Purpose. Study of the non-seed capacity and durability of structural elements of rocket and space technology and gas turbine engines under conditions simulating operational ones.
Technical feature. The maximum temperature of the gas flow on the gas-dynamic stand is 1600 °C, the flow velocity is up to or transonic, the rate of change of the gas flow temperature is up to 1000 deg/s
Application area. Rocket science.
Advantages. There are no analogues in Ukraine. The equipment is unique in all major indicators.
Description. It is possible to create a mechanical load of the object of study in combination with a thermal one, as well as introduce corrosive components (for example, seawater salts) into the gas flow.