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RELEC
project
(Relativistic ELECtrons)
MICROSATELLITE KARAT FOR PLANETARY MISSIONS,
ASTROPHYSICAL AND GEOPHYSICAL RESEARCH
2
UNIFICATED SPACECRFAFT KARAT WITH PAYLOAD
Spacecraft mass on the
orbit – 110 kg
Three-axes orientation
Active operational time of a
mission no lesss than 3
years
3
VIBRO-DYNAMIC TESTS
4
5
TEST ‘S FACILITY
6
BASIC PRINCIPLES OF UNIVERSAL SPACECRAFT KARAT
ELABORATION
• already tested and elaborated Russian on-board systems, instruments,
modules and units are used;
• design and interfaces are made in accordance wuth international
standards;
• module construction of small spacecraft;
• on-board systems formed the spacecraft are also unificated.
Spacecraft mass is about 100 kg
Stabilisation accuracy - 4 ×10-3 degree/s
Orientation accuracy - 10·solid min
Time of active operations 3 year
On-board memory volume - no less than 8 GByte
Scientific data transfer with the use of S-LINEwill done of ciast th wjПередача
научной информации по радиолинии S- или X–диапазона
7 Spacecraft ative is actyve 3aода
EXPERIMENT RELEC ON-NOARD KARAT MISSION
Goal of experiments:
• study of cosmic ray and
magnetosphere energetic
particle acting on the upper
Atmosphere
•study of atmosphere
transient luminous effects.
8
Mission control and data receiving will be
provide be the Mission Control
Centre of Lavochkin space
corporation as well as the compact
ground receivers.
Ground receivers with antenna diameter 3,7 and 5 m
Unified platform “Karat” for small spacecraft
9
Group launching Special mission
Rokot Dnepr Soyuz Start-M
By-pass mission
1
History of the problem
Discovery of electron radiation belts
onboard ELECTRON satellites in 60’s.
MAXIS (1996) experiment onboard balloons,
Kiruna. High-energy electrons >500 keV
precipitations:
Flux - 5 х 1025 particles for eight days was
detected at low altitudes .
Total number of trapped electrons –
2 х 1025.
12345678
The X-rays (produced from ~1.7 MeV electrons) measurements
showed that there are two main types of precipitation – long-term
(~100 s) and short enhancements (~10 s) modulating the count
rate. MAXIS measurements.
Precipitation of ~100 keV electrons from radiation belts measured
in SAMPEX experiment.
Scientific objectives
Magnetosphere relativistic electron
acceleration and precipitation research.
Study of high-energy particle acting on the
upper Atmosphere and ionosphere.
Search of transient phenomena in possible
connection with energetic particle interactions
in the Atmosphere
Study of acceleration processes in the
Atmosphere as the possible source of high
energy magnetosphere electrons
Crucial demands
Simultaneous observations of energetic
electron & proton flux and low-frequency
electromagnetic wave intensity variations
with high temporal resolution.
Fine time structure measurements of
transient lightning events in optics, UV, X-
and gamma rays.
Monitor detection of charge and neutral
background particles in different areas of
near-Earth space.
Demands to the instruments
electron detectors: wide energy range (~0.1-10.0 MeV),
temporal resolution ~1 ms, pitch-angle distribution
measuring, wide dynamical range (from ~0.1 up to
105 part./cm2s).
Low-frequency analyzer: measuring of two field
components at least, frequency bands ~0.1-10 kHz.
X- and gamma-ray detectors: temporal resolution
~1 mcs, sensitivity ~10-8 erg/cm2 for burst.
Additional: detecting of protons with energies > 1 MeV,
wide-field observe of Atmosphere in optics, UV, X- and
gamma-rays with possibility of imagination in optics.
