Chandrayaan-3 serves as a continuation of the Chandrayaan-2 mission, aimed at showcasing the ability to safely land and rove on the lunar surface. This mission comprises a Lander and Rover configuration and is set to launch from the Satish Dhawan Space Centre (SDSC) SHAR in Sriharikota, propelled by the LVM3 launch vehicle. The propulsion module will transport the lander and rover configuration to a lunar orbit of 100 kilometers. Within the propulsion module, the Spectro-polarimetry of Habitable Planet Earth (SHAPE) payload will conduct spectral and polarimetric measurements of Earth from the lunar orbit.
The Lander payloads include Chandra's Surface Thermophysical Experiment (ChaSTE), which measures thermal conductivity and temperature, the Instrument for Lunar Seismic Activity (ILSA), which gauges seismic activity around the landing site, and the Langmuir Probe (LP), which estimates plasma density and its variations. Additionally, a passive Laser Retroreflector Array from NASA will be included for lunar laser ranging studies.
The Rover payloads consist of the Alpha Particle X-ray Spectrometer (APXS) and the Laser Induced Breakdown Spectroscope (LIBS), both of which are instrumental in deriving the elemental composition of the vicinity surrounding the landing site.
Chandrayaan-3 comprises an indigenous Lander module (LM), a Propulsion module (PM), and a Rover, with the objective of developing and demonstrating new technologies necessary for interplanetary missions. The Lander possesses the capability to achieve a soft landing at a predetermined lunar site and deploy the Rover, which will conduct in-situ chemical analysis of the lunar surface during its mobility. The Lander and Rover are equipped with scientific payloads to carry out experiments on the lunar surface. The primary function of the PM is to transport the LM from the launch vehicle injection to the final lunar 100 km circular polar orbit and subsequently separate from the LM. Additionally, the Propulsion Module incorporates a scientific payload to enhance its value, which will be operated after the separation of the Lander Module. The GSLV-Mk3 has been designated as the launcher for Chandrayaan-3, responsible for placing the integrated module into an Elliptic Parking Orbit (EPO) measuring approximately 170 x 36,500 km.
The mission objectives of Chandrayaan-3 are as follows:
1. Demonstrate safe and soft landing on the lunar surface.
2. Showcase Rover roving capabilities on the moon.
3. Conduct in-situ scientific experiments.
To accomplish these mission objectives, the Lander is equipped with several advanced technologies, including:
1. Altimeters: Laser and RF-based altimeters.
2. Velocimeters: Laser Doppler Velocimeter and Lander Horizontal Velocity Camera.
3. Inertial Measurement: Laser Gyro-based Inertial referencing and Accelerometer package.
4. Propulsion System: 800N Throttleable Liquid Engines, 58N attitude thrusters, and Throttleable Engine Control Electronics.
5. Navigation, Guidance & Control (NGC): Powered Descent Trajectory design and associated software elements.
6. Hazard Detection and Avoidance: Lander Hazard Detection and Avoidance Camera and Processing Algorithm.
7. Landing Leg Mechanism.
To validate the performance of these advanced technologies in Earth conditions, several special tests for the Lander have been planned and successfully executed. These tests include:
1. Integrated Cold Test: Demonstrating the performance of integrated sensors and navigation through a helicopter-based test platform.
2. Integrated Hot Test: Assessing closed-loop performance with sensors, actuators, and NGC using a Tower crane as the test platform.
3. Lander Leg Mechanism Performance Test: Conducted on a lunar simulant test bed to simulate different touchdown conditions.
The overall specifications for Chandrayaan-3 are provided below:
1. Mission Life (Lander & Rover): Approximately one lunar day, equivalent to around 14 Earth days.
2. Landing Site (Prime): 4 km x 2.4 km at coordinates 69.367621 S, 32.348126 E.
3. Science Payloads:
Lander:
- 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 Configuration:
- Propulsion Module: Carries the Lander from launch injection to Lunar orbit.
- Lander Module: Accommodates the Rover.
5. Mass:
- Propulsion Module: 2148 kg
- Lander Module: 1752 kg, including the 26 kg Rover
- Total: 3900 kg
6. Power Generation:
- Propulsion Module: 758 W
- Lander Module: 738 W, with Bias
- Rover: 50 W
7. Communication:
- Propulsion Module: Communicates with IDSN
- Lander Module: Communicates with IDSN and Rover. Chandrayaan-2 Orbiter serves as a contingency link.
- Rover: Communicates exclusively with the Lander.
8. Lander Sensors:
- Laser Inertial Referencing and Accelerometer Package (LIRAP)
- Ka-Band Altimeter (KaRA)
- Lander Position Detection Camera (LPDC)
- Lander Hazard Detection and Avoidance Camera (LHDAC)
- Laser Altimeter (LASA)
- Laser Doppler Velocimeter (LDV)
- Lander Horizontal Velocity Camera (LHVC)
- Micro Star sensor
- Inclinometer and Touchdown sensors
9. Lander Actuators:
- Reaction wheels: 4 units (10 Nms & 0.1 Nm)
10. Lander Propulsion System:
- Bi-Propellant Propulsion System (MMH + MON3)
- Four 800 N Throttleable engines and eight 58 N Throttleable engines
- Throttleable Engine Control Electronics
11. Lander Mechanisms:
- Lander leg
- Rover Ramp (Primary & Secondary)
- Rover
- ILSA, RAMBHA & ChaSTE Payloads
- Umbilical connector Protection Mechanism
- X-Band Antenna
12. Lander Touchdown Specifications:
- Vertical velocity: ≤ 2 m / sec
- Horizontal velocity: ≤ 0.5 m / sec
- Slope: ≤ 120
The scientific payloads on the Chandrayaan-3 Lander Module and Rover are equipped with the following objectives:
Lander Payloads:
1. Radio Anatomy of Moon Bound Hypersensitive ionosphere and Atmosphere (RAMBHA) - Langmuir probe (LP): Measure near-surface plasma density (ions and electrons) and its temporal variations.
2. Chandra's Surface Thermophysical Experiment (ChaSTE): Measure thermal properties of the lunar surface in the near-polar region.
3. Instrument for Lunar Seismic Activity (ILSA): Measure seismicity around the landing site and investigate the structure of the lunar crust and mantle.
4. Laser Retroreflector Array (LRA): Passive experiment to study the dynamics of the Moon system.
Rover Payloads:
1. Laser Induced Breakdown Spectroscope (LIBS): Perform qualitative and quantitative elemental analysis, derive the chemical composition, and infer mineralogical composition to enhance our understanding of the lunar surface.
2. Alpha Particle X-ray Spectrometer (APXS): Determine the elemental composition (Mg, Al, Si, K, Ca, Ti, Fe) of lunar soil and rocks in the vicinity of the lunar landing site.
Propulsion Module Payload:
1. Spectro-polarimetry of Habitable Planet Earth (SHAPE): Enable future discoveries of smaller planets in reflected light, allowing us to explore a variety of exoplanets and assess their habitability or the presence of life.
Detailed three-dimensional views of the Chandrayaan-3 modules, including the integrated module, Lander Module, Propulsion Module, Rover on Ramp, and deployed Rover, can be found below.
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Three dimensional views of Chandrayaan-3 modules are provided below:
Chandrayaan-3 – Elements
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