Chandrayaan-2 (pronunciation; from Sanskrit: Chandra, "Moon" and yāna, "craft, vehicle") is the second lunar exploration mission developed by the Indian Space Research Organisation (ISRO) after Chandrayaan-1. It consists of a lunar orbiter, the Vikram lunar lander, and the Pragyan rover, all of which were developed in India. The main scientific objective is to map and study the variations in lunar surface composition, as well as the location and abundance of lunar water.

The spacecraft was launched from the second launch pad at the Satish Dhawan Space Centre in Andhra Pradesh on 22 July 2019 at 09:13:12 UTC by a LVM3-M1 rocket. The craft reached lunar orbit on 20 August 2019. The Vikram lander attempted a lunar landing on 6 September 2019; the lander crashed due to a software error.

The lunar orbiter continues to operate in orbit around the Moon. A follow-up landing mission, Chandrayaan-3, was launched in 2023 and successfully performed a lunar landing.

On 12 November 2007, representatives of the Roscosmos and ISRO signed an agreement for the two agencies to work together on the Chandrayaan-1's follow-up project, Chandrayaan-2. ISRO would have the prime responsibility for the orbiter, rover and the launch by GSLV, while Roscosmos was to provide the lander. The Indian government approved the mission in a meeting of the Union Cabinet, held on 18 September 2008 and chaired by Prime Minister Manmohan Singh. The design of the spacecraft was completed in August 2009, with scientists of both countries conducting a joint review.

Although ISRO finalised the payload for Chandrayaan-2 on schedule, the mission was postponed in January 2013 and rescheduled to 2016 because Russia was unable to develop the lander on time. In 2012, there was a delay in the construction of the Russian lander for Chandrayaan-2 due to the failure of the Fobos-Grunt mission to Mars, since the technical issues connected with the Fobos-Grunt mission which were also used in the lunar projects including the lander for Chandrayaan-2 needed to be reviewed. The changes proposed by Roscosmos necessitated increase in lander mass and required ISRO to decrease mass of its rover and accept some reliability risk. When Russia cited its inability to provide the lander even by a revised time-frame of 2015 due to technical and financial reasons, India decided to develop the lunar mission independently. With new mission timeline for Chandrayaan-2 and an opportunity for a Mars mission arising with launch window in 2013, unused Chandrayaan-2 orbiter hardware was repurposed to be used for the Mars Orbiter Mission.

Chandrayaan-2 launch had been scheduled for March 2018 initially, but was first delayed to April and then to October 2018 to conduct further tests on the vehicle. On 19 June 2018, after the program's fourth Comprehensive Technical Review meeting, a number of changes in configuration and landing sequence were planned for implementation which increased the gross lift-off mass of spacecraft from 3,250 kg to 3,850 kg. Initially an uprated GSLV Mk II was the chosen launch vehicle for Chandrayaan-2 but this increased spacecraft mass and issues with launch vehicle upratement forced the launch vehicle to be switched to more capable LVM3. Issues with engine throttling were found during testing pushing the launch to the early 2019 and later two of the lander's legs received minor damage during one of the tests in February 2019 delaying the launch even further.

Chandrayaan-2 launch was scheduled for 14 July 2019, 21:21 UTC (15 July 2019 at 02:51 IST local time), with the landing expected on 6 September 2019. However, the launch was aborted due to a technical glitch and was rescheduled. The launch occurred on 22 July 2019 at 09:13:12 UTC (14:43:12 IST) on the first operational flight of a GSLV MK III M1.

On 6 September 2019, the lander during its landing phase, deviated from its intended trajectory starting at 2.1 km (1.3 mi) altitude, and had lost communication when touchdown confirmation was expected. Initial reports suggesting a crash were confirmed by ISRO chairman K. Sivan, stating that "it must have been a hard landing". The Failure Analysis Committee concluded that the crash was caused by a software glitch. Unlike ISRO's previous record, the report of the Failure Analysis Committee has not been made public.

