公开(公告)号：US6068219A

公开(公告)日：2000-05-30

申请号：US59471

申请日：1998-04-13

申请人： Allen A. Arata

发明人： Allen A. Arata

IPC分类号： B64C3/48 ,  B64C3/50 ,  B64C9/26 ,  B64C39/10 ,  B64C15/00 ,  B64C29/00 ,  B64C3/44

CPC分类号： B64C9/26 ,  B64C3/50 ,  B64C2039/105 ,  Y02T50/12 ,  Y02T50/145 ,  Y02T50/32

摘要： In accordance with the present invention, there is provided an aerodynamic control device for integrated use with an aircraft having an inboard lifting member. The inboard lifting member having a leading edge, a pair of opposing distal edges and a trailing edge. The control device is provided with a movable outboard member which extends substantially about the leading, distal and trailing edges of the inboard lifting member and is spaced apart therefrom. The outboard member is provided with a leading edge portion, a pair of opposing distal edge portions, and a trailing edge portion which are collectively movable in unison in relation to the inboard lifting member to form an uninterrupted airfoil surface extending about the inboard lifting member and the outboard member for achieving desired aerodynamic control of the aircraft.

摘要翻译： 根据本发明，提供了一种用于与具有内侧提升构件的飞机一体使用的空气动力学控制装置。 内侧提升构件具有前缘，一对相对的远侧边缘和后缘。 控制装置设置有可移动的外侧构件，其基本上围绕内侧提升构件的前端，远端和后缘延伸并与其间隔开。 外侧构件设置有前缘部分，一对相对的远侧边缘部分和后缘部分，后缘部分可相对于内侧提升部件共同移动，以形成围绕内侧提升部件延伸的不间断翼面，以及 用于实现飞机所需的空气动力学控制的外侧构件。

公开(公告)号：US5992796A

公开(公告)日：1999-11-30

申请号：US828826

申请日：1997-03-13

申请人： Brian E. Smith

发明人： Brian E. Smith

IPC分类号： B64C1/26 ,  B64C3/40 ,  B64C5/02 ,  B64C5/04 ,  B64C5/12 ,  B64C5/14 ,  B64C30/00 ,  B64C39/12 ,  B64C3/56

CPC分类号： B64C30/00 ,  B64C1/26 ,  B64C3/40 ,  B64C39/12 ,  B64C5/02 ,  B64C5/04 ,  B64C5/12 ,  B64C5/14 ,  Y02T50/145

摘要： A secondary wing system for use on an aircraft augments the lift, stability, and control of the aircraft at subsonic speeds. The secondary wing system includes a mechanism that allows the canard to be retracted within the contour of the aircraft fuselage from an operational position to a stowed position. The top surface of the canard is exposed to air flow in the stowed position, and is contoured to integrate aerodynamically and smoothly within the contour of the fuselage when the canard is retracted for high speed flight. The bottom portion of the canard is substantially flat for rotation into a storage recess within the fuselage. The single canard rotates about a vertical axis at its spanwise midpoint. The canard can be positioned between a range of sweep angles during flight and a stowed position in which its span is substantially parallel to the aircraft fuselage. The canard can be deployed and retracted during flight. The deployment mechanism includes a circular mounting ring and drive mechanism that connects the canard with the fuselage and permits it to rotate and to change incidence. The deployment mechanism further includes retractable fairings which serve to streamline the wing when it is retracted into the top of the fuselage.

摘要翻译： 在飞机上使用的二次翼系统以亚音速提升飞机的提升，稳定性和控制。 副翼系统包括一种机构，其允许将卡车从飞行器机身的轮廓从操作位置缩回到收起位置。 将鸭子的顶部表面暴露在收起位置的空气流中，并在轮廓缩回以进行高速飞行时，在机身轮廓内空气动力学和平滑地整合。 该底部的底部基本上是平的，用于旋转进入机身内部的存储凹槽。 单个鸭嘴在其横向中点处围绕垂直轴线旋转。 该挡板可位于飞行期间的扫掠角范围和其跨度基本上平行于飞行器机身的收起位置之间。 在飞行过程中，可以部署和收回鸭子。 展开机构包括一个环形安装环和驱动机构，将机箱与机身连接，并允许其旋转并改变发生。 展开机构还包括可伸缩整流罩，用于在机翼缩回到机身顶部时简化机翼。

