Adjustment and Braking Engine

    • Adjustment and Braking Engine

    Purpose:
    Unmanned Spacecraft reactive control system
    Year of release: 2010
    Flight qualification of the product:
    Letter "O", flight use
    Possibility to adapt the product to customer requirements: Yes
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    Parameter Value
    Propellants, Fuel/Oxidizer UDMH/NTO
    Total Nominal Thrust 464.0 N
    One Thruster Nominal Thrust 116.0 N
    Nominal Specific Impulse of Thruster, Steady State 2,855 m/s
    Nominal Inlet Pressure 1.47 MPa
    Inlet Operating Pressure 1.37…1.57 MPa
    Total Firing Time, up to 2,000 s
    Cycle Life, Number of Starts-up, up to 5,000
    Nozzle Expansion Ratio 53
    Operating Voltage 27 V
    Mass, not over 8.0 kg

    Description

    Propulsive burn formation for center of mass velocity variation during spacecraft orbit control and braking. Design features: - A four-chamber engine based on four the 11D428A-24 thrusters with integrated propellant supply system. The thrusters are rigidly b
    ... Propulsive burn formation for center of mass velocity variation during spacecraft orbit control and braking.
    Design features:
    - A four-chamber engine based on four the 11D428A-24 thrusters with integrated propellant supply system. The thrusters are rigidly bracket-mounted.
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