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公开(公告)号：US5427329A
公开(公告)日：1995-06-27
申请号：US45899
申请日：1993-04-12
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , Y10T292/1021
摘要： A latch pin actuator (34) for use in connection with an aircraft (10) having folding wings or wing tips (12). The actuator (34) includes housing (38) mountable to a wing portion (12, 16). A latch pin (21) in the form of a hydraulic cylinder is slidably mounted within the housing (38) and on a piston (44) which is fixed to the housing (38). Variable volume fluid chambers (46, 48) are defined in the cylinder body of the latch pin (21). A primary lock member (58) is movable between locked and unlocked positions such that retraction of the latch pin (21) is prevented when the primary lock (58) is in a locked position. In preferred form, a hydraulic actuator (78) is used to move the primary lock member (58) between locked and unlocked positions and to operate a sequencing valve which delivers hydraulic pressure to a chamber (48) of the latch pin (21) after actuation of the primary lock (58). The latch pin actuator (34) may also include a secondary lock member (60) which can be ganged to operate in unison with adjacent latch pin actuators (34).
摘要翻译： 一种用于与具有折叠翼或翼尖（12）的飞行器（10）结合使用的闩锁销致动器（34）。 致动器（34）包括可安装到翼部（12,16）的壳体（38）。 液压缸形式的锁销（21）可滑动地安装在壳体（38）内并固定在壳体（38）上的活塞（44）上。 可变体积流体室（46,48）限定在闩销（21）的缸体中。 主锁定构件（58）可在锁定位置和解锁位置之间移动，使得当主锁（58）处于锁定位置时，防止闩销（21）的收缩。 在优选形式中，液压致动器（78）用于将主锁定构件（58）在锁定位置和解锁位置之间移动，并且操作顺序阀，其在经过锁定销（21）的腔室（48）之后将液压传递到闩锁销（21）的腔室（48） 致动主锁（58）。 闩锁销致动器（34）还可以包括辅助锁定构件（60），该辅助锁定构件可被联动以与相邻的闩锁销致动器（34）一致地操作。
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公开(公告)号：US5379969A
公开(公告)日：1995-01-10
申请号：US45901
申请日：1993-04-12
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , Y10T292/432 , Y10T292/558
摘要： A plurality of radially extendable/retractable lock bolts (LB) are carried by a piston head (PH). A cylinder body (CB) in which the piston head (PH) is located includes a lock-bolt cavity (52) or cavities. When the actuator is in a lock position (fully extended or fully retracted), the lock bolt or bolts (LB) are in radial alignment with the lock bolt cavity or cavities. A locking piston (LP) within the actuator is movable axially to place a bolt block (62) radially inwardly of the lock bolt or bolts (LB), to in such position block the lock bolt or bolts (LB) against a radial inward movement out from the lock bolt cavity (52) or cavities. The locking piston (LP) includes a piston face (60) against which hydraulic fluid pressure may be directed, to move the locking piston (LP) axially, for retracting the bolt block (62) out from its position radially inwardly of the lock bolt or bolts (LB). This frees the lock bolt or bolts (LB) so that they can move radially inwardly, out from the lock bolt cavity 52 or cavities.
摘要翻译： 多个可径向伸缩的锁紧螺栓（LB）由活塞头（PH）承载。 活塞头（PH）所在的缸体（CB）包括锁定螺栓腔（52）或空腔。 当执行器处于锁定位置（完全伸出或完全缩回）时，锁定螺栓或螺栓（LB）与锁定螺栓腔或腔体径向对准。 致动器内的锁定活塞（LP）可以轴向移动，以将锁定螺栓或螺栓（LB）的径向向内的螺栓块（62）放置在此位置，以防止锁定螺栓或螺栓（LB）径向向内移动 从锁定螺栓腔（52）或空腔中脱出。 锁定活塞（LP）包括活塞面（60），液压流体压力可以朝向该活塞面轴向移动，以使锁定活塞（LP）轴向移动，以将螺栓块（62）从其锁定螺栓径向向内的位置 或螺栓（LB）。 这释放了锁定螺栓或螺栓（LB），使得它们可以从锁定螺栓腔52或空腔中径向向内移动。
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公开(公告)号：US5350135A
公开(公告)日：1994-09-27
申请号：US45903
申请日：1993-04-12
IPC分类号： B64C3/56
CPC分类号： B64C3/56
摘要： A folding wing tip (14) on an aircraft (2) carries a lug (16) that moves into alignment with lugs (6, 10) on the inboard wing portion (4) as the wings spread. The lug (16) pivots an inhibitor (28) that is interconnected by linkage to a valve spool (122). The pivoting of the inhibitor (28) causes the spool (122) to shift its position so that a sense port is brought into communication with a return port. Return pressure in the sense port indicates a spread wing condition. When the wing tip (14) is folded, springs move the inhibitor (28) and the valve spool (122) back to their original positions. This communicates the sense port with a pressure port to indicate a folded wing condition. The spool (122) is preferably also biased into its original position by fluid pressure. In addition, the lug (16) has a cam (92) that engages a roller (84) carried by the inhibitor (28) when the wing tip (14) is moved into a folded position. Abutment of the cam (92) and roller (84) pivots the inhibitor (28) back into its original position.
