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The Odyssey Project

The Odyssey Project. AAE450 – Fall 2006 Senior Spacecraft Design. Design Team. Propulsion & ACS Jon Fromm David Helderman Stephanie White ConOps Matt Harvey David Helderman Ashley Ruic Orbits Stephanie White Structures Hadi Ali April Miller Aaron Schinder Power Systems

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The Odyssey Project

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  1. The Odyssey Project AAE450 – Fall 2006 Senior Spacecraft Design Purdue University Aeronautics and Astronautics

  2. Design Team Propulsion & ACS • Jon Fromm • David Helderman • Stephanie White ConOps • Matt Harvey • David Helderman • Ashley Ruic Orbits • Stephanie White Structures • Hadi Ali • April Miller • Aaron Schinder Power Systems • Norman Herbertz Systems Engineering • David Helderman • Ashley Ruic Payload – Optics, Comm • Nick Andrews • Craig Bittner • Matt Dennis • Elisabeth Hanssens • Ashley Ruic Cost & Scheduling • Matt Harvey Launch Vehicle • Nick Sochinski Thermal • Chris Murphy Purdue University Aeronautics and Astronautics David Helderman

  3. Presentation Outline Component Presentations 10:05 Break 10:15 Optics 10:35 Structures & Mechanisms 10:50 Propulsion & ACS 11:05 Communications & Data Handling 11:20 Launch & Auxiliary Systems 11:35 Cost, Scheduling, & ConOps Purdue University Aeronautics and Astronautics David Helderman

  4. Module Naming Convention • Reasons for naming convention • 15 possible sites • Assigning space • Location of modules • Examples of naming convention • Communication antenna module site 1.3 • Earth Viewing Telescope module site 2.2 - 2.3 3.1 1.1 2.1 1.2 1.3 1.4 2.4 3.4 3.5 2.4 1.5 Purdue University Aeronautics and Astronautics

  5. Space OpticsAshley Ruic Purdue University Aeronautics and Astronautics

  6. Space Optics Design • Design Problem • System required to have space viewing capabilities • Requirements • Equivalent to Hubble (HST) • Resolution of 0.05 arcsec • Design choices • 1 or 2 optical systems • Single or double mirror • Solid glass vs. segmented Beryllium mirror Hubble image of the Eagle Nebula showing the formation of stars* *http://hubblesite.org/newscenter/archive/releases/1995/44 Purdue University Aeronautics and Astronautics Ashley Ruic

  7. Hubble Comparison • Hubble (HST) • Solid glass mirror cost: $10 M/m2 • HST cost: $45.2 M • Segmented Beryllium • Segmented Beryllium mirror cost: $3 M/m2 • Total segmented mirror cost: $13.6 M $45.2 M $13.6 M 800 kg 113 kg * Cost information from AAMSD presentation, 15 March 2005 Purdue University Aeronautics and Astronautics Ashley Ruic

  8. SVT Design Considerations • SVT is design driver • FGS necessary for resolution • Hubble: 0.05 arcsec • Requires super-module • Necessity for second launch • Incorporation of new technology • Segmented Beryllium mirror (JWST) • Light weight • Mechanisms act as on-site calibration • Shape-memory material for CCD holder • Minimize storage space • Minimize mass of structure HST-like spectrum viewing capabilities Odyssey Project Segmented Beryllium mirror Purdue University Aeronautics and Astronautics Ashley Ruic

  9. SVT Details • Metrics • Mass of SVM subsystem: • 137.7 kg • 797.7 kg (incl FGS) • 2797.7 kg (incl FGS & module) • Power: 1565 W • Data rate: 1.5 GB/day • Manufacturing • Corning OCA or Axsys Technologies, Inc • Polish to reflect specific wavelength • Assemble telescope Existing JWST Beryllium mirrors • * http://www.mdatechnology.net/techsearch.asp?articleid=175 • http://www.axsys.com/pr-030922.php Purdue University Aeronautics and Astronautics Ashley Ruic

  10. QuestionsAshley Ruic Backup Slides Purdue University Aeronautics and Astronautics

  11. Earth OpticsNick Andrews Purdue University Aeronautics and Astronautics

  12. EVT Requirements and Function • Function • Observe the Earth • Requirements • Earth viewing resolution of 1 meter (comparable to IKONOS and Quikbird) • Telescope must operate with pointing accuracy of 0.005 degrees (69 m) • Telescope must provide complete coverage of the Earth over a period of 25 days - field of view wider than the greatest distance between two ground tracks (113km) 1m resolultion image of Purdue University *Goggle Maps Purdue University Aeronautics and Astronautics Nick Andrews

