ai-aerospace/ams_data_full_2000-2020 huggingface dataset:
vi Development of a High- Performance, Low -Profile Translation Table with Wire Feedthrough   for a Deep Space CubeSat  ....................................................................................................................... 155  Alex Few  

Use of Volute Springs in Space Applications  ............................................................................................ 163  Chris Floyd, Ian Bournelis & Cary Clark    A Multi- Sectioning, Reconfigurable Electr omagnetic Hammering Propulsion for Mole Penetrators  ........ 171  Jerzy Grygorczuk, B artosz  Kędziora, Ł ukasz  Wiśniewski,  Marta Tokarz, J. Krasowski ,   Krzysztof Bieńkowski, M. Drogosz,  R. Graczyk  & Marcin Dobrowolski  

Development of a Magneto -Resistive Angular Position Sensor for Space Mechanisms  ......................... 177  Robert Hahn, Tilo Schmidt, Klaus Seifart, Bastian Olberts & Fer nando Romera 

Cu-Al-Ni Shape Memory Single Crystal Wires with High Transformation Temperature........................... 185  Alain Hautcoeur , Florian Fouché & Jacques Sicre  

Prevailing Torque Locking Feature in Threaded Fasteners using Anaerobic Adhesive.  .......................... 193  Alan Hernandez & Daniel  Hess    A New Architecture for Absolute Optical Encoders ................................................................................... 199  Timothy Malcolm, John Beasley & Mike Jumper    Digital Image Correlation for Performance Monitoring  .............................................................................. 205  Miguel Palaviccini , Dan Turner & Michael Herzberg  

Deployment System for Three Axis CubeSat Electric Field Instrument  ................................................... 213  Dana Turse, Larry Adams & Chris Esser  

Degradation of Sputter -Deposited Nanocomposite MoS 2 Coatings for NIRCam during Storage in Air  ... 221  Jeffrey Lince , Stuart  Loewenthal & Charles Clark  

The Dynamic Particle Generation of Lubr icating Greases for use in Space Mechanisms  ....................... 235  Jason Galary  

APM for a Constellation Intersatellite Link –  EM Qualification and Lessons Learned .............................. 247  Frank Härtel & Horst Kozilek  

Design Development of a Combined Deployment and Pointing System for the International   Space Station Neutron Star Interior Composition Explorer Telescope  ..................................................... 261  Jason Budinoff , Keith Gendreau, Zaven Arzoumanian, Charles Baker, Robert Berning,   Todd Colangelo,  John Holzinger, Jesse Lewis, Alice Liu, Alissa Mitchell,  Chuck Monroe,   Richard Pugh &  Roger Willey    Development of Compact Mechanically Driven Systems for High Strain Composite Slit -Tubes  ............. 269  Bruce Davis & Mark Lake 

James  Webb Space Telescope Deployment  Brushless DC Motor Characteristics Analysis  ................... 279  Anh Tran 

Development of a Deployment and Latching Mechanism for a Pointing System on the Neutron   Star Interior Composition Explorer (NICER) for Goddard Space Flight Center  ........................................ 293  Robert Berning  & John Holzinger
vii Tape Hinge/Lenticular Strut Hinge Qualification and Evolution  ................................................................ 303  Donald Gibbons  

Design and Development of NEA Scout Solar Sail Deployer Mechanism  ............................................... 315  Alexander Sobey & Tiffany Russell Lockett  

MOPITT Mechanisms –  16 Years In- Orbit Operation on TERRA  ............................................................. 329  Andrew Gibson, Florian Nichitiu, Dwight Caldwell, John Hackett ,   Robert Deschambault  & James  Drummond   Electrical Noise Performance of Gold- on-Gold Slip Rings  ........................................................................ 345  Ron Hayes, Erik Mumm & Kyle Gotthelf  

Slip Ring Electrical Anomalies Found After Protoflight Vibration Testing  ................................................. 359  Troy Nilson, Scott Christiansen & Chad Hebert  

