ai-aerospace/ams_data_full_2000-2020 huggingface dataset:
iii PREFACE  

The Aerospace Mechanisms Symposium (A MS) provides a unique forum for those  active in the design, produc tion and use of aerospace mechanisms. A major focus is the  reporting of problems and solutions associ ated with the development and flight  certification of new mechanisms. Organized by the Mechanisms Education Association,  the National Aeronautics and Space Admi nistration and Lockheed Martin Space  Systems Company (LMSSC) share the respons ibility for hosting the AMS. Now in its  37th symposium, the AMS continues to be well attended, attracti ng participants from  both the U.S. and abroad.   The 37 th AMS, hosted by the Johnson Space Cent er (JSC) in Galveston, Texas, was  held May 19, 20 and 21, 2004. During these three days, 34 papers were presented.  Topics included deployment mechanisms, tri bology, actuators, pointing and optical  mechanisms, Space Station and Mars Rove r mechanisms, release mechanisms, and  test equipment. Hardware displays during the supplier exhibit gave attendees an opportunity to meet with developers of cu rrent and future mechanism components.    The high quality of this symposium is a result  of the work of many people, and their  efforts are gratefully ack nowledged. This extends to t he voluntary members of the  symposium organizing committee representing the eight NASA field centers, LMSSC,  and the European Space Agency. Appreciation is also extended to the session chairs,  the authors, and particularly the personnel at JSC responsible for the symposium  arrangements and the publication of these proceedings. A sinc ere thank you also goes  to the symposium executive committee who is responsible for the year-to-year  management of the AMS, incl uding paper processing and prepar ation of the program.     The use of trade names of manufacturers in  this publication does not constitute an  official endorsement of such products or manuf acturers, either expressed or implied, by  the National Aeronautics and Space Administration.
v CONTENTS 

Symposium Schedul e ............................................................................................................. .................vii 

Symposium Organizing and Ad visory Co mmittees.................................................................................. x i 

A Description of Mechanisms used in the Low Resolution Airglow & Au rora Spec trograph .....................1  Philip Kalmanson, Russell Starks,  Stefan Thonnard & Kenneth Dymond 

STEREO/SECCHI Coronagraph Hollow-Core Motor Development  and Test ing....................................15   Augustus Moore, Alexander Price,  David Akin & Ralph Horber 

Design and Development of the Primary and Secondary Mirror Deployment Systems   for the Cry ogenic JW ST......................................................................................................... ..................29   Paul Reynolds, Charlie Atkinson & Larry Gliman 

A Boresight Adjustment Mechanism  for use on Laser  Altime ters............................................................45   Claef Hakun, Jason Budinoff, Gary  Brown, Fil Parong & Armando Morell 

Deployment Mechanism for the Spac e Technology 5 Mi cro Sate llite .....................................................59   Peter Rossoni, Caner Cooperrider & Gerard Durback 

Development of a Strain Energy Deployable Boom for the Space Te chnology 5 Mission ......................73  Stew Meyers & James Sturm 

Latch-up Anomaly Study for Reflector Deployment of IN SAT-2E Sate llite..............................................87   G. Nagesh, S. Ravindran & N. Bhat 

A Strain Free Lock and Release Mechanism for an Elastically Suspended Two-Axis Gimbal ...............97   Armond Asadurian, Richard Pugh & Jim Hammond 

Force and Torque Margins for Co mplex Mechanica l Systems..............................................................107   Robert Postma 

Establishing Adequate Performance Margin for Space Flight Stepper Motor Mec hanisms..................119   David Marks 

HST Solar Arra y 3 Lat ches ...................................................................................................... ..............131   Mike Garrah 

Lessons Learned on Cryogenic Rocket Engine's Gi mbal Bearing Lubricat ion Select ion .....................137   Christian Neugebauer & Manfred Falkner 

The Integration of a Load Limiter to an Orbiter Over-Cent er Mec hanism .............................................143   Adam Gilmore & Tim Rupp 

Minimizing Torque Disturbanc e of Stepper Motors ...............................................................................1 47   Jim Sprunck 

