A control design oriented mathematical model for the Scirocco plasma wind tunnel

In this paper the mathematical model of a modern arc heated Plasma Wind Tun nel used to test parts of space vehicles during the re-entry phase is prese nted. Due to the complexity of the physical processes arising during the op erating of the plant, a number of simplification is proposed to obtain a co ntrol design oriented fast and efficient simulation software. Such a softwa re was successfully used during the design phase to become confident with t he dynamic behavior of the facility and to achieve a process-control integr ated design. During the operating life of the wind tunnel it will be used t o support the test engineers in the design of the control laws for the trac king of the desired trajectories in temperature and pressure on the test ar ticle. A short description of the test control algorithm which is based on the above model is also provided.