Chandrayaan-1 Mission Colloquium at TIFR, Mumbai August 17, 2007 K Thyagarajan Prog. Dir, IRS/SSS ISRO Satellite Centre
When the media asked former chairman, ISRO
whether India can afford to send a craft to the Moon, he replied
“Can India afford not to go the Moon�
Outline of presentation
Why go to the Moon?
What’s known about Moon?
Chandrayaan-1 Mission objectives
Payloads in the Mission
Spacecraft configuration
Launch vehicle
Mission profile
Imaging strategy for lunar coverage
Deep Space Network (DSN)
Indian Space science data Center (ISSDC)
Why go to the Moon
The origin of Moon is still not clearly understood and there have been several speculations
Space programme for Lunar exploration was undertaken as early as 1959.
Several Lunar exploratory missions since then have been conducted
Interest in Lunar science was renewed when imaging systems onboard NASA’s “Galileo” spacecraft sent picture of the previously unexplored regions of the Moon during 1990
Galileo identified a large impact basin, about 2500km in diameter and 10 to 12 km deep in the south pole Aitken Region on the far side of the Moon
Why go to the Moon (Contd ..)
With the development of new technology, a new era of lunar exploration by many countries have now begun using advanced instruments and microelectronics
Apart from scientific interest, the Moon could have economic benefits to mankind and could be of strategic importance
The Moon’s surface has about one million tonnes of Helium-3
Moon contains 10 times more energy in Helium-3 than all the fossil fuels on Earth
Helium-3 is believed to be fuel of the future
Outpost for further planetary explorations and possible human settlements
What is known about Moon? Landing and Sample Return Missions A-13
Apollo 11-17 (13),
Luna 16, 20, 24 (1969-74) Orbiting Missions Clementine (1994) UVVIS, NIR, LWIR, LIDAR Mineral Mapping Lunar Prospector (1998) -ray, , Neutron Spectrometers, Magnetometer, Electron Reflectometer, Doppler Gravity Chemical Mapping, Water (?) SMART-1(2003) Mapping of geological and mineralogical resources (Res: 40m)
A-15 L-24 A-17 L20 A-11
A-14
L-16
A-12 A-16
Future Lunar missions
Chang’e-1 by China scheduled for late 2007
Selene by Japan scheduled for late 2007
Moon’s Topography, mineral content and gravity
LRO by USA scheduled in late 2008
3D map of Moon, Moon’s Soil composition & mineral distribution
Water-ice at poles, selection of soft-landing sites, etc
Russian Mission Scheduled for 2009
Understanding the origin and Evolution of the Moon The bulk chemistry of Moon
Physical Properties of the Moon
Topography
Nature of the Lunar Crust
Gravity Magnetic Field
The Lunar Far-side: Rock types, Chemistry
Radiation Environment
Special Regions of Interest: Polar Regions ,
South Pole Aitken Region, Selected Basins and Craters with central uplift
Water on Moon?
Objectives of the Chandrayaan-1 Mission
Simultaneous Mineralogical, Chemical & Photo-geological Mapping at resolutions better than previous and currently planned Lunar missions
High resolution VIS-NIR mapping of the lunar surface to identify Fe, Al, Mg, Ti bearing mineral with high spatial resolution (100m)
3D mapping of lunar surface at very high spatial resolution (~5 m)
High Resolution Laser ranging for topographical Map of the Moon (~0.1 deg longitudinal separation grids)
Create Expertise & Motivate the Young Minds in Space and Planetary Science
Chandrayaan-1 Mission Configuration : 100 km polar orbiter Observation Period : 2 years
Hyper Spectral Imager (HySI) (0.4-0.9µm) Terrain Mapping Camera (TMC)(0.5-0.75 µm)
Lunar Laser Ranging Instrument (LLRI) Low energy X-ray spectrometer (LEX) (1-10KeV) High energy X- ray spectrometer (HEX) (10-200KeV)
A new era of International Cooperation Based on science objectives and spacecraft resources, several AO proposals were accepted; they will complement/add to the Indian experiments to meet the basic science goals of the mission.