State -of-the-Art Reaction Wheel Optimization for Fi ne-Pointing Space Platforms:  Minimizing   Induced Vibration Impacts On Hubble Space Telescope Jitter Performance  ........................................... 373  Martin Hasha 

Microspine Gripping Mechanism for Asteroid Capture  ............................................................................. 401  Ezekiel Merriam, Andrew Berg, Andrew Willig, Aaron Parness, Tim Frey  & Larry Howell  

Hammering Mechan ism for HP3 Experiment (InSight)  ............................................................................. 415  Jerzy Grygorczuk , Łukasz Wi śniewski , Bartosz K ędziora, Maciej Borys , Rafał  Przybył a,   Tomasz Kuci ński, Maci ej Ossowski, Wojciech Konior, Olaf Krömer, Tilman Spohn ,   Marta Tokarz  & Mateusz Biał ek 

Testing and Measurement of Mechanism -Induced Disturbances  …………………… ............................…4 29  Laoucet Ayari , Michael Kubitschek , Gunnar Ashton, Eric Marquardt  & Steve Johnston  

Development and Testing of a High- Precision Position and Attitude Measuring System for   a Space Mechanism  ………………………………………..…………………  ........................................ ……4 39  Nikolay Khanenya, Gabriel Paciotti, Eugenio Forzani & Luc Blecha  

Development and Testing of a Bi -Stable Actuator based on a High Transition Temperature   Shape Memory Alloy  ……………………… ……………………………………………………………… …. .. ..453  Gabriel Paciotti , Jacques -Eric Bidaux, Hervé Girard, Fabrice Rottmeier & Luc Blecha 

Holding Brakes for Space Mechanisms with Minimum Power  Requirement .…………………  ......... ……465   Ted Hopper , Christoph Stuckmann, Scott Starin & Walter Whitehead  

Lean Development of the Future Actuator  ……………………  ........................................................... ……473   Mathias Burkhalter , Matthias Schulke, Beny Wüthrich & Oliver K unz
viii SYMPOSIUM SCHEDULE  

WEDNESDAY, 4 MAY 2016  

7:00 Wednesday Presenters' Breakfast – Biltmore San Jose Room  

8:00 CHECK -IN AND REFRESHMENTS - Biltmore Atrium  

8:15 INTRODUCTORY REMARKS  – Biltmore Ballroom  

William Caldwell, Host Chairman, NASA Ames Research Center, Mt View, CA   Edward Boesiger, General Chairman, Lockheed Martin Space Systems, Sunnyvale, CA   David Korsmeyer Engineering Director, NASA Ames Research Center, Mt View, CA  

8:30 SESSION I – MOSTLY INSTRUMENTS  Steve Koss, Session Chair   Naval Research Laboratory, Washington, D.C.  

- ATLAS Beam Steering Mechanism (BSM) Lessons Learned, Ken Blumenstock et al., NASA  Goddard Space Flight Center, Greenbelt, MD  

- Injection of a Body into a Geodesic: Lessons Learnt from the LISA Pathfinder Case, Dan iele  Bortoluzzi et al., University of Trento, Trento, Italy    - Mechanisms Design for the S5P -TROPOMI Instrument, Erik Tabak et al., InnoSpace, Rotterdam,  The Netherlands    - Tests on the Ductility of Stainless Steel and Titanium Alloy Aerospace Fasteners, J arrod Whittaker  & Daniel Hess, University of South Florida, Tampa, FL   - Development and Testing of a “Backlash- Free“ Gas -Tight High -Precision Sample Dosing  Mechanism for the ExoMars 2018 Rover, Daniel Redlich et al., OHB System AG,  Oberfpfaffenhofen, Germ any 

