ai-aerospace/ams_data_full_2000-2020 huggingface dataset:
Fi gure 6. Normalized LQF vs. axial load for a range of average temperature but constant temperature  gradient  of 12°C for 305- size all -Steel Bearing  

Results from the Silicon Nitride Hybrid Bearing   A matrix of test data was  also collected for an ABEC 7 305- size hybrid ball bearing with silicon nitride balls .  In this series of tests, the applied axial load ranged from 89 to 222 N ( 20 to 50 lb ). The exact bearing  temperature was not controlled to a specific predetermined temperature, but rather was varied and recorded while testing under a wide set of heat sinks and heat lamp output . This resulted in a range of average  temperatures from approximately 15 to 30°C, and a temperature differential that ranged from approximately 10 to 16°C . The LQF observations throughout this range of test conditions will be presented in the next  sections .   Effect of Average Temperature on LQF   Figure 7 represents the normalized LQF as a function of average temperature for a 305- size hybrid bearing,  where each graph represents a different axial load. In these graphs, each curve represents a particular  fixed temperature differential value ( DT). The trends show that there is an increase in LQF as average  temperature rises in an approximately linear fashion. However, in some fixed load values, the slopes of  curves at different D T values are not parallel . This indicates that the sensitivity of LQF to T ave is dependent  on the temperature differential across the bearing. Figure 7a  suggests that at low preload, a smaller DT  results in  a slightly  higher sensitivity to T ave, while Figure 7c suggests that at higher preload, a smaller D T  results in  a slightly  lower sensitivity to T ave.   To separate the impact of thermal gradient, Figure 8 shows the normalized LQF as a function of average  temperature for a constant temperature gradient of 12 °C for each of the axial loads tested. The results  show that each curve appear somewhat parallel under these conditions, indicating for the same gradient, the LQF is sensitive to average temperature to the same degree, except for the 222 N ( 50 lb ) load case.  This contrasts with the steel bearing, where each curve was parallel except for the lowest load of 89 N   (20 lb ).      NASA/CP—2018-219887 551
F igure 7a. Applied load of 89 N ( 20 lb)    Figure 7b. Applied load of 133 N ( 30 lb )        Figure 7c. Applied load of 178 N ( 40 lb )    Figure 7d. A pplied load of 222 N ( 50 lb) Figure 7. Normalized LQF vs. average temperature for variable applied loads and constant temperature  gradient for 305- size Hybrid Bearing  

Figure 8. Normalized LQF vs. average temperature for variable applied loads but constant temperature  gradient of 12°C for 305-size Hybrid Bearing  

Effect of Temperature Gradient on LQF   Figur es 9 represents the normalized LQF as a function of temperature gradient for a 305- size hybrid  bearing, where each graph represents a different axial load. In the  plots, each curve represents a fixed  average temperature. The trends show that there is  generally  an increase in LQF with increased  temperature gradient, but the slope is  influenced by axial loads . Although it is only one data point, in the  case of the largest 222 N (50 lb) load, the LQF actually decreased with increasing DT for an average  temperature of 24°C . Again, the LQF trends suggest a complex interdependence between average  temperature, temperature gradient, and axial loads.  

NASA/CP—2018-219887 552
Fi gure 9a. A pplied load of 89 N ( 20 lb) Figure 9b. Applied load of 133 N ( 30 lb )

       Figure 9c.  Applied load of 178 N ( 40 lb ) Figure 9d. Applied load of 222 N ( 50 lb )

Figure 9. Normalized LQF vs. temperature gradient for variable applied loads and constant average  temperature for 305- size Hybrid Bearing  

Figure 10 shows the coupled relation between temperature gradient and axial load on LQF in a more  condensed way . This graphs the LQF as a function of temperature gradient for a constant average  temperature of 24°C for each of the applied loads . The curves show that the slope of this relation between  LQF and temperature gradient is non- linearly a function of axial load.  

