公开(公告)号：US06648270B1

公开(公告)日：2003-11-18

申请号：US10157705

申请日：2002-08-07

申请人： Edward L. Burnett ,  John W. Vinson ,  Brian Quayle ,  Michael C. Carter ,  Kenneth Gousman ,  Scott Wan Weelden ,  Steven P. Ericson ,  Stephen G. Justice

发明人： Edward L. Burnett ,  John W. Vinson ,  Brian Quayle ,  Michael C. Carter ,  Kenneth Gousman ,  Scott Wan Weelden ,  Steven P. Ericson ,  Stephen G. Justice

IPC分类号： B64C2900

CPC分类号： B63H21/34 ,  B60V1/06 ,  B60V1/08

摘要： A vehicle is disclosed having a hull with a longitudinal, vertical and lateral axis, the hull further having front end and rear ends and first and second sides. A turbofan engine mounted in said hull, said engine having an exhaust duct. First and second front exhaust nozzles are mounted on the first and second sides of the front end of the hull. First and second rear exhaust nozzles are coupled to the first and second sides of said hull at said rear. All of the exhaust nozzles are rotatable from a vertically downward position to at least a partially horizontal direction and incorporating shudders to adjust the flow rate of exhaust gas from said turbofan engine therethrough. A duct system for coupling the exhaust duct of the turbofan engine to all of the nozzles.

摘要翻译： 公开了具有纵向，纵向和横向轴线的船体的车辆，船体还具有前端和后端以及第一和第二侧。 安装在所述船体中的涡扇发动机，所述发动机具有排气管。 第一和第二前排气喷嘴安装在船体前端的第一和第二侧上。 第一和第二后排气喷嘴在所述后部联接到所述船体的第一和第二侧。 所有的排气喷嘴可以从垂直向下的位置旋转到至少部分水平的方向，并且包括颤抖器以调节来自所述涡轮风扇发动机的废气的流量。 用于将涡轮风扇发动机的排气管道与所有喷嘴联接的管道系统。

公开(公告)号：US20050178900A1

公开(公告)日：2005-08-18

申请号：US10437679

申请日：2003-05-13

申请人： Brian Quayle

发明人： Brian Quayle

IPC分类号： B64C25/14 ,  B64C25/10

CPC分类号： B64C25/14

摘要： An aircraft landing gear is movable between a retracted position and an extended position. The aircraft landing gear comprises a nonfolding, nonhinged shock strut that extends along a shock strut axis from a proximal end to a distal end and remains at an essentially constant length throughout an extension/retraction cycle. A trunnion is coupled to the proximal end of the shock strut and capable of pivoting in combination with the shock strut about a canted trunnion axis. A multiple-wheel truck is coupled to the distal end of the shock strut. A drag strut is coupled to the shock strut at a position intermediate to the shock strut proximal and distal end and is capable of folding as the landing gear is retracted and straightening as the landing gear is extended. The canted trunnion axis is canted so that the shock strut retracts in a forward and inboard direction and extends downward and outboard.

摘要翻译： 飞机起落架可在缩回位置和伸出位置之间移动。 飞机起落架包括非折叠的非冲击支柱，其沿着冲击支柱轴线从近端延伸到远端并且在整个延伸/缩回循环期间保持基本上恒定的长度。 耳轴耦合到冲击支柱的近端并且能够围绕围绕倾斜轴颈的冲击支柱组合地枢转。 多轮卡车联接到冲击支柱的远端。 拖曳支柱在冲击支柱近端和远端的中间位置处耦合到冲击支柱，并且当起落架延伸时起落架缩回并矫直，能够折叠。 倾斜的耳轴轴线倾斜，使冲击支柱向前和向内缩回，向下和向外延伸。

公开(公告)号：US06942182B2

公开(公告)日：2005-09-13

申请号：US10437679

申请日：2003-05-13

申请人： Brian Quayle

发明人： Brian Quayle

IPC分类号： B64C25/14 ,  B64C25/01

CPC分类号： B64C25/14

摘要： An aircraft landing gear is movable between a retracted position and an extended position. The aircraft landing gear comprises a nonfolding, nonhinged shock strut that extends along a shock strut axis from a proximal end to a distal end and remains at an essentially constant length throughout an extension/retraction cycle. A trunnion is coupled to the proximal end of the shock strut and capable of pivoting in combination with the shock strut about a canted trunnion axis. A multiple-wheel truck is coupled to the distal end of the shock strut. A drag strut is coupled to the shock strut at a position intermediate to the shock strut proximal and distal end and is capable of folding as the landing gear is retracted and straightening as the landing gear is extended. The canted trunnion axis is canted so that the shock strut retracts in a forward and inboard direction and extends downward and outboard.