  13. Telescope Layout • Located in modules 2.2 and 2.3, points towards Earth • Mirror assembly features • 2-mirror unit with CCD chipset • Mirror’s composed of ULE glass with aluminum honey-combed support • Focal length of 0.6m • 3-axis control • 0.5μm viewing spectrum • Light-reducing shroud features • Outer surface reflects heat • Inner surface absorbs light • Baffling reduces light reflection • Sun-shade reduces glare Cutaway view of the EVT Purdue University Aeronautics and Astronautics Nick Andrews

  14. Mirror Construction • Uses a honeycombed-aluminum truss as the base • Coated with Ultra Low Expansion (ULE) glass, which is then trimmed down to the proper curvature • Outer layer magnesium fluoride is then applied to the surface • Primary design consideration based on Coefficient of Thermal Expansion (CTE) Properties of Mirror Materials for Primary Mirror Mirror Schematic *http://www.matweb.com Purdue University Aeronautics and Astronautics Nick Andrews

  15. Image Collection Procedure • 10 km-diameter image area • EVT pivots to collect entire requested area • 0.65s relocation time • 0.05 second exposure time • 2.5 cm movement during exposure • Images processed on the ground Purdue University Aeronautics and Astronautics Nick Andrews

  16. CCD Chipset • Goal: Produce digital images at a 1m to pixel ratio • 21 CCD chips 2000 x 2000 pixels • 30mm by 30mm • 15μm per pixel • Arranged to capture all of the light of the secondary mirror CCD Chipset Layout CCD chips after production Purdue University Aeronautics and Astronautics Nick Andrews

  17. QuestionsNick Andrews Purdue University Aeronautics and Astronautics

  18. Structures & MechanismsAaron Schinder Purdue University Aeronautics and Astronautics

  19. Module Structure • Purpose: Survive launch forces • 6g axial acceleration compression, buckling • 1.5g lateral acceleration bending, torsion • Modules attach to the core in tension during launch • Internal equipment mass mounted to the endplate • Connect to the core via the docking mechanism • Standard size is 1m Purdue University Aeronautics and Astronautics Aaron Schinder

  20. Alignment Fin Core Structure • Core resists bending, compression, and torsion loads • Structural “backbone” of the spacecraft • Transfers loads from segment to segment during launch Purdue University Aeronautics and Astronautics Aaron Schinder

  21. Material Trade Study Fitness Coefficients • Seven materials ranked according to: • Thermal conductivity • Thermal expansion coefficient • Fitness coefficients for structural applications (combinations of material properties to minimize mass for endplates, beams, rods, and columns) • Titanium selected for all core and module structural applications • Plates • Beams • Columns1 • Rods1 Final Scoring Scheme and Selection 1. Peery, David. Aircraft Structures. New York: McGraw-Hill, 1950. 279. 2. Matweb Material Property Data. 4 Nov. 2006 <http://www.matweb.com>. 3. Larson, Wiley J., and James R. Wertz. Space Mission Analysis and Design. 3rd ed. El Segundo: Microcosm Inc., 1999. 466. Purdue University Aeronautics and Astronautics Aaron Schinder

  22. Loads Considered and Summary • Total structural mass is about 50% of the total spacecraft mass, compared with 21.7% for average spacecraft * • Result of modular architecture and requirements for independently docking units Torsion Inter-brace buckling Core buckling Core bending Examples of considered failure modes Summary of primary structural mass * Larson, Wiley J., and James R. Wertz. Space Mission Analysis and Design. 3rd ed. El Segundo: Microcosm Inc., 1999. 896. Purdue University Aeronautics and Astronautics Aaron Schinder

  23. QuestionsAaron Schinder Backup Slides Purdue University Aeronautics and Astronautics

  24. Structure of Propulsion SegmentHadi Ali Purdue University Aeronautics and Astronautics

  25. Structural Design of the Propulsion Segment • Objective: • Design the configuration and the structure of the propulsion segment • Subject to volume and mass constraints • To sustain loads it experiences on ground and during launch • Approach: • Choose material and structural geometry • Size I-beam arrangement to support tanks • Size rods to support I-beams • Use Z-brackets to support the tanks • Results: • Material: Aluminum 7075-T6 (density=2.78 g/cm3) • Final weight of the structure in the segment (without tanks) = 350 kg • Final dimensions of the propulsion segment = 3.0 m diameter X 2.0 m length Pressurant Tank Rod Propellant Tank Z-Bracket Electric Propulsion Engine I-Beams Purdue University Aeronautics and Astronautics Hadi Ali

