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Friedrich K Straub

from Mesa, AZ
Age ~73
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Also known as:
Friedrich Ulrike Straub, Kathleen Kaplan, Kate Hitt
Phone and address:
3135 E Fairbrook St, Mesa, AZ 85213
Related to:
Jameson DedonKarl Straub Friedrich, 74Mary Straub, 96Christa HuenichJames Straub
Connected to:
Brittany H Straub, 37Deanna C Straub, 54Delores D Straub, 67Diana L Straub, 59Douglas J Straub, 59Ginny Straub, 80Glenn R Straub, 92Greg J Straub, 53Joyce L Straub, 79Judith L Straub, 75

Friedrich Straub Phones & Addresses

  • 3135 E Fairbrook St, Mesa, AZ 85213
  • Chandler, AZ
  • 1760 E Halifax St, Mesa, AZ 85203 (480) 251-7007

Work

Company: Boeing Position: Rotor dynamics technical fellow

Education

Degree: High school graduate or higher

Skills

Systems Engineering • Aerospace • Aerospace Engineering • Composites • Spacecraft • Finite Element Analysis • Engineering Management • Simulations • Program Management • Simulink • Structural Dynamics • Stress Analysis • Aircraft • Avionics • Space Systems • Matlab • Fortran • Aircraft Design • Flight Test • Ansys • Aeronautics • Cfd • Propulsion • Dynamics • System Design • Mil Std 1553 • Trade Studies • Damage Tolerance • Systems Design

Industries

Defense & Space

Resumes

Resumes

Friedrich Straub Photo 1

Rotor Dynamics Technical Fellow

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Location:
Phoenix, AZ
Industry:
Defense & Space
Work:
Boeing
Rotor Dynamics Technical Fellow
Skills:
Systems Engineering
Aerospace
Aerospace Engineering
Composites
Spacecraft
Finite Element Analysis
Engineering Management
Simulations
Program Management
Simulink
Structural Dynamics
Stress Analysis
Aircraft
Avionics
Space Systems
Matlab
Fortran
Aircraft Design
Flight Test
Ansys
Aeronautics
Cfd
Propulsion
Dynamics
System Design
Mil Std 1553
Trade Studies
Damage Tolerance
Systems Design

Publications

Us Patents

Helicopter In-Flight Rotor Tracking System, Method, And Smart Actuator Therefor

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US Patent:
6453669, Sep 24, 2002
Filed:
Sep 19, 2001
Appl. No.:
09/955769
Inventors:
Dennis K. Kennedy - Mesa AZ
Friedrich K. Straub - Mesa AZ
Ahmed A. Hassan - Mesa AZ
Assignee:
The Boeing Company - Seattle WA
International Classification:
F01B 2910
US Classification:
60527, 60528
Abstract:
A system for quasi-statically correcting tracking of rotor blades of a helicopter rotor during operation includes a trim tab mounted on each rotor blade and deflectable relative to the rotor blade so as to change a tracking path of the rotor blade, and a rotor track and balance analyzer that includes sensors for acquiring rotor tracking and balance information and is operable to process the rotor tracking and balance information so as to predetermine a new tab position to which the trim tab should be deflected for bringing the tracking path of a mistracking rotor blade into alignment with a reference path. The trim tab is deflected by an actuator mounted to the rotor blade, the actuator having an actuating element coupled with the trim tab and formed of a smart material such that the actuating element deforms proportional to a stimulus applied to the actuating element. An electrical locking device is included which is operable when de-energized to lock the trim tab against deflection, and operable when energized to unlock to permit the trim tab to be deflected. A trim actuation control system in communication with the rotor track and balance analyzer and the locking device is arranged to energize the locking device and to supply electrical power to the actuator so as to deflect the trim tab to the new tab position predetermined in the rotor track and balance analyzer, and to then de-energize the locking device and cut off the electrical power to the actuator.

