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Chandrayaan-3 stands as the subsequent mission succeeding Chandrayaan-2, a mission that effectively showcased the ability to safely land on and orbit the lunar surface, encompassing both the lander and rover components. The launch is scheduled to be facilitated by the LVM3 from the Satish Dhawan Space Centre (SDSC) SHAR, situated in Sriharikota. The propulsion module will transport the combined lander and rover configuration to a lunar orbit at an altitude of 100 km.
Notably, within the propulsion module lies the Habitable Planet Earth (SHAPE) payload, specifically the Spectro-Polarimeter, aimed at conducting spectral and polar metric analyses of Earth from its lunar vantage point.
The payloads on the lander encompass several crucial experiments, including Chandra’s Surface Thermophysical Experiment (ChaSTE) designed to gauge thermal conductivity and temperature. The Instrument for Lunar Seismic Activity (ILSA) has been incorporated to measure seismic activity around the designated landing area. Furthermore, the Langmuir Probe (LP) is tasked with estimating plasma density and its fluctuations. An additional feature is the inclusion of a passive Laser Retroreflector Array, contributed by NASA, intended for lunar laser ranging investigations.
Concurrently, the rover is equipped with advanced payloads such as the Alpha Particle X-ray Spectrometer (APXS) and the Laser-Induced Breakdown Spectroscope (LIBS). Both instruments are instrumental in determining the elemental composition within the proximity of the landing site.
Important Components Used in Chandrayaan-3 Mission
The composite Chandrayaan-3 mission encompasses three integral components: an indigenous Lander Module (LM), a Propulsion Module (PM), and a Rover. The primary objective revolves around the development and demonstration of innovative technologies imperative for interplanetary missions.
The Lander of Chandrayaan-3 is engineered with the capability to execute a gentle touchdown at a predetermined lunar site, from which it will deploy the rover. The rover’s primary function is to conduct in-situ chemical analysis of the lunar surface while in motion. Both the Lander and Rover are equipped with scientific payloads meticulously chosen for a series of experiments set to be performed on the lunar terrain.
The Propulsion Module (PM) fulfills a critical role in transporting the Lander Module (LM) from its launch vehicle injection point to the final lunar orbit, a circular polar orbit positioned at an altitude of 100 km. Additionally, the PM and LM are detached from each other by the Propulsion Module. Intriguingly, the propulsion module is augmented with its own scientific payload, which comes into operation subsequent to the separation of the Lander Module.
Designated as the launch vehicle for Chandrayaan-3, the LVM3 M4 will propel the Integrated Module into an Elliptic Parking Orbit (EPO) characterized by dimensions of approximately 170 x 36,500 km.
To achieve the Chandrayaan-3 mission objectives, several advanced technologies are present in Lander such as,
| Altimeters | Laser and RF-based Altimeters |
| Velocimeters | Laser Doppler Velocimeter & Lander Horizontal Velocity Camera |
| Inertial Measurement | Inertial Measurement Laser Gyro based Inertial referencing and Accelerometer package |
| Propulsion System | 800N Throttleable Liquid Engines, 58N attitude thrusters, and Throttleable Engine Control Electronics |
| Navigation, Guidance & Control (NGC) | Powered Descent Trajectory design and associated software elements |
| Hazard Detection and Avoidance | Lander Hazard Detection & Avoidance Camera and Processing Algorithm |
| Landing Leg Mechanism |
To demonstrate the above-advanced technologies under Earth conditions, several lander-specific tests have been planned and successfully completed.
- Integrated Cold Test – To perform integrated sensor and navigation performance testing using a helicopter as the test platform.
- Integrated Hot Testing – To perform closed-loop performance testing with sensors, actuators, and NGC using a tower crane as the test platform.
- Lander leg advanced mechanism performance test on lunar simulant test bed simulating various touch-down conditions.
