| Ionosat-Micro | |
| Image Alt: | General feature of Ukrainian Satellite "Microsat-M" |
| Mission Type: | Ionosphere research |
| Operator: | State Space Agency of Ukraine |
| Website: | "Ionosat-Micro" Mission |
| Spacecraft: | "Mikrosat-M"[1] |
| Manufacturer: | Yuzhnoye State Design Office |
| Launch Mass: | 200kg (400lb) |
| Payload Mass: | 75kg (165lb) |
| Start Date: | 2020s |
| Orbit Reference: | Circular Solar-synchronous |
| Orbit Regime: | Low Earth |
| Orbit Inclination: | 97,9…98,2° |
| Orbit Arg Periapsis: | NaNkm (-2,147,483,648miles) |
Ionosat Micro is a Ukrainian satellite mission.[2]
The head scientific organization is the Space Research Institute of NAS of Ukraine and SSA of Ukraine.
"Ionosat-Micro" Mission realized under the National purpose scientific and technical space program of Ukraine.
Particular project tasks:
| Organizationation | Part in the project | |
|---|---|---|
| UKRAINE | ||
| Space Research Institute of National Academy of Sciences of Ukraine and State Space Agency of Ukraine (SRI), Kyiv | Coordination of research program. Maintenance of functioning of the Data processing, storage and distribution center PROMIS | |
| Yuzhnoye State Design Office, Dnipro | Spacecraft «Microsat-M» designing and launch, payload integration, spacecraft operation planning, formation of accompanying information on spacecraft parameters | |
| Lviv Centre of Space Research Institute, Lviv | Onboard scientific instrumentation integration. Creation of instruments: MWC, ODHS and electronic unit of PDA. Measurement realization and data processing | |
| Institute of Technical Mechanics, Dnipro | DN and DE sensors creation, measurement realization and data processing | |
| National Center of Space Facilities Control and Test | Flight control. Telemetry and scientific information receiving from the spacecraft | |
| POLAND | ||
| Space Research Center, Warsaw | Instrument RFA creation, measurement realization and data processing | |
| BULGARIA | ||
| Space Research and Technology Institute, Sofia | Instrument ID-2 creation, measurement realization and data processing | |
Formation of the scientific objectives of the project "Ionosat - Micro" was for a long time, and conceptual provisions were first formulated in the 1990s, during the development of unrealized mission "Warning." Then, after tragic Spitakskii earthquake (1988), the political leadership of the USSR initiated the development of new, more effective methods of earthquake prediction, based, in particular, on the use of non-traditional for Seismology approaches such as observation of ionospheric harbingers of earthquakes etc. Thus arose the idea of mission "Warning", which, if not collapse of the USSR (1991), could be the most ambitious satellite project in the history of world studies of the ionosphere. The "Ionosat-Micro" Mission on the satellite "Mikrosat-M" embodies the ideas of the mission "Warning" on modern scientific and technological basis.[3] [4]
For the diagnosis of electromagnetic processes in ionospheric plasma in the "Ionosat-Micro" Mission will be used complex instrument MWC, developed by Lviv Centre of Space Research Institute. Experimental testing elements MWC was conducted space experiments "Variant" in the Ukrainian remote sensing satellite "Sich-1M" (2004).[5] To measure the parameters of the ionosphere gas - concentration and temperature neutral and ionized gases - is a complex instrument DN - DE, established in Institute of Technical Mechanics. Flight testing sensors DN and DE experiment was carried out in "Potential" in the Ukrainian remote sensing satellite Sich-2 (2012).[6] In the "Ionosat-Micro" Mission involving foreign partners: Space Research Center of the Polish Academy of Sciences (translated) is instrument RFA creator and Space Research and Technology Institute is instrument ID-2 creator.
The satellite launch was planned for 2018. As of May 2019, work is go on.[7]
"Ionosat-Micro" scientific instrumentation set is installed on the satellite platform «Microsat-M» [8] designed by Yuzhnoye State Design Office to conduct scientific and technological experiments. Ideas for the satellite launching into orbit are processed.
| ORBIT | ||
|---|---|---|
| Circular, the operating range of heights | 620...710 km | |
| Inclination | 97,9...98,2° | |
| Solar-synchronous, local time in a descending node | 10...14 hours | |
| ORIENTATION | ||
| type | active three axes | |
| orientation error in the orbital coordinate system | not more than 5° (3σ) | |
| angular rate of spacecraft stabilization | not more than 0,01 °/с (3σ) | |
| DATA TRANSMISSION TO THE EARTH | ||
| X-range radio line | 30.72 Mbit/s | |
| S-range service radio line | 32 kbit/s | |
| SPACECRAFT WEIGHT | ||
| total | up to 200 kg | |
| payload | up to 75 ky | |
| WARRANTY PERIOD | ||
| not less than 3 years | ||
| SPACE AND TIME MEASUREMENTS ERRORS | ||
| spacecraft positioning error | not more than 1.5 km | |
| spacecraft orientation error (sensors axes) | not more than 1° | |
| onboard time scale error | not more than 1 msec | |
Scientific instrumentation onboard "Microsat-M" designation:
General characteristics of «Ionosat-Micro» scientific instrumentation set:
«Ionosat-Micro» scientific instrumentation set: