Transcript Document

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
«SUPER-SMALL» 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
«Spheres»
3 kg
Mutual manoeuvring of 3 nanosats
2006
«CubeSat»-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 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
© 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
 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
search & rescue system (COSPAS-SARSAT)
13
© 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)
 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”
14
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”
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)
К = 1, 4, 8
100 m
250 km
2592х1944
- Nadir
- Stereo
“TNS-ground” data link rate
665 kbps
Transmitter of “TNS-ground” data
link:
frequency
1,7 GHz
average power
5W
Antenna
λ/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.)

-
 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