1)Purpose to launch Chandrayaan 3
2)Which rocket is use in Chandrayaan 3 mission?
The Launch Vehicle Mark-III or LVM3 previously referred as the Geosynchronous Satellite Launch Vehicle Mark III or GSLV Mk III is a three-stage medium-lift launch vehicle developed by the Indian Space Research Organisation (ISRO). Primarily designed to launch communication satellites into geostationary orbit,It is also due to launch crewed missions under the Indian Human Spaceflight Programme.LVM3 has a higher payload capacity than its predecessor, GSLV.
3)GSLV Mark-lll or LVM3 (Geosynchronous Satellite Launch Vehicle)
| Functions | Medium-lift launch vehicle |
|---|---|
| Manufacturer | ISRO |
| Country of origin | India |
| Cost per launch | ₹500crore (US$63 million) |
Size 
| |
| Height | 43.43 m (142.5 ft) |
| Diameter | 4 m (13 ft) |
| Mass | 640,000 kg (1,410,000 lb) |
| Stages | 3 |
Capacity | |
Payload to LEO
| |
| Mass | 10,000 kg (22,000 lb) |
Payload to GTO | |
| Mass | 4,000 kg (8,800 lb) |
Associated rockets 
| |
| Family | Geosynchronous Satellite Launch Vehicle |
| Comparable |
|
Launch history 
| |
| Status | Active |
| Launch sites | CARE, Chandrayaan-2, OneWeb, Chandrayaan-3 |
| Total launches | 7 |
| Success(es) | 7 |
| Failure(s) | 0 |
| Partial failure(s) | 0 |
| First flight |
|
| Last flight | 14 July 2023 |
| |
| Height | 25 m (82 ft) |
| Diameter | 3.2 m (10 ft) |
| Empty mass | 31,000 kg (68,000 lb) each |
| Gross mass | 236,000 kg (520,000 lb) each |
| Powered by | Solid S200 |
| Maximum thrust | 5,150 kN (525 tf |
| Specific impulse | 274.5 seconds (2.692 km/s) (vacuum) |
| Burn time | 128 s |
| |
| Height | 21.39 m (70.2 ft) |
| Diameter | 4.0 m (13.1 ft) |
| Empty mass | 9,000 kg (20,000 lb) |
| Gross mass | 125,000 kg (276,000 lb) |
| Propellant mass | 116,000 kg (256,000 lb) |
| Powered by | 2 Vikas engines |
| Maximum thrust | 1,598 kN (163.0 tf) |
| Specific impulse | 293 seconds (2.87 km/s) |
| Burn time | 203 s |
| |
| Height | 13.545 m (44.44 ft) |
| Diameter | 4.0 m (13.1 ft) |
| Empty mass | 5,000 kg (11,000 lb) |
| Gross mass | 33,000 kg (73,000 lb) |
| Propellant mass | 28,000 kg (62,000 lb) |
| Powered by | 1 CE-20 |
| Maximum thrust | 186.36 kN (19.003 tf) |
| Specific impulse | 442 seconds (4.33 km/s) |
| Burn time | 643 s |
4) Important Dates
i)August 1
Chandrayaan will start orbiting the moon. In 5 days it will reach the Moon's outer orbit
ii)August 17
The spacecraft's propulsion module will separate from the lander module
iii)August 23
in the evening 5:47 p.m. The lander will land on the surface of the moon
Chandrayaan will travel around 4 lakh km in 42 days.
5)LVM3-M4/ Chandrayaan-3 Mission
Chandrayaan-3, India's third lunar exploration mission is ready to take off in fourth operational mission (M4) of LVM3 launcher. ISRO is crossing new frontiers by demonstrating soft landing on lunar surface by its lunar module and demonstrate roving on the lunar terrain. It is expected to be supportive to ISRO's future interplanetary missions Additionally the deployment of rover and in-situ scientific experiment will scale new heights in lunar expeditions by deploying Rover. Yes, ISRO is bringing the Moon closer to us.
6)Propulsion Module
Chandrayaan-3 consists of an indigenous propulsion module, lander module, and a rover with an objective of developing and demonstrating new technologies required for inter-planetary missions.
The propulsion module will carry the lander and rover from injection orbit to till 100 km lunar orbit. It also carries a Spectro-polarimetry of Habitable Planetary Earth (SHAPE) payload to study the spectral and polarimetric measurements of earth from the lunar orbit.
The main function of Propulsion Module is to carry the LM from launch vehicle injection orbit to till Lander separation.
*Propulsion Module Payload*
1)SHAPE
(Spectro-polarimetry of HAbitable Planet Earth)
An experimental payload to study the spectro-polarimetric signatures of the habitable planet Earth in the near-infrared (NIR) wavelength range (1-1.7 m).
7) Satellite Information
I)Major Specifications of Lander
Mission life:1 Lunar day (14 Earth days)
Mass:1749.86 kg including Rover
Power :738 W (Winter solstice)
Payloads:3
Dimensions (mm³): 2000 x 2000 x 1166 :
Communication:ISDN,Ch-2 Orbiter, Rover
Landing site:69.367621 5, 32.348126 E
*Lander Payloads*
1)RAMBHA-LP
(Langmuir Probe)
To measure the near surface plasma (ions and electrons) density and its changes with time.
2)ChaSTE
(Chandra's SurfaceThermo-physical Experiment)
To carry out the measurements of thermal properties of lunar surface near polar
region.
3)ILSA
(Instrument for Lunar Seismic Activity)
To measure seismicity around the landing site and delineating the structure of the lunar crust and mantle.
II)Major Specifications of Rover
Mission Life:1 Lunar day
Mass :26 kg
Power:50W
Payloads:2
Dimensions (mm³):917 x 750 x 397
Communication:Lander
*Rover Payloads*
1)APXS
(Alpha Particle X-Ray Spectrometer)
To derive the chemical composition and infer mineralogical composition to further enhance our understanding of lunar surface.
2)LIBS
Laser Induced Breakdown Spectroscope
To determine the elemental composition (Mg, Al, Si, K, Ca ,Ti, Fe) of lunar soil and rocks around the lunar landing site
*Important images*
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By- Tanishq Deshmukh
15 July 2023