Chandrayaan-2 orbiter performed a collision avoidance manoeuvre at 14:52 UTC on 18 October 2021 to avert possible conjunction with Lunar Reconnaissance Orbiter. Both spacecraft were expected to come dangerously close to each other on 20 October 2021 at 05:45 UTC over the Lunar north pole.

The primary objectives of the Chandrayaan-2 lander were to illustrate the ability to soft-land and operate a robotic rover on the lunar surface.

The scientific goals of the orbiter are

• to study lunar topography, mineralogy, elemental abundance, the lunar exosphere, and signatures of hydroxyl and water ice;
• to study the water ice in the south polar region and thickness of the lunar regolith on the surface; and
• to map the lunar surface and help to prepare 3D maps of it.

The name Chandrayaan means "mooncraft" in Sanskrit and most other Indian languages. The mission was launched on a GSLV Mk III M1 with an approximate lift-off mass of 3,850 kg (8,490 lb) from Satish Dhawan Space Centre on Sriharikota Island of Andhra Pradesh. As of June 2019, the mission has an allocated cost of ₹ 9.78 billion (approximately US$141 million which includes ₹ 6 billion for the space segment and ₹ 3.75 billion as launch costs on GSLV Mk III M1. Chandrayaan-2 stack was initially put in an Earth parking orbit of 170 km (110 mi) perigee and 40,400 km (25,100 mi) apogee by the launch vehicle.

The Chandrayaan-2 orbiter is orbiting the Moon on a polar orbit at an altitude of 100 km (62 mi). It carries eight scientific instruments; two of which are improved versions of those flown on Chandrayaan-1. The approximate launch mass was 2,379 kg (5,245 lb). The Orbiter High Resolution Camera (OHRC) conducted high-resolution observations of the landing site prior to separation of the lander from the orbiter. The orbiter's structure was manufactured by Hindustan Aeronautics Limited and delivered to the ISRO Satellite Centre on 22 June 2015.

• Dimensions: 3.2 × 5.8 × 2.2 m
• Gross lift-off mass: 2,379 kg (5,245 lb)
• Propellant mass: 1,697 kg (3,741 lb)
• Dry mass: 682 kg (1,504 lb)
• Power generation capacity: 1000 watts
• Mission duration: ~ 7.5 years, extended from the planned 1 year owing to the precise launch and mission management, in lunar orbit

The mission's lander is called Vikram (Sanskrit: Vikrama, lit. 'Valour' ) Pronunciation named after cosmic ray scientist Vikram Sarabhai (1919–1971), who is widely regarded as the founder of the Indian space programme. The Vikram lander detached from the orbiter and descended to a low lunar orbit of 30 km × 100 km (19 mi × 62 mi) using its 800 N (180 lb_f) liquid main engines. After checking all of its on-board systems it attempted a soft landing that would have deployed the rover, and performed scientific activities for approximately 14 Earth days. Vikram crash-landed during this attempt. The combined mass of the lander and rover was approximately 1,471 kg (3,243 lb).

The preliminary configuration study of the lander was completed in 2013 by the Space Applications Centre (SAC) in Ahmedabad. The lander's propulsion system consisted of eight 58 N (13 lb_f) thrusters for attitude control and five 800 N (180 lb_f) liquid main engines derived from ISRO's 440 N (99 lb_f) liquid apogee motor. Initially, the lander design employed four main throttle-able liquid engines, but a centrally mounted fixed-thrust engine was added to handle new requirements of having to orbit the Moon before landing. The additional engine was expected to mitigate upward draft of lunar dust during the soft landing. The four throttle-able engines of lander were capable of throttling between range of 40 to 100 percent incrementally in steps of 20%.Vikram was designed to safely land on slopes up to 12°.

Some associated technologies include:

• A high resolution camera, Laser Altimeter (LASA)
• Lander Hazard Detection Avoidance Camera (LHDAC)
• Lander Position Detection Camera (LPDC)
• Lander Horizontal Velocity Camera (LHVC), an 800 N throttleable liquid main engine
• Attitude thrusters
• Ka-band radio altimeters
• Laser Inertial Reference and Accelerometer Package (LIRAP) and the software needed to run these components.

Engineering models of the lander began undergoing ground and aerial tests in late October 2016, in Challakere in the Chitradurga district of Karnataka. ISRO created roughly 10 craters on the surface to help assess the ability of the lander's sensors to select a landing site.

• Dimensions: 2.54 m × 2 m × 1.2 m (8 ft 4 in × 6 ft 7 in × 3 ft 11 in)
• Gross lift-off mass: 1,471 kg (3,243 lb)
• Propellant mass: 845 kg (1,863 lb)
• Dry mass: 626 kg (1,380 lb)
• Power generation capability: 650 watts
• Mission duration: ≤14 days (one lunar day)

The mission's rover was called Pragyan (Sanskrit: Prajñāna, lit. 'Wisdom' ) Pronunciation) with a mass of 27 kg (60 lb), and would have operated on solar power. The rover was to move on six wheels, traversing 500 m (1,600 ft) on the lunar surface at the rate of 1 cm (0.39 in) per second, perform on-site analyses and send the data to the lander, which would have relayed it to the Mission Control on the Earth.

For navigation, the rover would have used:

• Stereoscopic camera-based 3D vision: two 1 megapixel, monochromatic navcams in front of the rover to provide the ground control team a 3D view of the surrounding terrain, and help in path-planning by generating a digital elevation model of the terrain. IIT Kanpur contributed to the development of the subsystems for light-based map generation and motion planning for the rover.
• Control and motor dynamics: the rover has a rocker-bogie suspension system and six wheels, each driven by independent brushless DC electric motors. Steering is accomplished by differential speed of the wheels or skid steering.

The expected operating time of Pragyan rover was one lunar day, or ~14 Earth days, as its electronics were not designed to endure the frigid lunar night. However, its power system has a solar-powered sleep/wake-up cycle implemented, which could have resulted in longer service time than planned. Two aft wheels of the rover had the ISRO logo and the State Emblem of India embossed on them to leave behind patterned tracks on the lunar surface.

• Dimensions: 0.9 × 0.75 × 0.85 m
• Power: 50 watts
• Travel speed: 1 cm/sec
• Mission duration: ~14 Earth days (one lunar day)

ISRO selected eight scientific instruments for the orbiter, four for the lander, and two for the rover. While it was initially reported that NASA and European Space Agency (ESA) would participate in the mission by providing some scientific instruments for the orbiter, ISRO in 2010 had clarified that due to weight restrictions it will not be carrying foreign payloads on the mission. However, in an update a month before launch, an agreement between NASA and Indian Space Research Organisation (ISRO) was signed to include a small laser retroreflector from NASA to the lander's payload to measure the distance between the satellites above and the microreflector on the lunar surface.

The orbiter has several scientific payloads.

• The Chandrayaan-2 Large Area Soft X-ray Spectrometer (CLASS) from the ISRO Satellite Centre (ISAC), which makes use of X-ray fluorescence spectra to determine the elemental composition of the lunar surface.
• The Solar X-ray monitor (XSM) from Physical Research Laboratory (PRL), Ahmedabad, primarily supports CLASS instrument by providing solar X-ray spectra and intensity measurements as input to it. Additionally these measurements will help in studying various high-energy processes occurring in the solar corona.
• The Dual Frequency L-band and S-band Synthetic Aperture Radar (DFSAR) from the Space Applications Centre (SAC) for probing the first few metres of the lunar surface for the presence of different constituents. DFSAR is expected to provide further evidence confirming the presence of water ice, and its distribution below the shadowed regions of the Moon. It has lunar surface penetration depth of 5 m (16 ft) (L-band).
• The Imaging IR Spectrometer (IIRS) from the SAC for mapping of lunar surface over a wide wavelength range for the study of minerals, water molecules and hydroxyl present. It features an extended spectral range (0.8 μm to 5 μm), an improvement over previous lunar missions whose payloads worked up to 3 μm.
• The Chandrayaan-2 Atmospheric Compositional Explorer 2 (ChACE-2) Quadrupole Mass Analyzer from Space Physics Laboratory (SPL), designed for carry out a detailed study of the lunar exosphere.
• The Terrain Mapping Camera-2 (TMC-2) from SAC for preparing a three-dimensional map essential for studying the lunar mineralogy and geology
• The Radio Anatomy of Moon Bound Hypersensitive Ionosphere and Atmosphere – Dual Frequency Radio Science experiment (RAMBHA-DFRS) by SPL for the studying electron density in the lunar ionosphere
• The Orbiter High Resolution Camera (OHRC) by SAC for scouting a hazard-free spot prior to landing. Used to help prepare high-resolution topographic maps and digital elevation models of the lunar surface. OHRC has a spatial resolution of 0.32 m (1 ft 1 in) from 100 km (62 mi) polar orbit, which is the best resolution among any lunar orbiter mission to date.

