ai-aerospace/ams_data_full_2000-2020 huggingface dataset:
Testing and  Development of the NEA Scout  Solar Sail Deployer  Mechanism ...................................... 323  Alex Few, Tiffany Lockett, Richard Wilson & David Boling  Mechanism Design & Flight Build of Furled High Strain Composite Ant enna for CubeSats ................. 337  Bruce Davis, Ryan VanHalle, Kevin Cox & Will Francis  Failure of the Ball ‐Lock Mechanism on the NanoRa cks CubeSat Deployer ......................................... 351  Michael Lewis & Conor Brown  Lessons Learned from a Deployment Me chanism for a Ka-band Deployable  Antenna for Cu beSats .......................................................................................................... .................. 361  Jonathan Sauder, Nacer Chahat, Richard Hodges, Eva Peral,  Yahya Rahmat-Samii & Mark Thomson  Design and Development of CubeSat Solar Array Deployment Mechanisms Using  Shape Memory Alloys ........................................................................................................... ................. 375  Allen Guzik & Othmane Benafan  Lessons Learned in the Flight Qualification of the S-NPP and NOAA -20 Solar Array Mechanisms ..... 389  Daniel Helfrich & Adam Sexton  Spacecraft Common Deployable Boom Hinge Deploy and Latching Mechanisms ............................... 403  Paul Lytal & Marcel Renson  Precision High-Strain Composite Hing es for Deployable Space Telescopes ........................................ 417  Mark Silver & Michael Echter  The Synchronization Mechanism for Solar Array with a Three-Stage Deployment ............................... 431  Zehong Yan, Hongjun Shang, Guowei Zhao, Qiaolong Yang, Jingya Ma & Jianjun Wang  Mechanisms and New Space ...................................................................................................... .......... 443   Bill Purdy  Development of the Multi-Purpose Transportation System for the Space Launch   System Core Stage Flight Article .............................................................................................. ............. 459  Sarah Sandridge, Hue Lien, Ronald Hunt, Ayana Reese & Christopher Doktor  NASA Docking System Block 1: NASA’s New Di rect Electric Docking System Supporting  ISS and Future Human Space Exploration ........................................................................................ .... 471  Justin McFatter, Karl Keiser & Timothy Rupp  Capture Latch Assembly for the NASA Docking System ....................................................................... 485  Brandon Dick, Nathan Mauch & Timothy Rupp  High Speed Bearing Wear Rate Measurements for Spacecraft Active Thermal Control  Fluid Pumps with a Novel Pin on Disk Apparatus ................................................................................ .. 499  Robert J. Bruckner & Richard A. Manco II  Accelerated Testing of Tribological Compone nts - Uncertainties and Solutions ................................... 513  Simon Lewis, Mike Buttery, Oliver Poyntz-Wright, Anthony Kent &   Achilleas Vortsellas  NASA/CP—2018-219887 vii
SYMPOSI UM SCHEDULE   WEDNESD AY, 16 MAY 2018   7:00 Wedn esday Presenters' Breakfast  – Veterans Room B   7:00 CHECK- IN AND REFRESHMENTS  – 5th F loor L obby   8:15 INTRODUCTORY REMARKS  – Superior Ballroom, Section A  Damon Delap, Host Chairman, NASA Glenn Research Center, Cleveland, OH   Edward Boesiger, General Chairman, Lockheed Martin Space, Sunnyvale, CA   Marla E. Pérez -Davis , Deputy  Director, NASA Glenn Research Center, Cleveland, OH   8:30 SESSIO N I – INSTRUMENTS  Session Chair : Rius Billing, MDA US Systems , Pasadena, CA   -Scroll  Compressor for Mars Atmospheric Acquisition John Wilson  & Bryce Shaffer, Air Squared, Inc. , Broomfield, CO; Ted Iskenderian, Jet Propulsion Laboratory, Pasadena, CA   -The Regolit h and Ice Drill for Exploration of New Terrains (TRIDENT); a One- Meter Drill for the Lunar Resource Prospector Mission Gale Paulsen et al., Honeybee Robotics Spacecraft Mechanisms Corp, Pasadena, CA/Longmont, CO;  James Smith & Jacqueline Quinn, NASA Kennedy Space Center, FL   -KaRIn Al ignment Mechanism Design, Development and Testing John Wolff, Jet Propulsion Laboratory, Pasadena, CA -Envir onmental Chamber Testing of a Rock Sampling Drill for Venus Exploration Fredrik Rehnmark et al., Honeybee Robotics Spacecraft Mechanisms Corp, Pasadena, CA ; Kristopher Kriechbaum et al., Jet Propulsion Laboratory, Pasadena, CA   10:10 SES SION II – BEARINGS & LUBRICATION   Session Chair: Merritt Webb, Harris Corporation, Fort Wayne, IN   -A Disc ussion of Friction Anomaly Signatures in Response to Electrical Discharge in Ball Bearings William Bialke, Lochridge Farm LLC, Trumansburg, NY -Efficac y  of Lead Naphthenate for Wear Protection in Mixed Lubrication Regime Jason Galary, NYE Lubricants Inc, Fairhaven, MA -Dynamic  Behavior of Ball Bearings under Axial Vibration Virgil Hinque & René Seiler, European Space Agency/ESTEC, Noordwijk, The Nether lands -The Design  & Development of the Ocean Color Instrument Precision Superduplex Hybrid Bearing Cartridge Joseph Schepis et al., NASA Goddard Space Flight Center, Greenbelt, MD; Timothy Woodard, Peter Ward & Michael Lee, The Aerospace Corporation, El Segundo, CA; Alfred Conti, The Barden Corporation, Danbury, CT; Jeffrey Guzek, Design Interface, Columbia, MD   11:50 LUNCH   Lunc h for AMS Attendees in the Superior Ballroom, Section D   NASA/CP—2018-219887 xi
12:50 SE SSION III – SOLID LUBRICATION   Session Chair : Brian Gore, The Aerospace Corporation, El Segundo, CA   -Evaluati on of Friction Characteristics and Low Friction Mechanism of Tungsten Disulfide for Space Solid Lubricant at Elevated Temperature in a Vacuum Ayaka Takahashi & Josaphat Tetuko S S, Chiba University, Chiba, Japan; Keizo Hashimoto, Teikyo University, Tokyo, Japan  -Performanc e of MoS 2 Coated Gears Exposed to Humid Air During Storage Tim Krantz  & Zachary Cameron, NASA Glenn Research Center, Cleveland, OH; Claef Hakun, NASA Goddard Space Flight Center, Greenbelt, MD; Iqbal Shareef, Bradley University, Peoria, IL; Michael Dube, NASA Langley Research Center, Hampton, VA   -An Improved  Solid Lubricant for Bearings Operating in Space and Terrestrial Environments Arindam Paul  et al., University of Akron, Akron, OH -Hybrid Lubr ication of PFPE Fluids and Sputtered MoS 2 Michael B uttery et al., European Space Tribology Laboratory, ESR Technology Ltd. , Warrington, United Kingdom   2:30 BREAK  2:45 SESSION  IV - “OH THE NOISE! NOISE! NOISE!”   Session Chair: John Beasley, BEI Precision Systems & Space Division, Maumelle, AR   -Solving a P erformance Limiting Resonance Frequency Problem of the SOFIA Secondary Mirror Mechanism by Structural ModificationsYannick Lammen, Andreas Reinacher  & Alfred Krabbe, Deutsches SOFIA Institut , University of  Stuttgart, Stuttgart, Germany   -Enhanced Vi bration Isolation Using a Magnetic Linear Gear for Highly Demanding Aerospace Applications Jose Luis Perez -Diaz & Efrén Diez -Jimenez , Universidad de Alcalá, Alcalá de Henares, Spain ;  Ignacio Valiente -Blanco et al.,  MAG SOAR S.L, Valdemoro, Spai n   -A Mechanis ms Perspective on Microvibration – Good Practices and Lessons Learned Geert Smet & Sandro Patti, European Space Agency, Noordwijk, The Netherlands 4:00 SESSION  V – POTPOURRI  OF POSTERS   Session  Chair : Joseph Pellicciotti, NASA HQ , Washington, D. C.   -Investiga tion of Bolt Preload Relaxation for JWST Thermal Heat Strap Assembly Joints with Aluminum - 1100 and Indium GasketsAndrew Bartoszyk et al., NASA Goddard Space Flight Center, Greenbelt, MD ; Thomas Walsh, Stinger  Ghaffarian Technologies, Greenbelt, MD; Jason Krom, Sigma Space Corporation, Lanham, MD; Edgar  Hemminger, Ares Corporation, Greenbelt, MD   -Validati on and Test Results of the 2.5D Technology for Pancake Slip Rings Mélanie Henry & San dro Liberatoscioli, RUAG Schweiz AG, Nyon, Switzerland -Quantifyi ng Threaded Fastener Locking Daniel Hess, University of South Florida, Tampa, FL; Christopher DellaCorte, NASA Glenn Research Center, Cleveland, OH   NASA/CP—2018-219887 x
