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Federal State Unitary Enterprise
“Russian Institute of Space Device
Engineering“ (FSUE “RISDE”)
Moscow, Russia
Selivanov A.S., Vishnyakov V.M.
Development and Flight Testing
of “TNS” Nanosatellites
Russian Federation, Tarusa
September 2007
© FSUE “RISDE”
1
Variant of small-size
satellites classification:
 SMALL SATELLITES
500 – 1000 kg
 MINISATELLITES
100 – 500 kg
В«SUPER-SMALLВ» SATELLITES:
 MICROSATELLITES
10 – 100 kg
 NANOSATELLITES
1 – 10 kg
 PICOSATELLITES
© FSUE “RISDE”
< 1 kg
2
Some specimen of supersmall
technological satellites
Producer of satellite
ESA
Satellite name / mass
PROBA-1,2,3
90-100 kg
Objective of satellite mission
Year of the
mission
Testing of basic elements and
systems (flight control, attitude
control, microthrusters, etc.) of new
supersmall S/C
2001, 2007
Singapore, NTU
X-SAT
100 kg
Testing of remote sensing
instruments
2008
Great Britain, SSTL
SNAP-1
6,5 kg
Orbital manoeuvring and inspection
of other satellites
2000
В«SpheresВ»
3 kg
Mutual manoeuvring of 3 nanosats
2006
В«CubeSatВ»-series
about 1 kg
Remote sensing, communications
and other applications
Since 2001
CubeSat TestBed-1
Testing «CSTB»-platform for 3…10
kg mass technological nanosats
2007
USA, NASA
USA, California
University & Other
developers
USA, Boeing Corporation
© FSUE “RISDE”
3
Technological
Nanosatellite TNS-0
(developed by
FSUE “RISDE”, Moscow)
© FSUE “RISDE”
4
“TNS-0” NANOSATELLITE:
OBJECTIVES
TNS-0 IS DESIGNED FOR SHORT-TIME FLIGHT TESTING:
- of a new nanosatellite platform
- of a new flight control method using GLOBALSTAR space
communication system
- of serviceability monitoring method using COSPAS-SARSAT space
system
- of new on-board miniaturized devices (power supply, Sun and
horizon optical sensors, controller units, etc.)
© FSUE “RISDE”
5
“TNS-0” NANOSATELLITE:
BASIC TECHNICAL DATA
• ORBIT
Low, with any inclination
• ATTITUDE CONTROL SYSTEM
Passive, magnetic
• POWER SUPPLY
Lithium battery, 10 AВ·h
• TEMPERATURE CONTROL SYSTEM
Passive
• TOTAL MASS (except launching device)
4.5 kg
• MEDIUM LIFETIME ON THE ORBIT
1 to 3 months
• CONTROL & TELEMETRY
through GLOBALSTAR system
• SERVICEABILITY MONITORING
through COSPAS-SARSAT system
© FSUE “RISDE”
6
“TNS-0” NANOSATELLITE:
LIST OF ELEMENTS
AND THEIR MASSES
GLOBALSTAR modem
(Qualcomm standart)
280
Orientation Magnet
150
GLOBALSTAR antenna
250
Magnetic Dampers
100
COSPAS-SARSAT Alarm
Buoy
600
Lithium battery
COSPAS-SARSAT antenna
70
Cables
100
System Controller
200
Load-carrying Plate
500
4 Sun Sensors
50
Mounting Elements
150
Horizon Sensor
50
Total Mass (g):
© FSUE “RISDE”
2000
4500
8
“TNS-0” NANOSATELLITE:
FLIGHT CONTROL CIRCUIT
“TNS-0”
nanosatellite
“GLOBALSTAR” System
SKKP
(Russia)
NORAD
(USA)
Main Flight control
centre (Korolyov city)
Flight control centre “FCC-TNS”
in FSUE “RISDE”
© FSUE “RISDE”
9
FLIGHT CONTROL CENTRE “FCC-TNS”
IN FSUE “RISDE”
© FSUE “RISDE”
10
Launch of “TNS-0” from ISS
28 March 2005
International reg. Number - 2005-007C
NORAD Catalogue Number- 28547
Russian Space Researcher Salizhan SHARIPOV:
(left) checking “TNS-0” before its Flight
© FSUE “RISDE”
(right) pushing away the Nanosatellite off the Station
11
Method of “TNS-0” launch
from International Space Station (ISS)
- Vorb
© FSUE “RISDE”
12
Geography of “TNS-0” successful
Contacts via GLOBALSTAR System
�Total period of active work – 68 days. Overall lifetime – 5 months
пѓ� First-ever application of new satellite control technology - through low-orbit
satellite communication system GLOBALSTAR (24% of the contacts were
successful)
пѓ� First-ever experimental determination of GLOBALSTAR restrictions
пѓ� First-ever satellite serviceability monitoring by means of the International
search & rescue system (COSPAS-SARSAT)
13
В© space
FSUE “RISDE”
MAIN RESULTS
OF “TNS-0” FLIGHT TESTING
�Total period of active work – 68 days (up to 5 June 2005)
� Overall lifetime – 5 months (up to the end of August 2005)
пѓ� Successful testing of the experimental nanosatellite platform and
miniaturized on-board devices (solar sensors, lithium power-supply
batteries, on-board controller, etc.)