SARA21 - A New Rotary Actuator  for Space A pplicati ons .................................................................... 153   Olivier Secheresse, Laurent Cadiergues & Julien Rabin 

Rolamite Joints for Spacecraft S ubsystem Vibrati on Isolat ion ..............................................................163   Gregory Compton & Matthew Botke 

Free Space Optical Communica tions System Pointe r...........................................................................171   Mark Rosheim & Gerald Sauter
vi Space Applications of MEMS: In itial Vacuum Test Results   from the SwRI Vacuum  Microprobe Facility....................................................................................... ....179   Philip Valek, D. McComas, G. Miller, J. Mitchell & S. Pope 

The Challenges of Designing the Rocker-Bogie Sus pension for the Mars Ex ploration Rover .............185   Brian Harrington & Chris Voorhees 

Deployment Process, Mechanization, and Test ing for the Mars Ex ploration Rovers ...........................197    Ted Iskenderian 

Development of Mars Explorati on Rover Lander Peta l Actuat ors .........................................................211   Boz Sharif & Ed Joscelyn 

Brake Failure from Residual Magnetism in the Ma rs Exploration Rover Lander Petal Actuator...........221   Louise Jandura 

High Gain Antenna Gimbal for the 2003-2004 Mars Exploration Rover Pr ogram .................................237   Jeff Sokol, Satish Krishnan & Laoucet Ayari  

A Low Mass Translation Mechanism for   Planetary FTIR Spectrometry using an Ultrasonic Piezo Linear Mo tor .................................................251   Matthew Heverly, Sean Dougherty, Geoffrey Toon, Alejandro Soto & Jean-Francois Blavier 

Pancam Mast Assemb ly on Mars  Rover............................................................................................. ...263   Robert Warden, Mike Cross & Doug Harvison 

Rock Abrasi on Tool............................................................................................................. ...................277   Thomas Myrick, Kiel Davis & Jack Wilson 

Review of International Space Stat ion Mechanical Syst em Anoma lies ................................................291   David McCann 

Space Station Bert hing Mec hanisms.............................................................................................. .......301   Robert Foster, John Cook, Paul Smudde & Mark Henry 

Mechanism Analysis and Verification Approach for ISS Tr uss Asse mbly.............................................315   Wesley Bruner, Carlos Enriquez & Sreekumar Thampi 

Life of Scanner Bearings with Four Space Liqui d Lubricant s................................................................333   Dean Bazinet, Mark Espinosa, Stuart Loewenthal, Lois Gschwender,    William Jones, Jr. & Roamer Predmore  

Hubble Space Telescope Fine Guidance Sensor  Post-Flight Bear ing Inspec tion ................................343   Joe Pellicciotti; Stuart Loewenthal, William Jones, Jr. & M. Jumper 

Effect of Test Atmosphere on Moving Mec hanical Assembly Test  Perform ance ..................................357   David Carre & P. Bertrand 

The X-38 V-201 Fin Fold Actuation Mechani sm.................................................................................... 363   Christian Lupo, Brandan Robertson & George Gafka 

The X-38 V-201 Flap Ac tuator Me chani sm......................................................................................... ...377   Jeff Hagen, Landon Moore, Jay Estes & Chris Layer
vii SYMPOSIUM SCHEDULE 

WEDNESDAY, 19 MAY 2004  

8:00  Wednesday Presenters' Breakfast – Vine I Room    8:00  CHECK-IN AND REFRESHMENTS  – Group Registration Desk and South Ballroom Foyer   9:00  INTRODUCTORY REMARKS  - Moody II Room  Christopher Hansen, Host Chairman  NASA Johnson Space Cent er, Houston, TX  Edward A. Boesiger, Operations Chairman Lockheed Martin Space Systems Company, Sunnyvale, CA  CENTER WELCOME General Jefferson D. Howell Jr.,  Center Director   NASA Johnson Space Cent er, Houston, TX 