  26. Dimensions of Structural Components D=0.06 m Cross-section D=0.96 m 7g*Payload/2 7g*Payload/2 0.3 m D=0.33 m 7g*Mass He tank 7g*Mass Hydrazine tanks 0.02 m 0.24 m 0.015 m 0.02 m 0.04 0.52 m 0.51 m 0.37 m 0.04 Cross-section 1.48 m All dimensions are in meters Purdue University Aeronautics and Astronautics Hadi Ali

  27. Analysis of Structural Components D=0.96 m -Check for buckling: D=0.33 m ok -Check for bending: ok 0.04 0.37 m 0.04 0.52 m 0.51 m -Check for shear: 1.48 m ok All dimensions are in meters Purdue University Aeronautics and Astronautics Hadi Ali

  28. QuestionsHadi Ali Backup Slides Purdue University Aeronautics and Astronautics

  29. PropulsionJohn Fromm Purdue University Aeronautics and Astronautics

  30. Odyssey Propulsion Systems • Altitude Maintenance • Counteracts atmospheric drag • 1 kW hydrazine decomposition arcjet thruster • Provides 1 m/s ΔV over 18 hrs • Isp: 420 s • Thrust: 0.17 N • Attitude Control • Reaction wheel unloading • Rapid orientation changes • Emergency attitude control and altitude maintenance • Twelve 45 N hydrazine decompostion monoprop thrusters • Isp: 220 s Thruster Cluster Propulsion Components Purdue University Aeronautics and Astronautics Jon Fromm

  31. Fuel Distribution System • Designed to be refuelable and reliable • Refuelable via Orbital Express • Three 5.52 MPa hydrazine tanks • Three 55.2 MPa Helium tanks • Single fault tolerant and double fault survivable plumbing configuration • Helium feed for experiment segment • 1019 kg of hydrazine • 110 kg of Helium • Orbital Express System • ASTRO configured to deliver hydrazine and Helium • Autonomous rendezvous and docking Fuel Distribution System Plumbing and Instrumentation Diagram Orbital Express Docking Mechanism Orbital Express ASTRO Vehicle Purdue University Aeronautics and Astronautics Jon Fromm

  32. Thrusters Fuel Tank Solar Array Module Super-module and Segment Propulsion Antennas • Module propulsion • 8 Helium cold gas thrusters • 3 “pan and scan” antennas • 12km range with full de-orbit capability • And separate and reattach • Single use system • Super-module and segment propulsion • Hydrazine fueled, helium pressurized • Eight control and one primary thrusters • Super-module propulsion is disposable • Segment propulsion is refuelable by Odyssey Concept for Module Propulsion Unit Structural Concept for Super-module Segment Propulsion Concept Design Purdue University Aeronautics and Astronautics Jon Fromm

  33. QuestionsJohn Fromm Backup Slides Purdue University Aeronautics and Astronautics

  34. Attitude Control System (ACS)Stephanie White Purdue University Aeronautics and Astronautics

  35. Odyssey Attitude Control SystemLayout • Rate-sensing gyroscopes • Housed in Rate Sensing Units (RSU) • Modules 1.1, 2.1, 3.1 • Reaction wheels • Housed in Reaction Wheel Assemblies (RWA) • Modules 1.5, 3.5 • Fine Guidance Sensors (FGS) • Super-module RWA2 RWA1 RSU3 RSU2 RSU1 Hardware modules FGS1 FGS2 FGS3 Ref: SM3A Media Guide Super-module Purdue University Aeronautics and Astronautics Stephanie White

  36. Δv Budget Ref:SMAD Purdue University Aeronautics and Astronautics Stephanie White

