Main Scientific Objectives
Measurement of gamma radiation from the Martian surface,
powerful solar flares and gamma-bunts. The instrument operates
continuously along the Earth-to-Mars trajectory recording cosmic
gamma-rays. In orbit around Mars, the instrument measures gamma
spectra of the surface.
Instrument
Detection unit with a thermal control system
Spectrometric amplifier
Power supply unit
Amplitude analysis unit
Data processing unit and output to the MORION system
The detection unit with an amplifier and a thermal control
system will be mounted on a special deploying structure to prevent
heat loads from spacecraft hardware
Main Characteristics
Volume of each of two HpGe 90 cm3
Measurement range 0.03 to 8 MeV
Number of spectral channel 4096
Time resolution in burst mode 61 µ s
Time resolution in planet mode 1-5 min
Time resolution in background mode 10 to 120 min
Mass 25.65 kg
Main Scientific Objectives
High-precision localization (delta-phi = 10 sec of are) of
gamma-burst sources using data from ULYSSES and near-Earth satellites
Investigation of gamma-burst emission mechanisms
Analysis of low-energy absorption features
Study of thermal emission in the burst decay phase
Test of the Mars atmosphere model using the absorption of X-rays
from the sources Sco-X1 and Cyg-X1
Main Characteristics
Sensor #1, 2 cleaved NaI(Tl). d X h - 72 X 10 mm
Energy range 4 keV to 1 MeV
Energy resolution 36-40% FWHM at 5.9 keV
7.6-8.0 FWHM at 662 keV
Sensitivity 5 X 10-7 erg/cm2
Resolution 1 ms for integral measurements
0.25 s for spectral analysis
Power consumption 3 W
Mass 6.0 kg
Cosmic gamma burst spectrum with 3 absorption features at 10.4,
18.3, and 25.8 keV (experiment LILAS, PHOBOS mission data).
Main Objectives
Study of pulsations, rotations and the internal structure of stars.
Photometric microvariability of stars is the only observable manifestation of
processes occurring in their internal structures.
Method
Long-term, continuous, and high-accuracy photometry of stars
along the Earth-to-Mars trajectory
Instrument
EVRIS contains a telescope, a photometer. and a CCD-based star
sensor. The instrument is installed on the PAIS platform.
Main Characteristics
Limiting magnitude mv < 4
Number of stars to be observed 10-20
Spectral range of observations 300-800 nm
Periods of expected pulsations 1-10 min
Photometer FOV 16 min of arc
Star sensor FOV 3°
Scanning zone size 30°-60°
Pointing accuracy 0.5-1 min of arc
Brightness measurement accuracy 10-6
Information capacity 1 Mbit/day
Duration of one observation session 3-4 weeks
Power consumption 5 W
Mass 7.4 kg
Main Objectives
Study of the Sun's internal structure from measurements of solar
brightness oscillations
Method
Long-term, continuous, and high-accuracy photometry of the Sun
along the Earth-to-Mars trajectory
Instrument
SOYA consists of a solar photometer with a filter at 845 nm with a 5 nm
passband, a two-axis solar sensor built around COD-arrays for making
corrections of photometric data by changing the spacecraft orientation. The
SOYA and EPICAM instruments share a common electronics unit.
Main Characteristics
Brightness resolution Delta-I/I 10-6
FOV 1-5°
Number of pixels in a CCD array 1024 pixels
Angle measurement accuracy 20 sec of arc
Mass 1 kg
Main Scientific Objective
Study of radiation conditions along flight trajectories to
Mars and near the planet
Timely forecast of the spacecraft irradiation dose
Dosimetric control on board the spacecraft
Processes of generation and propagation of charged particles in the
interplanetary space
Estimation of meteorite hazard to a spacecraft
Measure Sun's X-ray flux
Estimate the energy of solar X-ray bursts
Determine the energy spectra and spatial distribution of
charged particle fluxes within a wide energy range
Identify the mass composition of charged particle fluxes
Determine an integral dose and its rate as well as spectra of linear
losses of charged particle energy
Measure the density of micrometeoritic particle flows
Hardware
Component Mass Power
SF-2 photon spectrometer 5 kg 2 W
SES-20 charged particle spectrometer 5 kg 5 W
KS-18M cosmic-ray monitor 3 kg 3 W
RADIUS-MD meter of absorbed radiation dose
TERS equivalent dose meter 1.5 kg 1.5 W
AFDP-2 micrometeorite flux meter
RADIUS-MI interface unit
Main Characteristics
X-ray radiation flux 2 to 20 keV
Energy and spatial distribution of charged
particle fluxes within energy ranges
for electrons 0.07 to 1.5 MeV
for protons 0.05 to 200 MeV
for heavy nuclei (2 <= Z <= 20) 2 to 4.0 MeV/nucleon
Micrometeorite fluxes:
Velocity range 3 to 35 km/s;
Mass range 5 X 10-4 to 109g
Self-charges particles 10-14 to 10-9 C
Spacecraft dose rate behind 0.1 mm, 1.0 mm, and 10.0 mm Al
Spectra of linear losses of charged particle energy within 0.3 to 1500
keV/µ m
Operation Program
Continuous operation along the Earth-to-Mars trajectory; the
data capacity is 2 Mbit/day
Operation near Mars should follow a special program
Data volume is 0.2 Mbit/day
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