摘要翻译： 飞机起落架可在缩回位置和伸出位置之间移动。 飞机起落架包括非折叠的非冲击支柱，其沿着冲击支柱轴线从近端延伸到远端并且在整个延伸/缩回循环期间保持基本上恒定的长度。 耳轴耦合到冲击支柱的近端并且能够围绕围绕倾斜轴颈的冲击支柱组合地枢转。 多轮卡车联接到冲击支柱的远端。 拖曳支柱在冲击支柱近端和远端的中间位置处耦合到冲击支柱，并且当起落架延伸时起落架缩回并矫直，能够折叠。 倾斜的耳轴轴线倾斜，使冲击支柱向前和向内缩回，向下和向外延伸。

公开(公告)号：US06824092B1

公开(公告)日：2004-11-30

申请号：US10696795

申请日：2003-10-30

申请人： Walter M. Franklin, III ,  John M. Morgenstern ,  Howard Lee ,  Brian Quayle ,  Ken Hajic ,  John Scarcello ,  Alan E. Arslan

发明人： Walter M. Franklin, III ,  John M. Morgenstern ,  Howard Lee ,  Brian Quayle ,  Ken Hajic ,  John Scarcello ,  Alan E. Arslan

IPC分类号： B64C502

CPC分类号： B64C5/02 ,  B64C30/00

摘要： A supersonic aircraft comprises a wing having upper and lower surfaces and extending from a leading edge to a trailing edge and at least two engine nacelles coupled to the lower surface of the wing on the trailing edge. The supersonic aircraft further comprises an inverted V-tail abutting to the upper side of the wing comprising a central vertical stabilizer, at least two inverted stabilizers coupled to sides of the central vertical stabilizer and coupled to the wing and supporting at least two engine nacelles, and at least two ruddervators respectively pivotally coupled to at least two inverted stabilizers. The supersonic aircraft also comprises a controller coupled to at least two ruddervators and capable of adjusting the aircraft longitudinal lift distribution throughout a flight envelope to maintain a reduced sonic boom and reduced drag trim condition.

摘要翻译： 超音速飞行器包括具有上表面和下表面并从前缘延伸到后缘的翼，以及耦合到后缘上的翼的下表面的至少两个发动机舱。 超音速飞机还包括邻近机翼上侧的倒V形尾翼，其包括中心垂直稳定器，耦合到中心垂直稳定器侧面的至少两个倒置稳定器，并联接到机翼并支撑至少两个引擎机舱， 并且至少两个舵杆分别枢转地联接到至少两个倒立的稳定器。 超音速飞机还包括耦合到至少两个舵机的控制器，并且能够调整整个飞行信封处的飞行器纵向升力分布，以保持减小的声波起重臂和减少的拖曳修剪状况。

公开(公告)号：US08783617B2

公开(公告)日：2014-07-22

申请号：US13445815

申请日：2012-04-12

申请人： Michael W. Harbeck ,  Brian Quayle

发明人： Michael W. Harbeck ,  Brian Quayle

IPC分类号： B64C1/38

CPC分类号： B64C1/0009 ,  B64C2001/0045 ,  Y02T50/12

摘要： An air vehicle fuselage adapted for transonic operation is disclosed. The fuselage has a body and a close-out. A lower surface of the body has a waterline value that varies along a fore-aft direction of the fuselage and is equal to a first waterline value at a forward end of the close-out and rise to a second waterline value at an aft end of the close-out. The lower surface has a drag-reduction blivet that includes a first region wherein the lower surface drops to a point comprising a third waterline value that is below the first waterline value and a first inward radius and then rises over a second region disposed aft of the first region wherein a second radius that is a minimum radius of the lower surface within the second region is greater than the first radius.

