Chandrayaan 3 PPT Presentation And Google Slides Themes

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Introduction Of Chandrayaan 3
Chandrayaan 3 is India's third lunar mission to
soft land on the lunar south pole region. The
mission will conduct scientific experiments to
study the lunar geology, atmosphere, and
environment.
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Three Mission Objectives
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Key Technologies
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Mission Components
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Specifications For Chandrayaan-3 
Sl No. Parameter Specifications Sl No. Parameter Specifications
1. Mission Life (Lander Rover) One lunar day (14 Earth days) 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.
2. Landing Site (Prime) 4 km x 2.4 km 69.367621 S, 32.348126 E 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
3. Science Payloads LanderRadio Anatomy of Moon Bound Hypersensitive ionosphere and Atmosphere (RAMBHA) Chandras 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) 9. Lander Actuators Reaction wheels 4 nos (10 Nms 0.1 Nm)
4. Two Module Configuration Propulsion Module (Carries Lander from launch injection to Lunar orbit) Lander Module (Rover is accommodated inside the Lander) 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
5. Mass Propulsion Module 2148 kg Lander Module 1752 kg including Rover of 26 kg Total 3900 kg 11. Lander Mechanisms Lander leg Rover Ramp (Primary Secondary) Rover ILSA, Rambha Chaste Payloads Umbilical connector Protection Mechanism, X- Band Antenna
6. Power generation Propulsion Module 758 W Lander Module 738W, WS with Bias Rover 50W 12. Lander Touchdown specifications Vertical velocity 2 m / sec Horizontal velocity 0.5 m / sec Slope 120
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Objectives Of Scientific Payloads
SI. No Lander Payloads Objectives Objectives
1. Radio Anatomy of Moon Bound Hypersensitive ionosphere and Atmosphere (RAMBHA) Langmuir probe (LP) To measure the near surface plasma (ions and electrons) density and its changes with time
2. Chandras Surface Thermo physical Experiment (ChaSTE) To carry out the measurements of thermal properties of lunar surface near polar region. 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. 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. It is a passive experiment to understand the dynamics of Moon system.
SI. No Rover Payloads Objectives
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. No Propulsion Module Payload Objectives
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).
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Event Date
Launch July 14, 2023
Lunar transfer orbit July 15, 2023
Landing on the lunar south pole region August 23-24, 2023
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The Significance Of Chandrayaan-3
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Mission Profile
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Mission Profile
Animation of Chandrayaan-3
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Nominal Flight Sequence
S.No Event Flight Time (s) Altitude (km) Inertial Velocity (km/s)
1 2xS200 Ignition 0.00 0.024 0.452
2 L110 Ignition 108.10 44.668 1.788
3 2xS200 Separation 127.00 62.171 1.969
4 PLF Separation 194.96 114.805 2.560
5 L110 Separation 305.56 175.352 4.623
6 C25 Ignition 307.96 176.573 4.621
7 C25 Shut-off 954.42 174.695 10.242
8 Satellite Separation 969.42 179.192 10.269
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LVM3-M4-Chandrayaan-3 Mission Timeline
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Chandrayaan-3 Capture First Image
The Moon, as viewed by Chandrayaan-3 during Lunar
Orbit Insertion
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Conclusion Of Chandrayaan 3
Chandrayaan 3 was a successful mission that
achieved its objectives of soft landing on the
lunar south pole region and conducting scientific
experiments. The mission has furthered India's
space exploration capabilities and has helped to
gain a better understanding of the Moon.
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