The payloads on the Vikram lander were:

• Instrument for Lunar Seismic Activity (ILSA) MEMS based seismometer by LEOS for studying Moon-quakes near the landing site
• Chandra's Surface Thermo-physical Experiment (ChaSTE) thermal probe jointly developed by SPL, Vikram Sarabhai Space Centre (VSSC) and Physical Research Laboratory (PRL), Ahmedabad for estimating the thermal properties of the lunar surface
• RAMBHA-LP Langmuir probe by SPL, VSSC for measuring the density and variation of lunar surface plasma
• A laser retroreflector array (LRA) by the Goddard Space Flight Center for taking precise measurements of distance between the reflector on the lunar surface and satellites in lunar orbit. The microreflector weighed about 22 g (0.78 oz) and cannot be used for taking observations from Earth-based lunar laser stations.

Pragyan rover carried two instruments to determine the abundance of elements near the landing site:

• Laser induced Breakdown Spectroscope (LIBS) from the laboratory for Electro Optic Systems (LEOS), Bangalore
• Alpha Particle Induced X-ray Spectroscope (APXS) from PRL, Ahmedabad

• 
  CHACE2
• 
  XSM
• 
  CLASS
• 
  ILSA MEMS sensor package
• 
  Laser retroreflector array (LRA)
• 
  LIBS
• 
  APXS
• 
  ChaSTE

The orbiter, which is still active, did experiments on Lunar Atmospheric composition, trace elements, and more

• Detection of sodium: In October 2023, the orbiter discovered an abundance of sodium on the Moon. The moon is shown to have a tail of Sodium atoms thousands of Kilometers long. Due to phenomena like photon stimulated desorption, solar wind sputtering, and meteorite impacts, sodium atoms gets knocked off the surface. Solar radiation pressure accelerates the sodium atoms away from the Sun, forming an elongated tail toward the antisolar direction. Using the large area X-raySpectrometer, CLASS, the probe has spotted and mapped sodium on the Moon.
• Hydroxyl and Water molecules: The Chandrayaan-1 probe detected water on the Moon for the first time. Chandrayaan-2 detected Water, as well as Hydroxyl ions on the Moon, August 2022. It distinguished between these two with the aid of IIRS (Imaging Infrared Spectrometer). Between 29 and 62 degrees north latitude, the probe detected the presence of these two molecules. Along with this, it also observed that the sunlit regions contain higher concentrations of these two.
• Distribution of Gas in Lunar Atmosphere: Chandra Atmospheric Composition Explorer-2, detected Argon-40 in Lunar exosphere. The distribution of Ar-40 has significant spatial heterogeneity. The NASA probe, LADEE, detected Argon near the Equatorial region, but Argon far from that, was detected for the first time. There are localised enhancements (termed as Argon bulge) over several regions including the KREEP (potassium (K), rare-earth elements, and phosphorus (P)) and South Pole Aitken terrain.
• Presence of Rare elements: Chandra's Large Area Soft X-ray Spectrometer (CLASS), detected magnesium, aluminium, silicon, calcium, titanium, iron etc. It also examined and detected minor elements – chromium and manganese, for the first time. The findings have paved the path for adding knowledge about the magmatic evolution of the Moon, its nebular conditions and much more.
• Solar X-ray Monitor (XSM), has witnessed a huge amount of microflares outside the active regions of the Sun for the first time.
• The DFSAR instrument studied the subsurface features of the Moon, detected signatures of the sub-surface water-ice, mapped lunar morphological features in the polar regions in high resolution.
• The TMC 2, which is conducting imaging of the Moon at a global scale, found interesting geologic signatures of lunar crustal shortening, and identification of volcanic domes. The OHRC, mapped Moon With a resolution of 25 cm at 100 km altitude.
• DFRS experiment, studied the ionosphere of the Moon, which is generated by the solar photo-ionisation of the neutral species of the lunar tenuous exosphere. The experiment showed that Moon's ionosphere has a plasma density of the order of 10^4 cm^3, in the wake region which is at least one order of magnitude more than that is present in the day side.

