Chandrayaan-1
Chandrayaan-1, India's first mission to Moon, was launched successfully on October 22, 2008 from SDSC SHAR, Sriharikota. The spacecraft was orbiting around the Moon at a height of 100 km from the lunar surface for chemical, mineralogical and photo-geologic mapping of the Moon. The spacecraft carried 11 scientific instruments built in India, USA, UK, Germany, Sweden and Bulgaria.
After the successful completion of all the major mission objectives, the orbit has been raised to 200 km during May 2009. The satellite made more than 3400 orbits around the moon and the mission was concluded when the communication with the spacecraft was lost on August 29, 2009.
प्रमोचन भार / Launch Mass: 1380 kg
मिशन कालावधि / Mission Life : 2 years
शक्ति / Power: 700 W
प्रमोचक राकेट / Launch Vehicle: PSLV-C11
उपग्रह का प्रकार / Type of Satellite: Science & Exploration
निर्माता / Manufacturer: ISRO
स्वामी / Owner: ISRO
अनुप्रयोग / Application: Planetary Observation
कक्षा का प्रकार / Orbit Type: Lunar.
mission Remote Sensing, planetary Since
Weight 1380 kg (Mass at lift off )
Onboard 700 Watts
power
Stabilization 3- axis Stabilization using reaction wheel and attitude control thrusters, sun senso fiber gyros and accelerometers for attitude determination.
Payloads Scientific Payloads from India
(a) Terrain Mapping camera (TMC)
(b) Hyper spectral imager (HySl)
(c) Lunar Laser Ranging Instrument (LLRI)
(d) High Energy X-ray spectrometer (HEX)
(e) Moon impact Probe (MIP)
Scientific Payloads from abroad
(f) Chandrayaan-1 X-ray spectrometer(CIXS)
(g) Near infrared spectrometer (SIR – 2)
(h) Sub keV Atom Reflection Analyzer (SARA)
(i) Miniature synthetic Aperature Radar (Mini SAR)
(j) Mon Mineralogy Mapper (M3)
(k) Radiation Dose Monitor (RADOM)
Launch Date 22 October 2008
Launch site SDSC, SHAR, Sriharikota
Launch vehicle PSLV – C11
Orbit 100km X 100 km: Lunar Orbit
Mission 2 years
CHANDRAYAAN - 2
Chandrayaan-2
mission is a highly complex mission, which represents a significant
technological leap compared to the previous missions of ISRO. It comprised an
Orbiter, Lander and Rover to explore the unexplored South Pole of the Moon.
After
the injection of Chandrayaan-2, a series of maneuvers were carried out to raise
its orbit and on August 14, 2019, following Trans Lunar Insertion (TLI)
maneuver, the spacecraft escaped from orbiting the earth and followed a path
that took it to the vicinity of the Moon. On August 20, 2019, Chandrayaan-2 was
successfully inserted into lunar orbit.
The
Orbiter placed in its intended orbit around the Moon will enrich our
understanding of the moon’s evolution and mapping of the minerals and water
molecules in Polar regions, using its eight state-of-the-art scientific
instruments. The Orbiter camera is the highest resolution camera (0.3 m) in any
lunar mission so far and will provide high resolution images which will be
immensely useful to the global scientific community.
Orbiter
weight
Electric Power
Generation Capability
Lander —
Vikram
weight
Electric Power
Generation Capability
650 W
Rover —
Pragyan
weight
Electric Power
Generation Capability
Key payloads
Chandrayaan 2
Large Area Soft X-ray Spectrometer
Elemental composition of the moon
Imaging IR
spectrometer
Mineralogy mapping and water –ice confirmation
Synthetic
Aperture Radar L & S Band
Polar-region mapping and sub-surface water-ice confirmation
Orbiter High
Resolution camera
High-resolution topography mapping
Chandra’s
Surface Thermo-physical Experiment
Thermal conductivity and temperature gradient
Alpha particle
X-ray Spectrometer and Laser Induced Breakdown spectroscope
In-situ elemental analysis and abundance in the vicinity of landing
site
Chandrayaan-3 is a follow-on mission to Chandrayaan-2 to demonstrate end-to-end capability in safe landing and roving on the lunar surface. It consists of Lander and Rover configuration. It will be launched by LVM3 from SDSC SHAR, Sriharikota. The propulsion module will carry the lander and rover configuration till 100 km lunar orbit. The propulsion module has Spectro-polarimetry of Habitable Planet Earth (SHAPE) payload to study the spectral and Polari metric measurements of Earth from the lunar orbit.
Lander payloads: Chandra’s Surface Thermophysical Experiment (ChaSTE) to measure the thermal conductivity and temperature; Instrument for Lunar Seismic Activity (ILSA) for measuring the seismicity around the landing site; Langmuir Probe (LP) to estimate the plasma density and its variations. A passive Laser Retroreflector Array from NASA is accommodated for lunar laser ranging studies.
Rover payloads: Alpha Particle X-ray Spectrometer (APXS) and Laser Induced Breakdown Spectroscope (LIBS) for deriving the elemental composition in the vicinity of landing site.
SR No. | Parameter | Specifications |
---|---|---|
1. | Mission Life (Lander & Rover) | One lunar day (~14 Earth days) |
2. | Landing Site (Prime) | 4 km x 2.4 km 69.367621 S, 32.348126 E |
3. | Science Payloads | Lander:
|
4. | Two Module Configuration |
|
5. | Mass |
|
6. | Power generation |
|
7. | Communication |
|
8. | Lander Sensors |
|
9. | Lander Actuators | Reaction wheels – 4 nos (10 Nms & 0.1 Nm) |
10. | Lander Propulsion System | Bi-Propellant Propulsion System (MMH + MON3), 4 nos. of 800 N Throttleable engines & 8 nos. of 58 N; Throttleable Engine Control Electronics |
11. | Lander Mechanisms |
|
12. | Lander Touchdown specifications |
|
The objectives of scientific payloads planned on Chandrayaan-3 Lander Module and Rover are provided below:
Sl. No | Lander Payloads | ||
---|---|---|---|
1. | Radio Anatomy of Moon Bound Hypersensitive ionosphere and Atmosphere (RAMBHA) | Langmuir probe (LP) | To measure the near surface plasma (ions and electrons) density and its changes with time |
2. | Chandra’s Surface Thermo physical Experiment (ChaSTE) | To carry out the measurements of thermal properties of lunar surface near polar region. | |
3. | Instrument for Lunar Seismic Activity (ILSA) | To measure seismicity around the landing site and delineating the structure of the lunar crust and mantle. | |
4. | LASER Retroreflector Array (LRA) | It is a passive experiment to understand the dynamics of Moon system. |
1. | LASER Induced Breakdown Spectroscope (LIBS) | Qualitative and quantitative elemental analysis & To derive the chemical Composition and infer mineralogical composition to further our understanding of Lunar-surface. |
2. | Alpha Particle X-ray Spectrometer (APXS) | To determine the elemental composition (Mg, Al, Si, K, Ca,Ti, Fe) of Lunar soil and rocks around the lunar landing site. |