-Reliab ility Calculation Methodologies for Mechanisms and Actuators Tanner Horne & Evan H arrington, Avior Control Technologies, Inc, Longmont, CO -Develo pment of the NEA Mini for Low Load Applications John Sudick & Geoff Kaczynski, NEA Electronics, Inc ., Moorpark, CA -Compliant  Mechanisms Re-Design based on Additive Manufacturing and Topology Optimization Lionel Kiener et al., Centre Suisse d'Electronique et de Microtechnique S.A., Neuchatel, Switzerland -Non- Pyr otechnic Multi -Point Release Mechanisms for Spacecraft Release Ambrosio Mejia, John Sudick & Geoffrey Kaczynski, Ensign Bickford Aerospace  NEA Electronics, Inc., Moorpark, CA   -Validat ion of a Novel High Performance Magnetic Gearbox for Space Ignacio Valiente- Blanco et al., MAG SOAR SL., Valdemoro, Spain;  Efrén Diez -Jimenez & José Luis Perez -Diaz, Universidad de Alcalá, Alcalá de Henares, Spain   -Qualification of a Networked Pyrotechnic Initiation System for the CST -100 Starliner Spacecraft David Novotney  et al. , Ensign Bickford Aerospace,  Simsbury, CT 6:00 - 10:0 0 RECEPTION  – Hilton Cleveland Downtown  Invited component suppliers display current products and provide tutorials along with FIRST Robotics  Team demonstrations and a light buffet meal.   NASA/CP—2018-219887 xi
THUR SDAY, 17 MAY 2018   7:00 Thursday Presenters' Breakfast  – Veterans Room B   8:00 SESSIO N VI – ACTUATORS   Session Chair: Boz Sharif, Cobham Motion Control Solutions , Hauppauge, NY   -Use and Ad vantages of Direct -Drive Brushless DC Actuators for Precision Instrument Pointing of the Total and Spectral Solar Irradiance Sensor Patrick Brown, Andrew Engelmann & Ryan Lewis, University of Colorado, Boulder, CO   -Testing and  Maturing a Mass Translating Mechanism for a Deep Space CubeSat Alex Few , Tiffany Lockett & Erik Loper, NASA Marshall Space Flight Center, Huntsville, AL; Richard Wilson & David Boling, Jacobs Technologies, Huntsville, AL   -Solar Ar ray Drive Assembly Qualification Lessons Learned Jonathan Wood, Lockheed Martin Space, Sunnyvale, CA; Timothy Pargett, Moog Space and Defense Group, Mountain View, CA   -Determi ning Root Causes of Mysterious Hardware Failures using High Resolution CT Scanning Michael Johnson, Jet Propulsion Laboratory, Pasadena, CA 9:40 BREAK  9:55 SESSIO N VII – CUBESATS   Session Chair: Henk Cruijssen, Airbus Defence & Space, Leiden, The Netherlands   -Testin g and  Development of the NEA Scout Solar Sail Deployer Mechanism Alex Few  & Tiffany Lockett, NASA Marshall Space Flight Center, Huntsville, AL; Richard Wilson & David Boling, Jacobs Engineering, Huntsville, AL   -Mechanism  Design & Flight Build of Furled High Strain Composite Antenna for CubeSats Bruce Davis et al., Roccor, Longmont, CO -Failure of  the Ball -Lock Mechanism on the NanoRacks Cubesat Deployer Michael Lewis & Conor Brown, NanoRacks, LLC, Webster, TX -Lessons Lear ned from a Deployment Mechanism for a Ka- band Deployable Antenna for CubeSats Jonathan Sauder et al., Jet Propulsion Laboratory, Pasadena, CA ; Yahya Rahmat -Samii, University of California Los Angeles, Los Angeles, CA ; Mark Thomson, Northr op Grumman Astro Aerospace,  Carpent eria, CA  -Design an d Development of CubeSat Solar Array Deployment Mechanisms Using Shape Memory Alloys Allen Guzik & Othmane Benafan, NASA Glenn Research Center, Cleveland, OH 12:00 LUNCH  

