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MOTOR aircraft, FIRST PLANE designed as a 'flying wing' AND / OR SMALL plane with radar signature

机译:MOTOR飞机,第一个飞机设计为具有雷达特征的“飞行翼”和/或小型飞机

摘要

1. An aircraft with a housing (12) of the fuselage and wings, a jet engine (20) and at least one channel (16) for a traction thread that extends from a forward (+ x) at the surface (14) of the air intake housing (18) through the jet engine (20) through the housing (12) for withdrawing back (-x) on the surface (14) housing the nozzle (22), characterized in that at least a portion of a jet engine (20), first of all the entire jet motor (20), as viewed in the direction (+ x) flight of the aircraft (10) located in front of an air inlet (18) and channel (16) for the traction of this flow has to appropriately formed and arranged curved portions (24, 28) .2. An aircraft according to claim 1, wherein the air inlet (18) when viewed in the flight direction is located behind the center of mass (M) of gravity of the aircraft (10) and / or geometric center (G) of gravity of the surface contour as viewed from above the housing (12). 3. An aircraft according to claim 1, wherein the inlet mouth (18) at its outer side is limited by a tapered forward edge terminating e.g., area of ​​the housing (12) .4. An aircraft according to claim 1, wherein the channel (16) for power flow at least partially double-symmetrically to the vertical longitudinal middle plane of the housing (12) .5. An aircraft according to one of the preceding claims, wherein the channel (16) for power flow comprises: adjacent to the air intake (18) a first curved portion (24) for changing the direction of flow, - adjoining the first curved portion (24) and extending in a direction ( + x) flight first longitudinal portion (26) d
机译:1.一种飞机,其具有机身和机翼的壳体(12),喷气发动机(20)和至少一个用于牵引线的通道(16),所述牵引线从前表面(+ x)​​在飞机的表面(14)处延伸。进气壳体(18)通过喷气发动机(20)穿过壳体(12),以便在容纳喷嘴(22)的表面(14)上缩回(-x),其特征在于,至少一部分喷气发动机(20),首先是整个喷气发动机(20),从位于进气口(18)和用于牵引的通道(16)前面的飞机(10)的飞行方向(+ x)​​观察这种流动必须适当地形成和布置弯曲部分(24、28).2。 2.根据权利要求1所述的飞机,其中,当从飞行方向观察时,所述进气口(18)位于所述飞机(10)的重心(M)和/或所述飞机的重心(G)的后面。从外壳(12)上方观察时的表面轮廓。 3.根据权利要求1所述的飞行器,其中,所述入口口(18)在其外侧由锥形的前边缘限制,所述前边缘终止于例如所述壳体(12).4的区域。 2.根据权利要求1所述的飞机,其特征在于,用于动力流的所述通道(16)至少部分地相对于所述壳体(12)的竖直纵向中间平面呈双对称形状。5。 7.根据前述权利要求中的任一项所述的飞机,其中,用于动力流的所述通道(16)包括:与所述进气口(18)相邻的,用于改变流动方向的第一弯曲部分(24),-邻接所述第一弯曲部分(24)。 24)并沿飞行方向(+ x)​​延伸的第一纵向部分(26)d

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