Chandrayan - 3
CHANDRAYAN-3
Chandrayan - 3 had launched on 14th July 2023 as well as Chandrayan 2 was launched on 22nd July 2019.
Chandrayaan-3 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 Lander and Rover configurations. It will be launched by LVM3 from SDSC SHAR, Sriharikota. The propulsion module will carry the lander and rover configuration till the 100 km lunar orbit. The propulsion module has a Spectro-polarimetry of Habitable Planet Earth (SHAPE) payload to study the spectral and Polari metric measurements of Earth from the lunar orbit.
Chandrayaan-3 consists of an indigenous Lander module (LM), a Propulsion module (PM), and a Rover to develop and demonstrate new technologies required for Interplanetary missions. The Lander will have the capability to soft land at a specified lunar site and deploy the Rover which will carry out in-situ chemical analysis of the lunar surface during its mobility. The Lander and the Rover have scientific payloads to carry out experiments on the lunar surface. The main function of the PM is to carry the LM from launch vehicle injection to the final lunar 100 km circular polar orbit and separate the LM from the PM. Apart from this, the Propulsion Module also has one scientific payload as a value addition which will be operated post-separation of the Lander Module. The launcher identified for Chandrayaan-3 is GSLV-Mk3 which will place the integrated module in an Elliptic Parking Orbit (EPO) of size ~170 x 36500 km.
mission objectives are
1) To demonstrate a Safe and Soft Landing on Lunar Surface
2) To demonstrate Rover roving on the moon and
3) conduct in-situ scientific experiments.
parameters - Specifiacations
1. Lunar Polar - Orbit From 170 x 36500 km to lunar polar orbit.
2. Mission life - Carrying Lander Module & Rover up to ~100 x 100
km launch injection. Subsequently, operation of the experimental payload for a period of 3 to 6 months.
3. Structure - Modified version of I-3 K.
4. Dry Mass - 448.62 kg (including pressurant).
5. Propellant Mass - 1696.39 kg.
6. Total PM Mass - 2145.01 kg.
7. Power Generation - 738 W, Summer solstices and with bias.
8. Communication - S-Band Transponder (TTC) – with IDSN.
9. Attitude Sensors - CASS, IRAP, Micro star sensor.
10. Propulsion System - Bi-Propellant Propulsion System (MMH + MON3).
YOU ARE WATCHING THE ORBIT OF CHANDRAYAN - 3.
To achieve the mission objectives, several advanced technologies are present in Lander such as,
1) Altimeters: Laser & RF based Altimeters
2) Velocimeters: Laser Doppler Velocimeter & 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 & Throttleable Engine Control Electronics
5) Navigation, Guidance & Control (NGC): Powered Descent Trajectory design and associate software elements
6) Hazard Detection and Avoidance: Lander Hazard Detection & Avoidance Camera and Processing Algorithm
7) Landing Leg Mechanism.
Source :- ISRO

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