CHANDRAYAAN

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CONTENTS INTRODUCTION EXPLORATION OF THE MOON SCIENTIFIC OBJECTIVES MISSION OBJECTIVES PAYLOADS LAUNCH VEHICLE GROUND SEGMENT SPACE CENTRES PARTICIPATING IN MISSION DAY TO DAY APPROACHES CONCLUSION

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INTRODUCTION

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EXPLORATION OF THE MOON Started with the advent of the space age and the decades of sixties and seventies saw a myriad of successful unmanned and manned missions to moon. Using the moon as a platform for further exploration of the solar system as well as the earth. The idea of undertaking an Indian scientific mission to Moon was initially mooted in a meeting of the Indian Academy of Sciences in 1999,as a result National Lunar Mission Task Force was constituted. Lots of studies were conducted by the scientists of the NLMTF and with its initial result, Government of India approved ISRO's proposal for the first Indian Moon Mission, called Chandrayaan-1 in November 2003.

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SCIENTIFIC OBJECTIVES To prepare a three-dimensional atlas (with high spatial and altitude resolution of 5-10 m) of both near and far side of the moon. To conduct chemical and mineralogical mapping of the entire lunar surface for distribution of mineral and chemical elements such as Magnesium, Aluminum, Silicon, Calcium, Iron and Titanium as well as high atomic number elements such as Radon, Uranium & Thorium with high spatial resolution. The Simultaneous photo geological, mineralogical and chemical mapping through Chandrayaan-1 mission will enable identification of different geological units to infer the early evolutionary history of the Moon.

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MISSION OBJECTIVES To realize the mission goal of harnessing the science payloads, lunar craft and the launch vehicle with suitable ground support systems including Deep Space Network (DSN) station. To realize the integration and testing, launching and achieving lunar polar orbit of about 100 km, in-orbit operation of experiments, communication/ tele command, telemetry data reception, quick look data and archival for scientific utilization by scientists.

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SPACE CRAFT Cuboids in shape of approximately 1.5 m side. Weighing 1380 kg at launch and 675 kg at lunar orbit. Accommodates eleven science payloads. After deployment, the solar panel plane is canted by 30º to the spacecraft pitch axis. The spacecraft employs a X-band, 0.7m diameter parabolic antenna for payload data transmission. The antenna employs a dual gimbals’ mechanism to track the earth station when the spacecraft is in lunar orbit. The propulsion system carries required propellant for a mission life of 2 years, with adequate margin. The spacecraft has three Solid State Recorders (SSRs) Onboard to record data from various payloads. SSR-1 will store science payload data and has capability of storing 32Gb data. SSR-2 will store science payload data along with spacecraft attitude information (gyro and star sensor), satellite house keeping and other auxiliary data. The storing capacity of SSR-2 is 8Gb. M3 (Moon Mineralogy Mapper) payload has an independent SSR with 10 GB capacity.

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PAYLOADS 1. Terrain Mapping Camera (TMC) 2. Hyper Spectral Imager (HySI) 3. Lunar Laser Ranging Instrument (LLRI) 4. High Energy X-ray Spectrometer (HEX) 5. Moon Impact Probe (MIP) 6. Chandrayaan-1 X-ray Spectrometer (C1XS) 7. Near-IR Spectrometer (SIR-2) 8. Sub keV Atom Reflecting Analyzer (SARA) 9. Radiation Dose Monitor Experiment (RADOM ) 10. Miniature Synthetic Aperture Radar (Mini-SAR) 11. Moon Mineralogy Mapper (M3)

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PAYLOADS Scientific Objective: The aim of TMC is to map topography of both near and far side of the Moon and prepare a 3-dimensional atlas with high spatial and elevation resolution of 5 m. Terrain Mapping Camera (TMC) The TMC will image in the panchromatic spectral region of 0.5 to 0.85 µm, with a spatial/ ground resolution of 5 m and swath coverage of 20 km. TMC uses Linear Active Pixel Sensor (APS) detector with in-built digitizer. Single refractive optics will cover the total field of view for the three detectors. The output of the detector will be in digitized form Payload Configuration details: TMC payload is developed by ISRO

