Modeling design of electronic-pneumatic cabin pressure control system

There exsit some problems for the present cabin pressure control system for fighter aircraft. For example, the mechanical inertia is large, response time is long and control precision is poor, also, the diaphragm is easily to fatigue. Based on the above issues, considering the high-speed and small tank capacity of fighter, combining the advantage of pneumatic and digital, the research on electronic pneumatic pressure control system was expanded. The mathematical model of the system components was established and problem of parameter identification was overcome on account of the mathematical description of the controlled object. In view of the trait of time-varying and nonlinear of system, the pole-zero configuration was carried out in a state of equilibrium. The correction device was designed, gain scheduling was carried out within the flight profile and the design of control algorithm was finished. The numerical simulation results show that this method can achieve the fast nonovershooting regulator and its control effect is good. For cabin pressure control system, this method can be transformed to PID form, which has strong robustness; Compared with pure PID control method, this method is independent of debugging personnel experience and possesses strict derivation, theoretical significance and practical value.