Lunch for AMS Attendees in the Superior Ballroom, Section D   1:00: S PECI AL PRESENTATION : Restore- L: Enabling a New Era   Hsiao Smith : Acting Deputy Division Director, Satellite Servicing Projects Division NASA Goddard Space  Flight Center   Hear about the mission to robotically refuel Landsat 7 in low earth orbit. Learn about the novel robotic hardware being developed to grab and refuel this satellite that was never designed to be refueled.   NASA/CP—2018-219887 xii
2:05 SES SION VIII – DEPLOY AND SOMETHING NEW   Session Chair: David Rohweller, Northrop Grumman Astro Aerospace, Carpinteria, CA   -Lessons Le arned in the Flight Qualification of the S -NPP and NOAA- 20 Solar Array Mechanisms, Dan Helfrich, NASA Goddard Space Flight Center, Greenbelt, MD ; Adam Sexton, Ball Aerospace Corporation , Boulder, CO   -Spacecraf t Common Deployable Boom Hinge Deploy and Latching Mechanisms Paul Lytal, NASA Jet Propulsion Laboratory, Pasadena, CA; Marcel Renson, D.E.B. Manufacturing Inc., Lakewood, NJ   -Precis ion High -Strain Composite Hinges for Deployable Space Telescopes Mark Silver & Michael Echter, MIT Lincoln Laboratory, Lexington, MA -The Synchr onization Mechanism for Solar Array with a Three- Stage Deployment Zehong Yan et al., Beijing Institute of Spacecraft System Engineering, Beijing, China; Guowei Zhao , Beihang University, Beijing, China   -Mechanism s and New Space Bill Purdy, Purdy Engineering, Poolesville, MD 4:05 BREAK  4:20 INVIT ED PRESENTATION  –Doug Wheelock, Aerospace Engineer and Astronaut   Doug has been launched into space via the Space Shuttle Discovery and Soyuz TMA -19, and spent more  than 5 months in space aboard the Space Station. He has made multiple spacewalks to repair equipment  and will have stories to tell.   7:00- 11:0 0 BANQUET  – Rock and Roll Hall of Fame   Dinner, entertainment and exhibits celebrating music history.   NASA/CP—2018-219887 xiii
FRIDA Y, 18 MAY 2018  7:00 Frid ay Presenters’ Breakfast  – Veterans Room B   8:00 SESSION  IX – TRANSPORTATION & DOCKING   Session Chair: Brandon Robertson, NASA Johnson Space Center, Houston, TX   -Developm ent of the Multi -Purpose Transportation System for the Space Launch System Core S tage Flight Article Sarah Sandridge , NASA Marshall Space Flight Center, Huntsville, AL; Hue Lien et al., Jacobs Space  Exploration Group, Huntsville, AL   -NASA Doc king System Block 1: NASA’s New Direct Electric Docking System Supporting ISS and Future Human Space Exploration, Justin McFatter, The Boeing Company, Houston, TX; Karl Keiser, The Boeing Company, Huntsville,  AL; Timothy Rupp, NASA Johnson Space Center, Houston, TX   -Capture Latc h Assembly for the NASA Docking System Brandon Dick & Nathan Mauch, The Boeing Company, Huntsville, AL; Timothy Rupp, NASA Johnson Space Center, Houston, Texas   9:15 BREAK  9:30 SESSION  X – TESTING   Session Chair: Peter Stromberg, Sandia National Laboratories, Albuquerque, NM  -High Speed  Bearing Wear Rate Measurements for Spacecraft Active Thermal Control Fluid Pumps with a Novel Pin on Disk ApparatusRobert Bruckner, NASA Glenn Research Center, Cleveland, OH; Richard Manco II, HX5 Sierra,Cleveland, OH -Accelerat ed Testing of Tribological Components - Uncertainties and Solutions Simon Lewis et al., European Space Tribology Laboratory, ESR Technology Ltd., Warrington, UnitedKingdom -Developm ental Bearing and Bushing Testing for Mars Gearboxes Dave Suffern & Jonathan Parker, Sierra Nevada Corp, Durham, NC -Experiment al Method for Determining Ball Bearing Lubricant Quantity Factor Yoshimi Takeuchi, Peter Frantz & Tim Woodard, The Aerospace Corp oration, El Segundo, CA 11:10 SPE CIAL PRESENTATION ON NASA GLENN RESEARCH CENTER  11:40 TECHNI CAL SESSIONS CONCLUSION   Stu Loewenthal, Deputy Chairman, Lockheed Martin Space, Sunnyvale, CA   11:55 LUNCH   Lunch f or AMS Attendees in the Superior Ballroom, Section D   1:00 – 5:00 TOURS   Attendees may go on a special tour of either NASA Glenn Research Center or NASA Plum Brook Station.   NASA/CP—2018-219887 xiv
