Medium-size High Enthalpy Shock TunnelAlso possible to use as a ballistic range for a small vehicle flight experiment
The facility was established as a pilot high enthalpy shock tunnel. At present, it also is being used as a ballistic range to conduct small vehicle flight experiments.
This facility, when used as a ballistic range, requires no gunpowder when launching a projectile (small-sized flight vehicle model). In light of this, we realized high operability as it is possible to conduct four tests a day.
Operations that do not use gunpowder are also helpful to reduce operational costs and to improve safety.
| Department | Space Technology Directorate I |
|---|---|
| Installation location | Kakuda Space Center |
| Ballistic range specifications | Secondary air storage tank pressure (MPa): 7.0 Piston weight (kg): 15 to 40 Compression tube length (m) / diameter (mm): 16 / φ210 Compression tube pressure (MPa): 75 Launch tube No. 1 length (m) / diameter (mm): 4.0 m / φ15 mm Launch tube No. 2 length (m) / diameter (mm): 6.5 m / φ72 mm Launch tube No. 3 length (m) / diameter (mm): 2.5 m / φ120 mm Number of tests: 4 times/day In the case of using a 3 g projectile: Speed of 3 km/s (actual) In the case of using a 600 g projectile: Speed of 200 m/s (actual) |
| Shock tunnel specifications | Test airflow stagnation enthalpy: Maximum of 25 MJ/kg Test airflow stagnation pressure: Maximum of 60 MPa Test airflow duration： more than 2 milliseconds Nozzle exit diameter: 400 mm Number of tests: 2 times/day |
| Year for improving the ballistic range | March 1999 |
