Transcript Pratham, IITB Student Satellite Conceptual Design Review

Pratham
IITB Student Satellite
Haripriya
Head, Integration Team
Pratham, IIT Bombay
19th June, 2010
Mission Statement
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Create a learning experience of working on a real life multidisciplinary complex system. Learning enhancement through
CDIO
(Conceive,
Design,
Integrate
and
Operate).
http://www.cdio.org/
Have the Satellite entirely designed by the student body of IIT
Bombay.
Success Criteria
Description
Mission Success
Flight Model ready
85%
Beacon Signal received
90%
TEC measurements at IITB
95%
Satellite functional for 4 months
100%
Information about Pratham
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Weight: ~10 kgs
Size: 260mm X 260mm X
260mm
Payload: Measuring TEC
Orbit: 10:30 polar
sun-synchronous, 817km
altitude
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Downlink at 2 frequencies
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Uplink used as kill switch
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4 months mission life
Student Team Size: 30
Departments:
Aerospace
Chemical
Civil
Computer Science
Electrical
Physics
Mechanical
PRATHAM
Core Group
(10 members)
Quality Team
Comm.
Power
Structure
Payload
Integration Team
OBC
Control
Thermal
PR Team
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
Team Size = 30
Two stage selection process
Quiz & Presentation
Launch
Dec 2010
Detailed
Design Phase
May 2010
Mar 10
Signed MoU
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
25
20
Continuity Plan
Documentation
Payload and
Communication
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Beacon
Total Electron Count of the
Ionosphere above Ground
Station
Faraday rotation method
used
CC Receiver
Rotor
Beacon is on all over the
world
ionosphere
Crossed Yagi
Downlink in 2 frequencies
(145.98 MHz & 437.455 MHz)
Uplink only used as kill
switch in case of malfunction
CC Transmitter
Base Station
OBC, ADCS and Power
SENSORS
SunSensor
(LEOS)
Solar Panels
On 4 sides
(ISAC)
OBC Circuit
Magnetometer
(Honeywell)
GPS
(ACCORD)
Power Circuit
ACTUATOR
Magnetorquer
Battery (ISAC)
ATTITUDE CONTROL
Systems Engineering
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System and Sub-System
Requirements
Mission Design
Weight Budget
Configuration Layout
Connectivity Diagram
Integration Sequence
Mechanical Subsystems
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Structural simulation of the
satellite under launch loads
Thermal design of the satellite
Integration with IBL230V2 LVI
Testing and Quality Assurance
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Electrical Quality ~0.98
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Mechanical QA ~1
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Validated by testing
Level 1 testing done by
individual Subsystems
On Board Computer In Loop
Simulations (OILS)
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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
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National Ground station
workshops
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11 participating universities
building Ground Station for
Pratham
MHRD Virtual Experiments
Collaboration with IPGP,
France
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Extensive help in
understanding TEC and
validating our approach
Data will be finally stored in
IPGP servers
Organizations Supporting Pratham
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ISRO
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ISAC
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VSSC
IIT Bombay
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IRCC
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CDEEP
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AEA
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SAMEER
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TIFR
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Boeing