Mission Information
|
MISSION_NAME |
CHANDRAYAAN-1
|
MISSION_ALIAS |
CH1
|
MISSION_START_DATE |
2008-10-22T12:00:00.000Z
|
MISSION_STOP_DATE |
2009-08-28T12:00:00.000Z
|
MISSION_DESCRIPTION |
Mission Overview
================
Chandrayaan-1, the first Indian mission to Moon, was designed to carry out
high resolution remote sensing studies of the Moon to further our
understanding of its origin and evolution. At 00:52 UT on 22 October
2008, the Indian Space Research Organization (ISRO) launched Chandrayaan-1
on-board an upgraded Polar Satellite Launch Vehicle (PSLV-C11) from the
Satish Dhawan Space Center (SDSC) in Sriharikota located along the
southeast coast of India. The PSLV-C11 injected the orbiter spacecraft
into an eleven-hour elliptical transfer orbit around the Earth on 23
October 2008.
The launch was planned such that the Moon is at one of its nodes when the
spacecraft arrives. In order to have multiple launch opportunities every
month and to contain burn errors, a phasing loop strategy with multiple
loops and five Earth bound maneuvers was adopted. The injection
parameters are as follows:
Semi-major axis : 17971.73 km
Eccentricity : 0.63094
Inclination : 17.9112 deg
Perigee height : 254.457 km
Apogee height : 22932.741 km
From 25 October through 4 November 2008 several maneuvers were performed
to put the spacecraft into a lunar transfer trajectory, and on 8 November
Chandrayaan-1 was successfully inserted into a lunar orbit. By 12
November the spacecraft had reached its intended 100-km circular polar
orbit for chemical, mineralogical, and photo-geologic mapping of the Moon
by its eleven on-board instruments; scientific observations were scheduled
to continue at this altitude for two years. The details of the five Earth
bound maneuvers, lunar insertion maneuver, and circularizing maneuvers at
the Moon are provided here:
.----------------------------------------------------------------------.
| | Central | Perigee | deltaV | Dur | Post Maneuver Orbit |
| Burn | Body | Number | (m/s) | (s) | perigee x apogee (km) |
|--------|---------|---------|-----------------------------------------|
| EBN #1 | Earth | 4 | 344.43 | - | 299.2 x 37908.1 |
| EBN #2 | Earth | 8 | 328.14 | 912.36 | 336.3 x 74715.6 |
| EBN #3 | Earth | 9 | 221.69 | 567.73 | 347.8 x 165015.1 |
| EBN #4 | Earth | 10 | 77.17 | 192.18 | 459.4 x 266612.9 |
| EBN #5 | Earth | 11 | 60.70 | 147.68 | 972.8 x 379859.2 |
| TCM | Earth | | 0.82 | 5.59 | 802.8 x 378499.2 |
|--------|---------|---------|--------|--------|-----------------------|
| LOI | Moon | - | 366.96 | 817.07 | 507.9 x 7510.1 |
| LBN #1 | Moon | - | 26.60 | 56.95 | 197.8 x 7507.1 |
| LBN #2 | Moon | - | 448.20 | 868.00 | 183.0 x 255.2 |
| LBN #3 | Moon | - | 17.03 | 31.30 | 103.3 x 253.9 |
| LBN #4 | Moon | - | 32.13 | 58.60 | 101.9 x 102.8 |
.----------------------------------------------------------------------.
From 16 to 19 May 2009 the Chandrayaan-1 spacecraft was raised to a 200-km
orbit to keep the temperature of the orbiter down after star trackers
failed. This change enabled further studies of orbital perturbations and
gravitational field variations and imaging of the lunar surface with a
wider swath. After completing more than 3400 orbits of the Moon in 312
days and providing a large volume of data from its suite of sensors that
met most mission objectives, communication with the spacecraft was
abruptly lost around 20:00 UT on 28 August 2009. ISRO officially
terminated the mission on 31 August 2009.