I. IR spectrometers for mineral mapping (SIR-2 and MMM) II. An experiment to detect neutral atoms (SARA) III. An experiment to search for water-ice at the poles (mini-SAR) IV. An experiment to monitor energetic particle environment (RADOM)
Lunar environment - Thermal
Sun movement restricted to 1.50 w.r.t lunar equator
Eternal lights at polar high land regions
Low temperature excursions (-150 C to –500 C) Presence of water nearby likely Continuous solar power generation possible
Lunar environment - Other
South Pole Atkin Region (SPAR), largest impact basin in Solar System extends from South pole to 400 S latitude on the far side
No known Seismic activity, no surface winds
Hard shadows, no atmospheric dispersion
Crystalline lunar soil can be paved glassy using microwaves, roads, craters to parabolic antenna backplanes
Comparison of Moon’s & Earth’s Orbit Moon
Earth
Semi-major axis
384.4 x 103 km
1.000 AU
Revolution period
27.32 days
365.26 days
Orbit inclination
18.3° to 29° w.r.t Earth’s equator
0.00 w.r.t ecliptic plane
Eccentricity
0.055
0.017
Obliquity
6.7°
23.4°
Rotation period
27.32 days
23 h 56 min
Radius
1738 km
6378 km
Mass
7.35 x 1022 kg
5.98 x 1024 kg
Mean density
3340 kg/m3
5520 kg/m3
Escape velocity at surface
2.38 km/s
11.2 km/s
Main Characteristics of Moon’s Orbit
The moon is a satellite of earth in a slightly elliptical orbit, inclination w.r.t the earth equator oscillating between 28035’ and 18021’ with a period of 18.6 years.
The angle between lunar equator and ecliptic plane is approximately 1.50 resulting in poor illumination of polar regions
No Atmospheric Drag
No SELENO-Magnetic Fields
100 Km Circular Polar Orbit (Period of 118 min.) selected to meet the Imaging requirements
CHANDRAYAAN-1 ORBIT • Altitude: 100km • Inclination: 90° • Period: 117.6 min • Mean ground velocity: 1.54 km/s • Earth as seen by Moon: 1.9° - 2.1°
• Beam width of 0.7 m X-band antenna: 3.6° • Moon disc at satellite: ±70°
SL.NO .
1
PAYLOAD
TMC
Spectral band 0.5 to 0.85μm
Sensor Config Three Stero
Objective
Topography
Cameras
2
HySI-VINR
0.4 to 0.92μm
Wedge filter Mineral mapping
3
LLRI
1064nm, 10mJ
4
HEX
20 – 250 keV
5
IMPACTOR
--------------
6
CIXS (LEX)
0.5 to 10keV
7
Mini-SAR
2.5GHz
Detection of poalr ice
8
SIR-2
0.93 to 2.
Mineral Mapping
9
SARA
10eV to 2keV
Mass spectrometer
10
RADOM
>8Kev
Si Semiconductor Radiation monitor
11
MMM
0.4-3.0μm
Topography &Gravity CdZnTe Detector
Chemical mapping Technology Demo
Swept Charge Chemical mapping CCD
Atmospheric neutrals& magnetic anomaly
Mineral Mapping
Payloads
Payloads from ISRO Terrain Mapping Camera with front, nadir and aft views(TMC). Hyper Spectral Imager(HySI). Lunar Laser Ranging Instrument (LLRI). High Energy X-ray payload(HEX). Moon Impact Probe (MIP) Payloads from international agencies Low Energy X-ray (LEX)payload (CIXS). From Rutherford Appleton Laboratory (RAL),UK / ESA Mini SAR from Applied Physics Laboratory (APL), USA under an MOU with NASA SIR-2 from Max Plank Institute, Germany under an MOU with ESA Radiation Dose Monitor from Bulgarian Academy of Sciences Sub-keV Atom Reflecting Analyser (SARA) Experiment developed jointly by IRF Sweden, SPL-VSCC India, ISAS/JAXA Japan and VBE Switzerland under an MOU with ESA Moon Mineralogy Mapper (M3) from JPL, US., under an MOU with NASA
Terrain Mapping Camera (TMC)
Stereoscopic imaging instrument in panchromatic spectral band for generating high resolution three dimensional map of Moon
Consists of fore, nadir and aft detectors housed in single enclosure
Spatial: Swath – 20km, Resolution – 5m
Spectral: 0.5 to 0.85µm
4000 pixel, 7µ linear APS detector
Hyper Spectral Imager (HySI)
In visible and near infra-red band
Spatial: Swath – 20km, Resolution – 80m
