Presentation is loading. Please wait.

Presentation is loading. Please wait.

Observatory - Overview July 13 & 14, 2010MMS I&T Pre-CDR Peer Review 1 Single Observatory Stowed.

Published byJuliana Lindsey Modified over 8 years ago

Similar presentations

Presentation on theme: "Observatory - Overview July 13 & 14, 2010MMS I&T Pre-CDR Peer Review 1 Single Observatory Stowed."— Presentation transcript:

1 Observatory - Overview July 13 & 14, 2010MMS I&T Pre-CDR Peer Review 1 Single Observatory Stowed

2 MMS Observatory w/SA Removed Mission Overview July 13 & 14, 2010 2 MMS I&T Pre-CDR Peer Review

3 July 13 & 14, 2010MMS I&T Pre-CDR Peer Review 3 SMART IS Components Mission Overview DIS DES ASPOC FEEPS EDI SDP HPCA EIS IS safe/arm panel 1 2 3 4 5 6 7 8 +X -X -Y +Y ADP DSS FEEPS Mag boom SCM & AFG Mag boom DFG SMART Components ADP - Axial Double Probe AFG - Analog Flux Gate Magnetometer (mounted on boom) ASPOC - Active Spacecraft Potential Control CEB - Central Electronics Box (Fields) CIDP - Central Instrument Data Processor DES - Dual Electron Spectrometer DFG - Digital Flux Gate Magnetometer (mounted on boom) DIS - Dual Ion Spectrometer EDI/GDU - Electron Drift Instrument/ GunDetector Unit EIS - Energetic Ion Spectrometer FEEPS - Fly’s Eye Energetic Particle Sensors HPCA - Hot Plasma Composition Analyzer IDPU - Instrument Data Processing Unit (FPI) SCM - Search-Coil Magnetometer (mounted on boom) SDP - Spin-Plane Double Probe CIDP, IDPU, and CEB are mounted under the IS deck

4 July 13 & 14, 2010MMS I&T Pre-CDR Peer Review 4 Clampband Locations Active Ring Simulator - Future Work Spacecraft Separation System RUAG PAS1666S - 1666mm clampband, shear lip design Spacecraft Separation System RUAG PAS1666S - 1666mm clampband, shear lip design Spacecraft Separation System RUAG PAS1666S - 1666mm clampband, shear lip design Launch Vehicle Separation System Atlas D1666 - 1666mm clampband, shear pin design - Also supplied by RUAG

5 July 13 & 14, 2010MMS I&T Pre-CDR Peer Review5 Observatory - Dimensions +X-X +Y -Y (3150 mm) [124.0”] (3478 mm) [136.9”] (3680 mm) [144.9”] (3690 mm) [145.3”] (3033 mm) [119.4”] +Y -Y +X-X maximum dimension = 3690 mm [145.3”] [12’ 1.3”]

6 July 13 & 14, 2010MMS I&T Pre-CDR Peer Review6 Observatory - Dimensions Active SOLAR ARRAY PANEL (.850 m 2 ) Passive Sep Plane (1230 mm) [48.4”] (680 mm) [26.7”] (66 mm) [2.6”] (110 mm) [4.3”] (1250 mm) [49.2”] (133 mm) [5.2”] (930 mm) [36.6”] (1666 mm) [65.6”] (1054 mm) [41.5”] Thrust Tube +X -X +Z -Z ORIGIN (216 mm) [8.5”] (167mm) [6.6”] (490 mm) [19.3”] (526 mm) [20.7”]

7 July 13 & 14, 2010MMS I&T Pre-CDR Peer Review7 Launch Configuration 4 Meter Fairing #1 #2 #3 #4 4916 mm [193.5”] 5936 mm [233.7”] LV I/F Four observatories will be stacked on top of each other will be clocked 180° from each other separation system details in covered in the Mechanical PDR

8 Instrument Suite Harness IS harness is the responsibility of SwRI SwRI is using the GSFC Pro-E model for harness routing and transfer of harness tie- down locations –as harness segments are fabricated, the mass of each segment will be added to the model Spacecraft is providing production break connector brackets where IS harness joins SC harness –brackets are attached to the thrust tube Harness between IS deck and SC deck is routed along the thrust tube and is attached via threaded inserts in the thrust tube ribs Some IS harness is routed across SC deck (FEEPS, magnetometers) –these areas are shown on the deck MICD Harness tie downs on the IS deck are bolted to the deck in post cured inserts and with bonded TC105s Purge lines are also routed using the same model July 13 & 14, 2010MMS I&T Pre-CDR Peer Review 8

