| 摘要 |
<p>The invention relates to aviation technology and, more specifically, to air inlets for supersonic aircraft propulsion systems. The invention is intended to achieve the technical result of ensuring the stable operation of the engine in all flight regimes up to a Mach number of M=3.0 by adjusting the apex angle of the stages of one of the swept wedges and the minimum area of the flow passage of the air inlet. The adjustable supersonic air inlet comprises an entrance in the form of a flow deceleration system, namely a supersonic diffuser (22) consisting of two multi-stage swept decelerating wedges (7, 20) which form a dihedral angle, and a cowl, which also forms a dihedral angle, all of the edges of the entrance lying in the same plane, an air inlet throat situated downstream of the deceleration system, and a subsonic diffuser (23), downstream thereof. Seen from the front, the entrance of the air inlet is shaped like a rectangle or a parallelogram. The number of stages on the swept wedges (7, 20) may be different; likewise, the sweep of the wedges may be different from one another and from the corresponding edges of the entrance. With the exception of the first stage, all of the stages of one of the two multi-stage swept wedges (7, 20) are rotatable about an axis situated at the intersection of the first and second stages of the wedge in question, forming a movable front panel (11). A movable rear panel (12) is situated in the subsonic diffuser.</p> |