Apparatus And Methods For Structurally-Integrated Conductive Conduits For Rotor Blades

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US Patent:
20060049302, Mar 9, 2006
Filed:
Aug 31, 2004
Appl. No.:
10/930478
Inventors:
Dennis Kennedy - Mesa AZ, US
Friedrich Straub - Mesa AZ, US
Robert Murrill - Gilbert AZ, US
International Classification:
B64C 27/00
US Classification:
244017110
Abstract:
Structurally-integrated conductive conduits for rotor blades are disclosed. In one embodiment, an elongated rotor blade includes a body having a root portion and a distal portion spaced apart from the root portion, a device coupled to the body, and a conduit assembly disposed within the body and extending between the root portion and the device. The conduit assembly includes a main body assembly having at least one of a conductive lead, a fluid line, and an optical fiber disposed within a matrix material, the conduit assembly extending from the root portion to the device. In alternate embodiments, the device may comprise an actuator, a smart actuator, a piezoelectric material, an electromagnetic device, an electromechanical device, a hydraulic actuator, a pneumatic actuator, a light, and a sensor.

Helicopter Rotor Blade Flap Actuator Government Interest

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US Patent:
61357138, Oct 24, 2000
Filed:
Jan 19, 1999
Appl. No.:
9/233986
Inventors:
David B. Domzalski - Gilbert AZ
Friedrich K. Straub - Mesa AZ
Dennis K. Kennedy - Mesa AZ
Assignee:
The McDonnell Douglas Helicopter Company - Mesa AZ
International Classification:
B64C 900
US Classification:
416 23
Abstract:
An actively controlled helicopter rotor blade includes a trailing edge flap actuated by a fast-acting actuator. A lightweight, rugged, fast-acting actuator suitable for use as the flap actuator comprises a pair of column actuators composed of a smart material such as piezoelectric, magnetostrictive, shape memory alloy or other material that exhibits a shape change when subjected to an external stimulus. Each of the column actuators is composed of multiple piezoelectric ceramic actuator elements bonded together to form the individual columns. Each of the column actuators engages the base of an actuator tube that, in turn, is urged against the column actuators by a tension member. Differential voltage applied to the columns causes a differential elongation of the column actuators, which causes the actuator tube to pivot about an axis proximal the tips of the column actuators. The movement of the actuator tube is coupled by a linkage to the rotor blade flap. Spherical joints are disposed between the column actuators and the actuator tube to prevent transmission of substantial bending loads to the column actuators and a mid-point support is also provided for each of the column actuators to limit the magnitude of acceleration induced bending loads, which would otherwise lead to tensile failure of the ceramic actuator elements.

Helicopter In-Flight Rotor Tracking System, Method, And Smart Actuator Therefor

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US Patent:
63223244, Nov 27, 2001
Filed:
Mar 3, 2000
Appl. No.:
9/518839
Inventors:
Dennis K. Kennedy - Mesa AZ
Friedrich K. Straub - Mesa AZ
Ahmed A. Hassan - Mesa AZ
Assignee:
The Boeing Company - Seattle WA
International Classification:
B64C 900
G01M 122
US Classification:
416 1
Abstract:
A system for quasi-statically correcting tracking of rotor blades of a helicopter rotor during operation includes a trim tab mounted on each rotor blade and deflectable relative to the rotor blade so as to change a tracking path of the rotor blade, and a rotor track and balance analyzer that includes sensors for acquiring rotor tracking and balance information and is operable to process the rotor tracking and balance information so as to predetermine a new tab position to which the trim tab should be deflected for bringing the tracking path of a mistracking rotor blade into alignment with a reference path. The trim tab is deflected by an actuator mounted to the rotor blade, the actuator having an actuating element coupled with the trim tab and formed of a smart material such that the actuating element deforms proportional to a stimulus applied to the actuating element. An electrical locking device is included which is operable when de-energized to lock the trim tab against deflection, and operable when energized to unlock to permit the trim tab to be deflected. A trim actuation control system in communication with the rotor track and balance analyzer and the locking device is arranged to energize the locking device and to supply electrical power to the actuator so as to deflect the trim tab to the new tab position predetermined in the rotor track and balance analyzer, and to then de-energize the locking device and cut off the electrical power to the actuator.

