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Chandrayaan-3 is the third Moon’s mission by the Indian Space Research Organisation (ISRO). It 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 a lander and the Pragyan rover configuration.

Chandrayaan-3 Rocket Specifications
Chandrayaan-3 Rocket (Sourceisro)

The launch of Chandrayaan-3 took place at 14 July 2023, at 2:35 pm, by LVM3 from SDSC (Satish Dhawan Space Centre) SHAR, Sriharikota.

Rocket Sequence :

Time (s)
2xS200 Ignition0.000.0240.452
L110 Ignition108.1044.6681.788
2xS200 Separation127.0062.1711.969
PLF Separation194.96114.8052.560
L110 Separation305.56175.3524.623
C25 Ignition307.96176.5734.621
C25 Shut-off954.42174.69510.242
Satellite Separation969.42179.19210.269
Chandrayaan-3 rocket launch
Chandrayaan-3 Mission (Source : isro)

Mission Objectives

  • To demonstrate Safe and Soft Landing on Lunar Surface
  • To demonstrate Rover roving on the moon
  • To conduct in-situ scientific experiments

The objectives of scientific payloads planned on Chandrayaan-3 Lander Module and Rover are :

Sl. NoLander PayloadsObjectives
1.Radio Anatomy of Moon Bound Hypersensitive ionosphere and Atmosphere (RAMBHA)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.
Sl. NoRover PayloadsObjectives
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.
Sl. NoPropulsion Module PayloadObjectives
1.Spectro-polarimetry of HAbitable Planet Earth (SHAPE)Future discoveries of smaller planets in reflected light would allow us to probe into variety of Exo-planets which would qualify for habitability (or for presence of life).

Chandrayaan-3 Specifications

Sl No.ParameterSpecifications
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 PayloadsLander: Radio Anatomy of Moon Bound Hypersensitive ionosphere and Atmosphere (RAMBHA) Chandra’s Surface Thermo physical Experiment (ChaSTE) Instrument for Lunar Seismic Activity (ILSA) Laser Retroreflector Array (LRA) Rover: Alpha Particle X-Ray Spectrometer (APXS) Laser Induced Breakdown Spectroscope (LIBS) Propulsion Module: Spectro-polarimetry of HAbitable Planet Earth (SHAPE)
4.Two Module ConfigurationPropulsion Module (Carries Lander from launch injection to Lunar orbit) Lander Module (Rover is accommodated inside the Lander)
5.MassPropulsion Module: 2148 kg Lander Module: 1752 kg including Rover of 26 kg Total: 3900 kg
6.Power generationPropulsion Module: 758 W Lander Module: 738W, WS with Bias Rover: 50W
7.CommunicationPropulsion Module: Communicates with IDSN Lander Module: Communicates with IDSN and Rover. Chandrayaan-2 Orbiter is also planned for contingency link. Rover: Communicates only with Lander.
8.Lander SensorsLaser Inertial Referencing and Accelerometer Package (LIRAP) Ka-Band Altimeter (KaRA) Lander Position Detection Camera (LPDC) LHDAC (Lander Hazard Detection & Avoidance Camera) Laser Altimeter (LASA) Laser Doppler Velocimeter (LDV) Lander Horizontal Velocity Camera (LHVC) Micro Star sensor Inclinometer & Touchdown sensors
9.Lander ActuatorsReaction wheels – 4 nos (10 Nms & 0.1 Nm)
10.Lander Propulsion SystemBi-Propellant Propulsion System (MMH + MON3), 4 nos. of 800 N Throttleable engines & 8 nos. of 58 N; Throttleable Engine Control Electronics
11.Lander MechanismsLander leg Rover Ramp (Primary & Secondary) Rover ILSA, Rambha & Chaste Payloads Umbilical connector Protection Mechanism, X- Band Antenna
12.Lander Touchdown specificationsVertical velocity: ≤ 2 m / sec Horizontal velocity: ≤ 0.5 m / sec Slope: ≤ 120
Chandrayaan-3 – Mission Profile
Chandrayaan-3 – Mission Profile (Sourceisro)

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