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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. - PowerPoint PPT Presentation
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© FSUE “RISDE” 1
Selivanov A.S., Vishnyakov V.M.
Development and Flight Testing
of “TNS” Nanosatellites
Russian Federation, Tarusa
September 2007
Federal State Unitary Enterprise “Russian Institute of Space Device
Engineering“ (FSUE “RISDE”)
Moscow, Russia
© FSUE “RISDE” 2
SMALL SATELLITES 500 – 1000 kg
MINISATELLITES 100 – 500 kg
«SUPER-SMALL» SATELLITES:
MICROSATELLITES 10 – 100 kg
NANOSATELLITES 1 – 10 kg
PICOSATELLITES < 1 kg
Variant of small-size satellites classification:
© FSUE “RISDE” 3
Some specimen of supersmall technological satellites
Producer of satellite Satellite name / mass Objective of satellite mission Year of the mission
ESA PROBA-1,2,3
90-100 kg
Testing of basic elements and systems (flight control, attitude control, microthrusters, etc.) of new supersmall S/C
2001, 2007
Singapore, NTU
X-SAT100 kg
Testing of remote sensing instruments
2008
Great Britain, SSTL SNAP-16,5 kg
Orbital manoeuvring and inspection
of other satellites
2000
USA, NASA «Spheres»
3 kg
Mutual manoeuvring of 3 nanosats 2006
USA, California University & Other developers
«CubeSat»-series
about 1 kg
Remote sensing, communications and other applications
Since 2001
USA, Boeing Corporation CubeSat TestBed-1 Testing «CSTB»-platform for 3…10 kg mass technological nanosats
2007
© FSUE “RISDE” 4
Technological
Nanosatellite TNS-0
(developed by
FSUE “RISDE”, Moscow)
© FSUE “RISDE” 5
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.)
“TNS-0” NANOSATELLITE: OBJECTIVES
© FSUE “RISDE” 6
• ORBIT Low, with any inclination
• ATTITUDE CONTROL SYSTEM Passive, magnetic
• POWER SUPPLY Lithium battery, 10 A·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
“TNS-0” NANOSATELLITE:BASIC TECHNICAL DATA
© FSUE “RISDE” 8
GLOBALSTAR modem (Qualcomm standart)
280 Orientation Magnet 150
GLOBALSTAR antenna 250 Magnetic Dampers 100
COSPAS-SARSAT Alarm Buoy
600 Lithium battery 2000
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): 4500
“TNS-0” NANOSATELLITE:LIST OF ELEMENTS AND THEIR MASSES
© FSUE “RISDE” 9
“TNS-0” NANOSATELLITE:
FLIGHT CONTROL CIRCUIT
Flight control centre “FCC-TNS” in FSUE “RISDE”
“TNS-0” nanosatellite
NORAD (USA)
SKKP
(Russia)
Main Flight control
centre (Korolyov city)
“GLOBALSTAR” System
© FSUE “RISDE” 10
FLIGHT CONTROL CENTRE “FCC-TNS” IN FSUE “RISDE”
© FSUE “RISDE” 11
Launch of “TNS-0” from ISS28 March 2005
Russian Space Researcher Salizhan SHARIPOV:
(left) checking “TNS-0” before its Flight
(right) pushing away the Nanosatellite off the Station
International reg. Number - 2005-007C NORAD Catalogue Number- 28547
© FSUE “RISDE” 12
Method of “TNS-0” launch from International Space Station (ISS)
“TNS-0”
Service Module of ISS
- Vorb
© FSUE “RISDE” 13
Geography of “TNS-0” successful Contacts via GLOBALSTAR System
Total period of active work – 68 days. Overall lifetime – 5 months First-ever application of new satellite control technology - through low-orbit satellite communication system GLOBALSTAR (24% of the contacts were successful) First-ever experimental determination of GLOBALSTAR restrictions First-ever satellite serviceability monitoring by means of the International space search & rescue system (COSPAS-SARSAT)
© FSUE “RISDE” 14
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) Successful testing of the experimental nanosatellite platform and miniaturized on-board devices (solar sensors, lithium power-supply batteries, on-board controller, etc.) 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” 15
TNS-0 №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” 16
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
EARTH REMOTE SENSING NANOSATELLITE “TNS-1”: BASIC TECHNICAL DATA
© FSUE “RISDE” 17
Fields of application: natural resources
investigation, ecological and agricultural monitoring, meteorology, education, etc.
Video data compression (JPEG) К = 1, 4, 8
Remote sensing instruments 2 digital photo cameras
Observation Modes - Nadir - Stereo
Type of cameras SONY DSC – V1“TNS-ground” data link rate 665 kbps
Spectral channels 3 visible spectral ranges (RGB)
Transmitter of “TNS-ground” data link:frequency 1,7 GHzaverage power 5 WLinear resolutions (from 650 km) 100 m
Swath width (from 650 km) 250 km Antenna λ/2-pin
Number of pixels 2592х1944
Earth receive station dia. 2,6 m
NANOSATELLITE “TNS-1”:REMOTE SENSING INSTRUMENTS
© FSUE “RISDE” 18
GLOBALSTAR modem280
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
300100
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
Total mass (g): 5200 *
* Total mass without launching appliances
NANOSATELLITE“TNS-1”: LIST OF ELEMENTS AND THEIR MASSES
© FSUE “RISDE” 19
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.)
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