公开(公告)号：US4475702A

公开(公告)日：1984-10-09

申请号：US474652

申请日：1982-12-28

申请人： James B. Cole

发明人： James B. Cole

IPC分类号： B64C3/48

CPC分类号： B64C3/48

摘要： A variable camber leading edge device having a movable nose section and an upper flexible panel extending rearwardly from the nose section. To move the nose section between its upper cruise position and a high lift downwardly deflected position, there is attached to the nose section a generally arcuate cam track, having its forward and rear portions curving upwardly. The cam track is constrained to move in a generally arcuate path by means of two spaced pair of rollers, and it is driven by a pinion gear engaging an upwardly facing middle portion of the track.

摘要翻译： PCT No.PCT / US82 / 01797 Sec。 371日期1982年12月28日 102（e）1982年12月28日PCT PCT 1982年12月28日PCT公布。 公开号WO84 / 02506 日期1984年7月5日。一种具有可移动鼻部的可变外倾凸缘装置和从鼻部向后延伸的上柔性面板。 为了将鼻部部分在其上巡航位置和高升力向下偏转位置之间移动，鼻部部分附接有大致弓形的凸轮轨道，其前部和后部向上弯曲。 凸轮轨道被限制为通过两个间隔开的一对辊子在大体上弧形的路径中移动，并且其由与轨道的面向上的中间部分接合的小齿轮驱动。

公开(公告)号：US4753402A

公开(公告)日：1988-06-28

申请号：US814604

申请日：1985-12-30

申请人： James B. Cole

发明人： James B. Cole

IPC分类号： B64C9/14 ,  B64C9/22 ,  B64C9/24 ,  B64C21/02

CPC分类号： B64C9/24 ,  B64C9/22 ,  Y02T50/32

摘要： YAn aircraft leading edge slat is biased when at an extended location toward a first position wherein the trailing edge of the slat is a predetermined distance from the wing upper surface. The slat is pivotable to a second position, when aerodynamic forces acting on the wing overcome the biasing force, wherein the slat trailing edge is pivoted upward and forward, and the distance between the slat trailing edge and the wing upper surface is increased. The slat is retracted and extended by a drive track which is supported inside the wing by upper rollers located chordwise within the wing cavity, a lower front roller, and a pair of roller rings rotatably mounted at opposite sides of a rotary actuator pinion gear. The pinion gear engages the drive track and moves the slat between the extended and retracted positions.

摘要翻译： 当在延伸位置朝向第一位置时，YAn飞机前缘板条被偏压，其中板条的后缘距离机翼上表面是预定距离。 当作用在机翼上的空气动力抵抗偏压力时，板条可枢转到第二位置，其中板条后缘向上和向前枢转，并且板条后缘和机翼上表面之间的距离增加。 板条通过驱动轨道缩回和延伸，该驱动轨道通过位于机翼内的弦向上的上辊支撑在机翼内部，下前辊和可旋转地安装在旋转致动器小齿轮的相对侧的一对滚子环。 小齿轮接合驱动轨道，并且在延伸位置和缩回位置之间移动板条。

公开(公告)号：US4053124A

公开(公告)日：1977-10-11

申请号：US708671

申请日：1976-07-26

申请人： James B. Cole

发明人： James B. Cole

IPC分类号： B64C3/48

CPC分类号： B64C3/48 ,  Y02T50/145

摘要： A variable camber apparatus for the leading and/or trailing edge of an airfoil that is operable for lift variation at high airspeeds of a jet aircraft such as for maneuvering of fighter aircraft. The cambering apparatus comprises an upper surface flexible skin panel which is supported along its inner edge by a wing spar assembly and along its outermost edge, by an airfoil edge forming structure. A hinged rib member, through a kinematic linkage mechanism associated between itself and the structure at the outermost edge of the airfoil section, bends and torsionally twists the airfoil edge forming structure about a relative spanwise axis. The kinematic linkage mechanism is slaved to rotating means of the rib member, for torsionally twisting the outermost edge of the airfoil section, upper surface portion, the precise amount of rotation so as to flexuously bend the upper surface and thereby contour it to conform to an aerodynamically predetermined curvilinear plot that will produce the desired camber and the change in the lift characteristics of the airfoil surface.