公开(公告)号：US5988563A

公开(公告)日：1999-11-23

申请号：US1147

申请日：1997-12-30

申请人： John B. Allen

发明人： John B. Allen

IPC分类号： B64C3/42 ,  B64C3/56 ,  B64C5/08 ,  B64C23/06 ,  B64C3/38 ,  B64C5/10 ,  B64C5/06

CPC分类号： B64C23/065 ,  B64C3/42 ,  B64C3/56 ,  B64C5/08 ,  Y02T50/145 ,  Y02T50/164

摘要： The present invention is directed to a unique foldable winglet assembly adaptable for use with an aircraft for maximizing the wing span of the aircraft during cruise operation while reducing wing bending moment during extreme flight maneuvers. A foldable winglet is pivotally joined to the aircraft wing and is rotatable during flight between a retracted position and a fully extended position. An actuator is mounted on the aircraft wing and attached to the foldable winglet. When the aircraft reaches cruise operation, the actuator can be manually or automatically energized to pivot the winglet from a substantially vertical, retracted position to a fully extended position wherein the winglet becomes an extension of the wing. During cruise, the wing and winglet form an enlarged wing that serves to maximize lift of the aircraft. When loads more severe than would occur at or near cruise, such as dive, are encountered, the loads overcome the action of the actuator and pivot the winglet to its initial, vertical position. This action, serves to reduce the bending moment acting on the wing as well as increase aerodynamic efficiency of the aircraft.

摘要翻译： 本发明涉及一种独特的可折叠小翼组件，适用于飞行器，用于在巡航操作期间最大化飞行器的机翼跨度，同时在极限飞行操作期间减少翼弯矩。 可折叠小翼枢转地连接到飞行器机翼，并且在缩回位置和完全伸出位置之间的飞行过程中可旋转。 执行机构安装在飞机机翼上并连接到可折叠的小翼上。 当飞行器到达巡航操作时，致动器可以被手动地或自动地通电，以将小翼从基本垂直的缩回位置枢转到完全伸出的位置，其中小翼成为机翼的延伸。 在巡航期间，机翼和小翼形成一个扩大的翼，用于最大限度地提升飞机的升力。 当遇到比在潜艇或附近发生的负载更严重的负载（例如潜水）时，负载克服致动器的作用并将小翼枢转到其初始的垂直位置。 这个动作用于减少作用在机翼上的弯矩，同时提高飞机的空气动力学效率。

公开(公告)号：US5941480A

公开(公告)日：1999-08-24

申请号：US852870

申请日：1997-05-08

申请人： Robert Henry Wille

发明人： Robert Henry Wille

IPC分类号： B64C3/48 ,  B64C9/02 ,  B64C1/06 ,  B64C3/58

CPC分类号： B64C3/48 ,  B64C9/02 ,  Y02T50/145 ,  Y02T50/32

摘要： A hinge line system (52) for an aircraft has a structural block (22) attached to a first edge of a hinge line. The structural block (22) has a flange (28) attached to a first end of an elastic sheet (32). A second structural block (24) is attached to a second edge of the hinge line. The second structural block (24) has a second flange (30) attached to a second end of the elastic sheet (32).

摘要翻译： 用于飞机的铰链系统（52）具有附接到铰链线的第一边缘的结构块（22）。 结构块（22）具有附接到弹性片（32）的第一端的凸缘（28）。 第二结构块（24）附接到铰链线的第二边缘。 第二结构块（24）具有附接到弹性片（32）的第二端的第二凸缘（30）。

公开(公告)号：US5897076A

公开(公告)日：1999-04-27

申请号：US650686

申请日：1996-05-20

申请人： Richard R. Tracy

发明人： Richard R. Tracy

IPC分类号： B64C3/14 ,  B64C3/44 ,  B64C30/00 ,  B64C3/54 ,  B64C3/50

CPC分类号： B64C3/44 ,  B64C3/14 ,  B64C30/00 ,  Y02T50/12 ,  Y02T50/145

摘要： A supersonic flight aircraft having a longitudinally forwardly extending fuselage having an axis in the direction of flight, and a wing, and which comprises the wing extending generally laterally relative to the axis, and having a leading edge angled forward or rearwardly relative to a normal to the axis at an angle , and the wing having leading edge sharpness defined by upper and lower wing surfaces, which taper toward the leading edge to define an angle .delta., closely proximate the leading edge at all spanwise locations; the angle and sharpness .delta. characterized in that at design supersonic cruise flight conditions, the wing has an attached shock, that is, the forwardmost shock wave produced in association with the wing extends generally along or rearwardly of the leading edge, whereby laminar boundary layer conditions are maintained over the leading edge and adjacent the surface of the wing; there being flap means associated with the wing leading edge that comprises upper and lower leading edge skins capable of being controllably expanded chordwise, a structure between the skins, which permits the chordwise expansion of the skins, and means for causing relatively greater chordwise expansion of the upper skin than the lower skin, to generate downward defection of the leading edge.

