1. The COEP Satellite project launched by ISRO
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SWAYAM
The COEP Satellite project launched by ISRO
Slide Presentation Compiled by
Prof.Ujwala Bongale
TCOER-Pune
For more information visit below mentioned website link
Website

2. SWAYAM
The COEP Satellite project launched by ISRO By
Ujwala Bongale

3. Contents What is Swayam About the programme Mission objectives
Time lines
Subsystems
Achievements

4. What is Swayam
Swayam is Mini satellite made by Pune students flies into space.
It aimed at developing a reliable bidirectional communications
platform, destined to orbit the Earth at a height of km.
Swayam has been launched successfully on 22nd of June 2016
along with SRO’s CARTOSAT-2C by Polar Satellite Launch
vehicle PSLV-C34
A Memorandum of Understanding (MoU) has been signed
between COEP and ISRO on 23rd May, 2013, for the development
and launch of SWAYAM.

5. About SWAYAM Satellite from College of Engineering, Pune
Mission objectives: To provide point to point messaging
services to the HAM Community.
Launch Mass: 1 kg
Frequency : MHz
Launch Date: Wednesday, June 22, 2016
Launch Vehicle: PSLV-C34 / Cartosat-2 series satellite
Type of Satellite: Student
Manufacturer: ISRO
Owner: ISRO

6. About the programme
Mission Swayam is the first satellite project of COEP's
Satellite Initiative under the CSAT programme.
The team consists of students from freshers to seniors and
spans all the engineering disciplines in the college.
The students in this team are selected after a rigorous
selection process that spans multiple rounds. In addition to
their regular academic work the team members dedicatedly
work on this project all year round to meet the project
deadlines.
The team published more than 15 research papers in
international conferences for last 7 consecutive years.

7. Mission objectives Messaging services
Swayam hosts points to point messaging services which will
enable to store and forward messages from one corner of globe
to the other via the satellite.
Send Message:
This service can be used to send a message from one Ground
station (source) to the satellite which is intended for another
Ground Station (destination).
An acknowledgment is sent to the source ground station
indicating that the message was logged properly by the satellite .

8. Mission objectives Receive Message:
This service can be used to download a message sent by some
other Ground Station to the satellite intended for the Ground
Station requesting this service.
The requesting ground station will receive a positive or negative
acknowledgment depending upon availability of the message

9. Timeline 22nd June 2016: Has been launched.
June : Swayam shipped from ISAC to SHAR and
integrated with PSLV.
February : Flight Model successfully undergone Vibration
and Thermo-Vacuum test at ISAC, Bangalore.
Satellite handed over to ISRO .
January :Flight Model assembly and bench level testing
completed at ISAC, Bangalore.
September 2014: Critical Design Review (CDR) successfully
cleared at ISAC, Bangalore.

10. Timeline
Aug 2013: Team visits ISRO Satellite Centre, Bangalore to finalize
Solar Panel Interface and Battery box design.
June 2013: Team visits Vikram Sarabhai Space Center, Trivandrum
for Flight considerations
Dec 2012: Bread-Board Integration testing complete.
Nov 2012: COEP GS receives its first Satellite Signal.
Oct 2012 : COEP develops its ground station.
Jan 2010 : Conceptual Design Review at ISRO Satellite centre.
Jan 2009 : Project officially approved by COEP.
Late 2008: Project initiative by a group of students.

11. Subsystems The Satellite team is divided broadly into five subsystems,
Attitude Control System
Communication
Spacecraft
Ground station segment
Onboard computer
Power
Structure

12. Attitude Control System

13. Attitude Control System
ACS controls the dynamic behavior of satellite like orientation and
motion of satellite.
In Swayam, the unique technique of Passive Magnetic Attitude
Control System (PMACS) is implemented for the first time on an
Indian satellite.
 It controls the orientation of satellite without any power
consumption with reasonable accuracy for communication.

14. Attitude Control System
It is the scientific mission of the Satellite to prove that PMACS is
a robust and cost effective solution for attitude control.
To evaluate the attitude behavior of the satellite in the orbit, the
space conditions and dynamic behavior of the satellite have been
simulated through a self developed software.
From the simulation results it has been observed that, the
stabilization of the satellite to the prescribed orientation i.e.
antenna along Earth’s magnetic field, takes around 15 to 20 days.