Instruments and Experiments
===========================
TMC
---
Terrain Mapping Camera (TMC) is designed to image in the panchromatic
spectral band of 0.5 to 0.75 microns with a stereo view in the forward,
nadir, and aft directions of the spacecraft movement and a base-to-
height ratio of 1. The swath of the instrument is 20 km. The key
features of TMC are:
Spatial sampling : 5 x 5 sq.m (from 100-km orbit)
Swath : 20 km
Spectral band : Panchromatic (0.5 to 0.75 micro-m)
Stereo mode : Along track triplet, B/H = 1
No. of gains & exposure : 4 each
Square wave response > 25
Signal to noise ratio > 350
The instrument is from Space Applications Centre, Ahmedabad, India.
HySI
----
The Hyper Spectral Imager (HySI), operating in the visible and near
infrared spectral region, is one of the three imaging instruments on-
board the Chandrayaan-1 spacecraft for mineralogical study of the Moon.
HySI is designed to map the entire lunar surface in 64 contiguous bands
in the visible and near infrared (VNIR: 421 to 964 nm) with a spatial
sampling of 80 m. A wedge filter is employed for the spectral
separation, and the image is mapped onto an area detector. The detector
output is processed in the front-end electronics to generate the 64-band
with 12-bit quantization. The key features of HySI are:
Spatial sampling : 80 x 80 sq.m (from 100-km orbit)
Swath : 20 km
Spectral range : 461 to 964 nm
No: of spectral bands : 64 continuous
No: of gains : 2
No: of exposure setting : 4
Quantization : 12-bits
Signal to noise ratio > 100
Square wave response > 40
The instrument is from Space Applications Centre, Ahmedabad, India.
M3
--
The Moon Mineralogy Mapper (M3) is an imaging spectrometer that operates
from the visible into the near-infrared (0.42 to 3.0 micron) where
highly diagnostic mineral absorption bands occur. The instrument
parameters and measurement modes for M3 are:
Overall:
40-km FOV (allows contiguous orbit overlap)
405 to 3000 nm spectral range
12 bits/pixel
Target mode (full resolution):
6000 spatial pixels (70 m/pixel)
260 spectral channels (10 nm/channel)
1 GB/orbit downlink: 10 to 12 deg longitude swath
Global Mode (reduced resolution):
300 spatial pixels (140 m/pixel for 100-km lunar polar orbit)
86 spectral channels (mixed 20 and 40 nm/channel)
1 GB/orbit downlink: 135 deg longitude swath (alternating poles)
The instrument is from Jet Propulsion Laboratory, NASA, USA.
LLRI
----
The Lunar Laser Ranging Instrument (LLRI) is designed to measure the
topography of the lunar surface. A 10-mJ diode-pumped pulsed laser
together with a 20-mm diameter telescope and a silicon avalanche
photodiode are the principal optical assemblies of this active remote
sensing instrument. The specifications of LLRI are:
Maximum range : 100 km (>100 km)
Range accuracy <= 5 m (<5 m)
Range resolution <= 5 m (<1.5 m coarse, <25 cm fine)
Data update rate : 10 Hz
Transmitter wavelength : 1064 nm
Pulse energy (min) : 10 mJ
Spectral bandwidth : 0.05 nm
Spectral Rx bandwidth < 10 nm
Optical Rx FOV : 0.05 deg
The instrument is from Laboratory for Electro-optics, Bangalore, India.
C1XS
----
The Chandrayaan-1 X-ray Spectrometer (C1XS) is an X-ray imaging
spectrometer comprising 24 Swept Charge Device (SCD) detectors and a
micro-structure collimator/filter assembly. The detectors are arranged
in three arrays of 8 (2 x 4) detectors each, providing an overall field
of view of 32 by 12 degrees in the 0.5 to 10 keV range with a resolution
of 140 eV. The SCDs are based upon CCD technology but have
significantly lower read noise and can also operate at higher
temperatures. (The C1XS SCDs operate with good signal-to-noise at -10
degrees Celsius.) This is achieved by an electrode and clocking
arrangement that 'sweeps' the charge to one collector in a corner of the
chip. The instrument is from Rutherford Appleton Laboratory, UK.