пѓ� First-ever application of the new satellite control technology through the
global satellite communication system GLOBALSTAR:
- nearly 90 contacts via GLOBALSTAR (24% of them - successful)
- stable control of all processes on board of “TNS-0”
- experimental determination of GLOBALSTAR restrictions (due to
non-global coverage of Earth surface by actual GLOBALSTAR constellation
and Earth stations, absence of roaming for several Earth regions, not a full
adaptation of GLOBALSTAR modem to on-board operation, etc.)
� Successful “TNS-0” serviceability monitoring by means of the
International space search & rescue system (COSPAS-SARSAT)
© FSUE “RISDE”
14
TNS-0 в„–6 (TNS-1) for Earth
remote Sensing Experiments
Side A – Solar Battery
Side B – Panel of Devices
Basic element of “TNS-1” Structure: 500 m-diameter
carbon/aliuminium cellular round plate
© FSUE “RISDE”
15
EARTH REMOTE SENSING
NANOSATELLITE “TNS-1”:
BASIC TECHNICAL DATA
 ORBIT
Sun-synchronous, 650 km
 ATTITUDE CONTROL SYSTEM
Three axis magnetic, stabilized by
rotation (1...3 rev/min) round the sun direction
 TEMPERATURE CONTROL SYSTEM
Passive
 POWER SUPPLY
Solar Battery, 24 W
 CONTROL & TELEMETRY
through GLOBALSTAR system
 LIFETIME ON THE ORBIT
2 to 3 Years
 TOTAL MASS (except launching device)
Less than 7,5 kg
 REMOTE SENSING INSTRUMENTS
Digital Photo cameras:
Linear resolution 50…100 m and Swath width 250 km in RGB mode
1,7 GHz-Transmitter
© FSUE “RISDE”
16
NANOSATELLITE “TNS-1”:
REMOTE SENSING INSTRUMENTS
Fields of application: natural resources
investigation, ecological and agricultural
monitoring, meteorology, education, etc.
Remote sensing instruments
2 digital photo
cameras
Type of cameras
Observation Modes
SONY DSC – V1
Spectral channels
3 visible spectral ranges (RGB)
Linear resolutions (from 650 km)
Swath width (from 650 km)
Number of pixels
© FSUE “RISDE”
Video data compression (JPEG)
Рљ = 1, 4, 8
100 m
250 km
2592С…1944
- Nadir
- Stereo
“TNS-ground” data link rate
665 kbps
Transmitter of “TNS-ground” data
link:
frequency
1,7 GHz
average power
5W
Antenna
О»/2-pin
Earth receive station dia. 2,6 m
17
NANOSATELLITE“TNS-1”:
LIST OF ELEMENTS AND THEIR MASSES
280
Transmitter of “TNS-ground”
data link (1,7GHz)
650
GLOBALSTAR antenna
250
Antenna 1,7 GHz
50
Magnetometer
270
System controller
250
Attitude control system:
- 3 inductors
- controller unit
300
100
Telemetry Sensors
100
2 Sun sensors
100
Power Supply
300
Horizon sensor
50
Cables
300
2 digital photo cameras
600
Load-carrying plate
800
GPS/GLONASS receiver
100
Mounting elements
150
GPS/GLONASS antenna
150
Solar battery
400
GLOBALSTAR modem
Total mass (g):
© FSUE “RISDE”
5200 *
* Total mass without launching appliances
18
Future Space Systems on the
base of “TNS” Nanosatellites
Space remote sensing System “Lokon”:
Constellation including 4-6 Nanosatellites
Orbits: 600…700 km (Height), 98º (Inclination), 4-6 Orbital Planes
Three visible spectral Ranges (RGB)
Observation Width – 250…300 km, linear Resolution – 50…100 m
Delivery of Space Monitoring Information (Images) to Users 1 to 2 Times
each Day directly in the monitored Locality
- Application of commonly used Personal ground-based Stations (F = 1,7
GHz, Aperture Dia 2,5 m) to receive Space Monitoring Information
- Wide Scope of Applications for “Lokon” Monitoring Information (Ecology,
Emergencies Mitigation, Agriculture, Fishing, Natural Resources, etc.)
пЃ±
-
 Low-orbit Space Communication System “KOSKON” including 6-12
Nanosatellites for gathering of global Emergencies Monitoring Information
and its transfer to central & local rescue Services
© FSUE “RISDE”
19
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