SYMPOSI UM ORGANIZING COMMITTEE  Host Cha ir - Damon C. Delap, NASA GRC   Co-Host Chair - Steven W. Bauman, NASA GRC   General Ch airman - Edward A. Boesiger, Lockheed Martin Space   Deputy Chairman - Stuart H. Loewenthal, Lockheed Martin Space   William Ca ldwell, NASA ARC   Jared A. Dervan, NASA MSFC   Adam G. Dokos, NASA KSC   Michael J. 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   Alan C. Littlefield, NASA KSC (retired)   Ronald E. Mancini, NASA ARC (retired)   Fred G. Martwick, NASA ARC   Donald H. McQueen, Jr., NASA MSFC   Robert P. Mueller, NASA KSC   Joseph W. Pellicciotti, NASA HQ   Minh Phan, NASA GSFC   Brandan Robertson, NASA JSC   Joseph P. Schepis, NASA GSFC   Donald R. Sevilla, JPL   James E. Wells, NASA LaRC   Jonathan P. Wood, Lockheed Martin Space   NASA/CP—2018-219887 xv
Scroll Compressor for Mars Atmospheric Acquisition  John Wilson*, Bryce Shaffer* and Ted Iskenderian**  Abstract  The Mars In Situ Resource Utilization Experiment (MOXIE) will be an experiment onboard the M2020  mission to Mars. The goal of this project is to develop and demonstrate flight hardware which can ingest  Martian atmosphere and convert it to O 2 and CO through solid oxide electrolysis. Air Squared, Inc was  tasked with designing a scroll compressor to capture the Martian atmosphere and compress the gas to a  specific pressure required to pass through the solid oxide electrolysis (SOXE) stack, converting the CO 2 into O 2 and CO.   Introduction  In Situ Resource Utilization (ISRU) technologies are critical to the advancement of human missions to  extraterrestrial bodies. For example, in a Design Reference Architecture mission study from 2009, it is  estimated that ISRU technology for generating oxygen will reduce the landed dry mass requirement from  100 to 70 metric tons. ISRU processes are achieved by collecting, separating, pressurizing or processing  materials found in the environment of extraterrestrial bodies.   In the MOXIE experiment aboard the M2020 mission to Mars, gasses from the Mars atmosphere are  collected and compressed for reaction in a Solid Oxide Electrolysis (SOXE) stack. The goal of this project  is to develop and demonstrate flight hardware which can ingest Martian atmosphere and convert it to O 2 and CO through solid oxide electrolysis. The oxygen can be used to for breathable air for astronauts and  potentially to generate fuel for any return mission.   Air Squared has been working with JPL and NASA on developing flight-ready hardware for MOXIE. Air  Squared’s contribution to this system is a compressor that compresses CO 2 from 5 torr up to at least 540  torr. The mechanism that feeds the MOXIE experiment with Martian atmosphere comprises an  electronically commutated direct current motor coupled to a “scroll pack” gas compressor. There is one  compressor assembly (motor plus scroll pack) in the MOXIE experiment. The compressor is of the scroll  type, with a moving (orbiting) scroll orbiting a stationary (fixed) scroll. The motion of the orbiting scroll is  controlled by ball-bearing mounted idler shafts. A brushless DC motor provides the rotational power.  Figure 1 shows an overview of the scroll compressor assembly.  *Air Squared, Inc., Broomfield, CO ** Jet Propulsion Laboratory, Pasadena, CA Proceedings of the 44th Aerospace Mechanisms Symposium, NASA Glenn Research Center, May 16-18, 2018  NASA/CP—2018-219887 1
