The invention describes a fuselage (2, 2 ', 2' ') for a convertible aircraft (1), comprising a nose (4) and a tail (5) arranged on opposite sides of each other along a first longitudinal axis (Y) of the fuselage (2); a first portion (100) and a second portion (101) arranged one after the other along a first axis (Y) from the head (4) towards the tail (5); and a power source (102) connectable with the at least one electric powertrain (40a, 40b, 40c, 40d, 40e, 40f) and arranged within the second part (101); the first and second portions (100, 101) define a first and second section (110, 111, 111 ''), respectively, in a plane orthogonal to the first axis (Y); the second section (111) defining at least one air inlet (120) open towards the exterior of the fuselage (2) itself and fluidly connected to the source (102) to deliver, in use, a flow of cooling air onto the source (102) itself as the aircraft (1) moves forward; the second section (111, 111 '') has a larger area than the first section (110), and the air inlet (120) is arranged at a side wall (19) of the second section (101) and is located outside the first section (100) in a viewing angle parallel to the first axis (Y).
本发明描述了一种用于可转换式飞行器(1)的机身(2,2’,2”),其包括沿着机身(2)的第一纵向轴线(Y)布置在彼此相对的两侧上的机头(4)和机尾(5);沿着第一轴线(Y)从机头(4)朝向机尾(5)一个接一个地布置的第一部分(100)和第二部分(101);以及可与至少一个电动动力系(40a,40b,40c,40d,40e,40f)连接并且布置在第二部分(101)内的电力源(102);第一和第二部分(100,101)在与第一轴线(Y)正交的平面中分别限定第一和第二区段(110,111,111”);第二区段(111)限定至少一个进气口(120),其朝向机身(2)自身的外部打开并且与源(102)流体连接,以在使用中随着飞行器(1)的向前运动而将冷却空气流输送到源(102)自身上;第二区段(111,111”)具有比第一区段(110)更大的面积;进气口(120)布置在第二部分(101)的侧壁(19)处并且在与第一轴线(Y)平行的视角中位于第一部分(100)的外部。
Fuselage for convertible aircraft capable of hovering
用于能够悬停的可转换式飞行器的机身
2024-12-31
Patent
Electronic Resource
Chinese