Chandrayaan-3 Mission Objectives
- Performing a safe and soft landing on the lunar surface
- Display the Rover moving on the moon and
- To conduct scientific experiments in situ.
LVM3-M4-Chandrayaan-3 Mission Important Dates
| Important Date | Activities on That Date |
| 23 August 2023 | ‘I have reached my destination and so have you!’: Chandrayaan-3 Chandrayaan-3 has successfully soft-landed on the moon. Congratulations, India! |
| 20 August 2023 | The Lander Module of Chandrayaan-3 is in a 25 km x 134 km orbit. Powered descent is expected to begin on August 23, 2023, around 1745 Hrs. (IST) |
| 19 August 2023 | The Lander Module of Chandrayaan-3 is in a 113 km x 157 km orbit around the moon. The second de-boosting is planned for August 20, 2023 |
| 17 August 2023 | The Lander Module of Chandrayaan-3 is successfully separated from the Propulsion Module. Deboosting is planned for August 18, 2023 |
| 16 August 2023 | The spacecraft is in an orbit of 153 km x 163 km after the launch on August 16, 2023 |
| 14 August 2023 | The Chandrayaan 3 Mission is in the orbit circularisation phase. The spacecraft is in a 151 km x 179 km orbit. |
| 9 August 2023 | Chandrayaan-3’s orbit has been reduced to 174 km x 1437 km after a maneuver performed on August 9, 2023. |
| 6 August 2023 | LBN#2 of Chandrayaan-3 is successfully completed. The spacecraft is in a 170 km x 4313 km orbit around the moon. |
| 5 August 2023 | Chandrayaan-3 has been successfully placed in the Moon’s orbit. As intended, an orbit of 164 km x 18074 km was achieved. |
| 1 August 2023 | The spacecraft has been placed in translunar orbit. The orbit achieved is 288 km x 369328 km. Lunar-Orbit Insertion (LOI) is planned for August 5, 2023. |
| 25 July 2023 | The orbit-raising operation was performed on July 25, 2023. The next firing (translunar injection), is planned for August 1, 2023. |
| 22 July 2023 | The 4th orbit-raising maneuver (Earth-bound perigee firing) is successfully completed. The spacecraft is now in an orbit of 71351 km x 233 km. |
| 17 July 2023 | A 2nd orbit-raising maneuver was performed. The spacecraft is now in a 41603 km x 226 km orbit. |
| 15 July 2023 | The first orbit-raising maneuver (Earthbound Firing-1) has been successfully performed at ISTRAC/ISRO, Bengaluru. The spacecraft is now in a 41762 km x 173 km orbit. |
| 14 July 2023 | LVM3 M4 vehicle successfully launched Chandrayaan-3 into orbit. Chandrayaan-3 has started its journey to the Moon in its precise orbit. The health of the spacecraft is normal. |
| 11 July 2023 | The ‘Launch Rehearsal’ simulating the entire launch preparation and process lasting 24 hours is over. |
| 6 July 2023 | The Chandryaan-3 launch is scheduled for July 14, 2023 at 14:35. IST from Second Launch Pad, SDSC-SHAR, Sriharikota. |
Overall Chandrayaan-3 Specification
| Sl No. | Parameter | Specifications |
| 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 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 Lander from launch injection to Lunar orbit) Lander Module (Rover is accommodated inside the Lander) |
| 5. | Mass | Propulsion Module: 2148 kg Lander Module: 1752 kg including Rover of 26 kg Total: 3900 kg |
| 6. | Power generation | Propulsion Module: 758 W Lander Module: 738W, WS with Bias Rover: 50W |
| 7. | Communication | Propulsion 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 Sensors | Laser 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 Actuators | Reaction wheels – 4 nos (10 Nms & 0.1 Nm) |
| 10. | Lander Propulsion System | Bi-Propellant Propulsion System (MMH + MON3), 4 nos. of 800 N Throttleable engines & 8 nos. of 58 N; 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: ≤ 12 deg |
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