Figure 10. Normalized LQF vs. temperature gradient for variable applied loads and constant average  temperature of 20°C for 305- size Hybrid Bearing  

Effect of Axial Load on LQF   Figure 11 represents the normalized LQF as a function of axial loads for a 305- size hybrid bearing. Each  curve represents a constant average temperature, and all data were collected with a temperature gradient of 12°C . The results show that the LQF generally increases in direct proportion with the axial load, and  the magnitude of the LQF increases with the average temperature. These trends are consistent with the  NASA/CP—2018-219887 553
Refer ences   1.Y.  R. Takeuchi, P. P. Frantz, and M. R. Hilton, “Observations of Spacecraft Bearing Lubricant Redistribution Based on Thermal Conductance Measurements”, Proceedings of the 42nd Aerospace Mechanisms Symposium, NASA GSFC, May, 2014. 2.H. Poritsky, C. W. Hewlett, and R. E. Coleman, “Sliding Friction of Ball Bearings of the Pivot Type”, Journal of Applied Mechanics , December 1947. 3.G. S. Reichenback, “The Importance of Spinning Friction in Thrust Carrying Ball Bearings”, ASME 59-LUB-6. 4.R. C. Drutowski, “The Role of Micro- Slip for Freely Rolling Bodies”, ASME -ASLE International Lubrication Conference, 1964. 5.H. L. Heathcote, “The Ball Bearing: In the Making, Under Test and on Service”, Proc. Instn. OfAutomobile Engineers , Vol. 15, page 569, 1921. 6.A. Palmgren, “Sliding Friction in Ball Bearings”, Engineering, Vol. 107, pages 289, 1919. 7.J. A. Greenwood, H. Minshall, and D. Tabor, “Hysteresis Losses in Rolling and Sliding Friction”,Proc. Royal Society , pages 480- 507, July 1960. 8.A. Palmgren and B. Snare, “Influence of Load and Motion on the Lubrication and Wear of RollingElements”, Inst. Of Mech. Eng., London, 1957. 9.N. Biboulet and L. Houpert, “Hydrodynamic Force and Moment in Pure Rolling Lubricated Contacts”,Proc. IMechE Vol. 224 Part J: J. Engineering Tribology , March 2010 . 10. P. Frantz, “Diagnostic Methods for High Cycle Precision Mechanisms”,  2015 ASTM International Rolling Element Bearings Conference, Anaheim, CA, April 29, 2015. NASA/CP—2018-219887 557
NASA/CP—2008–215252 39th Aerospace Mechanisms Symposium Compiled by  E.A. BoesigerLockheed Martin Space Systems Company, Sunnyvale, California May 2008Proceedings of a Symposium held at theV on Braun Center, Huntsville, Alabama, Hosted by Marshall Space Flight Center and Lockheed Martin Space Systems Company,Organized by the Mechanisms Education AssociationMay 7–9, 2008
The NASA STI Program…in Proﬁle  Since its founding, NASA has been dedicated   to the advancement of aeronautics and space science. The NASA Scientiﬁc and Technical Information (STI) Program Ofﬁce plays a key  part in helping NASA maintain this important role.  The NASA STI program operates under the  auspices of the Agency Chief Information Ofﬁcer. It collects, organizes, provides for archiving, and disseminates NASA’s STI. The NASA STI program provides access to the NASA Aeronautics and Space Database and its public interface, the NASA Technical Report Server, thus providing one of the largest collections of aeronautical and space science STI in the world. Results are published in both non-NASA channels and by NASA in the NASA STI Report Series, which includes the following report types: • TECHNICAL PUBLICATION. Reports of  completed research or a major signiﬁcant phase of research