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Michael E Renzelmann

from Woodinville, WA
Age ~72

Michael Renzelmann Phones & Addresses

  • 21430 78Th Ave, Woodinville, WA 98072
  • Auburn, WA

Publications

Us Patents

Dynamic Adjustment Of Wing Surfaces For Variable Camber

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US Patent:
7641152, Jan 5, 2010
Filed:
Apr 13, 2007
Appl. No.:
11/734842
Inventors:
Dan Onu - Redmond WA, US
John D. Winter - Seattle WA, US
Candy L. Carr - Everett WA, US
Paul M. Vijgen - Everett WA, US
Gary A. Emch - Marysville WA, US
Michael E. Renzelmann - Woodinville WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
G05D 1/00
US Classification:
244194
Abstract:
The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i. e. , inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

Reduced Door Opening Force And Enhanced Security Flight Deck Door Mechanism

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US Patent:
7770949, Aug 10, 2010
Filed:
Oct 24, 2007
Appl. No.:
11/923238
Inventors:
James J. Kunda - Snohomish WA, US
Shannon J. Kupfer - Kirkland WA, US
Michael E. Renzelmann - Woodinville WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
E05B 15/02
E05C 1/06
US Classification:
29234116, 292144, 292340, 29234115
Abstract:
An aircraft door mechanism includes a solenoid connected to a support assembly. The solenoid displaces the latch pin between a solenoid energized and a solenoid de-energized position. A catch assembly rotatably connected to the support assembly is positioned to engage a 3 degree or less taper portion of the latch pin in the solenoid energized position. When the latch pin moves to the solenoid de-energized position, a latch bolt supported by the door rotates the catch assembly. The latch bolt includes a distal bulbous end which multiplies the force applied to the door to rotate the catch assembly. If the latch pin is extended, a substantially greater force is required to force the latch pin to the solenoid de-energized position owing to the reduced taper of the latch pin. Authorized door entry is therefore easier and unauthorized door entry is made more difficult.

In-Flight Detection Of Wing Flap Free Wheeling Skew

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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.

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.

Dynamic Adjustment Of Wing Surfaces For Variable Camber

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US Patent:
8447445, May 21, 2013
Filed:
Nov 18, 2009
Appl. No.:
12/620698
Inventors:
Dan Onu - Redmond WA, US
John D. Winter - Seattle WA, US
Candy L. Carr - Everett WA, US
Paul M. Vijgen - Everett WA, US
Gary A. Emch - Marysville WA, US
Michael E. Renzelmann - Woodinville WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 13/00
US Classification:
701 11, 244201
Abstract:
The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i. e. , inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

Reduced Door Opening Force And Enhanced Security Flight Deck Door Mechanism

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US Patent:
20060076457, Apr 13, 2006
Filed:
Oct 12, 2004
Appl. No.:
10/963356
Inventors:
James Kunda - Snohomish WA, US
Shannon Kupfer - Kirkland WA, US
Michael Renzelmann - Woodinville WA, US
International Classification:
B64C 1/14
US Classification:
244129500
Abstract:
An aircraft door mechanism includes a solenoid connected to a support assembly. The solenoid displaces the latch pin between a solenoid energized and a solenoid de-energized position. A catch assembly rotatably connected to the support assembly is positioned to engage a 3- degree or less taper portion of the latch pin in the solenoid energized position. When the latch pin moves to the solenoid de-energized position, a latch bolt supported by the door rotates the catch assembly. The latch bolt includes a distal bulbous end which multiplies the force applied to the door to rotate the catch assembly. If the latch pin is extended, a substantially greater force is required to force the latch pin to the solenoid de-energized position owing to the reduced taper of the latch pin. Authorized door entry is therefore easier and unauthorized door entry is made more difficult.

Latch Pin Inhibitor For Folding Wing-Tip Aircraft

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US Patent:
53501357, Sep 27, 1994
Filed:
Apr 12, 1993
Appl. No.:
8/045903
Inventors:
Michael E. Renzelmann - Woodinville WA
Mark H. Smith - Vashon Island WA
Assignee:
The Boeing Company - Seattle WA
International Classification:
B64C 356
US Classification:
244 49
Abstract:
A folding wing tip (14) on an aircraft (2) carries a lug (16) that moves into alignment with lugs (6, 10) on the inboard wing portion (4) as the wings spread. The lug (16) pivots an inhibitor (28) that is interconnected by linkage to a valve spool (122). The pivoting of the inhibitor (28) causes the spool (122) to shift its position so that a sense port is brought into communication with a return port. Return pressure in the sense port indicates a spread wing condition. When the wing tip (14) is folded, springs move the inhibitor (28) and the valve spool (122) back to their original positions. This communicates the sense port with a pressure port to indicate a folded wing condition. The spool (122) is preferably also biased into its original position by fluid pressure. In addition, the lug (16) has a cam (92) that engages a roller (84) carried by the inhibitor (28) when the wing tip (14) is moved into a folded position.

Self-Monitoring Latch Pin Lock For Folding Wing Aircraft

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US Patent:
52014797, Apr 13, 1993
Filed:
Jan 30, 1992
Appl. No.:
7/828308
Inventors:
Michael E. Renzelmann - Woodinville WA
Assignee:
The Boeing Company - Seattle WA
International Classification:
B64C 356
US Classification:
244 49
Abstract:
A latch pin and locking system for use in connection with an aircraft having folding wings or wing tips. The system includes a plurality of individual latch pin units, each of which has a pin that is hydraulically driven in extension and retraction. When extended, the pins cooperatively lock wing tip hinge structure which prevents wing tip folding movement. Each latch pin unit has a locking body that prevents pin retraction of its respective pin after extension thereof for wing tip locking. The locking bodies of all of the latch pin units are drivingly interlinked, so that all lock and/or unlock as a single network. The network is driven by a single power drive unit. In the event any one locking body in the network fails, the network is broken, and thereby provides an indication that maintenance is required.
Michael E Renzelmann from Woodinville, WA, age ~72 Get Report