Application of Pneumatic Thermal Experiment DC Power Supply System

   Hypersonic aircraft fly in the atmosphere, and the surrounding air is strongly compressed by bow shock waves, causing intense friction with the surface of the aircraft. Most of the kinetic energy of the aircraft is converted into air thermal energy, resulting in a sharp rise in air temperature. The high-temperature air creates a huge temperature difference with the surface of the aircraft, and some of the thermal energy is transferred to the surface of the aircraft through the boundary layer. This heating phenomenon is called "aerodynamic heating" or aerodynamic heat.

   To ensure the safety of hypersonic aircraft and confirm whether the aircraft materials and structures can withstand the thermal shock and high-temperature stress damage generated during high-speed flight, a transient aerodynamic thermal simulation system for high-speed aircraft is established to conduct static and dynamic aerodynamic thermal simulation experiments and thermal strength experiments on the materials and structures of high-speed aircraft.

   The aerodynamic thermal test methods can be divided into two categories: "convection mode" and "non convection mode". The "convection mode" is mainly represented by high-temperature structural wind tunnels. During the experiment, high-temperature and high-speed airflow is rapidly passed over the surface of the structure to achieve forced convection heat transfer. The "non convective method" is a thermal testing method dominated by heat conduction or radiation, in which a tungsten spiral filament is used as the radiation source, sealed in a transparent quartz glass tube, and energized to emit strong infrared light in a radiative aerodynamic thermal environment simulation.