9:30  SESSION I – Instrument Mechanisms  Robert Renken, Session Chair Ball Aerospace & Technologies, Boulder, CO • A Description of Mechanisms used in the Low Resolution Airglow & Aurora Spectrograph Philip Kalmanson, Praxis, Inc., Alexandria, VA; Russell Starks, EVI Technology, Columbia, MD;  Stefan Thonnard & Kenneth Dymond, Naval Re search Laboratory, Washington, D.C.  • STEREO/SECCHI Coronagraph Hollow-Core Motor Development and Testing Augustus Moore, Alexander Price & David Akin, Lo ckheed Martin Space Systems, Palo Alto, CA;  Ralph Horber, H. Magnetics Inc., Marshfield, MA • Design and Development of the Primary and Se condary Mirror Deployment Systems for the  Cryogenic JWST Paul Reynolds, Charlie Atkinson & Larry Gliman, Northrop Grumman Space Technology,  Redondo Beach, CA • A Boresight Adjustment Mechanism for use on Laser Altimeters Claef Hakun, Jason Budinoff, Gary Brown, Fil Parong & Armando Morell, NASA Goddard Space  Flight Center, Greenbelt, MD   11:30  LUNCH BREAK – Box lunch is provided   12:45  SESSION II – Release, Deploy and Margins  Patrice Kerhousse, Session Chair ESA/ESTec, Noordwijk, The Netherlands • Deployment Mechanism for the S pace Technology 5 Micro Satellite   Peter Rossoni, Caner Cooperrider & Gerard Durback, NASA Goddard Space Center, Greenbelt,  MD • Development of a Strain Energy Deploy able Boom for the Space Technology 5 Mission  Stew Meyers & James Sturm, N ASA Goddard Space Center, Greenbelt, MD  • Latch-up Anomaly Study for Reflector Deployment of INSAT-2E Satellite G. Nagesh, S. Ravindran & N. Bhat, Indian S pace Research Organization, Bangalore, India  • A Strain Free Lock and Release Mechanism fo r an Elastically Suspended Two-Axis Gimbal  Armond Asadurian, Richard Pugh & Jim Ha mmond, Moog, Inc., Chatsworth, CA  • Force and Torque Margins for Complex Mechanical Systems Robert Postma, The Aerospace Corporation, El Segundo, CA • Establishing Adequate Performance Margin for Space Flight Stepper Motor Mechanisms  David Marks, Moog, Inc., Durham, NC   3:45  BREAK
viii   4:00  Announcement – Moving Mechanical Assemblies Standard for Space and Launch Vehicles   Brian Gore  The Aerospace Corporation, El Segundo, CA 

4:15  SESSION III – Poster Preview   Kornel Nagy, Session Chair  Johnson Space Center, Houston, TX • HST Solar Array 3 Latches Mike Garrah, Swales Ae rospace, Beltsville, MD  • Lessons Learned on Cryogenic Rocket Engine's Gimbal Bearing Lubrication Selection  Christian Neugebauer & Manfred Falkner, Au strian Aerospace GmbH, Vienna, Austria  • The Integration of a Load Limiter to an Orbiter Over-Center Mechanism Adam Gilmore & Tim Rupp, NASA J ohnson Space Center, Houston, TX  • Minimizing Torque Disturbance of Stepper Motors Jim Sprunck, Starsys Research  Corporation, Boulder, CO  • SARA21 - A New Rotary Actuator for Space Applications Olivier Secheresse, SNECMA Moteurs, Cr amayel, France; Laurent Cadiergues, CNES,  Toulouse, France; Julien Rabi n, ACSIENCE, Paris, France  • Rolamite Joints for Spacecra ft Subsystem Vibration Isolation  Gregory Compton & Matthew Botke,  ABLE Engineering, Goleta, CA  • Free Space Optical Communications System Pointer Mark Rosheim & Gerald Sauter, Ro ss-Hime Designs, Inc., Minneapolis, MN  • Space Applications of MEMS: Initial Vacuum Test Results from the SwRI Vacuum Microprobe  Facility Philip Valek, D. McComas, G. Miller, J. Mitche ll & S. Pope, Southwest Research Institute, San  Antonio, TX 

6:30-9:30 RECEPTION & DISPLAYS AT THE MOODY GARDENS AQUARIUM   Invited component and software suppliers displa y current products and provide tutorials.   THURSDAY, 20 MAY 2004  

