Pratham IITB Student Satellite Project
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Transcript of Pratham IITB Student Satellite Project
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PrathamIITB Student Satellite Project
Saptarshi BandyopadhyayProject Manager and System Engineer
Pratham, IIT Bombay15th May, 2011
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Student satellite – The Idea! Aim - To develop a satellite in
a time frame of 2-3 years be of low cost low mass (< 10kgs) 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. MINI – SPUTNIK2. ASUSAT3. NCUBE4. SSETI5. AAU Cubesat6. SNOE7. ICARUS8. CATSAT9. DTUSAT10. MEROPE11. COMPASS12. SEEDS
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Mission Statement for Pratham
Acquiring knowledge in Satellite and Space Technology.
Have the Satellite entirely designed by the student body of IIT Bombay.
Have the Satellite launched; measure TEC of the Ionosphere above IITB.
Involve students from other universities in our Satellite project.
DescriptionMission
Success
Flight Model ready 85%
Beacon Signal received 90%
TEC measurements at
IITB95%
Satellite functional for 4
months100%
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/
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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
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Payload
Control
PRATHAM
Power
OBC Thermal
Student Team Size: 7(usually 25)
Departments:AerospaceChemicalCivilComputer ScienceElectricalPhysicsMechanical
Social Goal
Structure
Quality Team
Integration Team
Comm.
Core Group(10 members)
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Technical Mentors Prof K. Sudhakar (Aero) Prof P. M. Mujumdar (Aero) Prof H. Arya (Aero) Prof H. B. Hablani (Aero) Prof S. P. Bhat (Aero) Prof K. Chatterjee (Elec) Prof B. G. Fernandes (Elec) Prof K. N. Iyer (Mech) Dr K P Ray (SAMEER) Prof Madhu N. Belur (Elec) Prof Krithi Ramamritham (CS)
Prof R. K. Pant (Aero) Prof K. K. Isaac (IIST) Prof U. N. Gaitonde (Mech) Prof R. K. Shevgaonkar (PU) Prof R. N. Banavar (Syscon) Prof D. K. Sharma (Elec) Prof R. P. Shimpi (Aero) Prof Girish Kumar (Elec) Prof Kavi Arya (CS) Prof B Bandyopadhyay (Syscon) Prof C. Amarnath (Mech)
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Documentation and Reviews
Work done by Pratham
Team
Once every weekReviewed by the Team
Once every monthReviewed by the IITB Faculty
Once every 2-3 monthsReviewed by the ISAC Engineers
End of Design PhaseOnce every 6-10 monthsRigorous reviews by the IITB Faculty Mentors & ISAC Engineers
IITB Faculty Mentors: 30 Departments:AerospaceComputer ScienceElectricalMechanicalSystems and Controls
Major emphasis on documentation since “We want to preserve our
knowledge”
All our documents are available on our website www.aero.iitb.ac.in/pratham/
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Timeline
Concept feasibility proved to IITBAug 2007
Requirements Capture Phase finished Apr 2008
Conceptual Design Phase finishedAug 2008
Preliminary Design Phase finishedDec 2009
Signed MoU with ISROSept 2009
Detailed Design PhaseAug 2010
LaunchEnd of 2011
Oct
07
Sep
t 0
8
Sep
t 0
9
Mar
10
20Team Size = 30
2520
Two stage selection processQuiz & Presentation
Continuity PlanDocumentation
Ap
r 1
1
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D RegionE Region
F1 RegionF2 Region
ION
OSP
HER
E
Payload Sub-System 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
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Communication Sub-System
Low bit rate Beacon (145.980 MHz)
CW transmitter, 0.6 Watt power Resonant Helical/Non-resonant
Monopole of 18 cm
High bit rate (1.2kbps) Monopole for downlink of data (437.455 MHz)
FSK transmitter, 0.6 Watt power Resonant Monopole of 17 cm
NO telecommand Kill Switch (Uplink) added to satisfy
IARU’s constraint for getting license Resonant Monopole of 17 cm
Beacon
Crossed Yagi
Rotor
Base Station
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OBC, ADCS and Power
OBC Circuit
SENSORS
SunSensor(LEOS)
GPS(ACCORD)
Magnetometer(Honeywell)
ACTUATORMagnetorquer
ATTITUDE CONTROL
Solar PanelsOn 4 sides(ISAC)
Battery (ISAC)
Power Circuit
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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
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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)
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Interaction with students from other universities
National Ground station workshops
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
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Organizations Supporting Pratham ISRO
ISAC VSSC
IIT Bombay IRCC CDEEP AEA
SAMEER TIFR Boeing
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Thank You