Modules inside Chandrayaan 2

1. CHANDRAYAAN 2

2. GSLV MARK 3

4. 1. 3 Stage
2. Medium Lift
3. ₹375 Crore
4. 43.4 m × 4 m
5. 640 Mg
6. Leo Payload :10 Mg
7. GTO Payload : 4Mg
8. 4/4
9. Sub Orbital First Flight : 18 12 2014
10. Orbital First Flight : 5 6 2017
FEATURES

5. First stage – S200 Boosters
Length 25 m (82 ft)
Diameter 3.2 m (10 ft)
Empty mass 31,000 kg (68,000 lb) each
Gross mass 236,000 kg (520,000 lb) each
Propellant mass 205,000 kg (452,000 lb) each
Motor Solid S200
Thrust 5,150 kN (525 tf) each
Specific impulse 274.5 (vacuum)
Burn time 128 sec
Fuel HTPB

6. Second stage – L110
Length 21.39 m (70.2 ft)
Diameter 4.0 m (13.1 ft)
Empty mass 9,000 kg (20,000 lb)
Gross mass 125,000 kg (276,000 lb)
Propellant mass 116,000 kg (256,000 lb)
Engines 2 Vikas engines
Thrust 1,598 kN (163.0 tf)
Specific impulse 293 sec
Burn time 203 sec
Fuel UDMH / N₂O₄

7. Third stage – C25
Length 13.545 m (44.44 ft)
Diameter 4.0 m (13.1 ft)
Empty mass 5,000 kg (11,000 lb)
Gross mass 33,000 kg (73,000 lb)
Propellant mass 28,000 kg (62,000 lb)
Engines 1 CE-20
Thrust 200 kN (20 tf)
Specific impulse 443 sec
Burn time 643 sec
Fuel LOX / LH

8. ORBITER

10. FEATURES
1. Dimensions 3.1 x 3.1 x 5.8 m
2. Weight 3,850 kg

12. FEATURES
1. 2379 Kg
2. 3.2 x 5.8 x 2.1 m
3. 1 kW
4. 8 Payloads
5. 1year
6. 100X100 km lunar polar orbit.

13. PAYLOADS
1.
Terrain
Mapping
Camera
2
(TMC
2)
2.
Chandrayaan
2
Large
Area
Soft
X-ray
SPectrometer
(CLASS)
3.
Solar
X-ray
Monitor
(XSM)
4.
Orbiter
High
Resolution
Camera
(OHRC)
5.
Imaging
IR
Spectrometer
(IIRS)
6.
Dual
Frequency
Synthetic
Aperture
Radar
(DFSAR)
7.
Chandrayaan
2
Atmospheric
Compositional
Explorer
2
(CHACE
2)
8.
Dual
Frequency
Radio
Science
(DFRS)
experiment

14. TERRAIN MAPPING CAMERA 2 (TMC 2)
TMC 2 is a miniature version of the Terrain Mapping Camera
used onboard the Chandrayaan 1 mission. Its primary
objective is mapping the lunarsurface in the panchromatic
spectral band (0.5-0.8 microns) with a high spatial
resolution of 5 m and a swath of 20 km from 100 km lunar
polarorbit. The data collected by TMC 2 will give us clues
about the Moon's evolution and help us prepare 3D maps
of the lunar surface.

16. CHANDRAYAAN 2 LARGE AREA SOFT X-RAY SPECTROMETER
(CLASS)
CLASS measures the Moon's X-ray Fluorescence (XRF)
spectra to examine the presence of major elements such as
Magnesium, Aluminium, Silicon,Calcium, Titanium, Iron,
and Sodium. The XRF technique will detect these elements
by measuring the characteristic X-rays they emit when
excitedby the Sun's rays.

18. SOLAR X-RAY MONITOR (XSM)
XSM observes the X-rays emitted by the Sun and its corona,
measures the intensity of solar radiation in these rays, and
supports CLASS. Theprimary objective of this payload is to
provide solar X-ray spectrum in the energy range of 1-15
keV. XSM will provide high-energy resolution andhigh-
cadence measurements (full spectrum every second) of
solar X-ray spectra as input for analysis of data from CLASS.

20. ORBITER HIGH RESOLUTION CAMERA (OHRC)
OHRC provides high-resolution images of the landing site —
ensuring the Lander's safe touchdown by detecting any craters or
boulders prior toseparation. The images it captures, taken from
two different look angles, serve dual purposes. Firstly, they are
used to generate DEMs (DigitalElevation Models) of the landing
site. Secondly, they are used for scientific research, post-lander
separation. OHRC's images will be captured overthe course of
two orbits, covering an area of 12 km x 3 km with a ground
resolution of 0.32 m.

22. IMAGING IR SPECTROMETER (IIRS)
IIRS has two primary objectives:
• Global mineralogical and volatile mapping of the Moon in
the spectral range of ~0.8-5.0 µm for the first time, at the
high resolution of ~20 nm
• Complete characterisation of water/hydroxyl feature near
3.0 µm for the first time at high spatial (~80 m) and
spectral (~20 nm) resolutions IIRS will also measure the
solar radiation reflected off the Moon's surface in 256
contiguous spectral bands from 100 km lunar orbit.