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PAYLOADS Terrain Mapping Camera (TMC)

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PAYLOADS 2. Hyper Spectral Imager (HySI) Scientific Objective: To obtain spectroscopic data for mineralogical mapping of the lunar surface. The data from this instrument will help in improving the available information on mineral composition of the surface of Moon. Payload Configuration details: The uniqueness of the HySI is in its capability of mapping the lunar surface in 64 contiguous bands in the VNIR, the spectral range of 0.4-0.95 µm region with a spectral resolution of better than 15 nm and spatial resolution of 80 m, with swath coverage of 20 km. HySI will collect the Sun’s reflected light from the Moon’s surface through a tele-centric refractive optics and focus on to an APS area detector for this purpose. HySI payload is developed by ISRO

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PAYLOADS 2. Hyper Spectral Imager (HySI)

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PAYLOADS 3. Lunar Laser Ranging Instrument (LLRI) The elevation map of the Moon prepared using the laser ranging instrument carried onboard Chandrayaan-1 spacecraft will help in studying the morphology of large basins and other lunar features, study stress, strain and flexural properties of the lithosphere and when coupled with gravity studies. Scientific Objective: To provide ranging data for determining the height difference between the spacecraft and the lunar surface Payload Configuration details: LLRI works on the time-Of-Flight (TOF) principle. In this method, a coherent pulse of light from a high power laser is directed towards the target whose range is to be measured. A fraction of the light is scattered back in the direction of the laser source where an optical receiver collects it and focuses it on to a photoelectric detector. LLRI payload is developed by ISRO

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PAYLOADS 3. Lunar Laser Ranging Instrument (LLRI)

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PAYLOADS 4. High Energy X-ray Spectrometer (HEX) The High-Energy X-ray spectrometer covers the hard X-ray region from 30 keV to 270 keV. This is the first experiment to carry out spectral studies of planetary surface at hard X-ray energies using good energy resolution detectors. To identify excess 210Pb in lunar Polar Regions deposited there as a result of transport of gaseous 222Rn, a decay product of 238U from other regions of the Moon. This will enable us to understand transport of other volatiles such as water to the Polar Regions. To detect other radioactive emissions, to characterize various lunar terrains for their chemical and radioactive composition on the basis of specific/integrated signal in the 30-270 keV region. To explore the possibility of identifying Polar Regions covered by thick water-ice deposit from a study of the continuum background. Scientific Objective:

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PAYLOADS 4. High Energy X-ray Spectrometer (HEX) HEX payload developed by ISRO

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PAYLOADS 5. Moon Impact Probe (MIP) The impact probe of 35 kg mass will be attached at the top deck of the main orbiter and will be released during the final 100 km x 100 km orbit at a predetermined time to impact at a pre-selected location. During the descent phase, it is spin-stabilized. The total flying time from release to impact on Moon is around 25 minutes. . Design, development and demonstration of technologies required for impacting a probe at the desired location on the Moon. . Qualify technologies required for future soft landing missions. . Scientific exploration of the Moon from close range. Major Objective:

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PAYLOADS 5. Moon Impact Probe (MIP) Payload Configuration details: There are three instruments on the Moon Impact Probe: Radar Altimeter – for measurement of altitude of the Moon Impact Probe and for qualifying technologies for future landing missions. The operating frequency band is 4.3 GHz ± 100 MHz. Video Imaging System – for acquiring images of the surface of the Moon during the descent at a close range. The video imaging system consists of analog CCD camera. Mass Spectrometer – for measuring the constituents of tenuous lunar atmosphere during descent. This instrument will be based on a state-of-the-art, commercially available Quadrupole mass spectrometer with a mass resolution of 0.5 amu and sensitivities to partial pressure of the order of 10-14 torr.

