Haripriya Head, Integration Team Pratham, IIT Bombay 19 th June, 2010

Mission Statement  Create a learning experience of working on a real life multi- disciplinary complex system. Learning enhancement through CDIO (Conceive, Design, Integrate and Operate).  Have the Satellite entirely designed by the student body of IIT Bombay. DescriptionMission Success Flight Model ready85% Beacon Signal received90% TEC measurements at IITB95% Satellite functional for 4 months100% Success Criteria

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

Payload Control PRATHAM Power OBC Thermal Student Team Size: 30 Departments: Aerospace Chemical Civil Computer Science Electrical Physics Mechanical PR Team Structure Quality Team Integration Team Comm. Core Group (10 members) Core Group (10 members)

Review Process Work done by Pratham Team 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 End of Design Phase Once every 6-10 months Rigorous reviews by the IITB Faculty Mentors & ISAC Engineers IITB Faculty Mentors: 30 Departments: Aerospace Computer Science Electrical Mechanical Systems and Controls

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

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

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

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

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)

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

Organizations Supporting Pratham  ISRO  ISAC  VSSC  IIT Bombay  IRCC  CDEEP  AEA  SAMEER  TIFR  Boeing