Mission: Chandrayaan 3

July 15, 2023

Mission: Chandrayaan 3

In this blog you will get information about Chandrayaan 3 rocket, it's purpose ,which rocket is used, which engine are powered.etc so be ready to boost your knowledge by this blog.

1)Purpose to launch Chandrayaan 3

Its main purpose is to create and showcase innovative technologies essential for missions between planets. The propulsion module will transport the lander and rover from the injection orbit to the lunar orbit up to 100 km.This Mission cost over ₹615crore

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)

GSLV Mark-lll or LVM3 (Geosynchronous Satellite Launch Vehicle)- Chandrayaan 3

Size
Functions	Medium-lift launch vehicle
Manufacturer	ISRO
Country of origin	India
Cost per launch	₹500crore (US$63 million)
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	Angara Atlas V Falcon 9 H-IIA Long March 3B Long March 7 Titan IIIC Zenit rocket
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	18 December 2014 (suborbital) 5 June 2017 (orbital)
Last flight	14 July 2023

First stage – S200 Boosters
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

Second stage – L110
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

Third stage – C25
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