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    VTOL aircraft with a thrust-to-weight ratio smaller than 0.1
    52.
    发明申请
    VTOL aircraft with a thrust-to-weight ratio smaller than 0.1 有权
    垂直起落飞机的推力重量比小于0.1

    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

    IPC分类号： B64C29/00 ,  B64C23/00 ,  B64D27/16 ,  B64C9/00 ,  B64C15/02

    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。

    Short take-off aircraft
    57.
    发明授权
    Short take-off aircraft 有权
    短起飞飞机

    公开(公告)号：US08523101B2

    公开(公告)日：2013-09-03

    申请号：US12178711

    申请日：2008-07-24

    申请人： Olivier Cazals ,  Alexander Koch

    发明人： Olivier Cazals ,  Alexander Koch

    IPC分类号： B64C15/00

    CPC分类号： B64D27/20 ,  B64C5/12 ,  B64C15/02 ,  B64C39/12 ,  B64F5/40

    摘要： An aircraft capable of making short takeoffs and landings includes essentially a fuselage, a wing secured to the fuselage, a front horizontal stabilizer secured to the fuselage on the front end of the fuselage and at least two jet engines for propulsion. According to the architecture proposed, the propulsion engines are arranged side by side above the fuselage in a rear part of the fuselage with a width at least equal to the width of the propulsion group, a fuselage flap device is arranged in the back of the fuselage so that the fuselage flaps adopt at least a position in which the flaps are considerably in a horizontal plane and take at least a high-lift position in which the flaps are turned downward in such a way that the blast created by the jet engines is channeled towards the top surface of the fuselage flaps to induce a blowing effect.

    摘要翻译： 能够短时起飞和着陆的飞机基本上包括机身，固定在机身上的机翼，固定在机身前端的机身上的前水平稳定器和至少两个用于推进的喷气发动机。 根据所提出的结构，推进发动机在机身的后部并排布置在机身的后部，其宽度至少等于推进组的宽度，机身翼片装置布置在机身的后部 使得机身翼片至少采用襟翼相当于水平面的位置，并且至少采取高升力位置，在该位置襟翼向下转动，使得由喷气发动机产生的气流被引导 朝向机身襟翼的顶面，以引起吹风效果。

    Aircraft wing extension and nozzle system
    58.
    发明授权
    Aircraft wing extension and nozzle system 有权
    飞机机翼延伸和喷嘴系统

    公开(公告)号：US08469308B2

    公开(公告)日：2013-06-25

    申请号：US13224902

    申请日：2011-09-02

    申请人： Daniel B. Robertson ,  Kirk L. Groninga

    发明人： Daniel B. Robertson ,  Kirk L. Groninga

    IPC分类号： B64C15/00 ,  B64C27/22 ,  B64C27/82 ,  B64C3/48 ,  B64C29/00

    CPC分类号： B64C27/22 ,  B64C3/54 ,  B64C15/02 ,  B64C27/26 ,  B64C27/82 ,  B64C2027/8245 ,  Y02T50/14

    摘要： A system and method to control flight of an aircraft. The aircraft having an engine with a rotatably nozzle assembly configured to create forward propulsion and yaw control of the aircraft. The engine exhaust passing through the nozzle is redirected with a valve disposed within the nozzle. Lift is created with a lift system carried by the wing of the aircraft. Additional lift is created during flight with a retractable wing extension disposed within the wing of the aircraft.

    摘要翻译： 一种控制飞机飞行的系统和方法。 具有具有可旋转喷嘴组件的发动机的飞行器构造成产生飞行器的向前推进和偏航控制。 通过喷嘴的发动机排气用设置在喷嘴内的阀重新定向。 升降机是由飞机机翼所带的电梯系统造成的。 在飞行期间产生额外的升降机，其中可伸缩的机翼延伸部设置在飞行器的机翼内。

    RADIAL AND AXIAL COMPLIANT SLIDING SEAL INCORPORATING SPRING CAPTURING FEATURES FOR IMPROVED BEARING PLANE SEALING IN AN ARTICULATING NOZZLE
    59.
    发明申请
    RADIAL AND AXIAL COMPLIANT SLIDING SEAL INCORPORATING SPRING CAPTURING FEATURES FOR IMPROVED BEARING PLANE SEALING IN AN ARTICULATING NOZZLE 审中-公开
    径向和轴向合适的滑动密封件，用于改进轴承平面密封在喷嘴中的特殊功能

    公开(公告)号：US20110232262A1

    公开(公告)日：2011-09-29

    申请号：US12748609

    申请日：2010-03-29

    申请人： Thomas M. Barry, JR. ,  James F. Hyland, JR.

    发明人： Thomas M. Barry, JR. ,  James F. Hyland, JR.

    IPC分类号： B64C29/00 ,  F02K1/00 ,  F16J15/34

    CPC分类号： F16L27/082 ,  B64C15/02 ,  F02K1/805

    摘要： A seal assembly (80) adaptable for use between swivel ducts (36, 38, 40) or between a swivel duct (36) and an exhaust duct (81), has a seal (84), a seal carrier (82) and a spring (98). The spring is maintained between the seal carrier and the seal by means of a seal carrier spring holder (88) and a seal retention holder (96) such that the spring urges the seal away from the seal carrier to land the seal on an adjacent swivel duct (40).

    摘要翻译： 适于在回转管道（36,38,40）之间或旋转管道（36）和排气管道（81）之间使用的密封组件（80）具有密封件（84），密封件承载件（82）和 春天（98）。 弹簧通过密封载体弹簧保持器（88）和密封保持保持器（96）保持在密封载体和密封件之间，使得弹簧迫使密封件远离密封载体以使密封件在相邻的旋转件 导管（40）。