- Realization and Testing of the In Field Pointing Mechanism for the Evolved Laser Interferometer  Space Antenna, Gert Witvoet & Jet Human, TNO Technical Sciences, Delft, The Netherlands    11:30 LUNCH  - Lunch for AMS Attendees in the Biltmore Courtyard    12:30 SESSION II – BEARINGS   Lionel Gaillard, Session Chair   ESA/ESTeC, Noordwijk, The Netherlands   

- Suomi -NPP Mission On- orbit Experience with Toroid Ball Bearing Retainers under Unidirectional  and Reversing Motion, Otto Bruegman et al., NOAA, Silver Spring, MD    - Failure Analysis and Recovery of a 50- mm Highly Elastic Intermetallic NiTi Ball Bearing for an ISS  Application, Christopher DellaCorte & S. Adam Howard, NASA Glenn Research Center, Cleveland,  OH; Lewis E. Moore III, NASA Marshall Space Flight C enter, Huntsville, AL  

- Ball Bearing Analysis with the ORBIS Tool, Jacob Halpin, Halpin Engineering LLC, Torrance, CA  

- Extended Life Testing of Duplex Ball Bearings, Jeffrey Mobley, Michael Robertson & Charles  Hodges, Sierra Nevada Corporation, Durham, NC
ix 2:30 BREAK 

2:45 SESSION III –  POTPOURRI  OF POSTERS & PAPERS   Scott Starin, Session Chair   Avior Control Technologies, Inc., Longmont, CO  

- Piezoelectric Actuators and Future Motors for Cryogenic Applications in Space, Christian Belly,  Francois Barillot & Fabien Dubois, Cedrat Technologies, Meylan, France  

- Development of a Self -latching Hold- down RElease Kinematic (SHREK), Ruggero Cassanelli,  AEREA S.p.A., Turate, Italy  

- Challenges of Designing a 13- Hz High -Load Vibration Isolation System with Tight V olume  Constraints: Lessons Learnt and Path Forward, Stella Dearing & Dale Ruebsamen, Honeywell  Aerospace, Defense and Space, Glendale, AZ  

- Development of a High- Performance, Low -Profile Translation Table with Wire Feedthrough for a  Deep Space CubeSat, Al ex Few, NASA Marshall Space Flight Center, Huntsville, AL  

- Use of Volute Springs in Space Applications, Chris Floyd, Ian Bournelis & Cary Clark, Lockheed  Martin Space Systems Company, Littleton, CO    - A Multi- Sectioning, Reconfigurable Electromagnetic Hammering Propulsion for Mole Penetrators,  Jerzy Grygorczuk et al., Centrum Badań Kosmicznych PAN, Warsaw, Poland    - Development of a Magneto- Resistive Angular Position Sensor for   Space Mechanisms, Robert Hahn et al., HTS Hoch Technologie Systeme GmbH, Cosw ig, Germany  

- Cu-Al-Ni Shape Memory Single Crystal Wires with High Transformation Temperature, Alain  Hautcoeur & Florian Fouché,  Nimesis  Technology,  Mecleuves,  France; Jacques Sicre, CNES,  Toulouse, France 

- Prevailing Torque Locking Feature in Threaded Fasteners using Anaerobic Adhesive, Alan  Hernandez & Daniel Hess, University of South Florida, Tampa, FL 

- A New Architecture for Absolute Optical Encoders, Timothy Malcolm, John Beasley & Mike Jumper,  BEI Precision Systems & Space Company, Maumelle, AR  

- Digital Image Correlation for Performance Monitoring, Miguel Palaviccini & Dan Turner, Sandia  National Labs, Albuquerque, NM; Michael Herzberg, National Security Campus, Kansas City, MO  

- Deployment System for Three Axis CubeSat Electric Field Instrument, Dana Turse, Larry Adams &  Chris Esser, Composite Technology Development, Inc., Lafayette, CO    - Degradation of Sputter -Deposited Nanocomposite MoS 2 Coatings for NIRCam during Storage in Air,  Jeffrey Lince, The Aerospace Corporation, El Segundo, CA; Stuart Loewenthal & Charles Clark, Lockheed Martin Space Systems Company, Sunnyvale, CA    - The Dynamic Particle Generation of Lubricating Greases for use in Space Mechanisms, Jason  Galary, NYE Lubricants, Fairhaven, MA  

