India in Space v2vahia/IiS.pdf · 15/03/2005 India in Space 5 How to go to space and what to do...
Transcript of India in Space v2vahia/IiS.pdf · 15/03/2005 India in Space 5 How to go to space and what to do...
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India in Space
Mayank N VahiaTata Institute of Fundamental ResearchHomi Bhabha Road, Mumbai 400 005, INDIA
Special thanks to Dr. S Rangarajan for the visuals
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Why go to Space
• Long duration observation of earth
• Communication• Defence• Astronomy
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Is it easy to go to space?
NO• It costs 1000 Rs per gram of weight put in space – so
weight is limited• It must fit in a rocket so volume is limited• It must rely on Solar cells so power is limited• Launch itself is very violent• It takes the Sun directly so it gets heated• It faces intense radiation environment• Satellite cannot be repaired.Yet, a good satellite is an enormously powerful tool.
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How to go to space and what to do
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India launched its First Rocket on 21st November 1963 from Thumba.It was a ‘sounding rocket’ that took its payload to a little more than 100 km.
Our first satellite Aryabhatta was launched from Kapustin Yar in Russia on 9 May 1975 in a 398 km x 409 km 50.7° orbit. It weighed 360 kg. It re-entered the earth after 1 year.
Our first successful indigenously launched satellite was Rohini – 1B on a rocket called Satellite Launch Vehicle – 3.
The 35 kg satellite was launched on 18 July 1980 from Sriharikota in the 305x919km, 44.7°. It weighed 35 kg. It re-entered earth on 20 May 1981.This experimental satellite followed the failure of the Rohini-1A on 10 August 1979. THUMBA
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Motion of RocketMotion of Rocket
Using the principle of momentum we can calculate velocity of the rocket
as ∆∆∆∆V= Veln (Mo/M)
Mo
M=Mo-m
Ve
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LAUNCH VEHICLE FAMILY� ������������� ���� ������������� ��������� ������ ������������������� ������������ �������������� ��������������������������������� ��������������
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Polar Satellite Launch Vehicle
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The PSLV's Launch Sequence������������ ��� �������������� �� �������� ���� �� �� ��������������� ��� ����������������������� ��� ���������������������� ���� �������������� ���
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The Satellite Launch Vehicles
GSLV PSLVOverall length 49 m 42.2 mLift-off weight 401 t 283 t No. of stages 3 4Payload GSAT (~ 1500 kg) IRS (1000 kg)Orbit (GTO) 180 x 36,000 km 800 km
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DESIGN OF ORBITSDESIGN OF ORBITS
Equatorial Orbit
Inclined Orbit
Polar Orbit
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GSLV Orbit
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INSAT FAMILYINSAT FAMILYAPPLE
•SPIN STABILISED•1 TRANSPONDER
INSAT-1•3-AXIS STABILISED
• 12C, 2S•32 dbw (1 kw)
INSAT-2•3-AXIS STABILISED
• 12C, 6-ExtC,2S, MSS, Ku•36 dbw (1.5 kw)
INSAT-2E•3-AXIS STABILISED
• 17C, GLOBAL•36 dbw (2.5 kw)
INSAT-1
INSAT-2A,BINSAT-2C,D
INSAT-2E
INSAT-3B
INSAT-3C
INSAT-3D
INSAT-3E
DTH
APPLE
GSAT-2
INSAT-3A
INSAT- 3B•3-AXIS STABILISED
• 17C,2S,MSS,Ku, GLOBAL•36 dbw (2.5 kw)
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Typical reach of a satellite
Pointing accuracy required
Alt Vel Resolution Stability
36,000 km 3.1 km/s 2,000 km 3 deg
800 km 7.9 km/s 6 m 1.5 sec
36,0000 km
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� TELEPHONES
� TELEVISION
� BUSINESS COMMUNICATIONS
� MOBILE SATELLITE SERVICES
� GLOBAL POSITIONING SYSTEMS
� SEARCH AND RESCUE SERVICE
� WEATHER FORCASTING
� DISASTER WARNING SYSTEM
GEOSTATIONARY SATELLITE APPLICATIONS
