SATELLITE-BASED SPACE SCIENCE IN INDIASATELLITE-BASED SPACE SCIENCE IN INDIA

George JosephINDIAN SPACE RESEARCH ORGANISATION

George JosephINDIAN SPACE RESEARCH ORGANISATION

SPACE SCIENCESSPACE SCIENCES

• GROUND TELESCOPES

• BALLOON FACILITY

• SOUNDING ROCKETS

• SATELLITES

• ASTRONOMY AND ASTROPHYSICS• PLANETARY ATMOSPHERES AND

AERONOMY• EARTH SCIENCES AND SOLAR SYSTEM

STUDIES

PROGRAMMES:• IGBP• IMAP• ISTEP• INDOEX

Giant Meter wave Radio Telescope (GMRT) of National Center for Radio Astrophysics of TIFR in India

• GMRT IS WORLD’S LARGEST AREA RADIO TELESCOPE AT METER WAVELENGTH IE. IN THE FREQUENCY RANGE OF 100 MHZ TO 1400 MHZ.

• CONSISTS OF 30 PARABOLIC SHAPE ANTENNAS EACH WITH A DIAMETER OF 45 METERS.

• THE ANTENNAS LOCATED AS A Y-SHAPE ARRAY IN A REGION WITH SIZE OF 25 KM. IT IS AN APERTURE SYNTHESIS TELESCOPE WITH CAPABILITY OF OBSERVING IN THE FREQUENCY BANDS AT 150, 235, 327, 610 AND 1420 MHZ.

• IT HAS SENSITIVITY OF 0.10 MJy AT 1420 MHZ IN HOUR OF INTEGRATION.

• IN APERTURE SYNTHESIS MODE IT HAS BEAM SIZE OF 2 ARC SEC AT 1420 MHZ.

• POWERFUL INSTRUMENT FOR STUDIES OF RADIO PULSARS, SNRS , RADIO GALAXIES ETC.

Close up View of a 45 meter size parabolic antenna of GMRT. Several other

similar antennas of the central array are visible in the foreground.

Radio Image of the Supernova Remnant G11.2 – 0.3 from 610 MHz observations with the GMRT

Homi Bhabha

National Balloon Facility of TIFR-ISRO at Hyderabad, IndiaNational Balloon Facility of TIFR-ISRO at Hyderabad, India

BALLOON FACILITY PROVIDES :BALLOON DESIGN AND FABRICATION OF BALLOONS WITH A VOLUME OF UP TO 27MILLION CUBIC FEET . CAPABLE OF TAKING 600 TO1000 KG PAYLOAD TO ALTITUDE IN THE RANGE OF ABOUT 38 TO 41 KM.

BF LAUNCHED MORE THAN 450 BALLOON FLIGHTS SO FAR FOR COSMIC RAYS, X-RAY ASTRONOMY , GAMMA-RAY ASTRONOMY , INFRARED ASTRONOMY , ATMOSPHERIC SCIENCE AND OTHER AREAS OF RESEARCH.

HIGHEST ALTITUDE ATTAINED 41.5 KM FOR X-RAY ASTRONOMY PAYLOADS.

HEAVIEST LAUNCHED PAYLOAD IN 1 METER APERTURE FAR-INFRARED ASTRONOMY TELESCOPE WEIGHING ABOUT 1000 KG.

BALLOON MATERIAL, LOAD TAPES ETC. ALL MADE IN INDIA.

PROVIDES TELEMETRY AND TELECOMMAND PACKAGES TO THE EXPERIMENTERS. S-BAND USED FOR THE UP AND DOWN LINKS.

Hard X-ray detector:

balloon payload

Filled Balloon getting ready for launch

Launch truck with a payload suspended from the load line.

SOUNDING ROCKETSISRO has a range of Sounding Rockets known as Rohini Sounding Rockets for conducting scientific investigations. The sounding rocket launch services are available to others for flying scientific payloads.

Satellites 

  Early satellites 

ARYABHATTA ( 360 kg )  ROHINI ( 40 kg )  Stretched ROHINI Series ( 150 kg )  BHASKARA I & II ( Remote Sensing )  APPLE ( Communication ) 

Indian Remote Sensing Satellites ( IRS; Polar) 

Indian National Satellites (INSAT; Geosynchronous )

X-ray Astronomy studies began in India using balloons from Hyderabad and later with rockets from Thumba.

