CHANDRAYAAN 3 - OVERALL SPECIFICATIONS - IMPROVEMENT FROM EARLIER MISSIONS

Before we discussion overall specification. Here is the gist of several advanced technologies which 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.

Preparation : To demonstrate the above said advanced technologies in earth condition, several Lander special tests have been planned and carried out successfully viz.

  1. Integrated Cold Test - For the demonstration of Integrated Sensors & Navigation performance test using helicopter as test platform
  2. Integrated Hot test – For the demonstration of closed loop performance test with sensors, actuators and NGC using Tower crane as test platform
  3. Lander Leg mechanism performance test on a lunar simulant test bed simulating different touch down conditions.

The overall specifications for Chandrayaan-3 is provided below:

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:
  1. Radio Anatomy of Moon Bound Hypersensitive ionosphere and Atmosphere (RAMBHA)
  2. Chandra’s Surface Thermo physical Experiment (ChaSTE)
  3. Instrument for Lunar Seismic Activity (ILSA)
  4. Laser Retroreflector Array (LRA) Rover:
  5. Alpha Particle X-Ray Spectrometer (APXS)
  6. Laser Induced Breakdown Spectroscope (LIBS) Propulsion Module:
  7. Spectro-polarimetry of HAbitable Planet Earth (SHAPE)
4.Two Module Configuration
  1. Propulsion Module (Carries Lander from launch injection to Lunar orbit)
  2. Lander Module (Rover is accommodated inside the Lander)
5.Mass
  1. Propulsion Module: 2148 kg
  2. Lander Module: 1752 kg including Rover of 26 kg
  3. Total: 3900 kg
6.Power generation
  1. Propulsion Module: 758 W
  2. Lander Module: 738W, WS with Bias
  3. Rover: 50W
7.Communication
  1. Propulsion Module: Communicates with IDSN
  2. Lander Module: Communicates with IDSN and Rover. Chandrayaan-2 Orbiter is also planned for contingency link.
  3. Rover: Communicates only with Lander.
8.Lander Sensors
  1. Laser Inertial Referencing and Accelerometer Package (LIRAP)
  2. Ka-Band Altimeter (KaRA)
  3. Lander Position Detection Camera (LPDC)
  4. LHDAC (Lander Hazard Detection & Avoidance Camera)
  5. Laser Altimeter (LASA)
  6. Laser Doppler Velocimeter (LDV)
  7. Lander Horizontal Velocity Camera (LHVC)
  8. Micro Star sensor
  9. 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 Mechanisms
  1. Lander leg
  2. Rover Ramp (Primary & Secondary)
  3. Rover
  4. ILSA, Rambha & Chaste Payloads
  5. Umbilical connector Protection Mechanism,
  6. X- Band Antenna
12.Lander Touchdown specifications
  1. Vertical velocity: ≤ 2 m / sec
  2. Horizontal velocity: ≤ 0.5 m / sec
  3. Slope: ≤ 120

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