Space Platform 100

Purpose:
Design and manufacture of small spacecraft for technological scientific purposes, communications, remote sensing for operation in various types of orbits – from low circular to geostationary.
Year of release: 2016
Guaranteed service life (years):
Active life (SAS) - 5 years for remote sensing of the Earth (ERS), 10 years for small spacecraft (ICA) communication (with bringing SAS up to 15 years).
Estimated production / delivery time (months): 18
Flight qualification of the product: No
Brief history of flight qualification:
Most of the modules of the platform system, including the onboard control system and the orientation and stabilization system, are composed of previously developed and flight-qualified devices and equipment, which makes the platform even cheaper and more attractive by minimizing risks.
Possibility to adapt the product to customer requirements: Yes


Parameter Value
Working orbits Low circular orbit or the geostationary orbit
Platform weight Up to 120 kg
Payload weight Up to 100 kg
Payload power supply capacity 400 watts for RS and up to 1500 watts for the ICA connection
Orientation Three-axis, active
Orientation accuracy, deg Not more than 0,08. Not more than 0,0004.
Nominal voltage, V 27±0,5

Description

Platform for small spacecraft weighing up to 180 kg. Height of operation on different types of orbits – from low circular to geostationary. The ICA platform is divided into several independent modules. Each module separately is a subsystem of the platform and
... Platform for small spacecraft weighing up to 180 kg. Height of operation on different types of orbits – from low circular to geostationary. The ICA platform is divided into several independent modules. Each module separately is a subsystem of the platform and is a functionally and structurally separate unit, which has clearly defined mechanical, electrical and thermal interfaces.
Peculiar properties:
- untight;
- battery: Nickel-hydrogen for the ICA remote sensing; Li-ion for the ICA connection;
- passive thermal control system on heat pipes and heaters;
- system of orientation and stabilization on the basis of the star sensors and control engines-flywheels;
- maintaining the orbit parameters is carried out by the correction system based on the thermocatalytic propulsion system (hydrazine) for the remote sensing spacecraft, the electric propulsion system (xenon) for the communication spacecraft.

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Remark

Stage of development: The design documentation for the platform and the option of mounting the payload for remote sensing has been Released. All parameters and characteristics of the platform are confirmed.

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