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Erik L Godo

from Redmond, WA
Age ~60
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Also known as:
Erik Lars Godo
Phone and address:
15208 63Rd St, Redmond, WA 98052
(425) 882-2991
Related to:
Kristen M GoodrichKristin G Godo, 65Carl M Jorgensen, 61Kjell E Godo, 66Greta A Jorgensen, 64Einar Godo, 98Hannah O Dahl, 35Daniel A Dahl, 64Lars Jorgensen, 95Betty J Godo, 99
Connected to:
Adrian Godo, 51Ian K Godofsky, 37Fabricio S Godoi, 53Lourdes Y Godomar, 65Aline M Godon, 70Julie D Godon, 51Sharon A Godon, 55Miguel A Godos, 60Werner A Godosar, 86John Godosis, 51

Erik Godo Phones & Addresses

  • 15208 63Rd St, Redmond, WA 98052 (425) 882-2991
  • 15208 63Rd Ct, Redmond, WA 98052 (425) 882-2991
  • Enumclaw, WA
  • Kirkland, WA
  • 2407 170Th St, Bellevue, WA 98008 (425) 746-9075
  • Renton, WA

Work

Company: Bellevue ski school 1983 to 2012 Position: Ms and hs director

Education

Degree: Master of Science, Masters School / High School: University of Washington 1983 to 1996 Specialities: Electronics Engineering

Skills

Systems Engineering • Embedded Systems • Simulations • System Design • Engineering Management • Testing • Engineering • Aerospace • Simulink • Electronics • Matlab • Program Management • Integration • Software Engineering • Signal Processing • System Architecture • Embedded Software • Electrical Engineering • Fpga • Sensors • Labview • Pcb Design • Avionics • Algorithms • Debugging • Requirements Management • Image Processing • Digital Signal Processors • Programming • Circuit Design • Project Management • C • Pspice • C++ • Rf • Vhdl • Cross Functional Team Leadership • Software Development

Languages

Norwegian

Industries

Aviation & Aerospace

Resumes

Resumes

Erik Godo Photo 1

Seattle Section Volunteer

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Location:
Seattle, WA
Industry:
Aviation & Aerospace
Work:
Bellevue Ski School 1983 - 2012
Ms and Hs Director
Ieee 1983 - 2012
Seattle Section Volunteer
Boeing 1983 - 2012
Software Engineer and Electrical and Aeh Accounts Receivable
Education:
University of Washington 1983 - 1996
Master of Science, Masters, Electronics Engineering
Skills:
Systems Engineering
Embedded Systems
Simulations
System Design
Engineering Management
Testing
Engineering
Aerospace
Simulink
Electronics
Matlab
Program Management
Integration
Software Engineering
Signal Processing
System Architecture
Embedded Software
Electrical Engineering
Fpga
Sensors
Labview
Pcb Design
Avionics
Algorithms
Debugging
Requirements Management
Image Processing
Digital Signal Processors
Programming
Circuit Design
Project Management
C
Pspice
C++
Rf
Vhdl
Cross Functional Team Leadership
Software Development
Languages:
Norwegian

Publications

Us Patents

Braking Interlock For An Electric Brake System Of An Aircraft

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US Patent:
7618100, Nov 17, 2009
Filed:
Dec 13, 2006
Appl. No.:
11/610267
Inventors:
T. Todd Griffith - Seattle WA, US
Erik Godo - Redmond WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
G06F 19/00
US Classification:
303 20, 303 15, 303126, 701 70
Abstract:
An electric brake system for an aircraft includes a power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The interlock removes operating power from the brake mechanisms whenever the brake system sensor data does not indicate a legitimate brake application condition. The interlock processing occurs in parallel with the brake command processing such that even if an inadvertent brake command is generated, the brake mechanisms will be unable to act upon the inadvertent brake command.

Ground Towing Power Architecture For An Electric Brake System Of An Aircraft

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US Patent:
7857107, Dec 28, 2010
Filed:
Nov 1, 2006
Appl. No.:
11/555630
Inventors:
David Yamamoto - Mill Creek WA, US
Erik Godo - Redmond WA, US
Joel T. Purificacion - Shoreline WA, US
Marcelino Montano - Snohomish WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B60T 13/64
US Classification:
188 3H, 303 15
Abstract:
A power management architecture as disclosed herein is suitable for use in connection with an electric brake system of an aircraft. During ground towing operations when the aircraft engines are off, the power management architecture provides operating power to the electric brake system (and other aircraft systems that are required to support towing operations) via the main aircraft battery. This towing power mode prevents the battery from powering other aircraft systems during towing operations, thus reducing the load on the battery.

Power Switching System And Method For An Aircraft Electrical Brake System

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US Patent:
7875993, Jan 25, 2011
Filed:
Dec 22, 2006
Appl. No.:
11/615889
Inventors:
Erik Godo - Redmond WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B60L 1/00
US Classification:
307 91, 701 70
Abstract:
A system and method for switching power sources for an aircraft electric brake system is disclosed. The method removes battery power from electric brake actuator controls during flight until landing gear extension occurs. The method utilizes a logic circuit to switch between available power sources based on a plurality of control signals. The method minimizes the total power drawn during flight, and saves battery power if the aircraft calls for operating on battery power only.