7:15  Thursday Presenters' Breakfast - Vine I Room  7:45 Light Refreshments - South Ballroom Foyer   8:15  SESSION IV - Mars I - Moody II Room   Randall Lindemann, Session Chair   Jet Propulsion Laboratory, Pasadena, CA   • The Challenges of Designing the Rocker-Bogie Suspension for the Mars Exploration Rover  Brian Harrington & Chris Voorhees, Je t Propulsion Laboratory, Pasadena, CA  • Deployment Process, Mechanization, and Te sting for the Mars Exploration Rovers   Ted Iskenderian, Jet Propulsion Laboratory, Pasadena, CA • Development of Mars Exploration Rover Lander Petal Actuators Boz Sharif & Ed Joscelyn, Aeroflex  Motion Control Products, Hauppauge, NY  • Brake Failure from Residual Magnetism in the Mars Exploration Rover Lander Petal Actuator  Louise Jandura, Jet Propulsion Laboratory, Pasadena, CA   10:15  BREAK
ix 10:30  SESSION V – Mars II   William Skullney, Session Chair  Johns Hopkins University Appli ed Physics Laboratory, Laurel, MD  • High Gain Antenna Gimbal for the 2003-2004 Mars Exploration Rover Program Jeff Sokol & Laoucet Ayari, Ball Aerospace & Te chnologies Corp., Boulder, CO; Satish Krishnan,  Jet Propulsion Laboratory, Pasadena, CA • A Low Mass Translation Mechanism for Planetary FTIR Spectrometry using an Ultrasonic Piezo  Linear Motor  Matthew Heverly & Sean Dougherty, Alliance Spaces ystems Inc., Pasadena, CA; Geoffrey Toon,  Alejandro Soto & Jean-Francois Blavier,  Jet Propulsion Laboratory, Pasadena, CA  • Pancam Mast Assembly on Mars Rover Robert Warden, Mike Cross & Doug Harvison, Ball Aerospace & Technologies Corp., Boulder,  CO • Rock Abrasion Tool Thomas Myrick, Kiel Davis & Jack W ilson, Honeybee Robotics, New York, NY   12:30 LUNCH BREAK – Box lunch is provided   1:30  SESSION VI – ISS   Scott West, Session Chair  The Boeing Company, Houston, TX   • Review of International Space St ation Mechanical System Anomalies   David McCann, The Boeing Company, Houston, TX  • Space Station Berthing Mechanisms Robert Foster & John Cook, The Boeing Com pany, Houston, TX; Paul Smudde, The Boeing  Company, Huntington Beach, CA; Mark H enry, The Boeing Company, Huntsville, AL  • Mechanism Analysis and Verification Approach for ISS Truss Assembly Wesley Bruner, Carlos Enriquez & Sreekumar Thampi, The Boeing Company, Houston, TX  • International Space Station Solar A rray Wing Deployment Anomaly Resolution  David McCann, The Boeing Company, Houston, TX   3:30  BREAK   3:45  SPECIAL PRESENTATION – NASA Astronaut    Joe Tanner will give his insights into using and hand ling mechanisms in space. A veteran of three  space flights, Tanner has logged over 742 hours in space, including over 33 EVA hours in 5  space walks including those for HST servicing and installing the Space Station solar arrays.    5:30-10:30 SYMPOSIUM BANQUET AT LONE STAR FLIGHT MUSEUM   

5:30  Walk to Moody Gardens 3-D IMAX Theater  7:00  Tram to Lone Star Flight Museum – Bar-B-Que Dinner, Band & Displays   Entertainment provided by Ezra Charles and the Works  10:00  Return to the hotel via tram
x FRIDAY, 21 MAY 2004 