XSM
---
An X-ray Solar Monitor (XSM) supports the C1XS observations, providing
solar spectra as calibrations for the lunar data collected by C1XS from
which absolute elemental abundances can then be derived. XSM has a wide
field of view of 104 degrees and operates in the 0.8 to 20 keV spectral
range. Stand-alone observations of long-term solar X-ray emissions can
also be made. The detector comprises silicon diodes cooled by Peltier
elements. The instrument is from Rutherford Appleton Laboratory, UK.
SIR-2
-----
The Sub Infrared Spectrometer (SIR-2) is a miniaturized point-
spectrometer with a InGaAs array detector designed to provide good
signal-to-noise at temperatures around -70 degrees Celsius. The
spectrometer operates in the 0.9- to 2.4-micrometer wavelength range and
has 256 spectral channels with a resolution per channel of 6 nm/pixel.
This is coupled to a lightweight off-axis telescope which has an
aperture of 70 mm and a field of view of 1.1 mrad. A dedicated radiator
provides passive cooling of the optics and the spectrometer during
observations. The instrument is from Max Planck Institute for Solar
system science, Germany.
HEX
---
High Energy X-ray spectrometer (HEX) is designed to have a spatial
resolution of about 33 km at energies below 120 keV. The low signal
strength of these emissions requires a large area detector with high
sensitivity and energy resolution, thus a new generation CdZnTe solid
state detector is used in this experiment. The specifications of HEX
are:
Energy range : 30 to 270 keV
Energy resolution : 12% at 60 keV
ACS threshold ~ 50 keV
Spatial threshold : 33 km x 33 km FOV
The instrument is from ISRO satellite centre, Bangalore, and Physical
Research Laboratory, Ahmedabad, India.
Instrument : SARA (Sub-keV Atom Reflecting Analyzer)
Type : Mass spectrometer and solar wind monitor
Measurements : 10 ev - 2 kev with a 100-m spatial resolution
Science Goals : Atmospheric neutrals (H-Fe) composition and magnetic
anomalies
Principal Investigator : S. Barabash, ESA
SARA
----
The Sub-keV Atom Reflecting Analyser (SARA) comprises two detectors.
The Chandrayaan Energetic Neutrals Analyser (CENA) is a low-energy
neutral atom sensor with an range from 10 eV to 3.3 keV, and the Solar
Wind Monitor (SWIM) is an ion mass spectrometer with an energy range
from 10 eV to 15 eV. The main characteristics of the two sensors are:
Parameter CENA SWIM
---------------------------------------------------------------------
Particle to measure Neutrals Ions
Energy range 10 eV to 3.2 keV 10 eV to 15k eV
Energy resolution 50% 7%
Mass range 1 to 56 amu 1 to 40 amu
Mass resolution H,O, Na/Mg/Si/Al, H, He, O (> 20 amu)
K/Ca, Fe
Full FOV 15 x 160 deg 9 x 180 deg
Angular resolution 9 x 25 deg 4.5 x 22.5 deg
G-factor/sector, w/o 10^-2 cm2^2 sr eV/eV 1.6x10^-4 cm^2 sr eV/eV
Efficiency 0.2 cm^2 se eV/eV(at 25eV)
Efficiency (%) 0.01 to 1 0.1 to 5
The instrument is from Swedish Institute of Space Physics, Sweden, and
Space Physics Laboratory, VSSC, Trivandrum, India.
