BAUMANETS Spacecraft (Removed from Service). / December 9, 2008 /

The BAUMANETS spacecraft belongs to micro satellite category operating in sun-synchronous orbits. It is designed for scientific and technical and educational experiments. Optoelectronic equipments installed on board the spacecraft will allow the Earth’s surface observation in visible and near IR ranges, meteorological and hydrometeorological tasks, space geodesy tasks to be fulfilld as well as students to get practical experience in operating real spacecraft and optimization of micro satellite production technology.

The BAUMANETS spacecraft operating suggests that a number of experiments should be persuaded including optical remote sensing of Earth which may be of interest for numerous consumers of such data and therefore, various uses of the spacecraft are feasible.

Tasks to be Fulfiled

• Scientific and research experiments in data transfer;


• Acquisition of data on the Earth using remote sensing techniques;


• Monitoring of climate, hydrosphere, the Environment, regions of oil and gas production, risky situations, assessment of forests and agricultural lands, etc.


• Optimization of spacecraft control techniques.

The spacecraft mass is no more than 100kg and it belongs to micro satellite category in accordance with the western classification. A number of design characteristics is due to main payload requirement – digital multispectral camera designed for earth’s surface imaging.
The following experiments are planned to carry out on board BAUMANETS spacecraft: signal transmission via amateur radio link — MGTU-175 Experiment; research of the spacecraft behavior, its dynamic behavior when using electromagnetic attitude control system (control algorithm optimization); earth’s surface imaging by optoelectronic equipment and image data transfer to consumer; studying the possibility of using microwave data transfer channel; the use of GLOBALSTAR channel for telemetric data transmission

Main Characteristics

• Orbit — sun-synchronous


• Altitude — 600-800km


• Inclination — 98° (sun-synchronous orbit)


• Spacecraft mass — up to 100kg


• Dimensions no more than 700×700×700mm (cubic);


• Spatial resolution (for 600km altitude) – no worse than 50m;


• Single-axis stabilization with one wheel by pitch;


• Orientation accuracy – no worse than 2° by three axes;


• Stabilization accuracy – no worse than 0.01° per sec by three axes;


• Active lifetime — no less than 1 year


• Orbital injection is planned to make as main or piggyback payload on board DNEPR launcher

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