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PAYLOADS 5. Moon Impact Probe (MIP) MIP System Configuration The Moon Impact Probe (MIP) essentially consists of honeycomb structure, which houses all the subsystems and instruments. In addition to the instruments, the separation system, the de-boost spin and de-spin motors, it comprises of the avionics system and thermal control system. The avionics system supports the payloads and provides communication link between MIP and the main orbiter, from separation to impact and provides a database useful for future soft landing. MIP payload is developed by ISRO

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PAYLOADS 5. Moon Impact Probe (MIP)

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PAYLOADS 6. Chandrayaan-1 X-ray Spectrometer (C1XS) Scientific Objective: The primary goal of the C1XS instrument is to carry out high quality X-ray spectroscopic mapping of the Moon, in order to constrain solutions to key questions on the origin and evolution of the Moon. C1XS will use X-ray fluorescence spectrometry (1.0-10 keV) to measure the elemental abundance, and map the distribution, of the three main rock forming elements: Mg, Al and Si.

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Payload Configuration details: 6. Chandrayaan-1 X-ray Spectrometer (C1XS) PAYLOADS The instrument utilizes technologically innovative Swept Charge Device (SCD) X-ray sensors, which are mounted behind low profile gold/copper collimators and aluminium/polycarbonate thin film filters. The system has the virtue of providing superior X-ray detection, spectroscopic and spatial measurement capabilities, while also operating at near room temperature. A deployable proton shield protects the SCDs during passages through the Earth’s radiation belts, and from major particle events in the lunar orbit.

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PAYLOADS 6. Chandrayaan-1 X-ray Spectrometer (C1XS)

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PAYLOADS 6. Near-IR Spectrometer (SIR-2) Scientific Objective: SIR-2 will address the surface-related aspects of lunar science in the following broad categories: Analyze the lunar surface in various geological/ mineralogical and topographical units; Study the vertical variation in composition of crust; Investigate the process of basin, mania and crater formation on the Moon; Explore “Space Weathering” processes of the lunar surface; Survey mineral lunar resources for future landing sites and exploration.

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PAYLOADS 7. Near-IR Spectrometer (SIR-2) Payload Configuration details: SIR-2 is a grating NIR point spectrometer working in the 0.93-2.4 microns wavelength range with 6 nm spectral resolution. It collects the Sun’s light reflected by the Moon with the help of a main and a secondary mirror. This light is fed through an optical fiber to the instrument’s sensor head, where it is reflected off a dispersion grating. The dispersed light reaches a detector, which consists of a row of photosensitive pixels that measure the intensity as a function of wavelength and produces an electronic signal, which is read out and processed by the experiment’s electronics. SIR-2 is developed by the Max-Planck-Institute for Solar System Science, through the Max-Planck Society, Germany and ESA

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PAYLOADS 7. Near-IR Spectrometer (SIR-2)

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PAYLOADS 8. Sub keV Atom Reflecting Analyzer (SARA) Scientific Objective: SARA will image the Moon surface using low energy neutral atoms as diagnostics in the energy range 10eV - 3.2 keV to address the following scientific objectives: Imaging the Moon’s surface composition including the permanently shadowed areas and volatile rich areas Imaging the solar wind-surface interaction Imaging the lunar surface magnetic anomalies Studies of space weathering

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PAYLOADS 8. Sub keV Atom Reflecting Analyzer (SARA)

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PAYLOADS 9. Radiation Dose Monitor Experiment (RADOM ) Scientific Objective: RADOM will qualitatively and quantitatively characterize the radiation environment in near lunar space, in terms of particle flux, dose rate and deposited energy spectrum. The specific objectives are Measure the particle flux, deposited energy spectrum, accumulated radiation dose rates in Lunar orbit; Provide an estimate of the radiation dose around the Moon at different altitudes and latitudes; Study the radiation hazards during the Moon exploration. Data obtained will be used for the evaluation of the radiation environment and the radiation shielding requirements of future manned Moon missions.