The experiments mainly aimed at temporal and spectral measurements of bright X-ray Binaries.

Balloon Experiments are still conducted to evaluate the performance of new detector systems for the future satellite missions and study selected X-ray binaries.

Evolution of X-ray Astronomy in IndiaEvolution of X-ray Astronomy in India

Gamma ray Burst expt. on SROSS (1994)

IRS -P3Satellite

•Area 1200 sqcm.

– 2-18 keV;

– FOV 2.3 °X 2.3°

Scientific objectives:• Pointed mode observations (first from Indian

satellite) of periodic and aperiodic intensity variations of galactic X-ray sources .

• Detailed timing studies to measure pulse and orbital periods of x-ray binaries to understand accretion process.

• Search for long term variabilities in extragalactic sources

• Indigenous gas multi-layer gas filled proportional counters with slat collimator

IXAE on IRS-P3 (1996) Indian X-ray astronomy experiment (IXAE) (TIFR+ISAC)

Gas Proportional Counters

IXAE on IRS-P3 (1996)

X-ray light curve from GRS 1915+105

• ASTROSAT

A multiwavelength astronomical observatory

• CHANDRAYAAN-1

India’s first mission to the Moon

These will be the first dedicated science missions of the Indian Space Research Organization (ISRO)

• ASTROSAT

A multiwavelength astronomical observatory

• CHANDRAYAAN-1

India’s first mission to the Moon

These will be the first dedicated science missions of the Indian Space Research Organization (ISRO)

Two recent initiatives in Space ScienceTwo recent initiatives in Space Science

ASTROSAT : A Broad Spectral Band Indian Astronomy Satellite

An Indian National Space Observatory

A Collaborative Project of Tata Institute of Fundamental Research (TIFR), Mumbai

ISRO Satellite Centre (ISAC), Bangalore

Indian Institute of Astrophysics (IIA), Bangalore

Inter-University Centre for Astronomy & Astrophysics, Pune.

Raman Research Institute, Bangalore

Physical Research Laboratory, Ahmedabad

Canadian Space Agency

With participation of

Bhabha Atomic Research Center,Mumbai

Aryabhatta Research Institute of Observational Science,Nainital

Center for Space Research,Kolkata

& Many Indian Universities

                                                                           

Galaxy M81 as seen in the Ultraviolet light. Spiral structure of the Galaxy is traced by Young Hot stars.

Image of M81 in the Visible Light

                 

                                             

The High Energy Crab Nebula

Astrosat Instruments Four X-ray Astronomy Instruments and one Ultraviolet Instrument

With two Telescopes  

1. LAXPC : Large Area X-ray Proportional Counters with Aeff ≈ 6000

cm2 at 20 keV, FOV =10 X 10, sensitive in 3-80 keV band with low

spectral resolution (E/ΔE ≈ 5 to 12) . 2. CZT Imager : A new generation X-ray detector CdZnTe (Cadmium-Zinc-Telluride) array with a coded mask aperture having Aeff = 500 cm2 and medium spectral resolution (E/ΔE ≈ 20 to 30). 3. SXT : Soft X-ray Imaging Telescope using conical-foil mirrors with medium angular (~3' ) and spectral (E/ΔE ≈ 20 to 50) resolution in 0.3-8 keV with A eff ≈ 200 cm2 at 1 keV.

4. SSM : Scanning Sky Monitor (SSM) using 3 PSPCs with coded mask aperture , each with Aeff = 30 cm2 and energy band

of 2-20 keV.   5. UVIT : Ultraviolet Imaging Telescope (UVIT) has two similar telescopes each with 38 cm aperture primary mirror and photon counting imaging detectors covering simultaneously near-uv , far-uv and visible bands. A Charged Particle Monitor (CPM) as an auxiliary instrument for the control and operation of the Astrosat Instruments. 

Schematic View of aLAXPC

Parts of LAXPC

• Detector with Xenon at 2 to 3 atmosphere • WSC with 5 deg X 5 deg FOV • Main FOV Collimator with 1 deg X 1 deg FOV • Front-end Electronics and HV unit in the back plate of each LAXPC

LAXPC with Field of View Collimator installed for Balloon Experiment

CZT Imager

Energy Range 10 – 100 keV

Resolution = 5% @ 60 keV

Effective area ~ 1000 cm2

Energy Range: 0.3 – 8.0 keV

Effective Area: 200 cm2 @1.5 keV

20 cm2 @6.5 keV

Telescope: 2.0m focal length

Telescope Mirrors: Conical shells

Telescope PSF: <3 - 4 arcmin (HEW)

Detector: MAT CCD-22 (Cooled < -80 deg C)

Detector Format: 600 x 600 pixels

Detector Readout Modes: Photon counting, Imaging & Timing

Field of view: 41.3 x 41.3 arcmin

Pixel Scale: 4.13 arcsec/pixel

Sensitivity: 1.4 cps/milliCrab

Position Accuracy: 30 arcsecs

Scanning X-ray Telescope (SXT)X-ray Telescope (grazing incidence)+ X-ray CCD camera

POSITION SENSITIVE PROPORTIONAL COUNTER

Scanning Sky Monitor (SSM)Energy range: 2-10 keV; Field of view: 6°x 90° (FWHM)Source location capability 8-12' depending on intensity of the transient.Sensitivity 30 mCrab in 5 min integration

Coded mask : minimum slit size 0.95mm

No. of sky monitors: 3 )Event rate: nominal 200c/s; max 5000c/s;

Position resolution: 1.5mm FWHM along the wire

Two similar coaligned telescopes

Primary Mirror aperture : 38 cms

Secondary : 14 cms

Focal length : 503 cms

f/ratio : 13

Configuration : RC with focal plane

corrector

Corrected field : 0°.5

Passband Channel l : 120-180 nm

Channel I : 180 – 300 nm

Optical : 350-650 nm

Astrosat Mission Characteristics • Mission life of at least 5 years. Circular orbit of 600 km altitude and inclination of ≈8°. Orbital period of 100 minutes.

• Launch by well proven Indian Polar Satellite Launch Vehicle (PSLV) from Satish Dhawan Launch Center at Shriharikota (India).

• Mass of satellite 1608 kg including 868 kg mass of science payloads.

• Total Power generation = 1250 Watts , Payload Power needed is 488 Watts.

• Large number of On/Off, Data Commands and Time-tagged commands available for the control and operation of the Science Instruments .

• Data transmission by two X-band carriers at a rate of 105 Mbits per sec.

• A Charged Particle Monitor to control the operation of the instruments in zones of high fluxes of particles.

ASTROSAT

INDIAN MISSION TO MOONCHANDRAYAAN-1

• PROGRAMME INITIATED BY DR K. KASTURIRANGAN, CHAIRMAN, ISRO.

• HALF-DAY SYMPOSIUM ON INDIAN MISSION TO MOON AT 65TH ANNUAL MEET OF INDIAN ACADEMY OF SCIENCES AT LUCKNOW, OCTOBER, 1999.

• SYMPOSIUM OF THE ASTRONAUTICAL SOCIETY OF INDIA AT AHMEDABAD, FEBRUARY, 2000.

• CHAIRMAN, ISRO CONSTITUTED IN OCTOBER, 2000, A NATIONAL TASK FORCE TO STUDY VARIOUS ASPECTS TO REALISE A MISSION TO MOON.

Chandrayaan-1 payloads

* International + Joint

Terrain Mapping Camera Imaging (visible) 5 m res.Hyper-spectral Imager 32-band spectra (visible)Lunar Laser Ranging Instr. Topography (Nd-YAG)High-energy X-ray Spectrometer Volatile transport (radioactivity)Low-energy X-ray Spectrometer Chemical mapping (fluorescence)Mini SAR * 2.5 GHz (search for water-ice)Radiation Monitor * Dosimetry, spectrumIR Spectrometer * Composition (line scanner)Sub-keV Atom Reflecting Analyser *+

Neutrals; magnetic anomalies

Simultaneous Mineralogical, Chemical &

To map the South Pole Aitken region (ejecta and basin surface) for elements Mg, Fe, (Mg#) and Ca etc. to verify crustal evolution models.

