Chandrayaan-1 Mission Description Extracted from PDS3 Mission Catalog File. Mission Information =================== Mission Name: Chandrayaan-1 Mission Start Date = 2008-10-22 Mission Stop Date = 2009-08-28 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. 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: 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 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 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