Mini-SAR
--------
The Miniaturized Synthetic Aperture Radar (Mini-SAR) is a single
frequency (S-band; 13-cm wavelength) synthetic aperture radar in a light
weight (9 kg) package. Mini-SAR utilizes a unique hybrid polarization
architecture which allows determination of the Stokes parameters of the
reflected signal, intended to distinguish volume scattering (caused by
presence of ice) from other scattering mechanisms. The parameters for
Mini-SAR are:
Frequency : 2.38 GHz
Spacecraft velocity : 1631 m/s
Range swath : 8 km
Strip length : 325 km (SAR), 300 km (Scatterometer)
Boresight fain : 26.1 dB
Antenna efficiency : 53%
Transmit pulse width : 84 micro-sec (SAR), 83 micro-sec
(Scatterometer)
PRF : 3100 Hz (SAR), 3750 Hz (Scatterometer)
A/D sampling frequency : 8
The instrument is from Applied Physics Laboratory, Johns Hopkins
University, USA.
MIP
---
The Moon Impact Probe (MIP) has two technological and one scientific
experiments: a Moon Imaging System (MIS), a radar altimeter, and a mass
spectrometer known as CHACE (Chandra's Altitudinal Composition
Explorer). The nearly 34-kg MIP with features of a mini spacecraft is
designed to be piggy-backed on main orbiter and released for descent to
the Moon at a pre-determined location. The MIS essentially comprises a
CCD camera and processing electronics and is designed to acquire images
of lunar surface, compress them, and then transmit the compressed data
through a telemetry link to the orbiting Chandrayaan-1 spacecraft. A
altimeter consists of a C-band radar that makes use of an FM-CW type
transmitter with central and modulation frequencies of 4.3 GHz and 100
Hz, respectively, and a transmitted output power of 1 W (CW) with a
frequency deviation of +/-50 MHz. The salient features of CHACE are:
Mass range : 1 to 100 amu
Detector type : Electron multiplier
Resolution : Unit resolution
Dynamic range : 10^10
Min. detectable partial pressure: 5 x 10^-14 torr
Scan rate : 15 spectra/minute
Sensitivity : 10^-1 A/torr
The instrument is from Vikram Sarabhai Space Centre, Trivandrum, India.
RADOM
-----
The Radiation Dose Monitor (RADOM) is designed to measure the spectrum
(in 256 channels) of the energy deposited by primary and secondary
cosmic particles. It is a miniature spectrometer dosimeter containing a
single 0.3-mm thick semiconductor detector with a 2-cm-square area, one
low noise hybrid charge-sensitive preamplifier (A225F type) from AMPTEX
Inc., a fast 12-channel analog-to-digital converter, two micro-
controllers, and buffer memory. A pulse analysis technique is used for
obtaining the spectrum of the energy deposited in the silicon detector
which is then analysed and further converted to deposited dose and flux
values. The instrument is from Solar-Terrestrial Influences Laboratory,
Bulgarian Academy of Sciences.
Mission Phases
==============
Two main phases of significant periods of spacecraft activity are defined
for the Chandrayaan-1 mission: The Launch and Early Orbit phase and the
Lunar Orbit phase.
LAUNCH AND EARLY ORBIT
----------------------
Mission Phase Start Date: 2008-10-22
Mission Phase Stop Date: 2008-11-08
The Launch and Early Orbit Phase extended from the launch of the
spacecraft from the SDSC in Sriharikota, India, at 00:51 UT on 22
October 2008. This phase starts from lift-off and ends with lunar
capture. Orbit raising maneuvers and transmitting X-band data through
the stowed DGA are the major activities during this phase. During
other major activities, the spacecraft was kept at single inertial
attitude due to power, thermal, and communication link constraints.
The RADOM instrument was turned on during the first transfer orbit and
was kept on continuously. Three images were taken by TMC during en
route: the Australian sector of Earth at 02:38 UT on 29 October 2008,
the crescent Earth at 07:29 UT on 29 October 2008, after burn #4, and
the crescent Moon at 08:25 UT on 4 November 2008, after burn #5.
LUNAR ORBIT
-----------
Mission Phase Start Date: 2008-11-08
Mission Phase Stop Date: 2009-08-28
The sphere of influence occurred around 18:05:30 on 7 November 2008.
