SINOPSIS

This paper presents some calculus elements, which are useful for the aircraft / airplane's cockpit pressure system design. Based on the flow's equations, one defines the cockpit as controlled object and determines its transfer functions, the air leak process time constants, the air leak rate and the cockpit's necessary airflow rate. One also studies the dynamic behavior and the disturbance influence above the cockpit's air pressure values for different situations (with and without air flow rate's automatic control).