公开(公告)号：US3987983A

公开(公告)日：1976-10-26

申请号：US534828

申请日：1974-12-20

申请人： James B. Cole

发明人： James B. Cole

IPC分类号： B64C9/20

CPC分类号： B64C9/20 ,  Y02T50/32

摘要： An aircraft wing for use in a STOL aircraft incorporating upper surface blowing engines employs trailing edge flaps, including a main flap segment and an aft flap segment. The flaps are mounted on and externally hinged below the wing for movement between a retracted position and a plurality of extended positions. The main flap segment is hinged to its support for pivotal movement about a spanwise axis. The main flap segment is in a first position when retracted and normally remains in that position as the flaps are extended. When the flaps are extended and the main flap segment is in the first position, the upper airfoil surfaces of main flap segment and the aft flap segment form a smooth, continuous upper surface that extends downwardly and rearwardly from the upper airfoil surface of the wing. When the flaps are extended, the main flap segment can be pivoted about the spanwise axis to a second position to form spanwise slots between the forward portion of the main segment and the aft portion of the wing and between the aft portion of the main segment and the forward portion of the aft segment. In the first position, wherein the smooth, continuous, downwardly and rearwardly extending upper airfoil surface is formed, the trailing edge flap system can be employed with an upper surface blowing engine to take advantage of the Coanda effect to turn the exhaust stream issuing rearwardly and chordwise across the wing to turn the exhaust stream downwardly and rearwardly, thereby creating an upwardly directed, engine-generated lift component to augment the aerodynamic lift generated by the wing and flap structure. In the second position, the spanwise slots function to enhance the aerodynamic lift generated by the wing/flap combination as it moves through the air by allowing ambient air to flow through the slots.

公开(公告)号：US3941334A

公开(公告)日：1976-03-02

申请号：US563428

申请日：1975-03-31

申请人： James B. Cole

发明人： James B. Cole

IPC分类号： B64C9/24

CPC分类号： B64C9/24 ,  Y02T50/32

摘要： A variable camber apparatus for the leading edge of an airfoil that is operable for lift variation at high airspeeds of a jet aircraft such as for maneuvering of fighter aircraft. The cambering apparatus comprises an upper surface flexible skin panel which is supported along its inner edge by a wing spar assembly and along its outermost edge, by an airfoil edge forming structure. A hinged rib member, through a kinematic linkage mechanism associated between itself and the structure at the outermost edge of the airfoil section, bends and torsionally twists the airfoil edge forming structure about a relative spanwise axis. The kinematic linkage mechanism is slaved to the actuator of the rib member, for torsionally twisting the outermost edge of the airfoil section, upper surface portion, the precise amount of rotation so as to flexuously bend the upper surface and thereby contour it to conform to an aerodynamically predetermined curvilinear plot that will produce the desired camber and the change in the lift characteristics of the airfoil surface. Further, the combination of a variable camber wing leading edge mechanism with a high lift device, such as a leading edge flap, which is stowed within the airfoil envelope.

摘要翻译： 用于翼型件的前缘的可变的外倾装置，其可操作用于在喷气式飞行器的高空速下的升力变化，例如用于操纵战斗机。 弯曲装置包括上表面柔性外壳板，其通过翼梁组件沿着其内边缘并沿其最外边缘通过翼型边缘形成结构被支撑。 铰接肋构件通过与其自身和翼型部分的最外边缘处的结构相关联的运动连杆机构弯曲并扭转翼型边缘形成结构围绕相对翼展方向轴线。 运动连杆机构被从动到肋构件的致动器，用于扭转翼型部分的最外边缘，上表面部分，精确的旋转量，以便使上表面挠曲地弯曲，从而将其轮廓化以符合 空气动力学预定的曲线图，其将产生所需的弯度和翼型表面的升力特性的变化。 此外，可变的弧形前缘机构与诸如前缘翼片的高升力装置的组合，其被收起在翼型封套内。

公开(公告)号：US4752049A

公开(公告)日：1988-06-21

申请号：US814603

申请日：1985-12-30

申请人： James B. Cole

发明人： James B. Cole

IPC分类号： B64D15/04

CPC分类号： B64D15/04

摘要： A leading edge/anti-icing assembly for an airfoil comprising a leading edge slat having a nose section defining a heat exchange chamber. Anti-icing air directed into the heat exchange chamber flows rearwardly through the slat so as to have a deicing function, and is then discharged in a rearward direction from the trailing edge of the slat. Thus, the anti-icing air not only performs an anti-icing function over the upper surface of the slat, but also contributes to anti-icing over the upper surface portion of the main wing rearwardly of the trailing edge of the slat.

摘要翻译： 一种用于翼型的前缘/防冰组件，包括具有限定热交换室的鼻部的前缘板条。 导入热交换室的防冰空气向后流过板条，以具有除冰功能，然后从板条的后缘向后方排出。 因此，防冰空气不仅在板条的上表面上执行防冰功能，而且还有助于在板条的后边缘的后边缘的主翼的上表面部分上的防冰。

公开(公告)号：US4471928A

公开(公告)日：1984-09-18

申请号：US429871

申请日：1982-09-30

申请人： James B. Cole

发明人： James B. Cole

IPC分类号： B64C9/00 ,  B64C9/16 ,  B64C9/20 ,  B64C13/34 ,  B64C9/24

CPC分类号： B64C9/00 ,  B64C13/34 ,  B64C9/16 ,  B64C9/20

摘要： An actuation and extension mechanism for aerodynamically high-lift devices such as a wing leading edge slat or a wing trailing edge flap; wherein an aerodynamic panel is connected to one end of an extendible track member that is supported and guided by its other end through rollers fixedly mounted to wing rib structure. The track member incorporates a separate rack gear segment internally thereof as part of the extension or retraction mechanism and this combination of track and gear segment provides the primary support and drive means to the high-lift device, without compromising the structural strength, safety, or operational reliability of said combination.