Figure 1. P09H026A-A01 Scroll Compressor Assembly  Scroll Compressor Major Components  Scrolls  The scroll involutes are the heart of the scroll compressor. The involutes are sized for each application  depending on the operating pressures, flows and operating fluid, among other variables. There are two  scrolls for this application, one is called the fixed scroll and the other is called the orbiting scroll.  The orbiting scroll operating principle can be seen Figure 2. The fixed scroll is represented by the white  involute, which is stationary during operation. The orbiting scroll, shown in blue, orbits in a circular motion  about the fixed scroll involute. The scrolls capture pockets of gas (Orbiting-1) in the two outside chambers  and compress that gas radially inward until the pocket discharges out the center of the scrolls (Orbiting -3).  The two outside chambers (Orbiting-1) are called the suction volume or displacement of the compressor.  The scroll compressor displacement is how much volume is captured and moved through the involutes per  revolution of the orbiting scroll. The process continues to expel gas at the center, while a new cycle of  compression begins with fresh pockets of gas at the outer diameter (Orbiting-4).  Figure 2. Orbiting Scroll Operating Cycle Scroll PackHousingBLDC Motor Suction Volume Discharge Volume NASA/CP—2018-219887 2
The volume ratio of the compressor is defined as the ratio of the suction volume (Orbiting-1) to the discharge  volume (Orbiting-3). The built-in volume ratio of a scroll compressor directly impacts the compression  efficiency of the compressor, or how close the actual compression process is to an ideal compressions  process. In general, a large imposed pressure ratio over the machine will result in the selection of a large  volume ratio. Selection of the ideal volume ratio for an application is a complex optimization problem,  involving the compressor envelope, operating conditions, manufacturing considerations, as well as the cost  considerations.  Idler Shafts  There are many benefits to scroll technology, specifically for this application. This scroll compressor is what  Air Squared calls an oil-free design, which does not utilize any oil in the operating fluid for sealing.   Typically, oil is used in a scroll compressor to allow it to be a compliant design, which means that the orbiting  scroll involute directly contacts the fixed scroll involute. It is important for this application to not utilize oil in  the operating fluid due to the sensitivity to contamination of the downstream system.  Instead of utilizing an Oldham ring, which many oil lubricated refrigeration compressors use, the scrolls are  phased with one another using three idler shafts shown in Figure 3. The idler shafts not only control the  phasing of one scroll relative to the other, they also control the radial and axials gaps between the two  scrolls. The idler shafts have an offset shaft on a precisely toleranced “eccentric”. It is critical that the idler  shaft prevent the scrolls from touching for an oil-free design. Significant radial contact of the involutes could  result in a failure of either the scroll compressor or the downstream system from contamination.    Figure 3. Scroll Compressor Idler Shaft MOXIE Requirements  On the M2020 science rover, resources such as mass and power are constrained when compared to what  would be required for oxygen production on a human-scale mission. The volume available to the  compressor was severely limited in two dimensions due to the small packaging requirement for the MOXIE  experiment. Restrictions on all these resources drove design choices and compromises in compressor size,  operating speed, and performance.  Table 1. Compressor Requirements  Compressor Mechanical Requirements  Dimensions [mm] 150 x 96 x 175  Mass [kg] 1.96  Compressor Performance Requirements  Gas Inlet Pressure Range [Torr] 4 to 7  Gas Inlet Temperature Range [°C] -45 to +55 Gas Outlet Pressure [Torr] 760  Mass Flow Rate Minimum [g/hr] 60  Life [hr] 60  NASA/CP—2018-219887 3