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