6:30 -10:00 RECEPTION  – Biltmore Hotel   Invited component suppliers display current products and provide tutorials along with FIRST Robotics  Team demonstrations and a light buffet meal.
x THURSDAY, 5 MAY 2016  

7:00 Thursday Presenters' Breakfast –  Biltmore San Jose Room  

8:00 SESSION IV –  I LIKE T O MOVE IT   Rob Kyle, Session Chair   CDA Intercorp LLC, Deerfield, FL  

- APM for a Constellation Intersatellite Link –  EM Qualification and Lessons Learned, Frank Härtel &  Horst Kozilek, Airbus Defence and Space, Friedrichshafen, Germany  

- Design Development  of a Combined Deployment and Pointing System for the International Space  Station Neutron Star Interior Composition Explorer Telescope, Jason Budinoff et al., NASA Goddard Space Flight Center, Greenbelt, MD  

- Development of Compact Mechanically Driven Sys tems for High Strain Composite Slit -Tubes, Bruce  L. Davis & Mark Lake, Roccor, Louisville, CO  

- James Webb Space Telescope Deployment Brushless DC Motor Characteristics Analysis, Anh  Tran, Northrop Grumman Aerospace Systems, Redondo Beach, CA  

10:00 BREAK  

10:15 SESSION V – DEPLOY  Art Grant, Session Chair   Harmonic Drive LLC, Peabody, MA  

- Development of a Deployment and Latching Mechanism for a Pointing System on the Neutron Star  Interior Composition Explorer (NICER) for Goddard Space Flight Center, Robert Berning & John  Holzinger, Moog Inc. Chatsworth, CA  

- Tape Hinge/Lenticular Strut Hinge Qualification and Evolution, Donald Gibbons, Lockheed Martin  Space Systems Company, Sunnyvale, CA  

- Design and Development of NEA Scout Solar Sail Deployer Mechanism, Alexander Sobey & Tiffany  Lockett, NASA Marshall Space Flight Center, Huntsville, AL    - MOPITT Mechanisms –  16 Years In- Orbit Operation on TERRA, Andrew Gibson et al., Canadian  Space Agency, Ottawa, Canada  

12:15 LUNCH  - Lunch for AMS Attendees in t he Biltmore Courtyard    1:15 SESSION VI – ”OH THE NOISE!, NOISE!, NOISE! NOISE!”   Martin Gordinier, Session Chair   Gurley Precision Instruments, Troy, NY  

- Electrical Noise Performance of Gold- on-Gold Slip Rings, Ron Hayes, Erik Mumm & Kyle Gotthelf,  Honeybee Robotics Spacecraft Mechanisms Corporation, Longmont, CO    - Slip Ring Electrical Anomalies Found After Protoflight Vibration Testing, Troy Nilson, Scott  Christiansen & Chad Hebert, Sierra Nevada Corporation, Louisville, CO
xi - State -of-the-Art Reaction Wh eel Optimization for Fine- Pointing Space Platforms:  Minimizing  Induced Vibration Impacts On Hubble Space Telescope Jitter Performance, Martin Hasha,  Lockheed Martin Space Systems Company, Sunnyvale, CA  

2:45 BREAK 

3:00 SESSION VII – SMALL SAMPLE OF SAMPL ERS  Erik Mumm, Session Chair   Honeybee Robotics Spacecraft Mechanisms Corp., New York, NY  

- Microspine Gripping Mechanism for Asteroid Capture, Ezekiel Merriam et al., Brigham Young  University, Provo UT  

- Hammering Mechanism for HP3 Experiment (InSight), Jerzy Grygorczuk et al., ASTRONIKA Sp. z  o.o., Warsaw, Poland 