9 CEB CIDP IDPU AEB DIS #4 DIS #3 DIS #2 DIS #1 DES #2 DES #3 DES #4 DES #1 ASPOC #1 ASPOC #2 FEEPS EDI #2 EDI #1 SDP #4 SDP #2 SDP #1 SDP #2 HPCA EIS IS safe/arm panel +X -X +Y -Y purge manifold S-Band Antenna 1 8 7 6 5 4 3 2 Test/thermal pwr distribution panel vent Instrument Deck Components July 13 & 14, 2010MMS I&T Pre-CDR Peer Review9 Instrument Deck Components ADP - Axial Double Probe AEB - Axial Electronics Box ASPOC - Active Spacecraft Potential Control CEB - Central Electronics Box (Fields) CIDP - Central Instrument Data Processor DES - Dual Electron Spectrometer DIS - Dual Ion Spectrometer EDI/GDU - Electron Drift Instrument/ Gun Detector Unit EIS - Energetic Ion Spectrometer FEEPS - Fly’s Eye Energetic Particle Sensors HPCA - Hot Plasma Composition Analyzer IDPU - Instrument Data Processing Unit (FPI) SDP - Spin-Plane Double Probe - 19 IS instruments- SC vent - 4 IS electronics boxes- S-band antenna - IS safe/arm panel- 6 thrusters - IS purge manifold - IS test/thermal pwr distribution panel ` (blue = SC components mounted on instrument deck) thruster

10 July 13 & 14, 2010MMS I&T Pre-CDR Peer Review 10 Remaining Integration install solar arrays & magnetometer booms install ADP receiving element & orbital debris shields

11 GPS Hat Coupler 1 2 3 4 5 6 7 8 S-band Hat Coupler (+Z direction) DES Sensor Head SCM and AFG (mounted on mag boom not shown) DES Sensor Head GPS Hat Coupler DES Sensor Head DSS Stimulator DES Sensor Head GPS Hat CouplerGPS Hat Coupler GPS Hat Coupler S-band Hat Coupler (-Z direction) DFG (mounted on mag boom not shown) Star Sensors (really on underside of spacecraft deck) EIS HPCA Total of 24 Add-On Stimulus GSE for Thermal Tests Adding 1 foot clearance for TVAC GSE. The current minimum width needed with TVAC GSE attached = 157.5” or 13.1 feet 145.5” or 12.1’ FEEPS FEEPS (mounted on spacecraft deck) Stimulus and GSE Locations July 13 & 14, 2010 11 MMS I&T Pre-CDR Peer Review

Download ppt "Observatory - Overview July 13 & 14, 2010MMS I&T Pre-CDR Peer Review 1 Single Observatory Stowed."

Similar presentations

Aug.19, 1999 George T. Roach Integration Mission Design Center NASA- GSFC Code 543 Greenbelt, MD. 20771 301-286-2213 FAX 301-286-0343 -

Aug.19, 1999 George T. Roach Integration Mission Design Center NASA- GSFC Code 543 Greenbelt, MD FAX
Delta II –7920 Fitup Study Model TMA-56 f10 optics In-Line configuration Delta II Launch Vehicle 7920 H 10L Composite Fairing.

Delta II –7920 Fitup Study Model TMA-56 f10 optics In-Line configuration Delta II Launch Vehicle 7920 H 10L Composite Fairing.
AMS-02 tracker mechanics status of assembly and integration at UniGe Outer planes: - Tests of evaporator (cooling loop) integration - Tools to develop.

AMS-02 tracker mechanics status of assembly and integration at UniGe Outer planes: - Tests of evaporator (cooling loop) integration - Tools to develop.
AAE450 Spring 2009 Mass Savings and Finite Element Analysis (FEA) Preparation for Orbital Transfer Vehicle (OTV) 100 gram Case Tim Rebold STRC [Tim Rebold]

AAE450 Spring 2009 Mass Savings and Finite Element Analysis (FEA) Preparation for Orbital Transfer Vehicle (OTV) 100 gram Case Tim Rebold STRC [Tim Rebold]
AMS-02 tracker mechanics status of assembly and integration Inner tracker integration completion: - Assembly and cabling - Temperature and magnetic field.

AMS-02 tracker mechanics status of assembly and integration Inner tracker integration completion: - Assembly and cabling - Temperature and magnetic field.
MPSRThermal- 1 UCB, Oct 26, 2006 THEMIS MISSION PRE-SHIP REVIEW Thermal Christopher Smith University of California - Berkeley.