To detect any 222Rn (16.7 KeV) leaking from the lunar interior

To detect any 210Pb (46.5 KeV) depositing at polar or cold regions due to transport and decay of radon

To improve upon the gravity models of the Moon

Objectives of the First Moon Mission & selected experiments

Photogeological mapping

Chandrayaan -I

Chemical Mapping

Apollo15 & 16 used proportional counters having low resolution, could not distinguish nearby elements. Better sensors e.g. CCDs and Swept Charge Devices can measure Mg, Al, Si, Ca, Ti & Fe accurately.

Radiation Environment of Moon

210Pb, 210Po Paint

222Rn diffusion

The best technique for Chemical Mapping is X-ray fluorescence.

Mineral Mapping The best method for mineral studies is Imaging Spectroscopyi.e. Hyper Spectral Imaging.

Clementine (1994) has provided lunar mineral maps using amultispectral camera with a resolution of 120m and discrete spectral bands (450, 750, 900, 950, 1000 nm)

Mineral Reflectance Spectra

Chandrayaan -I

Topographic Mapping

ORBITER-4 & 5 photographed the entire lunar surface ata spatial resolution of 50 – 100 meters

Terrain Mapping Camera (TMC) is designed to have 5m

spatial resolution and will cover the whole moon in 6 months.

Height resolution of 5m can be achieved and we may getbetter Digital Elevation Map of the whole Moon.

Chandrayaan -I

Imaging with 3 Cameras eliminates occlusion produced by oblique view .Complete 3D coverage even for highly undulating terrains

What is new about the proposed mission?

210Pb mapping of the lunar surface, particularly at the lunar poles and degassing and transport of volatiles on the lunar surface can be understood

First attempt to study the energy region of 10-200 keV(X- ray region)

Better Spatial resolution (10 – 20 Km)

High resolution X-ray (CCD & CZT) sensors forchemical mapping

Terrain Mapping Camera for 5m spatial resolution

Population of small meteorites and better DEM

CHANDRAYAAN-1Terrain Mapping Camera – TMC

Ground Resolution : 5 M (from 100Km orbit)

Swath : 20 KM

Optics : Refractive Optics with mirror

Dimension : 415 x 240 x 160 (EO Module)

Mass : 6.0 Kg

Power : 13 watts

Field of view : ± 25.02º (along track)

± 5.7 º (across track)

TMC consists of Two units

EO module & Pay load electronics

Imaging with 3 Cameras eliminates occlusion produced by oblique view

CHANDRAYAAN-1

Hyper Spectral Imager - HySI-VNIR

Ground Resolution : 80 M (from 100Km orbit)

Swath : 20 KM

Spectral range : 0.4-0.93 µm

Optics : Refractive Optics

Dimension (in mm) : 207 x 175 x 150 (EO Module)

Mass : 3.1 Kg

Power : 16 watts

Field of view : ± 13º

HySI VNIR consists of Two units

EO module & Pay load electronics

Objective

X1

Xn

X1Xn

Flight Direction

Spectral Dimension ()

Wedge Filter

Detection Array Area

CHANDRAYAAN-1

Lunar Laser Ranging Instrument – LLRI

Vertical Resolution : < 5M (from 100Km orbit)

Laser Wave Length : 1064 nm

Laser Energy : 20 – 50 mJ

Optics

Transmitter : 38mm Gallilean telescope

Receiver : reflective 170mm

Dimension (in mm) : 350 x 350 x 240 (EO Module)

Mass : < 10 Kg

Power : < 15 w

LLRI consists of Two units

EO module & Electronics module

CHANDRAYAAN-1HIGH ENERGY X-RAY PAYLOAD – HEX

SPACIAL RESOLUTION 20 – 40 KM

ENERGY RANGE : 20 – 250 KeV

Dimension (in mm) : 180 x 145 x 194

(EO Module)

Mass : 15Kg

Power : 24.2 w

HEX consists of Two units

EO module & HEX DIP (235x210x120)

CHANDRAYAAN-1

Swath : 20 Km @ 100 Km Orbit Energy Range : 0.5 – 10 KeV

Dimension (in mm) : 185 x 112 x 140

(EO Module)

