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Pratham IITB Student Satellite

Pratham IITB Student Satellite. Haripriya Head, Integration Team Pratham , IIT Bombay 19 th June, 2010. Mission Statement.

wesley-pittman
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Pratham IITB Student Satellite

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  1. PrathamIITB Student Satellite Haripriya Head, Integration Team Pratham, IIT Bombay 19th June, 2010

  2. Mission Statement • Create a learning experience of working on a real life multi-disciplinary complex system.  Learning enhancement throughCDIO (Conceive, Design, Integrate and Operate). http://www.cdio.org/ • Have the Satellite entirely designed by the student body of IIT Bombay. Success Criteria

  3. Information about Pratham • Weight: ~10 kgs • Size: 260mm X 260mm X 260mm • Payload: Measuring TEC • Orbit: 10:30 polarsun-synchronous, 817km altitude • Downlink at 2 frequencies • Uplink used as kill switch • 4 months mission life

  4. Student Team Size: 30 Departments:AerospaceChemicalCivilComputer ScienceElectricalPhysicsMechanical PRATHAM Core Group (10 members) Comm. Quality Team Power Structure Payload Integration Team OBC Thermal Control PR Team

  5. Review Process Work done by Pratham Team End of Design Phase Once every 6-10 months Rigorous reviews by the IITB Faculty Mentors & ISAC Engineers IITB Faculty Mentors: 30 Departments:AerospaceComputer ScienceElectricalMechanical Systems and Controls Once every week Reviewed by the Team Once every month Reviewed by the IITB Faculty Once every 2-3 months Reviewed by the ISAC Engineers

  6. Timeline Requirements Capture Phase finished Apr 2008 Preliminary Design Phase finished Dec 2009 Launch Dec 2010 Conceptual Design Phase finished Aug 2008 Concept feasibility proved to IITB Aug 2007 Detailed Design Phase May 2010 Signed MoU with ISRO Sept 2009 Oct 07 Mar 10 Sept 08 Sept 09 20 Team Size = 30 25 20 Two stage selection process Quiz & Presentation Continuity Plan Documentation

  7. Payload and Communication Beacon CC Transmitter • Total Electron Count of the Ionosphere above Ground Station • Faraday rotation method used • Beacon is on all over the world • Downlink in 2 frequencies (145.98 MHz & 437.455 MHz) • Uplink only used as kill switch in case of malfunction CC Receiver Rotor ionosphere Crossed Yagi Base Station

  8. OBC, ADCS and Power SENSORS SunSensor (LEOS) Magnetometer (Honeywell) Solar Panels On 4 sides (ISAC) GPS (ACCORD) OBC Circuit Power Circuit ACTUATOR Magnetorquer ATTITUDE CONTROL Battery (ISAC)

  9. Systems Engineering • System and Sub-System Requirements • Mission Design • Weight Budget • Configuration Layout • Connectivity Diagram • Integration Sequence Mechanical Subsystems • Structural simulation of the satellite under launch loads • Thermal design of the satellite • Integration with IBL230V2 LVI

  10. Testing and Quality Assurance • Electrical Quality ~0.98 • From quality calculations, at the end of mission life • Mechanical QA ~1 • Validated by testing • Level 1 testing done by individual Subsystems • On Board Computer In Loop Simulations (OILS) • Level 2 testing of Power, OBC, Controls, and Communication • Clean Room built (100,000 class)

  11. Interaction with students from other universities • National Ground station workshops • 11 participating universities building Ground Station for Pratham • MHRD Virtual Experiments • Collaboration with IPGP, France • Extensive help in understanding TEC and validating our approach • Data will be finally stored in IPGP servers

  12. Organizations Supporting Pratham • ISRO • ISAC • VSSC • IIT Bombay • IRCC • CDEEP • AEA • SAMEER • TIFR • Boeing

  13. Thank You

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