Selivanov A.S., Vishnyakov V.M . Development and Flight Testing of “TNS” Nanosatellites

© 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