Mass : 5.2Kg

Power : 28 w

CIXS consists of Two units

CIXS & XSM

Low Energy X-ray Spectro Meter (CIXS & XSM)– ( LEX )

CHANDRAYAAN-1

Resolution : 100 m / pixel

: 10 m / pixel in a spot light / low altitude

Swath : 40km(Range)

: 8km(azimuth)

Frequency : 2.5 GHz

Antenna Dimension : 600mm x 1800mm

Mass : < 7.0Kg

Power : average 50 w

Mini Sar consists of Two units

Antenna & Radar Electronics

MINIATURE IMAGING RADAR INSTRUMENT-MINI SAR

Dr. PAUL SPUDISJHU/APL11100 John Hopkins Road Laurel MD USA

AO

CHANDRAYAAN-1

Moon Minerology Mapper – M3

Wave length range : 0.7 – 3.0 µm

Swath : 20 km @100km orbit

Special resolution : 30 m / pixel

Dimension (in mm) : 275 x 235 x 140

Mass : 5.5 Kg

Power : 8.3 watts

º

Dr. Carle M PietersBrown University,Providence, RI

CHANDRAYAAN-1

SIR-2

Type of Instrument : Grating NIR point spectro meter

Wave length range : 0.93 - 2.4 µm

Angular resolution :

Optics : 72 mm aperture;180mm focal length

Dimension (in mm) : 260 x 171 x 143 (EO Module)

146 x 125 x 33.5 (E-box)

Mass : 2.3 Kg

Power : 2.2 watts

SIR-2 consists of Two unitInstrument & E-boxDr. U. Mall et. alMax Planck Institute for Aeronomie LindauGermany

AO

CHANDRAYAAN-1

Sub Kev Atom Reflecting Analyzer– ( SARA )

SARA consists of Three units

LENA, SWIM & DPU

Energy Range : 10 eV– 2 KeV LENA : 10 eV– 15 KeV SWIM

Dimension (in mm) : 180 x 145 x 194

FOV : 15º x 160º LENA

: 9º x 180º SWIM

Mass : 3.5Kg(total)Power : 3.0 w (total)Dr. S. BarabashSwedish Institute of SpacePhysicsKiruna, Sweden

Dr. Anil BhardwajSPL, VSSCTrivandrum

AO

CHANDRAYAAN-1

Dimension (in mm) : 76 x 80 x 25 Mass : 0.16 Kg(total)

Dr. Tsvetan DachevSolar Terrestrial InfluencesLaboratoryBulgarian Academy of SciencesSofiaBulgaria

Radiation DOse Monitor – ( RADOM )

AO

CHANDRAYAN-1

SIR-2 (Infrared Spectrometer)

(Hyper Spectral Imager) HySI

(Low Energy X-ray) CIXS

MINI-SAR

(Solar Wind Monitor) SWIM

LLRI (Lunar Laser Ranging Instrument)

(High Energy X-ray) HEX

IMPACT PROBERADOM (Radiation dose monitor)

(Chandrayaan Energetic

Neutral Analyzer) CENA

PAYLOAD ACCOMMODATION

TMC (Terrain Mapping Camera)

M3

(Moon Mineralogy Mapper)

(Miniature Synthetic Aperture Radar)

(chandayana Imaging X-ray Spectrometer)

GTO: 240 X 36,000

ETO: 240 X 1,00,000 km

LTT: 240 X

3,86,000 KmMCC

MCC

LOI

PERIGEE MANEUVERS

Chandrayaan-1 Mission Phase

PROGRESS OF MOON IN ITS ORBIT

SUN

OPL. ORBIT

CAPTURE ORBIT

LAUNCH VEHICLESLAUNCH VEHICLES

POLAR SATELLITE LAUNCH VEHICLE ( PSLV ) 1 – 1.5 ton satellite into polar orbit

       ~ 3 ton satellite into near-earth inclined orbit

       ~ 1 ton satellite in geosynchronous transfer orbit (GTO)   

GEOSYNCHRONOUS LAUNCH VEHICLE (GSLV) 

      ~ 2.2 ton satellite into a GTO

  ~ 5 ton satellite in a near-earth inclined orbit

~ 4.5 ton satellite in GTO (GSLV MARK-III)