| 摘要 |
A decompression assembly (10; 10′) for an aircraft comprises a first cabin lining element (12; 12′) having a boundary area (14; 14′) and a second cabin lining element (20; 20′) having a boundary area (22; 22′), wherein the boundary area (22; 22′) of the second cabin lining element (20; 20′) is disposed at a smaller distance from an aircraft outer skin (24; 24′) than the boundary area (14; 14′) of the first cabin lining element (12; 12′). An air discharge opening (28; 28′) is disposed between the boundary area (14; 14′) of the first cabin lining element (12; 12′) and the boundary area (22; 22′) of the second cabin lining element (20; 20′) for discharging air from a cabin (18; 18′) of the aircraft into an area (30; 30′) of the aircraft located between the cabin lining elements (12, 20; 12′, 20′) and the aircraft outer skin (24; 24′). A decompression element (32; 32′) is adapted to release a pressure compensation opening (36; 36′) between the cabin (18; 18′) of the aircraft and the area (30; 30′) of the aircraft located between the cabin lining elements (12, 20; 12′, 20′) and the aircraft outer skin (24; 24′) in the event of decompression and is disposed in an area of the aircraft that is shielded from an interior of the cabin (18; 18′) of the aircraft by the first and/or the second cabin lining element (12, 20; 12′, 20′). |