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PAYLOADS 9. Radiation Dose Monitor Experiment (RADOM )

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PAYLOADS 10. Miniature Synthetic Aperture Radar (Mini-SAR) To detect water ice in the permanently shadowed regions on the Lunar poles, up to a depth of a few meters. Scientific Objective:

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PAYLOADS 11. Moon Mineralogy Mapper (M3) Scientific Objective: The primary Science goal of M3 is to characterize and map lunar surface mineralogy in the context of lunar geologic evolution. This translates into several sub-topics relating to understanding the highland crust, basaltic volcanism, impact craters, and potential volatiles. These M3 goals translate directly into the following requirements: Accurate measurement of diagnostic absorption features of rocks and minerals; High spectral resolution for disconsolation into mineral components; High spatial resolution for assessment geologic context and active processes;

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PAYLOADS 11. Moon Mineralogy Mapper (M3)

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LAUNCH VEHICLE The Indian Space Research Organization (ISRO) built its first Polar Satellite Launch Vehicle (PSLV) in the early 90s. The 45 m tall PSLV with a lift-off mass of 295 tones, had its maiden success on October 15, 1994, when it launched India's IRS-P2 remote sensing satellite into a Polar Sun Synchronous Orbit (SSO) of 820 km altitude. Since its first successful launch in 1994, PSLV has launched nine Indian Remote Sensing satellites as well as two micro satellites HAMSAT and IMS-1 built by ISRO, a recoverable space capsule SRE-1, and fourteen small satellites for foreign customers into polar Sun Synchronous Orbits. PSLV has four stages, using solid and liquid propulsion systems alternately. Six strap-on motors augment the first stage thrust. PSLV-XL is the upgraded version of PSLV. In PSLV-XL, the six strap-on motors carry 4 tones more propellant compared to PSLV. There is also an increase in the length of each strap-on Polar Satellite Launch Vehicle

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LAUNCH VEHICLE Polar Satellite Launch Vehicle

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GROUND SEGMENT GROUND SEGMENT FOR CHANDRAYAAN-1 MISSION Indian Deep Space Network (IDSN), Mission Operations Complex (MOX) and Indian Space Science Data Centre (ISSDC).

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GROUND SEGMENT Indian Deep Space Network (IDSN) The Indian Deep Space Network consists of a 18-m and a 32-m antennae that are established at the IDSN campus, Byalalu, Bangalore. The Network is augmented with a couple of stations in the western hemisphere in addition to the 64-m antenna in Bearslake, Russia to improve the visibility duration and to provide support from the antipodal point. The existing ISTRAC S-Band Network stations will be used to support the mission during Launch and Early Orbit Phase (LEOP) that includes Earth Transfer Orbit (ETO) up to a range of about 1,00,000 km. Although the 18-m antenna is tailored for Chandrayaan-1 mission, the 32-m antenna can also support other planetary missions.

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GROUND SEGMENT Indian Deep Space Network (IDSN) 18-m Antenna The 18-m dish antenna is configured for Chandryaan-1 mission operations and payload data collection. The antenna is established at the IDSN Campus, Byalalu, situated at the outskirts of Bangalore with built in support facilities. A fibre optic / satellite link will provide the necessary communication link between the IDSN Station and Mission Operations Complex (MOX) / Indian Space Science Data Centre (ISSDC). This antenna is capable of S-Band uplink (2 kW) and both X-Band and S-Band downlink.

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GROUND SEGMENT Indian Deep Space Network (IDSN) 32-m Antenna The wheel and track 32-m antenna is a state-of-the-art system that will support the Chandrayaan-1 mission operations and beyond. This is co-located with 18-m antenna in the IDSN site at Byalalu. A fibre optics / satellite link will provide the necessary connectivity between the IDSN site and Spacecraft Control Centre / Network Control Centre. This antenna is designed to provide uplink in both S-Band (20/2 kW) and X-Band (2.5 kW).

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GROUND SEGMENT Indian Deep Space Network (IDSN) External Network Stations External network stations APL, JPL (Goldstone, Canberra, Madrid), Hawaii, Brazil (Alcantara, Cuiaba) are requisitioned in for the purpose of extended visibility of Launch and Early Orbit Phase (LEOP) operations, as well as to gain the near continuous visibility during the normal phase operations.