that present the results of NASA programs and include extensive data or theoretical analysis. Includes compilations of signiﬁcant scientiﬁc and technical data and information deemed to be of continuing reference value. NASA’s counterpart of peer-reviewed formal professional papers but has less stringent limitations on manuscript length and extent of graphic presentations. • TECHNICAL MEMORANDUM. Scientiﬁc  and technical ﬁndings that are preliminary or of specialized interest, e.g., quick release reports, working papers, and bibliographies that contain minimal annotation. Does not contain extensive analysis. • CONTRACTOR REPORT. Scientiﬁc and  technical ﬁndings by NASA-sponsored contractors and grantees.• CONFERENCE PUBLICATION. Collected  papers from scientiﬁc and technical conferences, symposia, seminars, or other meetings sponsored or cosponsored by NASA. • SPECIAL PUBLICATION. Scientiﬁc, technical,  or historical information from NASA programs, projects, and missions, often concerned with subjects having substantial public interest. • TECHNICAL TRANSLATION. Englishlanguage translations of foreign scientiﬁc and technical material pertinent to NASA’s mission.  Specialized services also include creating   custom thesauri, building customized databases,  and organizing and publishing research results.  For more information about the NASA STI  program, see the following: • Access the NASA STI program home page at  <http://www.sti.nasa.gov> • E-mail your question via the Internet to   <help@sti.nasa.gov> • Fax your question to the NASA STI Help Desk  at 301– 621–0134 • Phone the NASA STI Help Desk at   301– 621–0390 • Write to:  NASA STI Help Desk NASA Center for AeroSpace Information 7115 Standard Drive Hanover, MD  21076–1320
iNASA/CP—2008–215252 39th Aerospace Mechanisms Symposium Compiled by  E.A. BoesigerLockheed Martin Space Systems Company, Sunnyvale, California May 2008 National Aeronautics andSpace Administration Marshall Space Flight Center • MSFC, Alabama  35812Proceedings of a Symposium held at the V on Braun Center, Huntsville, Alabama, Hosted by Marshall Space Flight Center and Lockheed Martin Space Systems Company,Organized by the Mechanisms Education AssociationMay 7–9, 2008
iiAvailable from: NASA Center for AeroSpace Information 7115 Standard Drive Hanover, MD  21076 –1320 301– 621– 0390 This report is also available in electronic form at <https://www2.sti.nasa.gov>Acknowledgments The high quality of this symposium is a result of the work of many people, and their efforts are gratefully acknowledged.  This extends to the voluntary members of the symposium organizing committee representing the eight NASA Field Centers,  Lockheed Martin Space Systems Company, and the European Space Agency. Appreciation is also extended to the session  chairs, the authors, and particularly the personnel at Marshall Space Flight Center responsible for the symposium   arrangements and the publication of these proceedings. A sincere thank you also goes to the symposium   executive committee who is responsible for the year-to-year management of the Aerospace Mechanisms   Symposium, including paper processing and preparation of the program.   TRADEMARKS Trade names and trademarks are used in this report for identiﬁcation only. This usage does not constitute an ofﬁcial  endorsement, either expressed or implied, by the National Aeronautics and Space Administration.