7:30  Friday Presenters’ Breakfast – Vine I Room   8:00  Light Refreshments - South Ballroom Foyer   8:30  SESSION VII – TRIBOLOGY/DEPLOYMENT  - Moody II Room  Lois Gschwender, Session Chair  Air Force Research Laboratory, Dayton, OH • Life of Scanner Bearings wi th Four Space Liquid Lubricants  Dean Bazinet, Mark Espinosa & Stuart Loew enthal, Lockheed Martin Space Systems,  Sunnyvale, CA; Lois Gschwender, Air Force Res earch Laboratory, Dayton, OH; William Jones,  Jr., SEST Inc., Middleburg Heights, OH; Roamer Predmore, Swales Aero space, Beltsville, MD  • Hubble Space Telescope Fine Guidance S ensor Post-Flight Bearing Inspection  Joe Pellicciotti, NASA Goddard Space Cent er, Greenbelt, MD; Stuart Loewenthal, Lockheed  Martin Space Systems, Sunnyvale, CA; William Jones, Jr., SEST Inc., Middleburg Heights, OH;  M. Jumper, BEI Precision Systems & Space Division, Maumelle, AR • Effect of Test Atmosphere on Moving Me chanical Assembly Test Performance   David Carre & P. Bertrand, The Aero space Corporation, El Segundo, CA  • The X-38 V-201 Fin Fold Actuation Mechanism Christian Lupo, Brandan Robertson & George Gafka,  NASA Johnson Space C enter, Houston, TX  • The X-38 V-201 Flap Actuator Mechanism  Jeff Hagen, Lockheed Martin Space Operations, Houston, TX; Landon Moore & Jay Estes, NASA  Johnson Space Center, Houston, TX; Chri s Layer, Moog, Inc., East Aurora, NY 

11:00  PRESENTATION: An Overview of JSC   

11:45   TECHNICAL  SESSIONS CONCLUSION    • PRESENTATION OF THE HERZL AWARD  • CLOSING REMARKS Stuart H. Loewenthal, General Chairman Lockheed Martin Space Systems Company, Sunnyvale, CA   1:30  BUSES DEPART HOTEL FOR JSC TOUR  

2:00-4:00 JOHNSON SPACE CENTER FACILITY TOUR
xi SYMPOSIUM ORGANI ZING COMMITTEE 

Christopher P. Hansen, Host Chairman, NASA JSC 

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

Obie H. Bradley, Jr., NASA LRC  Carlton L. Foster, NASA MSFC  Claef F. Hakun, NASA GSFC  Patrice Kerhousse, ESA/ESTeC  Alan C. Littlefield, NASA KSC   Edward C. Litty, JPL  Fred G. Martwick, NASA ARC  Martha E. Milton, NASA MSFC  Wilfredo Morales, NASA GRC  Robert P. Mueller, NASA KSC  Fred B. Oswald, NASA GRC  Minh Phan, NASA GSFC   Donald R. Sevilla, JPL   Mark F. Turner, NASA ARC  James E. Wells, NASA LRC 

    SYMPOSIUM ADVISORY COMMITTEE 

David F. Engelbert, NASA ARC (ret)  Robert L. Fusaro, NASA GRC (ret)  Ronald E. Mancini, NASA ARC (ret)  Stewart C. Meyers, NASA GSFC  John W. Redmon, Sr., NASA MSFC (ret)  William C. Schneider, NASA JSC (ret)  Bowden W. Ward, Jr., NASA GSFC (ret)
A Description of Mechanisms u sed in the Low  Resolution   Airglo w & Aurora Spectrograph 

Phillip Kalmanson*, Russel l Starks+, Stefan Thon nard** and Kennet h Dymond ** 

Abstract 

The Low Resolution Airglow & Auro ra Spectrograph (LORAAS) was an aeronomy Ins trume nt des igned by  the Naval Res earch Laboratory (N RL). LORAAS was launche d into polar orbit on February 23, 1999  aboa rd the ARGOS spacecraft a nd operated successfully until th e shutdo wn of the sp acecraft in April of  2002. Data g ained from th e on-o rbit pe rforma nce of the LORAAS  mecha nisms will be pre sented alon g  with the perfo rman ce data take n duri ng ground testing.   