Spectral: 0.4 to 0.95µm, resolution better than 15nm
256 x 512 pixel, 50µ area APS detector
Lunar Laser Ranging Instrument (LLRI)
Objectives
To determine the global topographical field of Moon using the laser altimetry data
To determine an improved model of the lunar gravity field
To supplement TMC and HySI payloads
Laser wavelength: 1064 nm
Laser energy: 10 mj
Vertical Resoultion: < 5m
Detector: Avalanche Photodiode
First time coverage of polar regions of Moon
High Energy X-ray Spectrometer (HEX)
Objectives
Identify degassing fault zones by mapping of 222Rn and its radioactive daughter 210Pb, helps understanding volatile transport on Moon
To determine the surface composition of Pb-210 in the uranium decay series by it’s 46.5 keV gamma ray
To determine the integral flux of gamma rays coming out of Moon in the region 10 – 250 keV
Energy Resolution: <7% @ 60 keV
Energy range: 20 – 250 keV
Spatial resolution: 20 km
Swath: 40 km x 40 km
Detector: CdZnTe (CZT)
Moon Impact Probe (MIP)
Objectives
Scientific exploration of the Moon near range
To design, develop and demonstrate technologies required for impacting a probe at the desired location on the Moon
Qualify some of the techniques required for soft-landing missions
Payloads
Mass spectrometer to assess the lunar atmosphere
Radar altimeter to measure the altitude with a resolution of 5m
Video imaging system (VIS) to take photographs of Moon’s surface
From 100km orbit, it takes ~18 minutes to hit the Moon surface
Low Energy X-ray Spectrometer (LEX)
Updated version of Smart-1 payload
Consists of two instruments
Chandrayaan-1 Compact Imaging X-ray Spectrometer (C1XS)
Main instrument
X-ray Solar Monitor (XSM)
Provides incident solar flux as input to C1X
Objective: To carry-out high quality X-ray spectroscopic mapping of the Moon in order to study elemental abundance of Moon
Basically measures fluorescent emissions from the surface of Moon and also monitors incident Solar X-ray emissions
Detects Mg, Al, Fe and Si during non-Solar flare conditions (C1X)
Detects Ca, Ti during Solar flare conditions (XSM)
Energy range: 0.5 to 10 keV
Miniature Synthetic Aperture Radar(Mini-SAR)
Objective
To map polar regions at an incident angle of app. 37 deg. Basically looks for ice / water deposits
To resolve discrepancy in the data available from Clementine, Lunar Prospector and Arecibo Radar satellites with respect to nature and amount of deposits in the lunar polar region
Range swath: 44km, Azimuth swath: 8km
Ground range resolution: 140m for altimeter
Radar system can operate as altimeter / scatterometer, radiometer and as a synthetic aperture radar
Smart Infra Red Spectrometer (SIR-2)
Updated version of SMART-1 payload
It is a highly compact and near infra-red spectrometer
Objective
Analyze the lunar surface in various geological / mineralogical / topographical units
Study of vertical distribution of crystal material
Investigate the process of crater, maria and basin formation on Moon
Explore “Space Weathering” process of the lunar surface
Search for ices at the lunar poles
SIR-2 collects the Sun’s light reflected by the Moon
Spectral Wavelength: 0.93 to 24 µm
Spectral resolution: 6nm
Sub keV Atom Reflecting Analyzer (SARA)
Consists of two payloads
Chandrayaan Energetic Neutral Analyzer (CENA)
Solar Wind Monitor (SWIM)
Objective
Imaging of the surface magnetic anomalies (Moon doesn’t have magnetic core, like in Earth. But Moon has different magnetic fields at different surface areas which is an anomaly)
Studies of space weathering, i.e., physical and chemical changes that occur to the exposed materials on the surface of the Moon
Imaging of Moon’s surface composition including imaging of permanently shadowed areas and search for volatile rich areas
Radiation Dose Monitor (RADOM)