Instruments
DRG-1 & DRG-2 - two identical detectors of X-, gamma-
rays and high-energy electrons of high temporal
resolution and sensitivity
DRG-3 - three axe directed detectors of energetic
electrons and protons
Telescope-T - optical imager
DUF - UV detector
NChA - low-frequency analyser
RChA - radio-frequency analyser
DOSTEL - dosimeter module
BE - module of commands and data collection
DRG-1 (DRG-2) instrument
Two identical NaI(Tl)/CsI(Tl)/plastic scintillator phosvich
detectors, both directed toward the Earth
Physical parameters:
X- and gamma-quanta electrons
energy range 0.01-2.0 MeV, 0.2-10.0 MeV
effective area ~200 cm2 ~200 cm2sr (geom. factor)
(total ~800 cm2)
temporal resolution 0.1 mcs 1.0 ms
sensitivity ~5·10-9 erg/cm2 ~10-1 part./cm2s
Technical parameters
Mass - < 7 kg;
sizes 300270200 mm;
power expenditure at 28 V no more 10 W.
DRG-3 instrument
Three identical NaI(Tl)/CsI(Tl)/plastic scintillator
phosvich detectors, directed along three axe mutually
normal (as Cartesian coordinate system)
Physical parameters:
electrons protons
energy range 0.1-10.0 MeV, 1.0-100.0 MeV
geom. factor ~2 cm2sr ~2 cm2sr
temporal resolution 1.0 ms 1.0 ms
sensitivity ~10 part./cm2s ~10 part./cm2s
Technical parameters
Mass - < 4 kg;
sizes 250250250 mm;
power expenditure at 28 V no more 6 W.
Scintillation detectors
To the sky
Along the geomagnetic
field line
Telesope -T instrument
Optical imager based on multi-grain mirror
Physical parameters:
Spectral band: 300-400 nm Technical parameters
Angle resolution: 0.4o. Mass - < 5 kg;
Angle of view: 7.5o.
Cells number: 4000. sizes 200200400 mm;
Photomultiplier channels power expenditure at 28
number: 64. V no more 6 W.
Time resolution: 100 s.
Amplitude range: 105.
DUF instrument
Two photomultiplier tubes with different input window
filters
Physical parameters:
Spectral band:
PMT1 - 300-400 nm
PMT2 (red) - 630-800 nm
Angle of view: 7.5o . Technical parameters
Time resolution: 100 s. Mass - < 1 kg;
Amplitude range: 106. sizes 14014080 mm;
power expenditure at 28 V
no more 1 W.
PMT1
PMT2
NChA instrument
Low-frequency analyzer: two magnetic field component
meters, two electric field component meters and
analyzer unit
Physical parameters:
Frequency band: 20 Hz - 20 kHz
number of spectral components:
Technical parameters
1024
Mass - < 3 kg;
frequency step: 20 Hz .
Time resolution: 2 s. sizes 16013080 mm;
Number of spectral component power expenditure at 28 V
categories: 16. no more 5 W.
magnetic and electric field component meters
ИМ
КВЗ2
45 ZИМ
КВЗ1
1,5 м
ZКВЗ2
XКВЗ2
ZКВЗ1
90
90
YКВЗ2
Z XКВЗ1 45
YКВЗ1
0,4 м (max)
VКА
Y
Z
Метки
X
Ориентация осей КВЗ Ориентация оси Z ИМ
Оси ZИМ, ZКВЗ1 и ZКВЗ2 должны быть взаимно ортогональны, причем:
1 Оси XКВЗ1, ZКВЗ1, XКВЗ2 и ZКВЗ2 лежат в одной плоскости, которая наклонена к вектору
скорости VКА на 45.
2 Оси ZИМ, YКВЗ1 и YКВЗ2 коллинеарны и перпендикулярны к плоскости осей XКВЗ1, ZКВЗ1,
XКВЗ2 и ZКВЗ2 (45 с направлением вектора скорости спутника VКА).
3 Оси XКВЗ1 и XКВЗ2 перпендикулярны между собой.
RChA instrument
Radio frequency analyzer
Physical parameters:
Technical parameters
Mass - < 1 kg;
sizes 10010050 mm;
power expenditure at 28 V
no more 5 W.
