Pratham IITB Student Satellite Project Saptarshi Bandyopadhyay Project

Pratham IITB Student Satellite Project Saptarshi Bandyopadhyay Project Manager and System Engineer Pratham, IIT Bombay 15 th May, 2011

Student satellite – The Idea! q q Aim - To develop a satellite in q a time frame of 2 -3 years q be of low cost q low mass (< 10 kgs) q launch it into orbit COTS instruments to reduce costs Success of mission attached to process of learning, not just final output Satellites are test-beds for new technology that need space qualification 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. MINI – SPUTNIK ASUSAT NCUBE SSETI AAU Cubesat SNOE ICARUS CATSAT DTUSAT MEROPE COMPASS SEEDS

Mission Statement for Pratham q Create a learning experience of working on a real life multi-disciplinary complex system. Learning enhancement through CDIO (Conceive, Design, Integrate and Operate). http: //www. cdio. org/ Acquiring knowledge in Satellite and Space Technology. Description Have the Satellite entirely designed by the student body of IIT Bombay. Flight Model ready Have the Satellite launched; measure TEC of the Ionosphere above IITB. Involve students from other universities in our Satellite project. Beacon Signal received TEC measurements at IITB Satellite functional for 4 months Mission Success 85% 90% 95% 100%

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

Student Team Size: 7 (usually 25) Departments: Aerospace Chemical Civil Computer Science Electrical Physics Mechanical PRATHAM Core Group (10 members) Quality Team Comm. Power Structure Integration Team Payload OBC Control Thermal Social Goal

Technical Mentors q Prof K. Sudhakar (Aero) q Prof R. K. Pant (Aero) q Prof P. M. Mujumdar (Aero) q Prof K. K. Isaac (IIST) q Prof H. Arya (Aero) q Prof U. N. Gaitonde (Mech) q Prof H. B. Hablani (Aero) q Prof R. K. Shevgaonkar (PU) q Prof S. P. Bhat (Aero) q Prof R. N. Banavar (Syscon) q Prof K. Chatterjee (Elec) q q Prof B. G. Fernandes (Elec) Prof D. K. Sharma (Elec) Prof R. P. Shimpi (Aero) q Prof K. N. Iyer (Mech) q q Prof Girish Kumar (Elec) q Prof Kavi Arya (CS) q Prof B Bandyopadhyay (Syscon) q Prof C. Amarnath (Mech) q q q Dr K P Ray (SAMEER) Prof Madhu N. Belur (Elec) Prof Krithi Ramamritham (CS)

Documentation and Reviews 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 q 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 Major emphasis on documentation since “We want to preserve our knowledge”

Timeline Team Size = 30 Two stage selection process Quiz & Presentation Launch End of 2011 Detailed Design Phase Aug 2010 25 Apr 11 Mar 10 Signed Mo. U with ISRO Sept 2009 Sept 09 20 Preliminary Design Phase finished Dec 2009 Sept 08 Oct 07 Requirements Capture Phase finished Apr 2008 Conceptual Concept Design Phase feasibility finished proved to IITB Aug 2008 Aug 2007 20 Continuity Plan Documentation

Payload Sub-System q q Measure Total Electron Count of the Ionosphere over India and France Expected TEC value is 25± 5 TECU (resolution of 0. 1 TECU, SNR of 500) 2 polarized radio signals are transmitted parallely Faraday rotation changes their angle of polarization The difference in their polarization angles is measured at the ground station IONOSPHERE q F 2 Region F 1 Region E Region D Region

Communication Sub -System q Low bit rate Beacon (145. 980 MHz) q q q High bit rate (1. 2 kbps) Monopole for downlink of data (437. 455 MHz) q q q CW transmitter, 0. 6 Watt power Resonant Helical/Non-resonant Monopole of 18 cm FSK transmitter, 0. 6 Watt power Resonant Monopole of 17 cm NO telecommand q q Kill Switch (Uplink) added to satisfy IARU’s constraint for getting license Resonant Monopole of 17 cm Beacon Rotor Crossed Yagi Base Station

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

Systems Engineering q q q System and Sub-System Requirements Mission Design Weight Budget Configuration Layout Connectivity Diagram Integration Sequence Mechanical Subsystems q q q Structural simulation of the satellite under launch loads Thermal design of the satellite Integration with IBL 230 V 2 LVI

Testing and Quality Assurance q Electrical Quality ~0. 98 q q Mechanical QA ~1 q q q Validated by testing Level 1 testing done by individual Subsystems On Board Computer In Loop Simulations (OILS) q q From quality calculations, at the end of mission life Level 2 testing of Power, OBC, Controls, and Communication Clean Room built (100, 000 class)

Interaction with students from other universities q National Ground station workshops q q 11 participating universities building Ground Station for Pratham MHRD Virtual Experiments 2 papers published at the International Astronautical Congress 2010 in Prague Collaboration with IPGP and Paris Diderot

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

Thank You