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公开(公告)号：US20150336665A1
公开(公告)日：2015-11-26
申请号：US14285462
申请日：2014-05-22
申请人： Chen Li Jing
发明人： Chen Li Jing
CPC分类号： B64C29/0066 , B64C29/0025
摘要： VTOL aircraft with a thrust-to-weight ratio smaller than 0.08, during vertical take-off/landing, obtains most vertical lift, besides traditional small vertical lift by high-temp bypass slot outlet (6) directing, under its opening, the closing of the tail of the power-off jet engine (3) by the valve (7) in tail cone, the closing and the stretching of the propelling nozzle (5), high-temp air (8) to spout out along the inclined downward direction of the wingspan, by a centrifugal impeller (13) accelerating, under the connecting of the transmission shaft (11) with a jet engine (4), and the opening of the cabin doors (15, 17) of the inlet (18) of the low-temp duct (16) and the auxiliary engine's inlet (14), low-temp air (21) to flow through the low-temp duct (21) and flow over the upper surface of the wing but not burn up it along the wingspan direction, thereby generating most vertical lift and enabling ailerons (1, 2) to control balances of the aircraft.
摘要翻译： 垂直起升/着陆期间，推力重量比小于0.08的垂直起降飞机，除了传统的小型垂直升降机外，还有高温旁路槽出口（6），在其开启时指示关闭 通过阀门（7）在尾锥中的关闭喷气发动机（3）的尾部，推进喷嘴（5）的关闭和拉伸，高温空气（8）沿倾斜向下喷出 通过在传动轴（11）与喷气发动机（4）的连接下的离心式叶轮（13）加速翼展的方向，以及入口（18）的舱门（15,17）的开口， 的低温管道（16）和辅助发动机的入口（14），低温空气（21）流过低温管道（21）并流过机翼的上表面但不燃烧 沿翼展方向，从而产生大多数垂直升降机，并使副翼（1,2）能够控制飞机的平衡。
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公开(公告)号：US09656748B2
公开(公告)日：2017-05-23
申请号：US14329949
申请日：2014-07-13
申请人： Chen Li Jing
发明人： Chen Li Jing
CPC分类号： B64C29/00 , B64C9/00 , B64C15/02 , B64C21/04 , B64C23/005 , B64C29/005 , B64C29/0066 , B64C2009/005 , B64D27/16 , Y02T50/166
摘要： VTOL aircraft with a thrust-to-weight ratio smaller than 0.1, during vertical take-off/landing, obtains an another lift, besides a lift generated by low-temp bypass duct (15) directing the low-temp air (18) from the turbofan engine (3) to flow, through its outlet (19) in form of low-temp planar jet (20), over the upper surface of the wing and in the direction of the wingspan, by high-temp bypass duct (15) directing the high-temp air (18) from the turbofan engine (3) to flow, through its outlet (12) in form of high-temp planar jet (13), above the low-temp planar jet (20) in the direction of the wingspan but not burn up the wing and enables the ailerons (1, 2) to control the balances of the aircraft more efficiently.
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公开(公告)号：US20150298805A1
公开(公告)日：2015-10-22
申请号：US14329949
申请日：2014-07-13
申请人： Chen Li Jing
发明人： Chen Li Jing
CPC分类号： B64C29/00 , B64C9/00 , B64C15/02 , B64C21/04 , B64C23/005 , B64C29/005 , B64C29/0066 , B64C2009/005 , B64D27/16 , Y02T50/166
摘要： VTOL aircraft with a thrust-to-weight ratio smaller than 0.1, during vertical take-off/landing, obtains another vertical lift, besides traditional vertical lift generated by low-temp bypass duct directing, under the closing of the propelling nozzle (7) of low-temp duct (6) of a turbofan engine and the opening of the inlet (14) of the low-temp bypass duct (15), the low-temp air (18) from the low-temp duct (6) to flow, in form of low-temp planar jet (20), over the upper surface of the wing along the wingspan, by high-temp bypass duct (15) directing, under the closing of the propelling nozzle (5) of high-temp duct (4) of the turbofan engine and the opening of the inlet (8) of the high-temp bypass duct (9), the high-temp air (18) from the high-temp duct (4) to flow, in form of high-temp planar jet (13), above the low-temp planar jet (20) but not burn up the wing along the wingspan and enables the ailerons (1, 2) to control the balances more efficiently.
摘要翻译： 在垂直起飞/着陆期间，推力重量比小于0.1的垂直起降飞机除了在推进喷嘴（7）的关闭下由低温旁通管道引导产生的传统垂直升力外还获得另一垂直升降机， 的涡轮风扇发动机的低温风道（6）和低温旁通管道（15）的入口（14）的开口，低温空气（18）从低温管道（6）到 以低温平面射流（20）的形式，沿着翼展在翼的上表面上，通过高温旁通管道（15）在高温下的推进喷嘴（5）的关闭下引导 涡轮风扇发动机的管道（4）和高温旁通管道（9）的入口（8）的开口，来自高温管道（4）的高温空气（18）以形式 的高温平面射流（13），在低温平面射流（20）之上，但不会沿翼展燃烧翼，并使副翼（1,2）更有效地控制平衡。
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