PrathamIITB Student Satellite
HaripriyaHead, Integration Team
Pratham, IIT Bombay19th June, 2010
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.
Description Mission Success
Flight Model ready 85%
Beacon Signal received 90%
TEC measurements at IITB 95%
Satellite functional for 4 months 100%
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:AerospaceChemicalCivilComputer ScienceElectricalPhysicsMechanical
PR Team
Structure
Quality Team
Integration Team
Comm.
Core Group(10 members)
Review Process
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
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 PhaseMay 2010
LaunchDec 2010
Oct
07
Sep
t 0
8
Sep
t 0
9
Mar
10
20Team Size = 30
2520
Two stage selection processQuiz & Presentation
Continuity PlanDocumentation
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 (145.98 MHz & 437.455 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)
ACTUATORMagnetorquer
ATTITUDE CONTROL
Solar PanelsOn 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
Thank You
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