CHANDRAYAAN-2: Orbiter Payloads

Report
CHANDRAYAAN-2
An Indo-Russian Collaborative mission
An Orbiter,
Lander, Rover
Mission
Fairing
Lander
(Russia)
Rover
(India)
Intermodular
adopter
(Russia)
Orbiter
(India)
GSLV (MK-II)
Launch Vehicle, Orbiter, Rover (India);
Lander (Russia)
CHANDRAYAAN-2
MISSION SCENARIO
 GSLV (Mk-II) will place an orbital flight vehicle (similar to Chandrayaan-1), carrying a
soft landing system up to Lunar Transfer Trajectory (LTT).
 Orbiter & Lander-Rover will be maneuvered separately for lunar polar insertion.
The landing system will be
commanded for its
controlled decent from
polar orbit .
Following landing,
the motorized rover with
scientific instruments and
tools will be released on
the lunar surface.
Most comprehensive Geochemical and Geophysical Investigation
of the Moon with more than a dozen payloads on Orbiter (5),
Rover (2) and Lander
CHANDRAYAAN-2: Orbiter Payloads
Imaging IR Spectrometer (IIRS)
Terrain Mapping Camera-2
(0.8 to 5 µm)
coverage
Lunar Mineralogy;
Fore optics
Detector
350
will cover
H2O, OH and
thermal regime
Convex
grating
[Improved
version of
Hyper-Spectral
Imager (HySI)
[0.4 to 0.9 µm]
flown on CH-1]
Stereo-viewing &
3D imaging of
lunar surface from
a 200km orbit
Tertiary
mirror
Primary
mirror
CHANDRAYAAN-2: Orbiter Payloads
L and S band
Synthetic Aperture Radar
L-band (1.25 GHz) and S-Band ( 2.0-2.2 GHz)
Lunar observations with a selectable resolution
of 2m, 5m or 10m, and a swath of 10km.
To operate in Circular Polarization mode and
Linear Polarimetric mode.
Radiating
patch
arrangement
for
Integrated
L-band and
S-band
antenna
17
0
17
0
8
5
1010m
m
8
5
1350m
m
Objective: To study lunar sub-surface
layers for presence of water ice
(based on circular polarization)
and other components (e.g. Ilmenite,
host of solar wind 3He), based on
modeled dielectric constant
CHANDRAYAAN-2: Orbiter Payloads
re fe re n ce
edges
T h e rm is to r :
H o n e y w e ll
1 9 6 -3 0 2 L A D -0 0 2
SS
IØ 1
IØ 2
DD
Ø R2
SS
DOD
DOS
SS
OG
ØR
RD
SS
OS
OD
SS
Ø R2
DD
IØ 2
IØ 1
SS
SS
IØ 1
IØ 2
DD
Ø R2
SS
DOD
DOS
SS
OG
ØR
RD
SS
OS
OD
SS
Ø R2
DD
IØ 2
IØ 1
SS
OD
OØ2
SS
IØ 1
RD
OS
DOS
ØR1
DD
SS
DOD
ØR2
OG
T2
SS
SS
DOS
RD
OS
OD
DOD
SS
IØ 1
IØ 2
Chandrayaan Large Area
Soft X-ray Spectrometer
SCD
&
[CLASS]
DOD
SS
OØ1
IØ 2
RD
OS
DOS
OD
OG
ØR1
RD
OG
SS
ØR1
T1
OS
SS
DOS
OD
DOD
SS
OØ1
IØ 2
w ire -b o n d
Silicon
Drift
Detector
(SDD)
SCD
Solar X-ray Monitor
Soft X-ray (1-8 keV) spectrometer for global mapping of major
elements (Mg, Al, Si, Ca, Fe, …)
Neutral and Ion Mass Spectrometer (NIMS)
A detail study of the lunar exosphere and
environment and possible time variability
CHANDRAYAAN-2: Rover Payloads
Laser Induced Breakdown
Spectroscopy
Alpha Particle Induced X-ray
Spectrometer (APIXS)
Robotic arm/Rover base
Electronics
Alpha source
Alpha source
Si (SDD)
<3cm
X-Ray detector
Lunar surface
LIBS Sub-Unit
Spectroscopy of volatiles produced by
laser ablation of lunar surface material
Lunar surface
Samp: R 3-4 cm
Alpha particle and X rays from a
radioactive source strikes lunar surface
Measure energy spectra of emitted
X rays via PIXE and XRF
Both instruments are primarily intended for chemical characterization of
localized lunar surface material.
