| 主权项 |
1. An air intake arrangement for an aircraft, comprising:
at least one air passage channel in fluid connection with an air intake orifice, with the air intake orifice configured to bleed off a flow of external air to enter into the air intake orifice at an upstream end of the at least one air passage channel, pass through said at least one air passage channel, and ventilate a confined zone of the aircraft; and an aerodynamically controlled shut-off unit comprised of:
a controllable mobile element configured to regulate flow of the external air through the at least one air passage channel toward the confined zone of the aircraft to vary a cross section of the at least one air passage channel relative to speed of the aircraft, anda control unit configured to control said controllable mobile element to vary the cross section of said at least one air passage channel relative to the speed of said aircraft, wherein the controllable mobile element is configured to regulate the flow of the external air through the at least one air passage channel by reducing the cross section of the at least one air passage channel during cruising flight to flow the external air through the at least one air passage channel at a minimal air flow rate toward said confined zone, and opening up the cross section of the at least one air passage channel during at least one of ground or take-off phase to flow the external air through the at least one air passage channel at a maximum air flow rate toward said confined zone, wherein said controllable mobile element is formed of an elastic blade configured to press spontaneously against a wall of said at least one air passage channel, with said elastic blade being fixed at one end to said at least one air passage channel, and said control unit is arranged in said at least one air passage channel, with said control unit including an aerodynamic surface formed by a profile piece positioned completely within and transversely to said at least one air passage channel, said profile piece having a single portion fixed to another end of said elastic blade and having at least one free end, said aerodynamic surface being configured to, responsive directly to airflow within the at least one air passage channel, generate a lift force to the profile piece to lift said elastic blade to reduce the cross section of the at least one air passage channel as said flow of external air passes through said at least one air passage channel toward said confined zone of the aircraft. |
