541 flight-proven satellite platforms, components and ground equipment from verified manufacturers worldwide.
Active suspension system for large-sized transformable spacecraft systems at ground modal testing. Simultaneously with the suspension, the dynamic…
Spacecraft thermal-vacuum test chamber automation (600 m³, ±150 °C, 750+ test points, 2000+ parameters, 720+ hr continuous operation).
Programmable control complex of large-sized product forms in real time. The principle of operation is based on measurement…
The accelerometer provides measurement of the apparent acceleration of ballistic and space equipment.
The accelerometer provides measurement of the apparent acceleration of ballistic and space equipment.
Formation of multiple impulses for attitude control of spacecraft in response to control system triggering commands.
In accordance with the specification of the customer. On the basis of the basic upper stage "Fregat" a…
Version: strain gauge sensor with cable jumper. Upon customer's request, it is made with a screwed fitting and…
Exception: the strain gage sensor can be supplied with a shock absorber at the request of the consumer.…
It is made according to "Regulation 98". Execution: the strain gage sensor at the request of the consumer…
Flight-proven transition/adapter compartments for Soyuz (Ø3715/4110 mm) and Zenit (Ø4100 mm) launch vehicles (345–465 kg) for spacecraft-LV interface.
The asynchronous controlled electric motor has a 2-phase supply voltage of 40 V, 1000 Hz; the speed of…
Version: thermoelectric converter (TC) consists of a sensitive element placed in the housing, a cable jumper and a…
It is made according to "Regulation 88". Version: piezoelectric transducer, consisting of a sensitive element installed in the…
It is made according to the "Regulation 98". Version: piezoelectric transducer, consisting of a sensor installed in the…
Flight-proven head fairings for Soyuz (Ø3715 mm) and Zenit (Ø4100 mm) launch vehicles (1180–1870 kg) for spacecraft aerodynamic/thermal…
Version: monoblock, including a primary inductive converter and a gain unit. The sensor is tight. Permissible leakage is…
Flight-proven strain-gauge absolute pressure sensor (0–11 kPa, 5% error, 0.35 kg) for liquid rocket engine control and diagnostics.
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