The Lunar Orbit Insertion maneuver was carried out at 11:20:46 on 8
November 2008 to put the spacecraft into an elliptical orbit (500 x 7500
km) around Moon. The orbit was later circularized to 100 x 100 km after
four lunar burns.
All the payloads were commissioned in a phased manner. The
commissioning
dates of each payload were:
.-----------------------------------.
| | Commissioning |
| Payload | Date (UTC) |
.-----------------------------------.
| TMC, RADOM | Operated en route |
| LLRI | 2008-11-16T03:50 |
| HySI | 2008-11-16T07:40 |
| Mini-SAR | 2008-11-17T14:00 |
| M3 | 2008-11-18T22:15 |
| SIR-2 | 2008-11-19T08:23 |
| C1XS | 2008-11-20T17:42 |
| HEX | 2008-12-05T11:52 |
| SARA | 2008-12-09T11:50 |
| | 2009-01-29T04:00 |
.-----------------------------------.
Summary of Sub-Phases during Lunar Orbit
========================================
****************************************************
Name: Limited operation zone (noon-midnight zone-1)
****************************************************
START_DATE: 2008-11-16
STOP_DATE: 2009-01-30
Sun angle with respect to the orbital plane: -30 deg to 45 deg.
Scientific Focus: Optical Imaging
Instruments operated: TMC, HySI, M3, SIR-2, C1XS, LLRI, RADOM
DESCRIPTION: To contain the bulk temperature of the spacecraft, the
payload operations were restricted during this phase. The maximum
number of payload sessions in a day was four. Typical data were
collected of the surface of the Moon such as polar, equatorial (near
side, far side), and higher latitude regions (near side, far side) by
TMC, HySI, M3, SIR-2, C1XS, and LLRI. A campaign to image Apollo
landing sites by all the imaging payloads was carried out from 7 to 11
January 2009. A 180-deg yaw rotation of the spacecraft was carried out
on 18 December 2008.
***************************************
Name: Intense imaging operation zone-1
***************************************
START_DATE: 2009-01-31
STOP_DATE: 2009-02-14
Sun angle with respect to the orbital plane: Greater than 45 deg and
less than 60 deg.
Scientific Focus: Optical Imaging
Instruments operated: TMC, HySI, M3, SIR-2, C1XS, LLRI, RADOM, SARA
DESCRIPTION: During this period, all the optical imaging payloads were
operated every orbit. The coverage of TMC-HySI was around the
equatorial region (+30 to -30 degrees), and M3 was operated in global
mode. SIR-2 and C1XS were operated during the illuminated limb of the
orbit, including the terminator crossing, while LLRI was operated during
the non-illuminated limb of the orbit.
***********************
Name: Dawn-dusk zone-1
***********************
START_DATE: 2009-02-15
STOP_DATE: 2009-04-15
Sun angle with respect to the orbital plane: Greater than 60 deg.
Scientific Focus: Radar imaging
Instruments operated: Mini-SAR, HEX, C1XS, RADOM, SARA
DESCRIPTION: During this period, Mini-SAR was operated at both poles.
As the spacecraft bulk temperature was low, the power requirement for
the heater increased. HEX was operated during the poles for a period of
20 minutes. The spacecraft was re-oriented about 40 to 50 degrees about
the yaw axis to maximize power generation and to charge the battery
during the payload non-operation period. The solar array was flipped by
180 degrees on 25 March 2009 when the Sun angle was 60 degrees with
respect to the solar panel.
***************************************
Name: Intense imaging operation zone-2
***************************************
START_DATE: 2009-04-15
STOP_DATE: 2009-05-18
Sun angle with respect to the orbital plane: Greater than 45 deg and
less than 60 deg.
Scientific Focus: Optical imaging
Instruments operated: TMC, HySI, M3, SIR-2, C1XS, RADOM, SARA
DESCRIPTION: During this period, the regions that M3 did not image
during the previous imaging season were covered in global mode. Higher
latitudes of the southern hemisphere (-30 to -60 degrees) were imaged by
TMC-HySI. SIR-2 and C1XS were operated during the illuminated limb of
the orbit. However, after failure of a star sensor, all payload
operations were minimized.
