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

1. 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

2. Variant of small-size satellites classification: • SMALL SATELLITES500 – 1000 kg • MINISATELLITES 100 – 500 kg «SUPER-SMALL» SATELLITES: • MICROSATELLITES 10 – 100 kg • NANOSATELLITES1 – 10 kg • PICOSATELLITES < 1 kg

3. Some specimen ofsupersmall technological satellites

4. Technological Nanosatellite TNS-0 (developed by FSUE “RISDE”, Moscow)

5. “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.)

6. “TNS-0” NANOSATELLITE:BASIC TECHNICAL DATA • ORBITLow, with any inclination • ATTITUDE CONTROL SYSTEMPassive, magnetic • POWER SUPPLYLithium battery, 10 A·h • TEMPERATURE CONTROL SYSTEMPassive • TOTAL MASS (except launching device) 4.5 kg • MEDIUM LIFETIMEON THE ORBIT 1 to 3months • CONTROL & TELEMETRY through GLOBALSTAR system • SERVICEABILITY MONITORING through COSPAS-SARSAT system

7. “TNS-0” NANOSATELLITE:LIST OF ELEMENTSAND THEIR MASSES

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”

9. FLIGHT CONTROL CENTRE “FCC-TNS” IN FSUE “RISDE”

10. Launch of “TNS-0” from ISS28 March 2005 • International reg. Number - 2005-007C NORAD Catalogue Number- 28547 Russian Space Researcher Salizhan SHARIPOV: (left) checking “TNS-0” before its Flight (right) pushing away the Nanosatellite off the Station

11. Method of “TNS-0” launch from International Space Station (ISS) Service Module of ISS - Vorb “TNS-0”

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 space search & rescue system (COSPAS-SARSAT)

13. 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)

14. TNS-0 №6 (TNS-1) for Earth remote Sensing Experiments SideA – Solar Battery SideB – Panel of Devices Basic element of “TNS-1” Structure: 500 m-diameter carbon/aliuminium cellular round plate

15. EARTH REMOTE SENSING NANOSATELLITE “TNS-1”: BASIC TECHNICAL DATA • ORBITSun-synchronous, 650 km • ATTITUDE CONTROL SYSTEM Three axis magnetic, stabilized by rotation (1...3 rev/min) round the sun direction • TEMPERATURE CONTROL SYSTEMPassive • POWER SUPPLYSolar Battery, 24 W • CONTROL & TELEMETRY through GLOBALSTAR system • LIFETIMEON THE ORBIT 2 to 3 Years • TOTAL MASS (except launching device) Less than 7,5 kg • REMOTE SENSING INSTRUMENTSDigital Photo cameras: Linear resolution 50…100 m and Swath width 250 km in RGB mode 1,7 GHz-Transmitter

16. NANOSATELLITE “TNS-1”:REMOTE SENSING INSTRUMENTS

17. NANOSATELLITE“TNS-1”:LIST OF ELEMENTSAND THEIR MASSES * 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 Informationand its transferto central & local rescue Services