Chandrayaan-1 Mission To The Moon
- Paper number
IAC-07-A3.6.A.02
- Author
Prof. Jitendra Goswami, Physical Research Laboratory, India
- Coauthor
Mr. Mylswamy Annadurai, Indian Space Research Organisation (ISRO), ISAC, India
- Year
2007
- Abstract
The Chandrayaan-1 mission to the Moon is the first Indian planetary exploration mission. The primary scientific objective of this mission, scheduled for launch in early 2008, is to further our understanding of the origin and evolution of the Moon based on high resolution selenological and chemical mapping of the Moon. A suite of baseline payloads, identified to meet this scientific objective, include a Terrain Mapping Camera (TMC), a Hyper-Spectral Imager (HySI), a Low Energy X-ray Spectrometer (LEX), a High Energy X-gamma ray Spectrometer (HEX) and a Lunar Laser Ranging Instrument (LLRI). These will provide simultaneous mineralogical, chemical and photo-geological mapping of the lunar surface at resolutions better than previous and currently planned lunar missions. They will allow (i) direct estimation of lunar surface concentration of the elements Mg, Al, Si, Ca, Ti and Fe with high spatial resolution (~20 km), (ii) High resolution (~100m) UV-VIS-NIR mapping of the lunar surface to identify abundances of various lunar minerals, (iii) High resolution 3D mapping of the lunar surface, and (iv) nature of volatile transport on moon, particularly to colder lunar polar regions. ISRO also offered opportunity to the international scientific community to participate in Chandrayaan-1 mission and several AO payloads were selected to enhance the overall scientific content of the mission. These include two infrared spectrometers (SIR-2 and Moon Mineral Mapper: MMM) for extending the range beyond that of the hyperspectral imager, a low-energy X-ray Spectrometer (CIXS) for high resolution chemical mapping, a sub-keV atom reflecting analyzer (SARA) for detection of low energy neutral atoms and studies of lunar surface magnetic anomalies, a miniature imaging radar instrument (Mini-SAR) to explore the polar regions of the moon to look for possible presence of water ice and a radiation dose monitor (RADOM) for monitoring energetic particle flux in the lunar environment. ESA will support development of CIXS, SIR-2 and SARA payload, while MMM and mini-SAR will be provided by NASA. There will be significant Indian contribution in the development of the CIXS and SARA payloads. RADOM will be provided by the Bulgarian Academy of Sciences. In addition to the primary scientific payloads an impactor carrying a high sensitive mass spectrometer, a video camera and a radar altimeter will also be a part of the overall payload system. The impactor will be released at the beginning of the mission to land it in a predetermined location on the lunar surface. The spacecraft design is adopted from flight proven Indian Remote Sensing Satellite bus coupled with suitable modifications specific to the lunar mission. Apart from the solar array, TTC and data trans-mission that are specific to lunar mission, other aspects of system design have flight heritage. The Chandrayaan-1 mission will be implemented using an advanced version of the indigenous Polar Satellite Launching Vehicle (PSLV-XL) that will place the 1 ton class lunar-craft into an elliptical transfer orbit and subsequently into a lunar transfer trajectory. Lunar orbit insertion maneuver will finally place the spacecraft into an eccentric orbit around the moon that will be trimmed to achieve 100 km circular polar orbit. The planned lifetime of the mission is two years.
- Abstract document
- Manuscript document
IAC-07-A3.6.A.02.pdf (🔒 authorized access only).
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