Updated version of similar instrument flown in MIR space station since 1988
Objective
Measure the particle flux, deposited energy spectrum, accumulated absorbed dose rate in the lunar orbit and evaluate the contribution of protons, neutron, electrons, gamma rays and energetic galactic cosmic radiation nuclei
Provide an estimation of the dose map around Moon at different altitudes
To evaluate the shielding characteristics (if any exists) of the Moon near environment towards galactic and solar cosmic radiation and solar particle events
The experiment will be useful for future manned missions
Moon Mineralogy Mapper (M3)
Payload is solar reflected energy imaging spectrometer
Objective
To assess the mineral resources of the Moon
To characterize and map the composition of the surface at high spatial resolution
Spectral- Range: 0.7 – 3.0 µm, Resolution: 10nm
Radiometric: Range 0 to max. Lambertian, Sampling 12 bits
Spatial: Swath 40km, Resolution 30m
SWIM
XSM
MIP RADOM
SIR-2 LLRI
CENA
CIXS
MiniSAR
TMC
M3
HEX HySI
Spacecraft Configuration
S-band transmission through omni antenna
Configured with two 90 hemi-spherical coverage antennas with opposite polarisation placed on the diametrically opposite face in the S/C
X-band transmission through Steerable Dual Gimbal Antenna Sensors – CASS, SPSS, Star sensor BMU handles Command, Telemetry, AOCS functions Bi propellant system for orbit raising & maintainence CCSDS – compatible with world-wide network & DSN Single bus / battery system
Canted Solar panel generates 700 W on normal incidence 27 AH Li Ion battery
PLATFORM SPECIFICATIONS (NORMAL MODE POINTING AND STABILITY)
Axis
Attitude Pointing
Rate
Yaw
0.05
3.0E-4 /s
Roll
0.05
3.0E-4 /s
Pitch
0.05
3.0E-4 /s
Post-facto attitude determination: 40 arc-sec for entire mission life
X-Band Downlinks from Chandrayaan-1 VIRTUAL CHANNEL - 0
1. 2. 3. 4.
TMC – APS1 TMC – APS2 TMC – APS3 HySI
SSR #1
VIRTUAL CHANNEL - 1 miniSAR VIRTUAL CHANNEL - 3
1. MIP 2. C1XS 3. HEX 4. SIR-2 5. LLRI 6. SARA 7. RADOM 8. S-LBT 9. GYRO 10.STAR SENSOR
SSR #2
Channel coder
SSR #3
VIRTUAL CHANNEL - 2 M3
X-band link
Mass Budget Bus Elements (kg)
Payload (kg) S/C Dry Mass (kg)
Growth Margin (kg)
405.0
89.0 494.0
9.0
Dry Mass (kg)
503.0
Propellant (kg)
797.5
Pressurant (kg)
Lift off Mass (kg)
3.5
1304.0
Power Budget Sub-system
HEX, LLRI, AO
Sunlit (W)
44
Eclipse (W)
44
IMAGING (Average) + CIXS 34(6+28)
0
DATA Tx
0
44
BUS
236
228
TOTAL
534
316
INT. LOSS (4%)
22
13
REQUIREMENT
556
329
GENERATION
607
27AH@ 25% DOD
MARGIN
51
DSN-18
Chandrayaan-1 Ground Segment ISTRAC IDSN STATIONS â&#x20AC;&#x201C; S BAND DSN-18 S/X (ALL Phases)
DSN-32 S/X (> 1 Lakh km)
Ant. Dia (m)
18.3
32
G/T (dB/K)
30.6
37.5
G/T looking at Moon (dB/K)
26.0
32.0
79
94/84
10(Az) /1(El) 5/ 0.5
0.4 0.01
20
20
0.05
0.05
-
0.3mm rms
Specifications
EIRP (dBW)
Antenna rates Velocity (deg/s) Accln. deg/s*2 Tone Ranging Accuracy (m) Range-rate Accuracy (m/s)
Surface finishing (wrt parabola)
Polar Satellite Launch Vehicle (PSLV)
Basic Capabilities
SSPO ( 725*725 km, i= 98.370 )
1250 kg
LEO (300*300 km )
3400 kg
GTO (240 * 36000 km, METSAT) 1050 kg Chandrayaan-1 (260 X 24000 km) 1304 kg
Vehicle Configuration (6S9+S139)+L40+S7+L2.5
Indian Lunar Mission Sun
GTO
ETO
Trans Lunar Injection Lunar Insertion Manoeuvre Mid Course Correction
Lunar Transfer Trajectory
To achieve 100 x 100 km Lunar Polar Orbit. PSLV to inject 1304 kg in GTO of 260 x 24000 km. Lunar Orbital mass of 623 kg with 2 year life time.
Initial Orbit ~ 1000 km Final Orbit 100 km Polar
Moon at Launch
Launch Window
It is necessary to have a LOI manoeuvre when Moon is at equator, i.e., when Moon is in the ascending or the descending node.
Two launch opportunities in 28 days (lunar cycle) are possible.