15. Communication
Spacecraft
Ground station segment

16. Communication Spacecraft The subsystem consists of:
Amplifiers: Low noise amplifier (LNA) & High Power
Amplifier (HPA) to amplify the received signal and the
output signal respectively.
Antenna: A dipole antenna
Transceiver: ‘Texas Instruments' CC1120 RF Transceiver
Terminal node controller: Microchip’s PIC
microcontroller, which is interfaced with the
Transceiver.

17. Ground station segment
COEP Ground Station Antennas

18. CSAT Ground Station

19. Communication Ground station segment
The team has established a fully functional Ground Station in the
premises with uplink and downlink capability in both the
435 MHz as well as the 145 MHz bands.
The team has successfully received signals from various analog
and digital satellites and the data has been verified from the
respective satellite teams.
The Ground Segment includes an array of 2 crossed Yagi
antennas for the  MHz band and a simple Yagi Uda and
Potato Masher antenna for the  MHz range.

20. Onboard computer

21. Onboard computer
The onboard computer (OC) subsystem is a fault tolerant
microcontroller (AT91SAM7x512 ) based system.
It is the second subsystem to start after power and plays a major role
in antenna deployment.
Over the course of the mission, OC collects crucial data about the
health of the various systems within the satellite and stores it in a
non-volatile memory, only to be sent to the ground station on
request.

22. Onboard computer
It also manages the payload of point to point communication
by storing and sending messages appropriately.
The major role of OC relies in handling the set of commands
received from the ground stations through the Communication
system.
OC is the master control system of the satellite.

23. Power

24. Power
The Power Subsystem is completely analog in nature and also fully
autonomous in its functioning, being the first subsystem to start up
after the launch.
It provides power to all the electrical systems on board the satellite
and protects them from electrical faults. 
DC-DC converters are used for conditioning and regulation of
power.

25. Power Load protection circuits are designed for triple redundancy and
work in coordination with On-board Computer and Terminal
Node Controller.
The Power system is responsible for the deployment of the
antenna for the communication system through a surge of
current.
Li-ion batteries are used for energy storage. On-board voltage,
current and temperature sensors monitor electrical and thermal
status of the satellite and provide a critical part of health
monitoring data (HMD).

26. Structure
The structure subsystem is responsible for providing a robust body for
the satellite which can house all the components and protect them from
the harsh conditions of space.
 Comparative studies of different materials revealed that Al
6061-T6 is better suited & used for the main frame of the satellite.
Other materials like ABS, FR4 have also been used as per the
specific requirements.
All these materials were first tested for their properties before
being put into use.
The main structure of the satellite consists of four rails and two frames.

27. Structure
Vibration Analysis: Simulations have been run and validated by
performing tests on both the qualification and flight models to
sustain vibrations during launch.
Thermal Management and Control: Temperature of the satellite has
to be maintained within a particular range in order to ensure
proper functioning.
A passive thermal system has been employed in Swayam.
Insulating materials like Kapton, white paint, low emittance tape,
black tape and Optical solar reflector are used.

28. Flight Model
Swayam Flight and Qualification Model[

29. Flight Model
Onlookers look at sattelites being launched from Satish Dhawan Space Centre at Sriharikota. (Source: PTI)

30. References Engineering, Pune.
 CSAT, Swayam. "COEP Satellite Initiative". CSAT. College of
Engineering, Pune.
Mission Swayam, Official Website. "Mission Swayam“. Official
Website. Team Swayam, COEP. Retrieved 10 January 2016.
Press Information Bureau, Department of Space. "Launch of
Satellites Designed by Students". Press Information Bureau Govt. of
India. Retrieved 2 December 2015.
"PSLV-C34 Brochure". ISRO. Retrieved 21 June 2016.
"ISRO to launch 20 satellites tomorrow". The Hindu  
ISSN  X. Retrieved 
External link
Mission Swayam | A COEP Students' Initiative – Official web site
COEP's Swayam |

31. This presentation is Space Technology OER Submission for FDP on
“Use of ICT for Online and Blended Learning”
Under –RC-1101 – 06-Team members submission
PPT Slide template credit : PPTTemplate.net