Oscillating Air Jets For Helicopter Rotor Aerodynamic Control And Bvi Noise Reduction

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US Patent:
60929901, Jul 25, 2000
Filed:
Jun 5, 1997
Appl. No.:
8/869725
Inventors:
Ahmed A. Hassan - Mesa AZ
Friedrich K. Straub - Mesa AZ
David B. Domzalski - Gilbert AZ
Assignee:
McDonnell Douglas Helicopter Company - Mesa AZ
International Classification:
B64C 2704
US Classification:
416 42
Abstract:
An active control system for reducing blade-vortex-interaction (BVI) noise generated by a rotor blade. The active control system includes a pressure sensor assembly, a device for changing a lift generated by the rotor blade, and a controller for activating the device upon a detected change in air pressure by the sensor assembly. The sensor assembly is disposed in close proximity to the rotor blade, and is adapted to detect a change in air pressure on a surface of the rotor blade near a leading edge of the rotor blade. The device is adapted to be activated by the controller, to thereby change a lift of the rotor blade. The controller activates the device to change a lift of the rotor blade in order to introduce a compensating pressure onto the surface of the rotor blade. This compensating pressure attenuates the magnitude of the change of air pressure. The device for changing a lift generated by the rotor blade can include at least one aperture on the rotor blade and a diaphragm in the interior of the rotor blade.

Active Blowing System For Rotorcraft Vortex Interaction Noise Reduction

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US Patent:
58136258, Sep 29, 1998
Filed:
Oct 9, 1996
Appl. No.:
8/727980
Inventors:
Ahmed A. Hassan - Mesa AZ
Friedrich K. Straub - Mesa AZ
David B. Domzalski - Gilbert AZ
Dennis K. Kennedy - Mesa AZ
Assignee:
McDonnell Douglas Helicopter Company - Mesa AZ
International Classification:
B64C 2700
US Classification:
244 1711
Abstract:
A pressurized porous surface near the leading edge of a rotorcraft blade, is designed to be used as an active control device which alleviates the aerodynamics of blade vortex interactions (BVI) and thus the impulsive BVI noise levels and signature. The pressurized porous surface can be actuated on an azimuth-dependent deployment schedule or actuated continuously. The pressurized porous surface is supplied with either positively pressurized air, negatively pressurized air, or a combination of both, when actuated. The pressurized porous surface targets the local blade aerodynamics, rather than the vortex strength or blade/vortex separation distance. This targeting can be achieved through use of negatively pressurized air (suction) blowing in a direction normal to the blade surface to reduce the rotor blade's effective thickness resulting in a smaller leading edge radius as perceived by the vortex wake, and positively pressurized air (blowing) to increase the effective thickness resulting in an increase in the leading edge radius of the blade.

Apparatus, System, And Method For Pitching And Twisting A Blade Of A Rotorcraft

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US Patent:
20140154074, Jun 5, 2014
Filed:
Dec 5, 2012
Appl. No.:
13/705780
Inventors:
The Boeing Company - , US
Terrence S. Birchette - Chandler AZ, US
Friedrich K. Straub - Mesa AZ, US
Assignee:
THE BOEING COMPANY - Chicago IL
International Classification:
B64C 11/32
US Classification:
416 1, 416147
Abstract:
A method and apparatus for moving a blade of a rotorcraft. The method comprises operating the rotorcraft and applying a torque to an elongate member connected to a tip portion of the blade during operation of the rotorcraft using a tip actuation mechanism that is external to the blade and associated with the elongate member such that the tip portion of the blade rotates about an axis through the blade.
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Friedrich K Straub from Mesa, AZ, age ~73 Get Report