4:00 INVITED PRESENTATION  - SOFIA and recent accomplishments of the program   Dr. Eric Becklin   Chief Scientist for the Stratospheric Observatory for Infrared Astronomy (SOFIA)    6:00- 10:00 BANQUET  – Mountain Winery   Dinner and entertainment at an historic winery in the Santa Cruz Mountains    FRIDAY, 6 MAY 2016 

7:30 Friday Presenters’ Breakfast  – Biltmore San Jose Room  

8:30 SESSION VIII –  MANUFACTURING/TESTING    Steve Bauman, Session Chair   NASA Glenn Research Center, Cleveland, OH  

- Testing and Measurement of Mechanism -Induced Disturbances, Laoucet Ayari et al., Ball  Aerospace & Technologies Corp., Boulder, CO  

- Development and Testing of a High- Precision Position and Attitude Measuring System for a Space  Mechanism, Nikolay Khanenya et al., Almatech, Lausanne, Switzerland  

9:30 BREAK 

9:45 SESSION IX –  ACTUATORS   Lance Werthman, Session Chair   Lockheed Martin Space Systems Co., Sunnyvale, CA  

- Development and Testing of a Bi -Stable Actuator based on a High Transition Temperature Shape  Memory Alloy, Gabriel Paciotti et al., Almatech, Lausanne, Switzerland  

- Holding Brakes for Space Mechanisms w ith Minimum Power Requirement, Ted Hopper et al.,  MACCON GmbH, Munich, Germany  

- Lean Development of the Future Actuator, Mathias Burkhalter et al., RUAG Space, Zurich,  Switzerland
xii 11:15 SPECIAL PRESENTATION ON NASA AMES  Jack Boyd, Senior Advisor to the NASA Ames Center Director  

TECHNICAL SESSIONS CONCLUSION   Stu Loewenthal, Deputy Chairman, Lockheed Martin Space Systems, Sunnyvale, CA   • Herzl Award Presentation –  Nadine Herzl -Kraft  

12:15 LUNCH  - Lunch for AMS Attendees in the Biltmore Courtyard  

1:30 – 5:00 TOUR    1:30  Buses depart hotel for industry tours     5:00  Approximate time buses return to hotel
xiii SYMPOSIUM ORGANIZING COMMITTEE 

Host Chair s  William Caldwell, NASA ARC   Fred G. Martwick, NASA ARC  

General Chairman -  Edward A. Boesiger, Lockheed Martin   Deputy Chairman -  Stuart H. Loewenthal, Lockheed Martin  

Steven W. Bauman, NASA GRC   Jared Dervan, NASA MSFC   Michael Dube, NASA NESC   Barry J. Dunn, NASA LaRC   Carlton L. Foster, NASA MSFC (retired)  Lionel Gaillard, ESA/ESTeC   Claef F. Hakun, NASA GSFC   Christopher P. Hansen, NASA JSC   Louise Jandura, JPL   Wayne Jermstad, NASA JSC   Alan C. Littlefield, NASA KSC   Ronald E. Mancini, NASA ARC (retired)   Donald H. McQueen, Jr., NASA MSFC   Robert P. Mueller, NASA KSC   Joseph Pellicciotti, NASA NESC   Minh Phan, NASA GSFC   Joseph P. Schepis, NASA GSFC   Donald R. Sevilla, JPL  James E. Wells, NASA LaRC
3 To meet figure requirements, a rather thick mirror was required, resulting in a significant mass.  This mirror  mass wa s a signific ant design driver. An increase in mirror mass results  in the need for a larger  counterbalance mass,  together inc reasing the total moving mass. The total moving mass is supported by  the flexures, which need to survive launch loads with out degradation.  

Flexures   The flexures were  electrical discharge machined from conventionally  machined titanium . Arrangement  of  the flexures  allows the mirror to rotate about two orthogonal axes.  Finite Element Method ( FEM ) structural  and modal analys is was used to trade structural mode frequencies to determine the optimal flexure  geometry . Flexures were designed to keep stresses within  levels to result in infinite life.  