  37. Fine Guidance Sensors (FGS) • FGS components • Mirrors, lenses, servos, prisms, beam-splitters and photomultiplier tubes • FGS target acquisition • FGS aim the SVT by locking onto “guide stars” • FGS1 monitors pitch and yaw • FGS2 monitors roll • FGS3 performs dual role • Provides redundancy • Performs astrometry FGS Used Aboard Hubble “HST Fine Guidance Sensors” www.oss.goodrich.com/HSTFineGuidanceSensors.shtml “HubbleSite – FGS” http://hubblesite.org/the_telescope/nuts_.and._bolts/instruments/fgs/ Target Acquisition Purdue University Aeronautics and Astronautics Stephanie White

  38. QuestionsStephanie White Backup Slides Purdue University Aeronautics and Astronautics

  39. CommunicationsMatt DennisElisabeth Hanssens Purdue University Aeronautics and Astronautics

  40. Communication Link Summary • 4 communication link scenarios • Ku-band • uplink and downlink • S-band • uplink and downlink Partial communication link budget Satellite-TDRS links Purdue University Aeronautics and Astronautics Matt Dennis

  41. Communication Hardware • Each communication system consists of: • One 0.5 meter antenna • Parabolic reflector • Gold-clad molybdenum mesh • Built by Harris Corporation • Two transceivers • One Ku-band transceiver • One S-band transceiver • Two systems located on opposite sides of the spacecraft will be used for increased access times and reliability • Estimated material cost • $4,000 for two antennas • $28,000 for four transceivers • Estimated system mass • 40 kg Communication Antenna Communication Antennas * Lu, Richard A. Modifying Off-the-Shelf, Low Cost, Terrestrial Transceivers For. 1 June 1996. Stanford University. 23 Nov. 2006 <http://ssdl.stanford.edu/ssdl/images/stories/papers/1996/ssdl9605.pdf>. Antennas Locations Purdue University Aeronautics and Astronautics Matt Dennis

  42. Satellites in geosynchronous orbits 9 operational satellites provide global coverage White Sands Ground Complex (WSGC) near Las Cruces, New Mexico 2 ground terminals at WSGC (one additional relay terminal in Guam) Data sent from WSGC to customer ground station NASA TDRSS Infrastructure TDRSS Overview *http://scp.gsfc.nasa.gov/tdrss/ Purdue University Aeronautics and Astronautics Elisabeth Hanssens

  43. TDRS Positions Operational TDRS Longitudes *http://msp.gsfc.nasa.gov/tdrss/oview.html Purdue University Aeronautics and Astronautics Elisabeth Hanssens

  44. QuestionsMatt Dennis Elisabeth Hanssens Backup Slides Purdue University Aeronautics and Astronautics

  45. Data HandlingCraig Bittner Purdue University Aeronautics and Astronautics

  46. Manufacturing and Specifications • Aitech Defense Systems produces radiation shielded computers • Includes all needed components (RAM, cache) except storage memory • Modify existing IBM PowerPC processors • Currently IBM produces a 2.2 GHz PowerPC 970FX • 24 GB of storage memory needed • Hubble uses 12 GB of memory for storage • Aitech produces 1 GB storage memory cards • Odyssey will use 28 storage memory cards • Computers and memory housed in Aitech enclosures • Each enclosure holds 8 items • Each enclosure will house 1 computer and seven 1 GB memory cards • Need 4 enclosures, 2 in each computer module • Total cost of computer system: $120,000 Aitech’s space-qualified computer www.rugged.com hubble.nasa.gov/a_pdf/news/facts/FS15.pdf http://www- 306.ibm.com/chips/techlib/techlib.nsf/techdocs/ 1DE505664D202D2987256D9C006B90A5 Aitech enclosure Purdue University Aeronautics and Astronautics Craig Bittner

  47. Computer System Layout • Distributed layout • Spread out and decentralized • Processing in two computer modules • Benefits of a distributed layout • Easier to add future computer modules • Disperses heat • Allows for a backup computer module • Two computer modules • A single computer can keep Odyssey in orbit • Loss of memory card slightly reduces storage Functionality Table for Computing System Distributed computer layout Purdue University Aeronautics and Astronautics Craig Bittner

  48. QuestionsCraig Bittner Backup Slides Purdue University Aeronautics and Astronautics

  49. Launch VehicleNick Sochinski Purdue University Aeronautics and Astronautics

  50. Cost Comparison • SpaceX reduces cost focusing on 5 areas • Overhead • Propulsion • Structures • Avionics • Launch operations Current launch vehicle cost comparison Falcon series launch vehicles Purdue University Aeronautics and Astronautics Nick Sochinski

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