Capture at descending node is not favourable in all seasons as Sun lies in the perigee side, causing long shadows near apogee.
Maximum shadow allowed per orbit is 100 minutes
Transfer phase to lunar capture CAP08AP09-NOM-00
350
70
Altitude = 511.063963km Geodetic latitude -4.250270° East Longitude 138.301821°
300
60
Velocity 9.707127° Flight Path Angle 80.292873° Velocity Azimuth 107.439542°
250
200
50
40
Orbit Size: 260km x 24075km Inclination = 17.93742° Arg Perigee = 169.06269°
150
30
100
20
50
10
0 0
50
100
150
Time in hrs elapsed since injection (Launch Apr 09, 2008)
200
0 250
Thousands
80
Injection parameters - version #1
Radial distance from Moon (km)
Radial distance from Earth (km)
Thousands
SOI index 11032
400
Consolidated Network Stations S.N 1.
2.
3.
Mission Phase
Stations
Short Range Support (Perigee arc coverage) â&#x20AC;&#x201C; S-band support During Spacecraft separation
Biak, Hawaii
During burn #1 (TM)
TT, Kourou, Natal
During burn #2 & #3 (TM)
Port Blair, Brunei, Biak
LEOP phase (upto 1 lakh km) S-band support (TC, TM, TRK)
Bangalore, Biak, MaryLand (APL), Mauritius, Hawaii, Lucknow, Bearslake
X-band support
Bangalore, Mauritius (post Hawaii (post LEB #2 & #3)
LEB
#1),
DSN support LEOP phase
Bangalore, Bearslake, Goldstone
APL,
Normal phase
Bangalore, Bearslake, APL, JPL -Goldstone (on requirement)
JPL-
Inertially fixed lunar polar orbit
Orbit regression is negligible. Lunar sun synchronous orbit not possible. Inertially fixed polar orbit experiences continuously varying sun illumination over a year.
Lunar Orbit as seen from Earth M
M
Face on T
Edge on T+7 days
Face on T+14 days
Classification of Payloads
Illumination dependant
Illumination independent
TMC + HySI M3 SIR-2 C1XS LLRI MiniSAR SARA HEX
Moon independent
RADOM XSM of C1XS SWIM of SARA
Sun aspect variations in a year
300 300
4 Months M 300 4 Months 300
Prime zone
Polar region
Imaging Strategy - Definitions
Prime Imaging season Season in which the solar aspect angle at lunar equator is within ±45°. Season comprises of 90 days centered around noon/midnight orbit suitable for optical imaging.
Prime Imaging Zone Region within ±60° latitude of lunar equator, sensitive to illumination variation resulting from sun movement over the season. This zone is covered by imaging payloads within 60 days centered on noon/midnight orbit restricting the solar aspect angle within ±30° with respect to the lunar equator.
Polar zone High latitude zones (beyond 60°) which are poorly illuminated and insensitive to sun movement. Low lands are permanently shadowed, high lands are perpetually under grazing sun rays. Imaging coverage is for 15 days wherein the solar aspect angle is restricted in the bands of ±30° and ±45° respectively.
Imaging Strategy – Definitions …
Secondary Imaging season Season in which the solar aspect angle at lunar equator is beyond ±45°. Season comprises of 90 days centered on dawn/dusk orbit. In this period, payloads which are not dependent on ground illumination levels like mini-SAR, HEX, LEX, LLRI, SARA and RADOM are operated.
Imaging Cycle All Sunlit longitudes of Moon are swept once in 28 days owing to rotation about its own axis termed as an Imaging Cycle. Each imaging season has TWO cycles.