摘要翻译： 公开了适用于跨音速操作的机载机身。 机身有一个身体和一个特写。 身体的下表面具有沿着机身的前后方向变化的水线值，并且等于在关闭的前端处的第一水线值，并且在尾端处升至第二水线值 结束了。 下表面具有减阻气泡，其包括第一区域，其中下表面下降到包括低于第一水线值的第三水线值和第一内侧半径的点，然后在安置在第一水线值之后的第二区域上升 第一区域，其中作为第二区域内的下表面的最小半径的第二半径大于第一半径。

公开(公告)号：US07216830B2

公开(公告)日：2007-05-15

申请号：US10655707

申请日：2003-09-05

申请人： Brian Quayle ,  John M. Morgenstern ,  Alan E. Arslan

发明人： Brian Quayle ,  John M. Morgenstern ,  Alan E. Arslan

IPC分类号： B64C3/10 ,  B64C25/10

CPC分类号： B64C1/0009 ,  B64C3/10 ,  B64C3/16 ,  B64C9/24 ,  B64C25/10 ,  B64C30/00 ,  B64C39/12 ,  B64C2001/0045 ,  B64D27/18 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

摘要： A supersonic cruise configuration aircraft comprises a fuselage extending on a longitudinal axis from a forward nose to an aft tail, and a wing coupled at an inboard section to the fuselage and extending to an outboard tip, and having a leading edge and a trailing edge. The aircraft further comprises a landing gear that is coupled to the wing and capable of stowing into the wing and fuselage on retraction. The landing gear has a landing gear strut. The wing is gulled with a dihedral at an angle that is increased inboard and aligns with the retracted landing gear. The wing has a minimum thickness sufficient to enclose the landing gear.

摘要翻译： 超音速巡航配置飞行器包括在纵向轴线上从前部鼻子延伸到尾部尾部的机身，以及在内侧部分连接到机身并延伸到外侧尖端并且具有前缘和后缘的机翼。 飞机还包括起落架，该起落架联接到机翼并且能够在收回时收入机翼和机身中。 起落架有起落架支柱。 机翼以一个增加在内侧并与缩回的起落架对准的角度以二面角度挖出。 机翼具有足以封闭起落架的最小厚度。

公开(公告)号：US20050067526A1

公开(公告)日：2005-03-31

申请号：US10655707

申请日：2003-09-05

申请人： Brian Quayle ,  John Morgenstern ,  Alan Arslan

发明人： Brian Quayle ,  John Morgenstern ,  Alan Arslan

IPC分类号： B64C1/00 ,  B64C3/10 ,  B64C3/16 ,  B64C9/24 ,  B64C25/10 ,  B64C30/00 ,  B64C39/12 ,  B64D27/18 ,  B64C15/00

CPC分类号： B64C1/0009 ,  B64C3/10 ,  B64C3/16 ,  B64C9/24 ,  B64C25/10 ,  B64C30/00 ,  B64C39/12 ,  B64C2001/0045 ,  B64D27/18 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

摘要： A supersonic cruise configuration aircraft comprises a fuselage extending on a longitudinal axis from a forward nose to an aft tail, and a wing coupled at an inboard section to the fuselage and extending to an outboard tip, and having a leading edge and a trailing edge. The aircraft further comprises a landing gear that is coupled to the wing and capable of stowing into the wing and fuselage on retraction. The landing gear has a landing gear strut. The wing is gulled with a dihedral at an angle that is increased inboard and aligns with the retracted landing gear. The wing has a minimum thickness sufficient to enclose the landing gear.

摘要翻译： 超音速巡航配置飞行器包括在纵向轴线上从前部鼻子延伸到尾部尾部的机身，以及在内侧部分连接到机身并延伸到外侧尖端并且具有前缘和后缘的机翼。 飞机还包括起落架，该起落架联接到机翼并且能够在收回时收入机翼和机身中。 起落架有起落架支柱。 机翼以一个增加在内侧并与缩回的起落架对准的角度以二面角度挖出。 机翼具有足以封闭起落架的最小厚度。