LIBS can detect traces of water vapour, if released from lunar soils
CHANDRAYAAN-2: Orbiter Payloads
Terrain Mapping Camera-2 (Schematic and Sub-System)
Detector
Head
Power
Package
Lens
Assembly
Mirror
Housing
Aft
Nadir
Camera
Electronics
Efforts towards reducing weight & power
- New configurations
- Lens weight optimization
- New components
- New Power system
Fore
Stereo-viewing & 3D imaging of lunar surface from a 200km orbit
CHANDRAYAAN-2: Orbiter Payloads
Imaging Infrared Spectrometer (IIRS)
Lunar Spectroscopy [up to 5.0 mm]
(first data set)
IIRS Schematic
Parameters
Specifications
Spatial Res. (m)
80
Swath (km)
40
Spectral range (mm)
0.8 to 5.0
SNR
500
No. of spectral
bands
~256
Quantization
Noise Equivalent
Radiance (NedR)
12 bits
<0.05 W/m2/sr/mm
Mineral maps at high spatial and spectral
resolution
Study of mare volcanism, variations in
basaltic composition, mantle
heterogeneity at basin and local scale
Signatures of hydroxyl (OH) and water
(H2O) molecules
(IR corrections from same data set)
Status
* Detailed configuration
* Implementation options
& PDR
Completed
CHANDRAYAAN-2: Orbiter Payloads
CLASS: Chandrayaan Large Area Soft X-ray Spectrometer
Surface geochemical mapping of
Mg, Al, Si, Ca, Ti and Fe
-5 deg C
Configuration
• Sensor
– Swept Charge Devices
(SCD) = 64 cm2
(e2V Technologies)
• Collimator
– Gold coated Cu collimator
– Aluminum filter (0.2μm)
• Door for radiation protection
– one time operation
– contains calibration sources
10
CHANDRAYAAN-2: Orbiter Payloads
Solar X-ray Monitor
Monitoring Solar flare X-ray Intensity
(over a wide range)
Stability at high count rate
SDD Module for XSM
Specifications
XSM Analog electronics
Two packages: Sensor & Electronics
Detector
Silicon Drift Detector
Energy Range
1 – 20 keV
70
Detector Area
30
mm2
60
Aperture
~1 mm2
~200 eV @ 5.9 keV
Field of View
±55 degree
Det. Temperature
-35 C
Cooling
Built-in TEC
Total power
6W
FWHM (ADC channels)
Energy Resolution
FWHM Vs. Count rate for various peaking time
2us
1.5us
1us
50
40
30
20
10
0
0
10
20
30
40
Count rate (x1000)
50
60
CHANDRAYAAN-2: Orbiter Payloads
Dual frequency (L- and S-band) SAR
Improved target detection and information
Incidence angle range from 10 to 35
Slant range Resolution: 80 m to 2m-75m
Full Polarimetry
High spatial resolution data
L-band SSPA (TRANSMITTER)H&V POL
Az
Transmitters
(L & S-band SAR
31.0°
8.5°
Antenna
11.20(L-band), 5.60(S-band)
EL. BEAM
200 km
Physical Beam
9.50
350
Beam
corresponding to
data window
10km
30km
95km
125km
Imaging geometry of Chandrayaan-2 SAR
Receiver,
Frequency
Generator and
Digital systems
CHANDRAYAAN-2: Orbiter Payloads
ChACE-2 :
Characterization of Lunar Neutral Atmosphere & its time variations
Repeat of ChACE-1 in
Chandrayaan-1 with a
larger mass range
Mass range : 1-300 amu
Detector
: CEM
Resolution : ~ 0.5 amu
Dynamic range : 109
Payload Mass : < 4 kg
Payload Power : ~30 W
CHANDRAYAAN-2: Rover Payloads
Alpha Particle X-ray Spectrometer (APXS)
Science objective:
Elemental composition of Lunar
surface soil and rocks
Technique
Elements Measured
PIXE
Na, Mg, Al, Si, P, S, Cl, K, Ca, Ti
XRF
Mn, Fe, Ni and higher Z elements
Schematic of rover (APXS on the arm)
Robotic arm
~35±10 mm
Electronics
head
Alpha
source
SDD
Schematic of the
APXS sensor head
Sample surface R: 3 cm
Test results with Detector at -350C,
yielded required resolution at Fe peak
CHANDRAYAAN-2: Rover Payloads
Laser Induced Breakdown Spectroscopy
Science objective:
LIBS: Proto-Model
(top-view)
Qualitative & Quantitative analysis of
lunar composition including volatiles
3D-CAD MODEL OF THE PROPOSED INSTRUMENT
LIBS Proto-Model
Top View
LIBS Proto-Model Bottom-View
Bottom-view
180 mm
Detection of hydrated
minerals by observing the H
emission line at 656 nm.
Thank you for your kind attention
Fairing

similar documents