DSN Visibility at 100 km orbit
Complete Lunar Surface Coverage DSN support for payload data transmission
Bangalore + APL-USA
Area covered in prime imaging zone
60º N to 60º S
Area covered in polar imaging zone
90°N to 60°N, 90°S to 60°S
Latitude zone covered in one visible orbit
60°
No: of orbits visible / day
10
Time required to visit all longitudes
2 prime image seasons
Time available for each prime imaging season
3 months
Time available for each secondary imaging season
3 months
Number of prime imaging seasons
3
Number of secondary imaging seasons
2
Minimum time required to cover entire lunar surface
15 months
Distinct Mission Features
Features that affect payload data processing
Spacecraft yaw rotation Imaging in ascending and descending paths Varying Illumination conditions Vernier ground track shifts Variation in altitude
Features that affect downlink
Sun outage Rain attenuation during Moon rise / Moon set
Worst Case Eclipse – Earth & Moon Shadow PENUMBRA
M
48 m M.S
M.S – Moon shadow,
UMBRA
72 m P.E.S
48 m M.S
48 m P.E.S
37 m E.S
P.E.S – Part Earth Shadow,
35 m 72 m 48 m 13 m M.S P.E.S M.S P.E.S
E.S – Earth Shadow
WORST CASE ECLIPSE–EARTH AND MOON SHADOW
PES
MS
48
LIT
27.5
PES
42.5
MS
PES
ES
48
51 9.5
MS
PES
48
42.5
LIT
27.5
MS
48
9.5
Duration in minutes MS –Moon Shadow LIT - Illumination period PES – Partial Earth Shadow ES – Earth Shadow
Total Duration: 6.7 hours
SUMMARY OF LUNAR ECLIPSES (2008-2010) Date
Eclipse Type
Saros
Umbral Mag
Eclipse Duration (hh:mm)
Geographic Regions of Eclipse Visibility
21 Feb, 2008
Total
133
1.111
16 Aug, 2008
Partial
138
0.813
03:36 00:51 03:09
09 Feb, 2009
Penumbral
143
-0.083
-
E Europe, Asia, Aus, Pacific, W N.A
07 Jul, 2009
Penumbral
110
-0.909
-
Aus, Pacific, Americas
06 Aug, 2009
Penumbral
148
-0.661
-
Americas, Europe, Africa, W Asia
31 Dec, 2009
Partial
115
0.082
01:02
Europe, Africa, Asia, Aus
26 Jun, 2010
Partial
120
0.0542
02:44
E Asia, Aus, Pacific, W Americas
21 Dec, 2010
Total
125
1.262
03:29 01:13
E Asia, Aus, Pacific, Americas, Europe
C.Pacific, Americas, Europe, Africa S.America, Europe, Africa, Asia, Aus
ISSDC Context Payload Reception Stations
S/C control center
Time Allocation Committee Science Working Group
Science Data Users
Space Science Mission Projects S/W Developers â&#x20AC;&#x201C; data products, tools
ISSDC Payload Developers Payload Operation Centers
Principal Investigators
ISSDC functions •
Primary Functions – Ingest / Archive / Data Management – Data processing – Search & Order / Access & Dissemination
– Interface to Spacecraft control centers, Data reception centers, Payload designers, Principal investigators, Mission software developers and Science data users
ISSDC facilities • Server and Storage Support Area • Network Support Area • Public Network Access Workspace • Private Network Access Workspace • SATCOM Network Access Workspace • Software & System Support Area • System Administration Workspace
• System test and Maintenance Support Workspace • Development, Integration and Test Support Workspace • Operations Area ( IDSN Ops facility)
OVERALL DATA FLOW DIAGRAM Chandrayaan-1 Ground Segment
S-LBT (RT- 2) S-LBT (Dwell) X-LBT (PB – SSR#2) Remote View (SSR #2) S-Band Tracking data TC Ack
PAYLOAD OPERATIONS Look angles
SCC
TC Schedule file
Cmd Request messages
DSN
Processed QLD input
Bangalore – 18 / 32 m
Archived PVAT
P/L Raw Data: TMC – APS 1, 2, 3, HySI, LLRI, HEX, C1XS, M3, SIR-2, SARA, MIP, RADOM SS + Gyro data (SSR #2)
EXTERNAL DSN Bearslake APL Tracking NASA data LBT (RT + Dwell) P/L raw data
OBT-UT Ref. Ephemeris Events Cmd schedule Pass schedule Instrument health
ISSDC
POC 1.TMC & HysI - SAC 2.LLRI - ISAC 3.HEX - PRL
4.CIXSA - RAL
Ephemeris Events 5.CIXSB - ISAC PVAT Command Acknowledgement 6.SIR-2 – Max Instrument Telemetry (P/L data) Planck, Germany Instrument House keeping OBT - UT 7.SARA - VSSC File-ready Notification email 8.miniSAR - APL
Command Messages Products & E-mail notification
9.M3 - JPL
Lunar DEM Generation
Global DEM generation from TMC triplet
More than 100000 image triplets
Grid interval size ~25-50m
LLRI data use to be explored
ISRO Moon Atlas • Cover the entire moon surface at Uniform Scale (1:25,000/50,000) • Consists of TMC & HySl Image and Image mosaics • Contains Digital Elevation Model derived from TMC • Softcopy & Hardcopy both • Vector and Raster databases
High level Data products
The high level data products from the AO payloads are
Near Infra-red Spectrometer (SIR-2)
Spectroscopic data corrected for dark bias and bad pixel data
Radiometric and wavelength corrected data
Details of lunar surface in various geological, mineralogical and topographical units