iiiTABLE OF CONTENTS Symposium Schedule  ........................................................................................................... ..........  vi Symposium Organizing and Advisory Committees  .......................................................................  xi Linear High-Force “Step and Repeat” Piezoelectric Motors  .........................................................  1 Jeffrey Paine, M. Johns, J. Sesler, M. Stefanick & J.A. Kennedy Development of a High Resolution Rotary Actuator for an Antenna Trimming Mechanism  .......  15 Jérôme Brossier, Xavier Jeandot, Yannick Baudasse, David Grima & Fabrice Champandard Implications of Underdamped Stepper Mechanism Performance and Damping Solution  Methodology  .................................................................................................................. ................  29 Shane Brown & Scott Starin Large Scale Magnetostrictive Valve Actuator  ................................................................................  4 5 James Richard, Elizabeth Holleman & David Eddleman Design and Development of a Miniaturized Double Latching Solenoid Valve  for the Sample Analysis at Mars Instrument Suite  .........................................................................  51 James Smith A New Structural Bonding Process for Ferromagnetic Sheet Stacking used in Electric  Motors (Rotors, Stators…) ..................................................................................................... ........  61 Christophe Casteras, Bruno Bonduelle & Frederic Martin Evaluation of Perﬂouropolyether Lubricant Lifetime in the High Stress and High  Stress-Cycle Regime for Mars Applications  ..................................................................................  6 9 Jason Herman & Kiel Davis Mars Science Laboratory Rover Mobility Bushing Development  ................................................  83  Benjamin Riggs  Space Shuttle Orbiter Atlantis Liquid Oxygen Pre-Valve Detent Roller Cracking  Investigation  ................................................................................................................ ...................  97 Elizabeth Holleman, David Eddleman, Rebecca Jacobs & James Richard Measuring the EHD Film Thickness in a Rotating Ball Bearing  ...................................................  107 Peter Ward, Alan Leveille & Peter Frantz Scanning System Development and Associated Bearing Cage Instability Issue  ...........................  117 Manfred Schmid & Christian Hehr
ivTABLE OF CONTENTS (Continued) Launch Lock Mechanism Design Fault Tree Use and Coatings Study  .........................................  131 Daniel Villa & Gustavo Toledo Lessons Learned Designing a Spherical Satellite Release Mechanism  .........................................  145 Ryan Hevner Wear Life Testing of a Mission Critical Separation Interface  ........................................................  157 Jonathan Wood & Joseph de la Fuente Circular Hall Transducer for Accurate Contactless Angular Position Sensing  ..............................  171 Laurent Sache, Serge Reymond, Pavel Kejik, Mikael Sjöholm, Daniel Bommottet, V olker Gass, Lionel Gaillard & Radjan Popovic Electrically Powered Separation Nuts  ......................................................................................... ..  185 Barney Little A Radiation-Hardened, High-Resolution Optical Encoder for Use in Aerospace Applications  ....  191 Pat Kreckie A Novel Grabbing/Latching Mechanism Without Moving Parts  ..................................................  199 Brian Gore & Gary Hawkins Docking System Mechanism Utilized on Orbital Express Program  ..............................................  207 Scott Christiansen & Troy Nilson Ultra Light Self-Motorized Mechanism for Deployment of Light Weight Spacecraft  Appendages  ................................................................................................................... .................  221 Cornel Bösch, C. Pereira, R. John, T. Schmidt, K. Seifart, H. Sparr, J. Lautier & T. Pyttel Development of the Aquarius Antenna Deployment Mechanisms and Spring/Damper  Actuator  ..................................................................................................................... .....................  