The COEP Satellite project launched by ISRO This work is licensed under a Creative Commons Attribution-NonCommercial-ShareAlike 2.5 India License. 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 https://en.wikipedia.org/wiki/Swayam www.coep.org.in/csat

SWAYAM The COEP Satellite project launched by ISRO By Ujwala Bongale

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

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 500-800 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.

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 : 437.025 MHz Launch Date: Wednesday, June 22, 2016 Launch Vehicle: PSLV-C34 / Cartosat-2 series satellite Type of Satellite: Student Manufacturer: ISRO Owner: ISRO

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.

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 .

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

Timeline 22nd June 2016: Has been launched. June 2016 : Swayam shipped from ISAC to SHAR and integrated with PSLV. February 2015 : Flight Model successfully undergone Vibration and Thermo-Vacuum test at ISAC, Bangalore. Satellite handed over to ISRO . January 2015 :Flight Model assembly and bench level testing completed at ISAC, Bangalore. September 2014: Critical Design Review (CDR) successfully cleared at ISAC, Bangalore.

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.

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

Attitude Control System

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.

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.

Communication Spacecraft Ground station segment

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.

Ground station segment COEP Ground Station Antennas

CSAT Ground Station

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 434-438 MHz band and a simple Yagi Uda and Potato Masher antenna for the 144-148 MHz range.

Onboard computer

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.

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.

Power

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.

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).

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.

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.

Flight Model Swayam Flight and Qualification Model[

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

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. 2016-06-21.  ISSN 0971-751X. Retrieved 2016-06-21. External link Mission Swayam | A COEP Students' Initiative – Official web site COEP's Swayam |

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