MPSRThermal- 1 UCB, Oct 26, 2006 THEMIS MISSION PRE-SHIP REVIEW Thermal Christopher Smith University of California - Berkeley.
B. Donakowski UCB/SSLFIELDS iCDR – MEP Mechanical 1 SPP FIELDS MEP Main Electronics Package Mechanical Packaging Bill Donakowski

B. Donakowski UCB/SSLFIELDS iCDR – MEP Mechanical 1 SPP FIELDS MEP Main Electronics Package Mechanical Packaging Bill Donakowski
SMART About NASA’s Magnetospheric Multiscale Mission (MMS) MAGNETIC RECONNECTION is a little-understood physical process at the heart of space weather.

SMART About NASA’s Magnetospheric Multiscale Mission (MMS) MAGNETIC RECONNECTION is a little-understood physical process at the heart of space weather.
Solar Probe Plus FIELDS Monthly Management Telecom Sep 17, 2012.

Solar Probe Plus FIELDS Monthly Management Telecom Sep 17, 2012.
Telecom 1 9/17/2012 SPP/FIELDS Solar Probe Plus FIELDS Monthly Management Telecom Sep 17, 2012.

Telecom 1 9/17/2012 SPP/FIELDS Solar Probe Plus FIELDS Monthly Management Telecom Sep 17, 2012.
SPP FIELDS V5 Antenna Mechanical Peer Review Draft 2 David Glaser, Paul Turin, Jeremy McCauley, John Bonnell, Dennis Seitz SSL UCB 7/17/13.

SPP FIELDS V5 Antenna Mechanical Peer Review Draft 2 David Glaser, Paul Turin, Jeremy McCauley, John Bonnell, Dennis Seitz SSL UCB 7/17/13.
Student Satellite Project University of Arizona Team Goals Design, Fabricate, and Analyze a Structure that will Support the Payload –Space Allocation of.

Student Satellite Project University of Arizona Team Goals Design, Fabricate, and Analyze a Structure that will Support the Payload –Space Allocation of.
STEREO IMPACT SEP Critical Design Review 2002-Nov-20 TvR IMPACT/SEP Thermal Design John Hawk, GSFC (301)-286-2754.

STEREO IMPACT SEP Critical Design Review 2002-Nov-20 TvR IMPACT/SEP Thermal Design John Hawk, GSFC (301)
1 NASA’s Goddard Space Flight Center 2005/4/14 LRO/CRaTER Technical Interchange Meeting LRO Mechanical Systems Giulio Rosanova / 543 301-286-5907 /

1 NASA’s Goddard Space Flight Center 2005/4/14 LRO/CRaTER Technical Interchange Meeting LRO Mechanical Systems Giulio Rosanova / /
THEMIS FRRSC - 1 KSC, Feb 12, 2007 SPACECRAFT OVERVIEW/STATUS Peter R Harvey THEMIS Project Manager.

THEMIS FRRSC - 1 KSC, Feb 12, 2007 SPACECRAFT OVERVIEW/STATUS Peter R Harvey THEMIS Project Manager.
Southwest Research Institute NSF Conference on Small Satellites Plasma Instrument Miniaturization and Integration: Approaches and Limitations C.J. Pollock,

Southwest Research Institute NSF Conference on Small Satellites Plasma Instrument Miniaturization and Integration: Approaches and Limitations C.J. Pollock,
23 - 1 NASA’s Goddard Space Flight Center LRO Integration and Test Joanne Baker GSFC Code 568 August 16-17, 2005.

NASA’s Goddard Space Flight Center LRO Integration and Test Joanne Baker GSFC Code 568 August 16-17, 2005.
Tielong Zhang On behalf of the CGS Team in the Institute of Geology and Geophysics, Chinese Academy of Science Spacecraft System and Payload China Geomagnetism.

Tielong Zhang On behalf of the CGS Team in the Institute of Geology and Geophysics, Chinese Academy of Science Spacecraft System and Payload China Geomagnetism.
GLAST LAT ProjectDOE/NASA Mechanical Systems Peer Review, March 27, 2003 Document: LAT-PR-0XXXX Section 5.1 Grid Box Design 1 GLAST Large Area Telescope:

GLAST LAT ProjectDOE/NASA Mechanical Systems Peer Review, March 27, 2003 Document: LAT-PR-0XXXX Section 5.1 Grid Box Design 1 GLAST Large Area Telescope:
N A S A G O D D A R D S P A C E F L I G H T C E N T E R I n s t r u m e n t S y n t h e s i s a n d A n a l y s i s L a b o r a t o r y Earth Atmosphere.

N A S A G O D D A R D S P A C E F L I G H T C E N T E R I n s t r u m e n t S y n t h e s i s a n d A n a l y s i s L a b o r a t o r y Earth Atmosphere.

Similar presentations

Ads by Google