235 Joel Johnson Deﬂection Analysis of the Space Shuttle External Tank Door Drive Mechanism  .........................  249 Michael Tosto, Bo Trieu, Brent Evernden, Drew Hope, Kenneth Wong & Robert Lindberg Failure of the Trailing Umbilical System Disconnect Actuator on the International  Space Station  ................................................................................................................ ..................  259 Adam Gilmore, Chris Schmitt, Laura Merritt & V . J. Bolton The Mars Climate Sounder In-Flight Positioning Anomaly  ..........................................................  271 Bruno Jau & David Kass
vTABLE OF CONTENTS (Continued) Icy Soil Acquisition Device for the 2007 Phoenix Mars Lander  ...................................................  289 Philip Chu, Jack Wilson, Kiel Davis, Lori Shiraishi & Kevin Burke  Sample Manipulation System for Sample Analysis at Mars  ..........................................................  303 Erik Mumm, Tom Kennedy, Lee Carlson & Dustyn Roberts A System for Suspending and Vibration-Isolating a Large Spacecraft for Testing in Vacuum  .....  317 David Keinholz Gas Strut Separation Alternative for Ares I  .................................................................................. .  331 Brian Floyd & James Owens Evaluation of Separation Mechanism Design for the Orion/Ares Launch Vehicle ........................  345 Kevin Konno, Daniel Catalano & Thomas Krivanek Focus Mechanism for Kepler Mission  ...........................................................................................  359 Kraig Koski Precision Linear Actuator for Space Interferometry Mission (SIM) Siderostat Pointing ...............  373 Brant Cook, David Braun, Steve Hankins, John Koenig & Don Moore Development of a Low-Cost Fine Steering Mirror  ........................................................................  387 Steve Wassom & Morgan Davidson Cryogenic Focus Mechanism for the Spitzer Space Telescope  .....................................................  401 William Schade Development of a Spacecraft Antenna Pointing Gimbal  ...............................................................  415 Chuck Monroe & Peter Rossoni
viSYMPOSIUM SCHEDULE WEDNESDAY, 7 MAY 2008 7:30  Wednesday Presenters’ Breakfast – Embassy Suites Hotel Redstone Boardroom   8:00  CHECK-IN AND REFRESHMENTS  – V on Braun Center South Hall Meeting Rooms   8:30  INTRODUCTORY REMARKS  – V on Braun Center South Hall Meeting Rooms Donald McQueen, Jr., Host Chairman   NASA Marshall Space Flight Center, Huntsville, ALEdward Boesiger, Operations ChairmanLockheed Martin Space Systems, Sunnyvale, CA   CENTER WELCOME   NASA Marshall Space Flight Center, Huntsville, AL 9:00  SESSION I—ACTUATORS & MOTORS  – V on Braun Center South Hall Meeting Rooms Chris Kalogeras, Session ChairBoeing Satellite Systems, El Segundo, CA • Linear High-Force “Step and Repeat” Piezoelectric Motors Jeffrey Paine, M. Johns, J. Sesler, M. Stefanick & J.A. Kennedy, Dynamic Structures and Materials LLC, Franklin, TN • Development of a High Resolution Rotary Actuator for an Antenna Trimming Mechanism Jérôme Brossier, Xavier Jeandot, Yannick Baudasse, David Grima & Fabrice Champandard, Thales Alenia Space, Cannes, France • Implications of Underdamped Stepper Mechanism Performance and Damping Solution   Methodology Shane Brown & Scott Starin, Ball Aerospace & Technologies Corp., Boulder, CO • Large Scale Magnetostrictive Valve Actuator James Richard, Elizabeth Holleman & David Eddleman, NASA Marshall Space Flight Center, Huntsville, AL • Design and Development of a Miniaturized Double Latching Solenoid Valve for the Sample  Analysis at Mars Instrument SuiteJames Smith, NASA Goddard Space Flight Center, Greenbelt, MD • A New Structural Bonding Process for Ferromagnetic Sheet Stacking used in Electric Motors Christophe Casteras, CNES, Toulouse, France; Bruno Bonduelle, SOTEREM, Castanet Tolosan, France; Frederic Martin, CLIX Industries, Toulouse, France
