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Directly-connected scramjet combustor model test and ram combustor model experiment facility

This is a Directly-connected scramjet combustor model test and ram combustor model experiment facility. The facility provides two heating methods, air flow heating via heat storage and pre-combustion using hydrogen and oxygen. Gas hydrogen and ethylene are fuels that can be supplied.

  • PDF Access map (Kakuda)
    • Department

    Space Technology Directorate I
    Installation location

    Kakuda Space Center
    Test environment

    Channel cross section: 32 mm × 147.3 mm
    Mach numbers: 2.0, 2.5, 3.0
    Total airflow temperature: 1000 to 2000 K (there are restrictions due to total airflow pressure)
    Total airflow pressure: Standard is 1 MPa (maximum of 2 MPa)
    Ventilation time: 10 seconds
    Ventilation frequency: 4 to 6 times/day (pre-combustion heating), 2 times/day (thermal storage heating)

    Measurement

    		 Pressure: Scanning valve mechanical pressure sensor (48ch×3 tanks) Temperature: 10-channel thermocouple Gas analysis: Sampling at the exit, a maximum of 10 points simultaneously
    Fuel/coolant water supply

    400 mm

    Fuel:
    [Gas hydrogen] 0.1 kg/s × 2 systems (used after switching from ethylene supply)
    [Ethylene] 0.1 kg/s × 1 system (maximum duration of 10 seconds)

    Coolant water: 400 liters at 3 MPa (approx. 5 liters/second)

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