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GROUND SEGMENT Mission Operations Complex (MOX) The nerve centre for this Moon Mission will be the Mission Operations Complex, situated within the ISTRAC campus, Bangalore. The MOX will be responsible for all spacecraft operations during various phases of the mission viz. pre-launch, launch and early orbit phase, normal phase and terminal phase, as well as for the health monitoring of the spacecraft and payloads. MOX is authorized for up linking of commands for change of onboard configuration, payload operations and conduction of maneuvers as required.

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GROUND SEGMENT Mission Operations Complex (MOX) ISTRAC Network Control Centre (NCC) NCC enables remote monitoring and control of all ISTRAC Ground Stations including IDSN and it is located in Peenya, Bangalore Campus. NCC also facilitates Data Service from all stations through Standard Station Computers, SLE Gateway or any other agency specific data interface through external station computers. The payload data acquisition system at IDSN also interfaces with NCC for obtaining the payload operations schedule. The multi-mission schedule system of ISTRAC provides the required schedules to NCC for day-to-day operations.

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GROUND SEGMENT Indian Space Science Data Centre (ISSDC) Indian Space Science Data Center (ISSDC) is a new facility being established by ISRO, as the primary data center for the payload data archives of Indian Space Science Missions. This data center, located at the Indian Deep Space Network (IDSN) campus in Bangalore, is responsible for the ingestion, archive, and dissemination of the payload data and related ancillary data for Space Science missions. The principal investigators of the science payloads as well as scientists from other institutions and general public will use this facility. Payload data from the satellites will be received at the data reception stations and subsequently transferred to ISSDC for further processing

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SPACE CENTRES PARTICIPATING IN THE CHANDRAYAAN-1 MISSION Indian Groups ISRO Headquarters, Bangalore ISRO Satellite Centre (ISAC), Bangalore ISRO Inertial Systems Unit (IISU), Thiruvananthapuram ISRO Telemetry, Tracking and Command Network (ISTRAC), Bangalore Laboratory for Electro-Optics Systems (LEOS), Bangalore Liquid Propulsion Systems Center (LPSC) Bangalore & Mahendragiri National Remote Sensing Agency (NRSA), Hyderabad Physical Research Laboratory (PRL), Ahmedabad Space Physics Laboratory (SPL), VSSC, Thiruvananthapuram Satish Dhawan Space Centre (SDSC), SHAR, Sriharikota Space Applications Centre (SAC), Ahmedabad Vikram Sarabhai Space Centre (VSSC), Thiruvananthapuram

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SPACE CENTRES PARTICIPATING IN THE CHANDRAYAAN-1 MISSION International Groups Applied Physics Lab, Johns Hopkins University, MD, USA Brown University, USA Centre d'Etude Spatiale des Rayonnements, Toulouse, France European Space Agency (ESA) Institute for Radiological Protection and Nuclear Safety, France Institute of Space and Astronautically Science, (ISAS/JAXA), Japan Jet Propulsion Laboratory, USA Max Planck Institute for Solar System Science, Lindau, Germany National Aeronautics and Space Administration (NASA) Naval Air Warfare Centre, Chinalake, CA, USA Nuclear Physics Institute, Czech Academy of Sciences Rutherford Appleton Laboratory, UK Solar-Terrestrial Influences Laboratory, Bulgarian Academy Swedish Institute of Space Physics, Kiruna, Sweden University of Bern, Switzerland University of Helsinki, Finland

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DAY TO DAY APPROACHES BY CHANDRAYAAN-I October 22, 2008   -- PSLV-C11 Successfully Launches Chandrayaan-1 October 23, 2008 -- Chandrayaan-1 Spacecraft’s Orbit Raised October 25, 2008 -- Chandrayaan-1 Spacecraft’s Orbit Raised Further October 26, 2008 -- Chandrayaan-1 enters Deep Space October 29, 2008 -- Chandrayaan-1’s Orbit Closer to Moon October 31, 2008 -- Chandrayaan-1 Camera Tested November 4, 2008   -- Chandrayaan-1 enters Lunar Transfer Trajectory November 8, 2008   -- Chandrayaan-1 Successfully Enters Lunar Orbit November 10, 2008   First Lunar Orbit Reduction Manoeuvre of Chandrayaan-1 Successfully Carried Out

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CONCLUSION