Spacecraft orientation and stabilization system

    • Spacecraft orientation and stabilization system

    Purpose:
    The spacecraft orientation and stabilization system is designed for the following tasks:
    - the initial stabilization of damping while separation of spacecraft from upper stage
    - securing spacecraft to an oriented state
    - maintaining the spacecraft in an oriented state
    - orientation of the spacecraft with specified accuracy during performing target operations
    - programmable turns and u-turns of spacecraft
    - restoring the orientation of the spacecraft
    - ensuring the energy level
    Year of release: 2019
    Guaranteed service life (years):
    5 years (intended time of use as part of the spacecraft); 7 years (in case of storage); Assigned resource: 50,000 hours
    Estimated production / delivery time (months): 24
    Flight qualification of the product: Yes
    Brief history of flight qualification:
    "Condor-E" spacecraft
    Possibility to adapt the product to customer requirements: Yes
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    Parameter Value
    Orbit MEO
    Weight without connecting harnesses 50 kg
    The accuracy of orientation determination 1 angular minute
    Accuracy of orientation maintenance 3 angular minutes
    Discrepancy in 2 angular minutes
    Discrepancy in indicating the flight attitude of the associated axes of the spacecraft relative to the ICS (Inertial Coordinate System) during target operations 20 angular seconds when using two SCMU (Stars Coordinate Measurement Unit) devices
    Stability 0,001 degree per second
    Working supply voltage 27 V
    Average orbit pass energy consumption 120 W
    Time of establishing the orbital orientation on Control Engines of Momentum Wheels ≤ 2 hours
    Time of establishing the orbital orientation on Liquid Rocket Engines (LRE) ≤ 0.5 hours
    Information exchange channel with Self-monitoring Execution Block GOST R 52070-2003

    Description

    High-precision orientation and stabilization system for medium-orbit spacecraft with moments of inertia from 100 to 5000 kg·m².
    Features:
    - three-circuit system of electrical reaction wheel type with a magnetic wa
    ...

    High-precision orientation and stabilization system for medium-orbit spacecraft with moments of inertia from 100 to 5000 kg·m².



    Features:


    - three-circuit system of electrical reaction wheel type with a magnetic way to reset the kinetic moment and control of Liquid Rocket Engines (LRE).

    - designed for leaky compartments

    - information interaction is provided by means of a redundant bus of the Multiplex Information Exchange Channel (MIEC)

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    Remark

    Made on the radiation-resistant element base of Russian rocket and space industry production

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