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公开(公告)号：EP2703624A1
公开(公告)日：2014-03-05
申请号：EP12777288.7
申请日：2012-04-28
发明人： DAVIDENKO, Aleksandr Nikolaevich , STRELETS, Mihail Yurievich , RUNISHEV, Vladimir Aleksandrovich , BIBIKOV, Sergey Yurievich , POLYAKOVA, Natalya Borisovna , SUTSKEVER, Anatoly Isaakovich , KOSITSIN, Aleksandr Anatolevich , GAVRIKOV, Andrey Yurievich , STEPANOV, Vladimir Alekseevich
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/026 , F02C7/057 , F05D2220/80 , Y10T137/0536
摘要： The invention relates to aeronautical engineering and, more specifically, to air intakes for supersonic aircraft propulsion systems. The technical result to be achieved by the invention consists in ensuring stable operation of the engine in all flight regimes up to the maximum Mach number of M=3.0 by adjusting the apex angle of stages of one of swept wedges and minimum area of the flow passage of the air intake. An adjustable supersonic air intake comprises an entrance in the form of a flow deceleration system - a supersonic diffuser (22) consisting of two multi-stage swept decelerating wedges (7) and (20) which form a dihedral angle; a shell, which also forms a dihedral angle, all edges of the entrance lying in the same plane; an air intake throat situated downstream of the deceleration system, and a subsonic diffuser (23), downstream thereof. As seen from the front, the entrance of the air intake has the shape of a rectangle or a parallelogram. The number of stages on swept wedges (7) and (20) may be different and the sweep of the wedges may be different from each other and from respective 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) and (20) are rotatable about an axis situated at the intersection of the first and second stages of the wedge, forming a movable front panel (11). A movable rear panel (12) is situated in the subsonic diffuser.
摘要翻译： 本发明涉及航空工程，更具体地涉及用于超音速飞机推进系统的进气口。 本发明要实现的技术结果在于通过调整扫掠楔块之一的顶角和流动通道的最小面积来确保发动机在所有飞行状态下的稳定运行，直到最大马赫数M = 3.0 的进气口。 可调节的超音速进气口包括流动减速系统形式的入口 - 由形成二面角的两个多级扫掠减速楔（7）和（20）组成的超音速扩散器（22） 壳体也形成二面角，入口的所有边缘位于同一平面内; 位于减速系统下游的进气喉，以及亚音速扩散器（23）。 从前方看，进气口的入口呈矩形或平行四边形。 扫掠楔（7）和（20）上的阶段数可能不同，并且楔形的扫掠可能彼此不同，并且与入口的各个边缘不同。 除了第一阶段之外，两个多级扫掠楔（7）和（20）中的一个的所有阶段可以围绕位于楔形件的第一和第二阶段的相交处的轴线旋转，形成 可动前面板（11）。 可移动后面板（12）位于亚音速扩散器中。
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公开(公告)号：EP2703624B1
公开(公告)日：2016-11-09
申请号：EP12777288.7
申请日：2012-04-28
发明人： DAVIDENKO, Aleksandr Nikolaevich , STRELETS, Mihail Yurievich , RUNISHEV, Vladimir Aleksandrovich , BIBIKOV, Sergey Yurievich , POLYAKOVA, Natalya Borisovna , SUTSKEVER, Anatoly Isaakovich , KOSITSIN, Aleksandr Anatolevich , GAVRIKOV, Andrey Yurievich , STEPANOV, Vladimir Alekseevich
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/026 , F02C7/057 , F05D2220/80 , Y10T137/0536
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公开(公告)号：EP2599719A1
公开(公告)日：2013-06-05
申请号：EP11820241.5
申请日：2011-04-07
发明人： POGOSYAN, Mihail Aslanovich , DAVIDENKO, Aleksandr Nikolaevich , STRELETS, Mihail Yurievich , RUNISHEV, Vladimir Aleksandrovich , TARASOV, Aleksey Zaharovich , SHOKUROV, Aleksey Kirillovich , BIBIKOV, Sergey Yurievich , KRYLOV, Leonid Evgenievich , MOSKALEV, Pavel Borisovich
CPC分类号： B64D27/20 , B64C3/10 , B64C5/02 , B64C15/02 , B64D7/00 , B64D33/02 , B64D2033/0286 , Y02T50/12 , Y02T50/44
摘要： The invention relates to multimode aircraft operated at supersonic and subsonic flight speeds in a wide range of flight altitudes. The invention is particularly applicable in multimode super-maneuverable aircraft capable of cruising at supersonic speed and having low radar signature. The technical effect to be achieved by the invention is to provide an aircraft which has low radar signature, is super-maneuverable at high angles of attack, has high aerodynamic efficiency at supersonic speeds while keeping high aerodynamic efficiency at subsonic modes, and can accommodate bulky cargo in its internal compartments. The integral aerodynamic configuration aircraft comprises fuselage (1) with strake (2), wing with panels (3) smoothly blended into fuselage (1), all-moving horizontal tail (AMHT) (4), and all-moving vertical tail (AMVT) (5). Mid-fuselage is flattened and formed longitudinally by a set of aerodynamic profiles. Engines are arranged in engine nacelles (6) spaced apart from each other horizontally, and centerlines of engines are oriented at an acute angle to the plane of symmetry of the aircraft in the direction of flight. Strake (2) comprises controlled pivoting portions (8).
摘要翻译： 本发明涉及在大范围的飞行高度中以超音速和亚音速飞行速度操作的多模飞机。 本发明特别适用于能够以超音速巡航并具有低雷达标志的多模超机动飞机。 本发明要实现的技术效果是提供一种具有低雷达签名的飞机，在高攻角下是超级机动的，在超音速下具有高空气动力学效率，同时在亚音速模式下保持高的空气动力学效率，并且可以适应庞大的 货物在其内部隔间。 整体空气动力学配置飞机包括机身（1），带有行星（2），机翼与面板（3）平滑地混合到机身（1），全移动水平尾翼（AMHT）（4）和全移动垂直尾翼（AMVT （5）。 中间机身被一组空气动力学特性纵向平坦化并形成。 发动机布置在水平彼此间隔开的发动机舱（6）中，并且发动机的中心线与飞行器的飞行方向上的对称平面成锐角。 肩带（2）包括受控的枢转部分（8）。
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