*****************************************************
Name: 200-km operation zone-1 (noon-midnight zone-2)
*****************************************************
START_DATE: 2009-05-19
STOP_DATE: 2009-08-16
Sun angle with respect to the orbital plane: Less than 60 deg.
Scientific Focus: Optical imaging
Instruments operated: TMC, HySI, M3, SIR-2, C1XS, RADOM, SARA
DESCRIPTION: The altitude of the orbit was raised to 200 km during the
period from 16 to 19 May 2009. During this maneuver, all the
illumination-dependent instruments were operated. Systematic coverage
was performed by TMC-HySI starting with the polar zone, mid-latitude
regions, and global coverage was carried out by M3 under different
illumination conditions. A 180-degree yaw rotation was carried out on
18 June 2009. Periodic attitude acquisition maneuvers were carried out.
During the total solar eclipse on 22 July 2009, nine consecutive images
of Earth were acquired by TMC to cover the path of totality. Other
payloads such as M3, SWIM (SARA), C1XS were also switched on during the
eclipse.
*************************************************
Name: 200-km operation zone-2 (Dawn-dusk zone-2)
*************************************************
START_DATE: 2009-08-17
STOP_DATE: 2009-08-28
Sun angle with respect to the orbital plane: Greater than 60 deg.
Scientific Focus: Radar imaging
Instruments operated: Mini-SAR, C1XS, RADOM
DESCRIPTION: Due to the change in the altitude of the orbit, the Mini-
SAR operation sequences were modified and polar imaging in SAR mode was
started on 17 August 2009. Periodic attitude acquisition maneuvers were
carried out. On 20 August 2008, bi-static observation with the Lunar
Reconnaissance Orbiter (LRO) was attempted. However, it was not
successful because of the uncertainty in the attitude. The RADR imaging
continued until radio contact with the spacecraft was lost on 28 August
2009.
|
MISSION_OBJECTIVES_SUMMARY |
Mission Objectives Overview
===========================
The main scientific objective of lunar mission was the photo-selenological
and chemical mapping of the Moon. Studies with high spectral and spatial
resolutions are needed to improve our understanding of the origin and
evolution of the Moon. The Chandrayaan-1 mission aimed to achieve this
goal by carrying out remote sensing observations over a wide range of the
electromagnetic spectrum for simultaneous mineralogical, chemical, and
photo-geological mapping of the lunar surface at resolutions better than
previous and contemporary lunar missions.
The Chandrayaan-1 payload had the following broad science and technology
objectives:
TMC
---
Science objectives:
- Perform systematic topographic mapping of the entire lunar surface,
including the far side and polar regions.
- Prepare a three-dimensional atlas of the Moon with high spatial and
altitude sampling for scientific studies. High-resolution imagery of
the entire Moon will help detailed study of specific lunar regions of
scientific interest and further our understanding of lunar evolution.
HYSI
----
Science objectives:
* Map the entire lunar surface in 64 contiguous band in the visible and
near-infrared from 421 to 964 nm with a spatial separation of 80 m.
* Combine these data with the study of deep craters such as the South
Pole-Aitken basin which contains surface expression of lower crustal
or upper mantle material, as well as central hills of targeted lunar
craters, to further our understanding of the mineralogical composition
of Moon's crust and its formation and evolution.
M3
--
Science objectives:
- Acquire low-resolution spectroscopic data of the entire lunar surface
at 14 m/pixel in 86 spectral channels to be used as a base-map.
- Acquire high spectral resolution data at 80 m/pixel in 260 channels.
- Perform a detailed mineral assessment of the different lunar terrains
to improve our understanding of the geologic evolution of the lunar
crust and lay a foundation for future in-depth exploration of the
Moon.
