A student satellite initiativeIndian Institute of Technology Madras

iitmsat

Part 1: The Mission The goals and objectives

Part 2: History What we have done so far?

Part 3: The SatelliteThe conceptual design of the satellite

Part 4: Future What we plan to do next.

Part 1: Mission

Mission Objectives

Primary Objectives

Design, fabricate, test and launch a small-satellite

Build a ground station for collection of data

Measure the energy spectrum of protons and electrons in the upper atmosphere

Investigate the possibility of creation of a small-satellite based earthquake prediction system

Part 1: Mission

Mission Objectives

Secondary Objectives

• learn basics of design, manufacture, system engineering and space technology through building a small satellite

Education

• Inspire young scientists and engineers to take up challenging tasks and work towards it collectively

Motivation

• Increase participation of IIT Madras in space research and technology development

University participation in space research

Part 1: Mission

6iitmsat 19th March 2010

Mis

sion

Opti

ons

Pure technology demonstration

Space-craft component innovation

Scientific Experiments

Earth Related

Magnetic/ Electric Field Measurement

Radiation (EM & Particle) Measurement

Astronomy Related

Micro-gravity experiments

Service based

Remote sensing

Determining earth quake epicenters

Mapping ocean currents

Communication

GPS Doppler Navigation

Particle Detector(HEPD)

Part 1 : MissionPayload Selection

Pressure buildup• SEME

waves generated

ULF/ELF seep through the ground

They travel as Alfven waves after ionosphere

Interact resonantly with trapped particles in the radiation belt

Precipitate charged particles

A Scientific Quest

Before an Earthquake

A series of events occur :

Part 1 : Mission

References:

Sgrigna, V. (2005). Correlations between earthquakes and anomalous particle bursts from SAMPEX/PET satellite observations. Journal of Atmospheric and Solar-Terrestrial Physics 67, 1448-1462.

Alexandrin, S. (2009). Observation of solar-magnetospheric and geophysical effects on the electron and proton fluxes detected by the satellite-borne ARINA experiment. Izvestiya Akademii Nauk. Serriya Fizicheskaya Vol 73, 379-381

Ionosphere interaction region

Inner Van- Allen Belt Boundary

Trap

ped

Parti

cles

Magnetic field lines

Part 2 : Mission

Not to Scale

SeismicActivity

Capture region

ULF waves as Alfven Waves

Not to Scale

Lowering of mirror points

300km 900 km

Not to Scale

Part 2: History

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Winter Excursion (Dec ‘09)

Project 1:Modification in design, and fabrication of the casing of the Cadmium Zinc Telluride Imager, which will be flown on ASTROSAT.

Project 2:Tracing the circuit of KETEK VITUS Pre-amplifier used with the Silicon Drift Detector.

Project 3:

Preliminary development of ground software for analysis of data from the CZT Imager.

Project 4:

Modification of on board software to compress data from the CZT before transmission.

Modification in the casing of CZT in TIFR

The pre-amplifier for SDD (Detector) in PRL

Part 3 : History

Goal• Gain some understanding of current space-

experiments and satellite payloads

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Pre Engineering ModelIC&SR innovative students project

Goals :Use as playground for experimentationGain practical experienceRecognize team strengths

Part 3 : History

• Design Detector Configuration

• and electronics

Preliminary Detector Design

• Power• Size• Mass• Data rate/ storage

Give detector requirements

• Basis for overall configuration of the satellite

Mission requirements

High Energy Particle Detector Configuration

31 mm

19 mm

Plastic Scintillator BC-404

CsI (Tl)

Si (300 μm)

Photodiode

Photodiode Detector Specifications

Energy Bin Resolution 1 MeVEnergy Range Protons: 7 MeV to 100 MeV

Electrons: 1 MeV to 15 MeV Geometric Area 30 mm x 30 mmActive Detector Volume 30 x 30 x 51.3 mmMass

2.2 Kg

Shielding 2 cm thick Aluminum shieldPower (Max. Consumption) 2 WData (Peak Data Rate) 2 Mbytes/ orbit (1 orbit = 100 min)

Part 3 : HistorySummer in ISAC (Apr ‘10)

Part 3: Satellite

Overall configuration of the satellite

Proposed configuration of the satellite. (Picture of the Pro-E model made by the student team)

Over-all Satellite Specifications

Dimensions 20 x 20 x 24 cm3

Mass 10 kg

Average power consumption

6 W

Attitude stabilization type

3-axis stabilized

Payload High Energy Charged Particle Detector

Mission Specifications

Orbit Low Earth Orbit

Altitude 600-800 km

Inclination 10-100 degrees

Mission Life-time > 1 year

Part 3 : Satellite

Part 4:Future

Part 4 : FutureTimeline

Part 4 : FutureLooking ahead… (Post Launch)

IIT Madras Space Centre

Continue collection and study of data from existing missions

Nurturing future missions (payloads, rovers, new technology)

Participation from all departments inside IIT Madras

20

Thank you.

Trapped Particle Motion

18th June 2010, ISAC Space Astronomy Group

Three kinds of motion:•Gyration•Bouncing•Longitudinal Drift

Part 2 : Mission

Locating the Latitude of the Epicenter

18th June 2010, ISAC Space Astronomy Group

Part 2 : Mission

Locating the Longitude of the Epicenter

18th June 2010, ISAC Space Astronomy Group

Longer drift life for:Electrons > 5 MeVProtons > 50 MeV

Part 2 : Mission

The project’s Vision

A student initiative to

DesignBuild

Operationalize

a small satellite (~10 kg)

Mission:Scientific experiment involving High Energy Particle Detection for studying ionospheric

earthquake precursors.

Part 1: Mission

University space programs

Inspiring young minds

Develop Human Resource for ISRO

Strengthen Institutional partnership

New science and technology for ISRO

Part 1: IntroductionPositive Impact

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Scientific Community

Improvements in various

fields of research

• Geophysical• Ionospheric • Magnetospheric

Part 1: IntroductionPositive Impact

Part 2:The Mission

Video of lightning storms causing

particle precipitation.

Part 2 : Mission