Actuators   A pair of voice coil actuators  is used to control each axis. The actuators were of an in- house custom design  to achieve high efficiency , utilizing  a high- performance cobalt -iron alloy along with an arrangement of axial  and radial magnets . Cobalt -iron shaping put most of the cobalt -iron near saturation , saving mass . The  actuators have redundant windings , with a primary  winding in the bobbin center  and a secondary winding  split inner and outer  of the primary winding. This arrangement  equalized  actuator performance of primary  and secondary  windings . Equalizing was needed as a result of the air gap ma gnetic field drop when moving  away from the magnet side of the actuator . High damping was incorporated by the inclusion of a copper  damping sleeve as a part of  each actuator .  

Damping   High damping adds greatly to the disturbance rejection capability of the system . Disturbances can originate  externally , as a result of jitter from momentum wheels and other sources propagating through the spacecraft  structure;  or internal ly, from electrical noise or quantization error  in the control system . Damping can be  provided by c losing a velocity loop, which does  not have to waste power to over come the  damping during  slew operations .  

Implementing a velocity loop, however,  results in several issues, including the need for a very sensitive  velocity sensor to detect low velocities, and could even result in decreased pointing stability as the result  of added electronics noi se. Such architecture could result in a very large and heavy velocity sensor with  very fine , non- robust  wire to achieve a high turn count, and m ight require pre- amplific ation near the sensor.  Deriving velocity from a position sensor also has its limitations, especially when trying to sense low velocities.     Passive damping with a shorted coil, such as a solid copper sleeve,  can waste power when slewing. In the  case of the BSM, operational mirror velocities are very small, thus there is insignificant impact upon operational power required to overcome shorted coil passive damping.  Thus, shorted coil damping was  implemented in the BSM actuator design.  Figure 3 shows actuator cross section and component views.     

Figure 3 .  BSM Ac tuator Cross Section, Bobbin Assy ., and Bobbins w ith Sleeves
8                  Before                After  

Figure 7.  Frequency Response Before  and After Counterbalance Shaft Change  

Hipot Over testing Failure   Qualification  of the in- house voice coi l actuator s required high potential ( hipot) and insulation resista nce  testing  to be performed. We referred to one of our  test specifications  document s, and applied a test voltage  of over 1000 volts, which resulted in a failed actuator windi ng. After investigation, it turned out that our  test  specification s were really intended to be used for cable  and connector  testing. Furthermore, we found out  that lower voltages were regularly being used for most cable t esting, more so for cables with miniature   connectors. Since our operational  voltage was no more than 12 volts, it was decided to test at 25 0 volts,  after which all h ipot and insulation resistance test s were passed without issue . So, the lesson learned is t o  not blindly follow documentation. We should have surveyed  the standard practice for motor winding hipot  and insulation resistance testing rather to follow a test specification that was not applicable. Another factor  was that  we were probably  overly confi dent that our design was bullet proof. It is not prudent to overtest.  

Undesirable Behavior of the Flight Model    The BSM Flight Model had completed its testing just at the point ready for environmental testing to begin.  The controls engineers discovered puzzling behavior of the BSM Flight Model not seen in the BSM  Engineering Model.  When making mirror motions from one point to another, the trajectory would miss the   commanded go-to point and then circle back before arrival  to that  point. While such behavior was always  seen in the BSM Engineering Model , it was not seen at the magnitude observed in the BSM Flight Model.   We were privileged to have one of our top technicians perform  the assembly of all the BSMs. During our  investigation, it was revealed that our technician observed an unusual behavior  during the balancing  process. The balancing process was dependent upon usage of  the highly sensitive internal position  sensors. The BSM Flight Model was mounted into  a cubical  framework that allowed the mechanism to be  oriented with gravity in six different directions, two with the counterbalance shaft vertical, and four with the