摘要翻译： 具有纵向向前延伸的机身的超音速飞行器具有沿飞行方向的轴线，以及机翼，并且其包括相对于所述轴线大致横向延伸的翼部，并且具有相对于法线方向向前或向后成角度的前缘 该轴具有角度+ Z，并且所述机翼具有由上下翼面限定的前缘锋利度，其朝向前缘逐渐变细，以在所有翼展方向位置处紧密靠近前缘限定角度角; 角度+ Z和锐度三角形，其特征在于，在设计超音速巡航飞行条件下，机翼具有附接的冲击，即，与翼相关联产生的最前面的冲击波大致沿前缘延伸或向后延伸，由此层流边界 在前缘和机翼表面附近保持层状态; 具有与机翼前缘相关联的皮瓣装置，其包括能够可控地伸展弦杆的上和下前缘皮肤，皮肤之间的结构，其允许皮肤的弦向膨胀，以及用于引起皮肤的相对较大的弦向膨胀的装置 上皮肤比较低的皮肤，产生下降的前缘。

公开(公告)号：US5836549A

公开(公告)日：1998-11-17

申请号：US781237

申请日：1997-01-10

申请人： Boyd B. Bushman

发明人： Boyd B. Bushman

IPC分类号： B64C3/48 ,  B64C11/18 ,  B64C3/16 ,  B64C3/36

CPC分类号： B64C3/48 ,  B64C11/18 ,  Y02T50/145

摘要： A jet airplane capable of supersonic flight has airfoils with leading edges. Each leading edge has a cavity which extends for substantially the entire length of the airfoil. The leading edge also has a cover which is approximately the same size as the cavity. The cover has an open position and a closed position. When the cover is in the open position, the leading portion has a concave profile. When the cover is in the closed position, the leading portion has a convex profile that gives the airfoil a conventional shape. The cover is rotated to the open position when the airplane reaches supersonic speed. At supersonic speed, a shock wave forms on the leading edge of the airfoil. However, the cavity forms a compression zone between the shock wave and the leading edge, diverting the heat and pressure of the shock wave away from the airfoil. Downstream from the compressed zone, pressure wakes form along the airfoil and cool the airfoil. At subsonic speed, the cover is rotated to the closed position to achieve optimal airfoil efficiency.

摘要翻译： 能够超音速飞行的喷气式飞机具有前缘的翼型。 每个前缘具有延伸到翼型件的基本上整个长度的空腔。 前缘还具有与空腔大致相同的盖。 盖子有打开位置和关闭位置。 当盖处于打开位置时，前导部分具有凹形轮廓。 当盖处于关闭位置时，引导部分具有凸起轮廓，其使翼型件成为常规形状。 当飞机达到超音速时，盖旋转到打开位置。 在超音速下，在翼型的前缘形成冲击波。 然而，空腔在冲击波和前缘之间形成压缩区，将冲击波的热量和压力转移离开翼型。 在压缩区下游，沿翼型形成压力，并冷却翼型。 在亚音速下，盖旋转到关闭位置以获得最佳的翼型效率。

公开(公告)号：US5645250A

公开(公告)日：1997-07-08

申请号：US112877

申请日：1993-08-26

申请人： David E. Gevers

发明人： David E. Gevers

IPC分类号： B64C1/00 ,  B64C3/38 ,  B64C3/54 ,  B64C3/56 ,  B64C25/52 ,  B64C25/54 ,  B64C25/66 ,  B64C35/00 ,  B64C35/02 ,  B64D27/00 ,  B64D27/02 ,  B64D27/08 ,  B64D29/04 ,  B64D35/04 ,  B64C11/46

CPC分类号： B64D35/04 ,  B64C1/00 ,  B64C25/52 ,  B64C25/54 ,  B64C25/66 ,  B64C3/38 ,  B64C3/54 ,  B64C3/56 ,  B64C35/00 ,  B64C35/002 ,  B64C35/008 ,  B64D27/00 ,  B64D27/08 ,  B64D29/04 ,  B64C2001/0045 ,  Y02T50/12 ,  Y02T50/145 ,  Y02T50/44

摘要： Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

摘要翻译： 披露了一些飞机的创新系统，以及包含它们的飞机。 特征包括内置式发动机，带有用于转动翼位螺旋桨的皮带传动系统; 复合起落架整合滑雪，浮桥和车轮子部件; 用于起落架和/或螺旋桨的枢转安装衔铁，其提供多个可能的起落架和/或螺旋桨结构; 以及具有可延伸翼板的复合翼结构，其允许飞行器的机翼跨度在飞行中几乎翻倍。 结合这种特征的飞机将比常规多引擎飞机享有几个安全优势，并且能够在飞行期间进行修改，这些飞行器可以在雪，硬表面（跑道）和水中任何一个上升降。