SIR
---
Science Objectives:
- Obtain high spatial and spectral resolution data to study mineralogy
of selected lunar targets (e.g., the distribution of olivine on the
central peaks of craters).
- The data will contribute to investigations of:
- The origin of the Moon and the Earth-Moon system,
- The character and evolution of the primitive lunar crust,
- The thermal evolution of the Moon and lunar volcanism, and
- The impact record and redistribution of crustal materials.
LLRI
----
Science Objectives:
- Acquire altimetry data that will accurately map topology of the Moon.
- Generate an improved model of the lunar gravitational field for better
understanding of the geophysics of the Moon.
- Use the data for significant insight into lunar evolution.
C1XS/XSM
--------
Science objectives:
- Perform global mapping of the Moon in X-rays of key rock-forming
elements (Si, Mg, Al and Fe).
- Determine the abundance of Mg across the Moon.
- Perform geochemical and stratigraphic investigations of large craters,
basins, and mare deposits, in particular the South Pole-Aitken basin.
- Evaluate of key lunar resources.
- Study the interaction of lunar plasma with the solar wind.
- Investigate Earth's X-Ray aurora and magnetotail.
- Study targets of opportunity such as comets during cruise.
- Study the long-term evolution of solar flares with XSM.
HEX
---
Science objectives:
- Study the transport of volatiles on the lunar surface through the
detection of 46.5 keV line from 210Pb decay which is a product
of volatile 222Rn, both belonging to the 238U decay series.
- Perform spectral studies at hard X-ray energies (30 to 270 keV)
using solid state detectors with good energy resolution.
SARA
----
Science objectives:
- Map the elemental composition of the lunar surface including the
permanently shadowed areas.
- Directly image the magnetic anomalies of the lunar surface (in
sputtered and backscattered LENAs).
- Study the processes of space weathering.
- Study the sputtering sources of the exospheric gases.
Mini-SAR
--------
Science objectives:
- Map a previously unknown region of the Moon and collect information
relevant to the possible existence of water/ice.
- Collect information about the scattering properties of the permanently
dark areas near the lunar poles at optimum viewing geometry and map
the terrain of these areas which are invisible to normal imaging
sensors.
MIP
---
Science objectives:
- Land in the south polar region of the Moon, an area of prime
interest from both lunar science and lunar resource perspectives.
- Demonstrate technologies useful for future landing mission and perform
a novel scientific experiment to measure the tenuous composition of
the lunar day side.
- Perform detailed remote sensing studies of the Moon at various
wavelengths across the electromagnetic spectrum.
RADOM
------
Scientific objectives:
- Monitor the radiation environment en route and during lunar orbit.
- Measure the amount of radiation absorbed due to energetic particles
of galactic and solar origins.
- Monitor the effect of solar particle events to assess the dose
received by the spacecraft and estimate the same for future, long-
duration missions to the Moon.
Ground Segment Overview
=======================
The Chandrayaan-1 ground segment can be subdivided into four main
entities: the Mission Operations Complex (MOX), Ground Stations Network
(GSN), Indian Space Science Data Centre (ISSDC), and Payload Operations
Centre (POC).
Mission Operations Complex
--------------------------
The MOX was located at Peenya campus of ISTRAC in Bangalore, India. All
phases of mission operations for Chandrayaan-1 were executed from the
MOX, and it provided facilities such as the Main Control Room, the
Mission Analysis Room, Mission Planning and Flight Dynamics, the Mission
Scheduling and Payload Scheduling Facility. Mission and spacecraft
specialists along with the operations crew from ISTRAC carried out
operations from the MOX.