摘要翻译： 用于空气动力学高升力装置的致动和延伸机构，例如机翼前缘板条或翼后缘板; 其中空气动力学面板连接到可伸缩轨道构件的一端，该可伸缩轨道构件的另一端通过固定地安装到翼肋结构的辊被支撑和引导。 轨道构件在其内部包括作为延伸或缩回机构的一部分的单独的齿条分段，并且轨道和齿轮段的这种组合将主要的支撑和驱动装置提供给高升力装置，而不损害结构强度，安全性或 所述组合的操作可靠性。

公开(公告)号：US4248395A

公开(公告)日：1981-02-03

申请号：US921474

申请日：1978-07-03

申请人： James B. Cole

发明人： James B. Cole

IPC分类号： B64C9/04 ,  B64C9/16 ,  B64C9/20 ,  B64C13/28

CPC分类号： B64C13/28 ,  B64C9/04 ,  B64C9/16 ,  B64C9/20 ,  Y02T50/32

摘要： Dual flap sections are supported by linkage, first for chordwise movement of the forward flap section rearwardly from the wing and for chordwise movement of the rear flap section rearwardly from the forward flap section, and then for tilting of the two flap sections conjointly to increase their angle of incidence relative to the wing. The forward flap section is supported by motion-amplifying compound linkage for effecting chordwise movement of the forward flap section relative to the wing, and the rear flap section is supported by motion-amplifying compound linkage from the forward flap section for effecting chordwise movement of the rear flap section relative to the forward flap section. Control mechanism for both motion-amplifying compound linkages is connected to the wing and is movable first to actuate the linkages primarily for shifting the two flap sections chordwise rearwardly from the wing and then primarily to tilt the foward and rear flap sections conjointly to increase their angle of incidence.

摘要翻译： 双翼片部分通过联动支撑，首先用于从翼部向后向前的翼片部分的弦向运动，并且使后翼片部分从前翼片部分向后方向运动，然后将两个翼片部分共同倾斜以增加它们 相对于机翼的入射角。 前翼片部分由运动放大复合连杆支撑，用于实现前翼部分相对翼的弦向运动，后翼部分由前翼片部分的运动放大复合连杆支撑，用于实现 后翼部分相对于前翼片部分。 用于两个运动放大复合连杆的控制机构连接到机翼，并且可以首先移动以致动联动装置主要用于将两个翼片部分从机翼向后向后移动，然后主要将前轮和后翼片部分共同倾斜以增加其角度 的发病率。

公开(公告)号：US4172575A

公开(公告)日：1979-10-30

申请号：US851027

申请日：1977-11-14

申请人： James B. Cole

发明人： James B. Cole

IPC分类号： B64C9/04 ,  B64C9/16 ,  B64C9/20 ,  B64C13/28

CPC分类号： B64C9/16 ,  B64C13/28 ,  B64C9/04 ,  B64C9/20 ,  Y02T50/32

摘要： A pair of motion-amplifying flap linkages connected externally to the undersurface of a tapered planform airfoil and being spaced apart spanwise thereof for a combined pseudo conical extension movement of a tapered-chord flap section. The pair of flap linkage mechanisms conjointly first extending the tapered chord flap section chordwise of the airfoil and then rotatably tilting the flap to increase its angle of incidence, such that the chordwise length of movement and rotation of the flap, is proportional to the length of the airfoil chord at that cross-section of the airfoil; and approximates a conic motion of the flap relative to the airfoil.

摘要翻译： 一对运动放大翼片连接器，其外部连接到锥形平面形翼型件的下表面并且间隔开，用于锥形翼形翼片部分的组合的假锥形延伸运动。 一对翼片连杆机构共同首先将锥形弦翼翼片部分翼型延伸到翅片上，然后可旋转地倾斜翼片以增加其入射角，使得翼片的弦向运动和旋转长度与 机翼横截面上的翼型弦; 并近似翼片相对于翼型件的圆锥运动。

公开(公告)号：US3994451A

公开(公告)日：1976-11-30

申请号：US455837

申请日：1974-03-28

申请人： James B. Cole

发明人： James B. Cole

IPC分类号： B64C3/48

CPC分类号： B64C3/48 ,  Y02T50/145

摘要： A variable camber apparatus for the leading and/or trailing edge of an airfoil that is operable for lift variation at high airspeeds of a jet aircraft such as for maneuvering of fighter aircraft. The cambering apparatus comprises an upper surface flexible skin panel which is supported along its inner edge by a wing spar assembly and along its outermost edge, by an airfoil edge forming structure. A hinged rib member, through a kinematic linkage mechanism associated between itself and the structure at the outermost edge of the airfoil section, bends and torsionally twists the airfoil edge forming structure about a relative spanwise axis. The kinematic linkage mechanism is slaved to rotating means of the rib member, for torsionally twisting the outermost edge of the airfoil section, upper surface portion, the precise amount of rotation so as to flexuously bend the upper surface and thereby contour it to conform to an aerodynamically predetermined curvilinear plot that will produce the desired camber and the change in the lift characteristics of the airfoil surface.