There were t hree m echanisms used in LORASS design and are as follo ws; a guillotine style dust cover  door a ssembly (DCDA), a one-axis sca n mirro r assembly (SMA), and a dete ctor doo r mecha nism (DDM).   These m echanisms are unique in  that th ey must all adhere to th e string ent requirements of contaminatio n  control due t o the sen sitivity of the optics u sed. In addition to su pportin g instrument ope ration whil e in  space, some of these m echani sms, such as th e DDM  and DCDA , were esse ntial for in strum ent ope ration  while o n the ground to ai d in instrumen t construction, calibration and stora ge. This p aper will pre sent a   descri ption of the afore mentioned  mechani sms in cluding  an overview of the  requi rements drivin g thei r  design, analy sis performed on the mech anism s and their comp onents, and final costs.   

Introduc tion 

LORAAS was built and designed by the NRL to observe the diffuse airg low emi tted by the thermosphere  and ionosphere region of t he at mosphere at altitudes bet ween 70 and 700 km. The LORAAS passband  operated in t he Far Ultrav iolet (FUV ) and Extreme Ultraviolet (E UV) rang e betwee n 80 – 170 nm. Th e  data obtain ed by LORAA S was used for stu dies of uppe r atmo spheri c structure, co mposition, and sunearth interac tion.   

Figure 1.  LORAAS Instr ument                                                    * Praxis Inc., Alexandri a, Virginia  ** Naval Research La boratory, Washing ton D.C.  + Formerly wit h Praxis Inc. – No w With E VI Technol ogy, Columbia, Marylan d 

Procee dings of the 37th Aeros pace Mec hanisms Sy mpos ium, Joh nson S pace Ce nter, May 19-2 1, 200 4  1
Instrumen t Overview 

The LORAAS ins trument was  comprised of four main components ; the Ultraviolet  Spec trograph As sembly   (USA), the control el ectronics, the high voltage power supply (HVPS), and t he harness assembly. The  USA contain s the optical bench and the me chanisms used on the instrum ent that su pport the opti cs.  Mounted  separately from the USA, the control ele ctronics contain  the circuit s used to provid e power and  control to th e mechani sms. The hi gh vol tage po wer suppl y is u sed to provide th e high  voltag e necessary  to operate th e we dge a nd strip style FUV/EUV dete ctor located in the USA. T he wi re harness provide s  the necessa ry powe r and signal co nnection s betwe en the contro l electroni cs, mechanisms, detecto r, and  HVPS. Although each of the main components can be further broken down  into subcomponents, only th e  USA will be discussed in detail. 

Ultraviolet Sp ectro graph A ssembly   The optical desi gn of the USA is a  0.25-m foca l length f/3 spe ctrograph in a near-Wadswo rth  config uratio n1. The optical  compo nents as sh own in Figur e 2 a re: a one -axis scan mi rror assem bly  (SMA), a me chanical grid  collimato r, a diffracti on g rating, and a n imaging d etector. The mech anisms  supportin g the optics a re the Dust Cover Doo r Asse mbly (DCDA), the Detec tor Door mec hanism (DDM).  Also mo unted to the USA  but not sh own are the suns hade, sun sensors, and the detector electronics.  The Spe ctrograph had a Field Of View (FOV) defin ed by the collim ator of 0.15 -degree Full Width at Half  Maximum (FWHM) i n the vertical direction an d 2.4  degrees FWHM in the  horizontal  directi on. Thi s FOV  transl ated in to an image resolution of 5 km by 120  km on the earth’s lim b as viewed by the LORAAS  instru ment while on orbit.    

Figure 2.  Inside of US A with Cov er and Sun Shad e Remov ed 

Scan Mirror Assembly  

Design  The SMA d efined the i nstrume nt Field  Of Re gard by rotating  a counterwei ghted silico n carbid e mirror  measuri ng 12 8 mm X 90 m m with a ma ss of ap proximately 0.41 kg. The SMA co mpone nts a re shown in   Figure 3. In addition to bei ng able to survive the operat ional an d lifetime req uirements the foll owing drove   the desi gn of the SMA, the SMA must:  • Rotate a sca n mirro r from  –5 to –13.5 degree s in 90 se cond s and return the  mirro r back to its   starting p osition in und er 5 seconds. (This mo tion was part of the no rmal op eratin g mode )  • Be able to rot ate the scan mirro r to –20 degrees (Thi s motion wa s required only rarely)  • Provide an a ccuracy of mirror pointin g knowledge to ±0.017 de gree. 

2