DOSTEL instrument
Dosimetry unit
Technical parameters
Mass - < 1 kg;
sizes 1008070 mm;
power expenditure at 28 V
no more 1 W.
BE instrument
Physical parameters:
Total data transfer: 500
Mbyte per day.
Number of control
commands : 24. Technical parameters
Number of digital Mass - < 4 kg;
commands: 256 categories. sizes 270250200 mm;
Possibility of flexible trigger. power expenditure at 28 V
no more 4 W.
Ranges of particles and quanta measuring in RELEC experiment
Electrons 0.2 – 10 MeV
> 10 MeV
> 0.3 MeV
Protons 0.3 – 60 MeV
> 50 MeV
3 – 150 MeV
>150 MeV
Gamma 0.05 – 1.0 MeV
Neutron 0.1 – 30 MeV
X-rays 10 – 100 keV
UV 300-400 nm
TOTAL RELEC characteristics
Mass 45 kg.
Power 60 W.
Data flow 500 MB/day.
Operational modes
- background mode:
provides 100% covering of the orbit with given time resolution < 1 second for
ex.
no more than 20 MBytes/day
- event mode:
provides a few (3-5) time intervals per orbit with fine (<1 mks) time resolution
initialized by trigger
about 50 MByte on event
four groups of instruments:
- DRGE-1, NChA
- DRGE-1(2), DUF, Telescope-T, RchA
- BChK, DOSTEL – only background mode
- BE – provides other instruments
Total – about 500 MByte/day
Trigger conditions:
1) Intrinsic trigger:
a) Given signal level;
b) Intensity on the given time interval;
c) Given signal level & intensity on the given time interval (a&b);
d) Coincidence of internal and external (from chosen other instrument) strobes.
2) External trigger:
a) Data fixation in the given time interval by the trigger signal from chosen other instrument.
b) Data fixation in the given time interval in the case of trigger of event
3)Trigger of event:
coincidence of intrinsic triggers from two or more instruments
В ремя з ап ис и в кол ь ц ев у ю В ремя з ап ис и в кол ь ц ев у ю
п а м я т ь п о с л е т р и г ге р а t 1 g п а м я т ь д о т р и г ге р а t1 g
15 5 15 5 15 5
РГД
20 мс
100 мс д л я Д У Ф
ДУФ
В рем я з ап ис и в кол ь ц ев у ю
памят ь д о т риггера
t1 r= 1 м с
РЧ А
БНД
вы д ает Т К
для
ф и кс а ц и и
инф в
С т р о б п о т р и гг е р у приб орах
t1 g = 1 0 м с С т роб по т риггеру
С т роб по т риггеру t 1 r= 3 м с
t1r = 3 м с
БН Д
С т роб ы не с овпал и , С т роб ы с овпал и , но
С т роб ы с овпал и , РЧА
с об ы т ия не з апис аны с об ы т ия не з апис аны
не м ожет з апис ат ь
с об ы т ие. З начит над о
и н ф о р м а ц и ю в F IF O
Р ЧА у д ерживат ь на
время с т роб а РЧ А
Other geophysical and space-
physics problems can be solved
using the same devices
Lithosphere-ionosphere connections
(earthquakes)
Atmosphere-ionosphere connections
(thunderstorms)
Technical applications
Dosimetry and SEU (single event upsets)
problem taking into account neutron
component of radiation.
Timetable
№ Name Beginning
End
(month, year)
1 Elaboration of Proposal on scientific payload March 2008
December 2008
2 Elaboration of documentation and test models December 2008
Manufacturing of models
December 2009
3.1. Manufacturing of engineering model (EM), tests of December 2009
EM.
March 2010
3.2. Manufacturing of test facility, complex tests of EM. December 2009
Correction of documentation.
March 2010
4.1. Manufacturing of flight example March 2010
Маy 2010
4.2. Manufacturing of test facility for flying example. March 2010
Маy 2010
5. Complex tests of flight example. Preparing of June 2010
launching. December 2010