Sub-keV Atom Reflecting Analyser (SARA)
Images of energetic neutral atom distributions for specific energy and mass group and time-dependent plots of total fluxes for them (CENA)
Energy spectra for the four specified mass group atoms
Linear plot of proton fluxes(SWIM)
High level Data products (contd.) Miniature Synthetic Aperture Radar (MiniSAR) •
Level 1 products ortho-rectified and resampled into oblique map projections
•
Four mosaics composed of multiply acquired data sets produced for regions above 80º lunar latitude using level2 stokes parameters
Moon Mineralogy Mapper (M3) •
Radiance at sensor and seleno-corrected spectral image cubes
•
Reflectance data
Radiation Dose monitor Experiment (RADOM) •
Estimated radiation dose equivalent from GCR,SPE and radiation dose maps around moon
•
Moon environment characteristics
Possible Fusion Data Products • Elemental composition and Mineral Maps:M3,SIR-2,HySI, C1XS,SARA • DEM from TMC with LLRI topo map • Magnetic anomaly map of SARA with TMC base map • Polar region map from MiniSAR, LLRI overlaid with TMC base map • Projection of X-ray line abundances from C1XS and HEX against DEM made from fusion of TMC and LLRI data • Fusion of mineral map, elemental composition map with topographic map • Integration of data from earlier lunar missions with that of Chandrayaan-1
Visualization tools and other utilities
Intended for public outreach and awareness.
Tool would show at a given point of time, how much imaging is done on the globe of Moon.
Overlay of processed data showing the information layers available for various instruments
Data Fusion (R&D)and other utilities (in the form of software)
User can generate fusion products using the utilities provided at ISSDC (generated by science teams or data processing teams) with required data download facility. This also includes visualization tools for looking at a particular area of interest
Education and Outreach Activity Plan Comprehensive education and public outreach programme is under development Activities aimed towards a broad range of ages and abilities Education and categories
Public
Outreach
programme
planned
in
four
Formal education
•
As part of basic curriculum for high school level students, providing resource and support material-this is a long term strategy / plan
•
Scientific research at university level (e.g. PLANEX Programme of ISRO)
Semi-formal education •
Introducing project work as part of school curriculum (similar to that in for B.Tech)
•
ISRO may provide tool kits (involvement of industries)
Education and Outreach Activity Plan (contd.) Informal Education • Seminar, talks on Moon,Chandrayaan-1 • Essay contest
• Exhibition • Team with local planetary society members, amateur observers /sky watchersto share and exchange ideas • Use website • Moon globe on website –similar to Google-Earth using TMC DEM
Public Outreach • Popular publication • Broadcast over national and local Radio and Television Network • Use of Website
• For common public cultural, mythological and historical stories related to Moon
Education and Outreach Activity Plan (contd.) A few sample questions which may be considered as project topic:
• Calculate distance between scale models of Earth and Moon • To learn about locations and geology of sites identified by • Chandrayaan-1 science team • Compare the process of regolith formation on the Moon and the relative process on Earth • Design a spacecraft for going to moon and choose a landing site of interest • Construct a model of lunar rover • Future lunar mission ideas
Outreach Implementation Plan The outreach activity would be implemented in steps •
Mission update on ISRO/ Chandrayaan-1 Website from T-90 day
•
Announcement of Opportunities towards Formal and Informal Outreach activities seeking proposals from different groups
Collaborative agencies would be selected from Research Laboratories,School, Colleges, Universities, National and Regional science museums and Planetariums based on the activities •
After obtaining approval from DOS/ISRO, activities would be carried out and monitored in collaboration with P & PR Unit ISRO
To Conclude – Why to go to Moon…
The first, of course, the scientific goals that despite many missions of the past, the question of origin and evolution of Moon still remains unanswered
The second objective is the challenges posed by technology and mission planning
The third factor is such a mission can inspire the new generation by the sheer excitement that such a flag-ship mission will evoke.
India cannot afford to lose out in its ability to pursue exploration