公开(公告)号：US5372336A

公开(公告)日：1994-12-13

申请号：US42634

申请日：1993-04-05

申请人： Carlos A. Paez

发明人： Carlos A. Paez

IPC分类号： B64C3/56

CPC分类号： B64C3/56 ,  Y02T50/145

摘要： A folding wing assembly for use on an aircraft is disclosed. The folding wing assembly includes inboard and outboard wing sections which are pivotally interconnected such that the outboard wing section may pivot between folded and unfolded positions. A fairing unit is further pivotally interconnected to both the wing sections and extends chordwise across the wing assembly. The fairing unit is provided with a seal extending chordwise across an inner spanwise end of the fairing. The seat is adapted to engage the underside of a sealing flange attached to the upper surface of the inboard wing section. The other spanwise end of the fairing is adapted to engage a seal carried by the outboard wing section when the outboard wing section is in its fully unfolded position. In this unfolded position, the sealing flange and the fairing unit are substantially flush with the upper surface of the inboard and outboard wing sections and function to cover and seal the joint area between the wing sections so as to minimize aerodynamic drag resulting from the joint.

摘要翻译： 公开了一种用于飞机上的折叠翼组件。 折叠翼组件包括内侧和外侧翼部分，其枢转地互连，使得外侧翼部分可在折叠位置和展开位置之间枢转。 整流罩单元进一步枢转地互连到两个翼部，并且绕翼组件延伸。 整流罩单元设有沿整流罩的内翼展端部并行延伸的密封件。 座椅适于接合附接到内侧机翼部分的上表面的密封凸缘的下侧。 当外侧翼部处于其完全展开位置时，整流罩的另一个翼展端适于接合由外侧翼部分承载的密封。 在该展开位置，密封凸缘和整流罩单元基本上与内侧和外侧翼部分的上表面平齐，并且用于覆盖和密封翼部之间的接合区域，以便最小化由接头产生的气动阻力。

公开(公告)号：US5320310A

公开(公告)日：1994-06-14

申请号：US21849

申请日：1993-02-24

申请人： Steven D. Mitchell

发明人： Steven D. Mitchell

IPC分类号： B63H9/06 ,  B64C3/48 ,  B64C9/08 ,  B64C3/56 ,  B63H9/08

CPC分类号： B64C3/48 ,  B63H9/0607 ,  Y02T50/145

摘要： An articulated wing has a fore wing portion and after wing portion connected to an articulate axis support structure which extends along the length of the wing and separates the two wing portions. Control actuators separately connect the fore and after wing portions to the articulate wing support structure in order to provide separate angular positioning capabilities for the two wing portions. Further, the articulate wing support structure itself may be rotated with respect to the mechanism it is attached to. These and other flexible controls over the wing attitude and size allow the wing to provide a number of force vector amplitudes as well as directions for any given fluid flow direction and velocity.

摘要翻译： 铰接翼具有前翼部分，并且在翼部分连接到沿翼的长度延伸并且分离两个翼部分的铰接轴支撑结构之后。 控制执行器将前后翼单独地连接到铰接翼支撑结构，以便为两个翼部分提供单独的角度定位能力。 此外，铰接翼支撑结构本身可以相对于其附接到的机构旋转。 这些和其他柔性的机翼姿态和尺寸控制使机翼能够为任何给定的流体流动方向和速度提供许多力矢量幅度以及方向。

公开(公告)号：US5114104A

公开(公告)日：1992-05-19

申请号：US591532

申请日：1990-10-01

申请人： Manuel Cincotta ,  Richard H. Nadolink

发明人： Manuel Cincotta ,  Richard H. Nadolink

IPC分类号： B64C3/48

CPC分类号： B64C3/48 ,  Y02T50/145

摘要： An articulated control surface for flight control utilizes a moldable conl surface that is shaped by contracting and elongating shape memory alloys embedded within the control surface. The shape memory alloys contract when heated via an applied electric current and elongate when cooled, i.e., the electric current is removed. The resulting control surface is capable of generating a curved control surface without any electro/mechanical or hydraulic control systems.

摘要翻译： 用于飞行控制的铰接控制表面利用可模制的控制表面，其通过收缩和延伸嵌入在控制表面内的形状记忆合金而成形。 形状记忆合金在通过施加的电流加热时收缩，并在冷却时延伸，即去除电流。 所得到的控制表面能够产生没有任何电/机械或液压控制系统的弯曲控制表面。