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Indian Remote Sensing Satellite orbit
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Line Array
DetectorOptics
Space craft
motion
Contiguous
scan lines
across scene
Area by area
BHASKARA TVCAMERA
Pixel by pixelOptomechanical scanner
INSAT-VHRR
Line by LinePush broom scanning
IRS-LISS
• Lower dwell time• Geometric distortion• Lower reliability due to
Oscillating mirror
• Large dwell time• High geometric fidelity• High reliability due to
non-moving parts
Orbit
Ground
resolution
element
Ground
coverage
IMAGING SENSORS - TYPES OF SCANNING
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CARTOSAT CARTOSAT -- 11PAN PAN -- 2.5M, 30 KM, 2.5M, 30 KM,
F/AF/A
RESOURCESATRESOURCESAT--11LISS3 LISS3 -- 23 M; 4 XS23 M; 4 XSLISS4 LISS4 -- 5.8 M; 35.8 M; 3--XSXSAWIFS AWIFS -- 70 M; 470 M; 4--XSXS
CARTOSATCARTOSAT--22PAN PAN -- 1M 1M
MEGHAMEGHA--TROPIQUES TROPIQUES SAPHIR SAPHIR
SCARAB & SCARAB & MADRASMADRAS
20012001
20022002
20032003
20052005
IRS-1C/1D LISS-3 (23/70M,STEERABLE PAN (5.8 M);
WiFS (188M)
INSAT-2E CCD
(1KM RESOLUTION;
EVERY 30 MINUTES)
INDIAN IMAGING SATELLITE SERIES
INDIAN IMAGING SATELLITE SERIES
19991999
IRS-P2 LISS-2
IRS-P3 (1996)WiFS MOS X-Ray,
IRS-P4 OCEANSAT OCM, MSMR
IRS-1A & 1B LISS-1&2 (72/36M,4 BANDS; VIS & NIR)
BHASKARA
RS-D1
19791979
19821982
1988/911988/91
1994199419961996
1995/19971995/1997
19991999
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REMOTE SENSING SATELLITE APPLICATIONS
WATER RESOURCE INFORMATION AND MANAGEMENT:
•Vegetation, cultivated and forest
•Land
•water
•climate
• GEOLOGY AND MAPPING
• OCEANOGRAPHY
• RURAL AND URBAN DEVELOPMENT
• DISASTER MANAGEMENT
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The data shown is of 5m resolution It is a merged product of PAN and LISS–III
Path 94 Row 59 acquired on 17Apr 2000
Mumbai as seen from IRS-1D
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PRINCIPLES OF REMOTE SENSING
0.4 0.8 1.2 1.6 2.0 2.4
REFLECTANCE
(%)
WAVELENGTH (µm)
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SILTY CLAY SOIL
MUCK SOIL
0
20
40
60
80
GREEN BAND (0.5-0.6 µm)
RED BAND (0.6-0.7 µm)
NEAR IR (0.7-0.9 µm)
TRUE COLOR COMPOSITE
BLUE BAND (0.4-0.5 µm)
FALSE COLOR COMPOSITE
1- SAND 2-VEGETATION 3-WATER
3
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REMOTE SENSING PERSPECTIVES
NATURAL SOURCE
ARTIFICIALSOURCE
BALLOON
•Energy source (Sun or transmitter)
•Transmission of energy from source to object
•Energy Interaction with object surface
•Transmission of energy to sensor
•Scattering, absorption by atmosphere
•Detection , Measurement and Output by sensor
•Data acquisition, recording, pre-processing and analysis/ interpretation
•Energy source (Sun or transmitter)
•Transmission of energy from source to object
•Energy Interaction with object surface
•Transmission of energy to sensor
•Scattering, absorption by atmosphere
•Detection , Measurement and Output by sensor
•Data acquisition, recording, pre-processing and analysis/ interpretation
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Atmospheric correction and Chlorophyll-a image from OCM data (Off Gujarat, February 27, 2000)
µW/cm2/sr/nm mg/m3
Band-3(uncorrected)
Band-3(corrected) Chlorophyll-a
Atmospherically correctedfor 490 nm Chlorophyll -a image
IRS-P4 OCM 490 nm data
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BASIC CONCEPT
SATELLITE ALTIMETRY FOR GRAVITY ANOMALY MODELING
FREE-AIR GRAVITY ANOMALY
SITE: BOMBAY HIGH
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The Indian sub continent is one among the world’s most
disaster prone areas
40 M ha flooding
68% Net sown area in 116 Dist
Sub-Himalayan/Western Ghats55% of area in Seismic Zone III-IV
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Satellites in Astronomy
Satellites have played a crucial role in astronomy because:
a) They give a view not contaminated by atmosphere
b) They can look at the same object for a long, long time.
