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.
| 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) |