Ground Stations Network
-----------------------
The Telemetry, Tracking and Command (TTC) functions, which are nearly
continuous health monitoring as well as commanding and tracking data
collection, were performed by a comprehensive network of ground
stations. For the orbit raising phase, the TTC functions were executed
by ground stations at ISTRAC network (Bangalore, Mauritius, Port Blair,
Brunei, Biak, Trivandrum), USN (Hawaii), INPE (Alcantara, Cuiaba), JPL
DSN (Goldstone, Canberra, and Madrid), and APL (Maryland). After the
100,000-km cross-over, IDSN (Bangalore-D18, D32), JPL DSN (Goldstone,
Canberra, and Madrid), and APL were used both for TTC functions and for
science data collection.
Indian Space Science Data Centre
--------------------------------
The Indian Space Science Data Centre (ISSDC) is the infrastructure which
facilitated science data processing, archival, and dissemination
functions for scientists. The data transfer system at ISSDC, with
suitable security systems, provided for the distribution of science data
(as per the data policy) to the concerned institutions. Level-0 and
Level-1 data products from the instruments, as applicable, were
routinely produced at ISSDC. The computer networking at ISSDC catered
to connectivity to the IDSN operations facility, the MOX, and the POCs.
Payload Operations Centres
--------------------------
Within India, the POCs were the Space Applications Centre (SAC) in
Ahmedabad (TMC, HySI, MIS), the ISRO Satellite Centre (ISAC) in
Bangalore (C1XS, HEX, LLRI), and the Vikram Sarabhai Space Center (VSSC)
in Trivandrum (SARA, MIP). The POCs were responsible for the analysis
of science data, providing quality information at the ISSDC and the MOX,
generation of higher level products, advising the Satellite Control
Centre (SCC) on any operations requirements and command needs, providing
calibration support and updates when necessary, and providing adequate
support for the life cycle maintenance of the software provided to the
ISSDC.
Acronym List
============
AOCE Attitude and Orbit Control Electronics
AOCS Attitude and Orbit Control System
APL Applied Physics Laboratory
BDH Baseband Data Handling
BMU Bus Management Unit
BPSK Binary Phase Shift Keying
CASS Coarse Analog Sun Sensor
CCD Charge Coupled Device
CCSDS Consultative committee for Space Data Systems
CENA Chandrayaan-1 Energetic Neutral Analyzer
CIXS Chandrayaan-1 Imaging X-ray Spectrometer
DGA Dual Gimbal Antenna
DTG Dynamically Tuned Gyroscope
DSN Deep Space Network
EBN Earth Bound maneuver Number
GSN Ground Station Network
H/W Hardware
HEX High Energy X-ray Spectrometer
HySI Hyper Spectral Imager
IAC Inertial Attitude Control
IDSN Indian Deep Space Network
INPE National Institute for Space Research in Brazil
ISAC ISRO Satellite Centre
ISRO Indian Space Research Organization
ISSDC Indian Space Science Data Centre
ISTRAC ISRO Telemetry, Tracking network
I/F Interface
JPL Jet Propulsion Laboratory
LBN Lunar Bound maneuver Number
LLRI Lunar Laser Ranging Instrument
LOI Lunar Orbit Insertion
LRO Lunar Reconnaissance Orbiter
LTT Lunar Transfer Trajectory
M3 Moon Mineralogy Mapper
MIP Moon Impact Probe
MLI Multi Layer Insulation
MOX Mission Operations Complex
Mini-SAR Miniaturized Synthetic Aperture Radar
RADOM Radiation Dose Monitor
POC Payload Operation Centre
PM Phase Modulation
PSK Phase Shift Key
PSLV Polar Satellite Launch Vehicle
TCM Trajectory Correction Maneuver
TMC Terrain Mapping Camera
SAC Space Applications Centre
SADA Solar Array Drive Assembly
SARA Sub-keV Atom Reflecting Analyzer
SCC Satellite Control Centre
SDSC Satish Dhawan Space Center
SIR-2 Short wave Infrared Radiometer
SPSS Solar Panel Sun Sensor
SSR Solid State Recorder
SWIM Solar Wind Monitor
TTC Telemetry, Tracking and Command
USN Universal Space Network, Inc.
VSSC Vikram Sarabhai Space Center
XSM Solar X-ray Monitor
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