A student satellite initiative Indian Institute of Technology Madras.
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Transcript of A student satellite initiative Indian Institute of Technology Madras.
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.
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
12
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
13
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)
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 : 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
Trapped Particle Motion
18th June 2010, ISAC Space Astronomy Group
Three kinds of motion:•Gyration•Bouncing•Longitudinal Drift
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
26iitmsat 19th March 2010
Scientific Community
Improvements in various
fields of research
• Geophysical• Ionospheric • Magnetospheric
Part 1: IntroductionPositive Impact