24. DUAL FREQUENCY SYNTHETIC APERTURE RADAR (DFSAR)
The dual frequency (L and S) SAR will provide enhanced capabilities
compared to Chandrayaan 1's S-band miniSAR in areas such as: L-
band for greater depth of penetration (About 5m — twice that of S-
band) Circular and full polarimetry — with a range of resolution
options (2-75 m) and incident angles (9°-35°) — for understanding
scattering properties of permanently shadowed regions The main
scientific objectives of this payload are: High-resolution lunar
mapping in the polar regions Quantitative estimation of water-ice in
the polar regions Estimation of regolith thickness and its distribution

26. CHANDRAYAAN 2 ATMOSPHERIC COMPOSITIONAL
EXPLORER 2 (CHACE 2)
CHACE 2 will continue the CHACE experiment carried out by
Chandrayaan 1. It is a Quadrupole Mass Spectrometer
(QMA) capable of scanning the lunar neutral exosphere in
the mass range of 1 to 300 amu with the mass resolution of
~0.5 amu. CHACE 2's primary objective is to carry out an
insitu study of the composition and distribution of the lunar
neutral exosphere and its variability.

28. DUAL FREQUENCY RADIO SCIENCE (DFRS) EXPERIMENT
To study the temporal evolution of electron density in the
Lunar ionosphere. Two coherent signals at X (8496 MHz),
and S (2240 MHz) band are transmitted simultaneously
from satellite, and received at ground based deep station
network receivers

31. FEATURES
1. Weight : 1,471 kg
2. Power : 650 W
3. Payloads : 4
4. Dimensions : 2.54 x 2 x 1.2 m
5. Mission Life : 1 lunar day

32. PAYLOADS
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))

33. RADIO ANATOMY OF MOON BOUND HYPERSENSITIVE
IONOSPHERE AND ATMOSPHERE (RAMBHA)
The lunar ionosphere is a highly dynamic plasma environment.
Langmuir probes, such as RAMBHA, have proven to be an effective
diagnostic tool to gain information in such conditions. Its primary
objective is to measure factors such as:
• Ambient electron density/temperature near the lunar surface
• Temporal evolution of lunar plasma density for the first time
near the surface under varying solar conditions

35. CHANDRA'S SURFACE THERMO-PHYSICAL EXPERIMENT
(CHASTE)
ChaSTE measures the vertical temperature gradient and thermal
conductivity of the lunar surface. It consists of a thermal probe
(sensors and a heater) that is inserted into the lunar regolith down to
a depth of ~10 cm. ChaSTE operates in two modes:
• Passive mode operation in which continuous in-situ measurements
of temperature at different depths are carried out
• Active mode operation in which temperature variations in a set
period of time, and the regolith's thermal conductivity under
contact, are estimated

37. INSTRUMENT FOR LUNAR SEISMIC ACTIVITY (ILSA))
ILSA is a triple axis, MEMS-based seismometer that can
detect minute ground displacement, velocity, or
acceleration caused by lunar quakes. Its primary objective is
to characterise the seismicity around the landing site. ILSA
has been designed to identify acceleration as low as 100 ng
/√Hz with a dynamic range of ±0.5 g and a bandwidth of 40
Hz. The dynamic range is met by using two sensors — a
coarse-range sensor and a fine-range sensor.

41. FEATURES
1. Weight : 27 kg
2. Power : 50 W
3. Payloads : 2
4. Dimensions : 0.9 x 0.75 x 0.85 m
5. Mission Life : 1 lunar day

42. PAYLOADS
1. Alpha Particle X-ray Spectrometer (APXS)
2. Laser Induced Breakdown Spectroscope
(LIBS)

43. ALPHA PARTICLE X-RAY SPECTROMETER (APXS)
APXS' primary objective is to determine the elemental composition
of the Moon's surface near the landing site. It achieves this through
X-ray f luorescence spectroscopy technique, where X-ray or alpha
particles are used to excite the surface. APXS uses radioactive
Curium (244) metal that emits high-energy, alpha particles — as well
as X-rays — enabling both X-ray emission spectroscopy and X-ray
fluorescence spectroscopy. Through these techniques, APXS can
detect all major rock-forming elements such as Sodium, Magnesium,
Aluminium, Silica, Calcium, Titanium, Iron, and some trace elements
such as Strontium, Yttrium and Zirconium.

45. LASER INDUCED BREAKDOWN SPECTROSCOPE
(LIBS)
LIBS' prime objective is to identify and determine the
abundance of elements near the landing site. It does this by
firing high-powered laser pulses at various locations and
analysing the radiation emitted by the decaying plasma.

47. LASER RETROREFLECTOR ARRAY (LRA)
To understand the dynamics of Earth's Moon system and
also derive clues on the Lunar interior.