vii11:45  LUNCH BREAK  – Box lunch is provided   1:00  SESSION II—BEARINGS & TRIBOLOGY  – V on Braun Center South Hall Meeting Rooms Ralph Carruth, Session ChairNASA Marshall Space Flight Center, Huntsville, AL • Evaluation of Perﬂouropolyether Lubricant Lifetime in the High Stress and High Stress-Cycle  Regime for Mars ApplicationsJason Herman & Kiel Davis, Honeybee Robotics Spacecraft Mechanisms Corp., New York, NY • Mars Science Laboratory Rover Mobility Bushing Development Benjamin Riggs, Jet Propulsion Laboratory, Pasadena, CA • Space Shuttle Orbiter Atlantis Liquid Oxygen Pre-Valve Detent Roller Cracking Investigation  Elizabeth Holleman, David Eddleman & James Richard, NASA Marshall Space Flight Center, Huntsville, AL; Rebecca Jacobs, Jacobs Engineering Science & Technical Services Group, Huntsville, AL • Measuring the EHD Film Thickness in a Rotating Ball Bearing Peter Ward, Alan Leveille & Peter Frantz, The Aerospace Corporation, El Segundo, CA • Scanning System Development and Associated Bearing Cage Instability Issue Manfred Schmid & Christian Hehr, EADS Astrium GmbH Satellites, Friedrichshafen, Germany 3:30  BREAK 3:45  SESSION III—RELEASE & SENSORS  – V on Braun Center South Hall Meeting Rooms John Bohner, Session ChairThe Aerospace Corporation, El Segundo, CA • Launch Lock Mechanism Design Fault Tree Use and Coatings Study Daniel Villa & Gustavo Toledo, Sandia National Laboratories, Albuquerque, NM • Lessons Learned Designing a Spherical Satellite Release Mechanism Ryan Hevner, Planetary Systems Corp., Silver Spring, MD • Wear Life Testing of a Mission Critical Separation Interface Jonathan Wood & Joseph de la Fuente, Lockheed Martin Space Systems Company, Sunnyvale, CA • Circular Hall Transducer for Accurate Contactless Angular Position Sensing Laurent Sache, Mikael Sjöholm, Daniel Bommottet & V olker Gass, RUAG Aerospace, Nyon, Switzerland; Serge Reymond, Pavel Kejik & Radjan Popovic, Ecole Polytechnique Fédérale de Lausanne, Lausanne, Switzerland; Lionel Gaillard, European Space Research and Technology Centre, Noordwijk, The Netherlands • Electrically Powered Separation Nuts Barney Little, Hi-Shear Technology Corporation, Torrance, CA
viii• A Radiation-Hardened, High-Resolution Optical Encoder for Use in Aerospace Applications Pat Kreckie, MicroE Systems, Natick, MA • A Novel Grabbing/Latching Mechanism Without Moving Parts Brian Gore & Gary Hawkins, The Aerospace Corporation, El Segundo, CA 6:30– 9:30 RECEPTION & DISPLAYS  – V on Braun Center Invited component suppliers display current products and provide tutorials   THURSDAY, 8 MAY 2008   7:30  Thursday Presenters’ Breakfast – Embassy Suites Hotel Redstone Boardroom8:00  Light Refreshments – V on Braun Center South Hall Meeting Room8:30  SESSION IV—DOCK & DEPLOY  – V on Braun Center South Hall Meeting Room Gérard Migliorero, Session ChairESA/ESTeC, Noordwijk, The Netherlands • Docking System Mechanism Utilized on Orbital Express Program Scott Christiansen & Troy Nilson, SpaceDev Inc., Louisville, CO • Ultra Light Self-Motorized Mechanism for Deployment of Light Weight Space Craft Appendages Cornel Bösch & C. Pereira, RUAG Aerospace, Wallisellen, Switzerland; R. John, T. Schmidt, K. Seifart & H. Sparr, HTS GmbH, Coswig, Germany; J. Lautier, ESA-ESTeC, Noordwijk, The Netherlands; T. Pyttel, University of Applied Sciences, Friedberg, Germany • Development of the Aquarius Antenna Deployment Mechanisms and Spring/Damper Actuator Joel Johnson, Jet Propulsion Laboratory, Pasadena, CA 10:00  BREAK 10:15  SESSION V—ANOMALY INVESTIGATIONS  – V on Braun Center South Hall Meeting   Rooms Joe Pellicciotti, Session ChairNASA Goddard Space Flight Center, Greenbelt, MD • Deﬂection Analysis of the Space Shuttle External Tank Door Drive Mechanism Michael Tosto & Robert Lindberg, National Institute of Aerospace/University of Virginia, Hampton, V A; Bo Trieu & Drew Hope, NASA Langley Research Center, Hampton, V A; Brent Evernden & Kenneth Wong, NASA Johnson Space Center, Houston, TX • Failure of the Trailing Umbilical System Disconnect Actuator on the International Space Station Adam Gilmore & Laura Merritt, NASA Johnson Space Center, Houston, TX; Chris Schmitt & V .J. Bolton, The Boeing Company, Houston, TX