| 摘要 |
<p>The air intake comprises two main flaps (1, 2) face to face and each pivoting about a shaft (4, 5) which is adjacent to a wall (6, 7) extending the flap (1, 2) in question rearwards, and in which a first boundary-layer bleed (8a, 8b) is arranged, the shafts (4, 5) being substantially parallel to the plane of the wings or of the fuselage so that the flaps (1, 2) move perpendicularly to this plane, and a ramp (11) pivoting about a shaft (12) adjacent to its leading edge (11a) by which it is adjacent to the wings and to the fuselage and substantially parallel to the shafts (4, 5) is upstream of the flap (1) closest to the wings and with which it defines another boundary-layer bleed (13) of variable section. Application to the equipping of orbital aeroplanes and of intercontinental supersonic transports. <IMAGE></p> |