Reduced Power Mode For An Aircraft Electric Brake System

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US Patent:
8204661, Jun 19, 2012
Filed:
Dec 21, 2006
Appl. No.:
11/614953
Inventors:
Erik Godo - Redmond WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
G06F 7/70
G06G 7/00
G06G 7/76
US Classification:
701 70, 701 3, 701 75, 701 78
Abstract:
An electric brake system for an aircraft as described herein is capable of operating in a normal full power mode, a low power mode, and a sleep mode. The full power mode is supported by the active power supply of the aircraft, while the low power and sleep modes are supported by the backup power supply (e. g. , a battery) of the aircraft. The low power mode is activated in response to the detection of certain conditions or operating states where full braking performance is not required. For example, the low power mode can be utilized in connection with towing operations and parking brake adjustment operations. The sleep mode is activated in response to the absence of braking commands for an extended period of time. Various parameters and/or settings of the electric brake system are adjusted, controlled, or regulated during the low power and sleep modes to achieve reduced power consumption relative to the full power mode.

Parking Brake Adjustment For An Aircraft Having An Electric Brake System

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US Patent:
20070084682, Apr 19, 2007
Filed:
Sep 15, 2006
Appl. No.:
11/532487
Inventors:
T. Griffith - Seattle WA, US
Erik Godo - Redmond WA, US
International Classification:
F16D 65/36
US Classification:
188156000
Abstract:
A system and procedures for adjusting a parking brake for an aircraft having an electric brake system are disclosed. Adjustment of a parking brake as described herein can compensate for thermal expansion or contraction of components of a parking brake mechanism, generally seen during and subsequent to an aircraft landing. Procedures for adjusting an aircraft parking brake as disclosed herein include setting the aircraft brakes to an initial state, comparing a measured elapsed time to a threshold time, measuring a brake temperature, adjusting the brakes to achieve a desired clamping force or brake actuator position, and engaging a friction brake in order to conserve power needed by an electric brake actuator.

Aircraft Electrical Brake Control System Architecture

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US Patent:
20080030069, Feb 7, 2008
Filed:
Aug 4, 2006
Appl. No.:
11/462510
Inventors:
T. Todd Griffith - Seattle WA, US
David T. Yamamoto - Mill Creek WA, US
Erik L. Godo - Redmond WA, US
International Classification:
B60T 13/74
US Classification:
303 20, 303 3
Abstract:
An electric brake system architecture for an aircraft with two or more electrical braking subsystems including brake system controls configured to communicate pilot pedal commands to electric brake actuator controllers that apply or release brakes in wheel groups. The system allows independent brake activation of wheel groups through a plurality of brake system controls and electric brake actuator controllers. The electric braking system further includes remote data consolidators to collect and transmit wheel data to brake system controls through a digital data communication bus. The system reduces aircraft weight, prevents inadvertent braking, and prevents error propagation between subsystems.

Loop Resistance Tester (Lrt) For Cable Shield Integrity

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US Patent:
62258109, May 1, 2001
Filed:
Feb 12, 1998
Appl. No.:
9/022576
Inventors:
Erik L. Godo - Redmond WA
Bruce Van Deventer - Lynnwood WA
Mervin E. Eaton - Shoreline WA
John F. Gonder - Mountlake Terrace WA
Assignee:
The Boeing Company - Seattle WA
International Classification:
G01R 3108
G01R 3128
H01H 3102
US Classification:
324525
Abstract:
A loop resistance tester (LRT) for shield integrity testing comprising three elements: a "drive" current coupler, a "sense" current coupler, joint probes, and an instrument assembly. A low-power excitation current is sent from the instrument into the drive coupler, which is essentially a transformer. This induces a current in the electrical cable under test, as long as that cable and the connected structure form a continuous current path, or loop. This induced loop current is detected by the "sense" current coupler (transformer) and is measured by the instrument. The ratio of the loop voltage to loop current, as phasor values, gives the complex loop impedance, the real part of which is the loop resistance.

Method And Apparatus For Actively Reducing Multiple-Source Repetitive Vibrations

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US Patent:
52455521, Sep 14, 1993
Filed:
Oct 31, 1990
Appl. No.:
7/608971
Inventors:
Anders O. Andersson - Seattle WA
Erik L. Godo - Kirkland WA
Assignee:
The Boeing Company - Seattle WA
International Classification:
G01M 700
G01H 1700
US Classification:
364508
Abstract:
A method and apparatus for reducing multiple-source repetitive vibrations in a region or structure (12) by applying control vibrations to the region or structure via actuators (18), frequently recalculating the control vibrations based on source elements to accommodate for varying phase differences between the sources of the repetitive vibrations (14) and (16), and cyclically updating the source elements of the control vibrations is disclosed. The repetitive vibrations are sensed (20) synchronously with the repetitive vibration source chosen as the reference source and decomposed into a number of frequency components corresponding to the reference source. The control vibrations are formed of the same frequency components and applied synchronously with the reference source. Each frequency component of the control vibrations is defined by source elements, one for cancelling vibrations produced by each of the repetitive vibration sources. A first estimate of the source elements of the frequency components, defining control vibrations that will reduce the sensed vibrations, is made.
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Erik L Godo from Redmond, WA, age ~60 Get Report