The launch of Chandrayaan-2 was initially scheduled for 14 July 2019, 21:21 UTC (15 July 2019 at 02:51 IST local time). However, the launch was aborted 56 minutes and 24 seconds before launch due to a technical glitch, so it was rescheduled to 22 July 2019. Unconfirmed reports later cited a leak in the nipple joint of a helium gas bottle as the cause of cancellation.

Finally Chandrayaan-2 was launched on board the LVM3 M1 launch vehicle on 22 July 2019 at 09:13:12 UTC (14:43:12 IST) with a better-than-expected apogee as a result of the cryogenic upper stage being burned to depletion, which later eliminated the need for one of the apogee-raising burns during the geocentric phase of mission. This also resulted in the saving of around 40 kg fuel on board the spacecraft.

Immediately after launch, multiple observations of a slow-moving bright object over Australia were made, which could be related to upper stage venting of residual LOX / LH2 propellant after the main burn.

After being placed into a 45,475 × 169 km parking orbit by the launch vehicle, the Chandrayaan-2 spacecraft stack gradually raised its orbit using on-board propulsion over 22 days. In this phase, one perigee-raising and five apogee-raising burns were performed to reach a highly eccentric orbit of 142,975 × 276 km followed by trans-lunar injection on 13 August 2019. Such a long Earth-bound phase with multiple orbit-raising manoeuvres exploiting the Oberth effect was required because of the limited lifting capacity of the launch vehicle and thrust of the spacecraft's on-board propulsion system. A similar strategy was used for Chandrayaan-1 and the Mars Orbiter Mission during their Earth-bound phase trajectory. On 3 August 2019, the first set of Earth images were captured by the LI4 camera on the Vikram lander, showing the North American landmass.

After 29 days from its launch, the Chandrayaan-2 spacecraft stack entered lunar orbit on 20 August 2019 after performing a lunar orbit insertion burn for 28 minutes 57 seconds. The three-spacecraft stack was placed into an elliptical orbit that passed over the polar regions of the Moon, with 18,072 km (11,229 mi) aposelene and 114 km (71 mi) periselene. By 1 September 2019, this elliptical orbit was made nearly circular with 127 km (79 mi) aposelene and 119 km (74 mi) periselene after four orbit-lowering manoeuvres followed by separation of Vikram lander from the orbiter on 07:45 UTC, 2 September 2019.

Landing site	Coordinates
Prime landing site	70°54′10″S 22°46′52″E / 70.90267°S 22.78110°E / -70.90267; 22.78110
Alternate landing site	67°52′27″S 18°28′10″W / 67.87406°S 18.46947°W / -67.87406; -18.46947

Two landing sites were selected, each with an ellipse of 32 km × 11 km (19.9 mi × 6.8 mi). The prime landing site (PLS54) was at 70.90267°S 22.78110°E (600 km (370 mi) from the south pole,) and the alternate landing site (ALS01) was at 67.87406° South 18.46947° West. The prime site was on a high plain between the craters Manzinus C and Simpelius N, on the near side of the Moon.