wheaton - Everett WA, US
Stephen R. Amorosi - Seattle WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 3/50
US Classification:
244214, 244213, 244210
Abstract:
The present invention is directed generally toward leading edge flap apparatuses and corresponding methods. One aspect of the invention is directed toward an aircraft system having an airfoil, an actuator driver, and a leading edge device with two flow surfaces and six links. In a further aspect of the invention, the flow surfaces of the leading edge device are at least approximately located in the same position when the actuator driver is in two different positions. Another aspect of the invention is directed toward an aircraft system having an airfoil and a leading edge device movable between at least a retracted position and an extended position along a motion path having two segments. The second flow surface can be positioned generally behind and/or generally above the first flow surface when the first and second flow surfaces are located in the first segment of the motion path.

Slat Skew Detection System

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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.

Leading Edge Flap Method

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US Patent:
7992826, Aug 9, 2011
Filed:
Oct 4, 2010
Appl. No.:
12/897646
Inventors:
James M. Wheaton - Collierville TN, US
Stephen R. Amorosi - Seattle WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 3/50
US Classification:
244214, 244213, 244210
Abstract:
A method of reducing drag of a leading edge device having first and second flow surfaces includes coupling the first flow surface to an airfoil and coupling the second flow surface to the first flow surface. The leading edge device may be moved between a retracted position and an extended position. The second flow surface may be positioned generally behind the first flow surface during at least a portion of the movement of the leading edge device between the retracted and extended positions.

Translating Conduit Apparatus For An Airplane Or Equipment

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US Patent:
20070034747, Feb 15, 2007
Filed:
Jun 30, 2005
Appl. No.:
11/170811
Inventors:
Stephen Amorosi - Seattle WA, US
Jeffrey Baucum - Sammamish WA, US
Dennis Chin - Mukilteo WA, US
International Classification:
B64C 3/50
B64C 13/00
US Classification:
244215000, 244099200
Abstract:
An apparatus for an airplane or other equipment is provided. The apparatus may comprise a multitude of connected arms which are adapted to rotate relative to one another. One end of the apparatus may be connected to a fixed wing, while another end of the apparatus may be connected to a moving slat. The apparatus may be used to deliver conduit from the fixed wing to the moving slat. The conduit may comprise one or more of an electrical de-icing wire, a sensor wire, a control wire, a fiber optic line, and a pneumatic line. Within an internal pathway of the apparatus, the conduit may be freely looped around a curved surface at least one-half turn and fixedly secured to a linear surface. Methods of use and assembly are also provided.

Wing Leading Edge Slat System

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US Patent:
20070102587, May 10, 2007
Filed:
Nov 7, 2005
Appl. No.:
11/268384
Inventors:
Kelly Jones - Snohomish WA, US
Stephen Fox - Everett WA, US
Stephen Amorosi - Seattle WA, US
International Classification:
B64C 3/50
US Classification:
244214000
Abstract:
A mechanism for extending and supporting a high-lift device relative to an airfoil has a pair of support ribs coupled to the airfoil. A carrier track is pivotally coupled to the high-lift device and positioned between the pair of support ribs. The carrier track has a slot opening along a lower length thereof. A gear rack is coupled within the slot opening. A pinion gear is positioned between the support ribs and below the carrier track. The pinion gear engages with the gear rack for extending the high-lift device relative to the airfoil. A plurality of rollers is rotateably coupled to the support ribs and in bearing contact with the carrier track. At least one roller is positioned above the carrier track and a second roller is positioned below the carrier track. The second roller is positioned concentrically with the pinion gear.

Continuous Skin Leading Edge Slats

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US Patent:
20210129974, May 6, 2021
Filed:
Nov 1, 2019
Appl. No.:
16/671888
Inventors:
- Chicago IL, US
Stephen R. Amorosi - Seattle WA, US
Matthew L. Anderson - Carnation WA, US
Ramon A. Burin - Lake Stevens WA, US
Michael R. Severance - Seattle WA, US
International Classification:
B64C 9/24
B64C 3/18
B64F 5/10
Abstract:
Continuous skin leading edge slats are disclosed. A disclosed example leading edge slat for use with an aircraft includes a single-piece nose skin defining upper and lower external surfaces of the leading edge slat, where the single-piece nose skin is to extend between a fore end and an aft end of the leading edge slat, and a box spar coupled to an inner surface of the single-piece nose skin. The box spar includes lateral walls extending away from the inner surface of the single-piece nose skin. The lateral walls define at least one compartment of the box spar.
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Stephen R Amorosi from Seattle, WA, age ~65 Get Report