c) They can be extremely stable
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SPACE SCIENCE - THE QUEST FOR KNOWLEDGE
�X-RAY ASTRONOMY
�GAMMA RAY BURSTS
�IONOSPHERIC PLASMA
�MIDDLE ATMOSPHERIC DYNAMICS
�EQUATORIAL ELECTROJET
�SOLAR FLARES AND STORMS
�IONOSPHERIC TOPOGRAPHY
�PLANETARY EXPLORATION
� ASTRONOMY AND ASTROPHYSICS
� AERONOMY AND PLANETARY ATMOSPHERES
� EARTH SCIENCES AND SOLAR SYSTEM STUDIES
� THEORETICAL PHYSICS
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Astronomy Satellite Missions By Indian Scientists
• Aryabhatta• Skaylab• GRB experiments on IRS satellites• Space Shuttle• Indian X-ray Astronomy Experiment• Solar X-ray Spectroscopy Experiment
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Future plans
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ASTROSAT
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Chandrayan 1
• 525 kg satellite
• 100 km orbit
• Possible Lander with 25 kg mass.
• 2 year orbit life time
• Launch in 2007 - 2008
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Scientific Objective:
Remote sensing of the moon in the visible, near infrared and X-ray for:
• Preparing 3-dimensional atlas of the moon with a resolution of 5-10 m
• Chemical mapping of lunar surface for Mg, Al, Si, Ca, Fe and Ti and heavy elements, such as 222Rn, U, Thand Gd.
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Scientific Instruments:
• Terrain Mapping Camera (TMC) with stereo imaging capability
• A Hyper-Spectral Imager (HySI) operating in 400-900 nm band
• A Lunar Laser Ranging Instrument (LLRI) with a height resolution of 10 m
• A Low Energy (1-10 keV) X-ray spectrometer.• A High Energy X-ray mapping camera (HEX)
As well as other payloads from India and abroad making a total of 11 packages.
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Mission Sequence:
• Launch into 240 km X 36000 km GTO by PSLV• Two consecutive in-plane perigee manuver to achieve
3,86,000 km apogee (Lunar Transfer Trajectory -LTT)• Coasting for 5 ½ days in LTT prior to lunar encounter• Lunar capture at peri-selene (nearest point in lunar orbit)• Satellite in near circular 1,000 km orbit of the moon• Solar panel deployment• In-plane corrections to reduce orbit height to 200 km,
polar• Study of orbit perturbations for 1-2 weeks• Reduce orbit altitude to 100 km circular, polar
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New Facilities:
• Deep Space Network located in Bangalore and Goldstone, California, USA.
• Supports spacecraft with 34 m diameter antenna with a power of 2 kW.
• Receiving spacecraft data with a transmitted power of 2 W.
• National Science Data Centre to process raw data.
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