摘要翻译： 飞机（2）上的折叠翼尖（14）承载着翼（16），当翼展开时，凸耳（16）与内侧翼部（4）上的凸耳（6,10）对齐。 凸耳（16）使通过连杆与阀芯（122）互连的抑制器（28）枢转。 抑制器（28）的枢转使得阀芯（122）移动其位置，使得感测端口与返回端口连通。 感应端口的返回压力表示传播翼状态。 当翼尖（14）折叠时，弹簧将阻尼器（28）和阀线筒（122）移回其初始位置。 这将传感端口与压力端口通信，以指示折叠的机翼状况。 卷轴（122）优选地通过流体压力被偏压到其初始位置。 此外，当翼尖（14）移动到折叠位置时，凸耳（16）具有接合由抑制器（28）承载的辊（84）的凸轮（92）。 凸轮（92）和辊（84）的基座使抑制剂（28）枢转回其初始位置。
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公开(公告)号：US5452643A
公开(公告)日：1995-09-26
申请号：US45900
申请日：1993-04-12
CPC分类号： B64C3/56
摘要： A hydraulic power drive unit (36) including a linear hydraulic piston cylinder unit (64) with a set of longitudinally spaced gear teeth (84) in the form of a rack. A pinion gear (86) is operatively engaged and driven by the rack (84). A differential which may include a carrier (102), planet gears (108, 110) and sun gears (120, 122) may be driven by the pinion gear (86) to selectively transfer drive power to two separate rotary drive outputs (38, 40). A switching valve (160) may be provided which is responsive to a reversal of hydraulic supply pressure. Operation of the switching valve (160) may be limited by mechanical interference between an inhibit dog (181) and a cam surface (196) on the carrier (102). The carrier (102) may also include a separate cam surface (140) positioned for actuation of separate electrical switches (146, 148) in order to monitor position of the drive outputs (38, 40).
摘要翻译： 液压动力驱动单元（36）包括具有齿条形式的一组纵向间隔开的齿轮齿（84）的线性液压活塞缸单元（64）。 小齿轮（86）由齿条（84）可操作地接合和驱动。 可以由小齿轮（86）驱动可包括载体（102），行星齿轮（108,110）和太阳齿轮（120,122）的差速器，以选择性地将驱动力传递到两个分离的旋转驱动输出（38， 40）。 可以提供响应于液压供应压力的反转的切换阀（160）。 切换阀（160）的操作可能受到禁止狗（181）和载体（102）上的凸轮表面（196）之间的机械干扰的限制。 载体（102）还可以包括单独的凸轮表面（140），其被定位成用于致动分开的电开关（146,148），以便监测驱动输出（38,40）的位置。
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公开(公告)号：US5381986A
公开(公告)日：1995-01-17
申请号：US046015
申请日：1993-04-12
IPC分类号： B64C3/56
CPC分类号： B64C3/56
摘要： A plurality of latch pins are locked into a latch position by primary locks and secondary locks. Each primary lock mechanically blocks movement of its corresponding secondary lock into the secondary lock's locked position when the primary lock is out of its locked position. The secondary locks are ganged together to cause them to move together into and out from their locked positions. A follow-up switch senses movement of the ganging mechanism. A latch pin inhibitor blocks movement of the latch pin into the latch position and is moved away to permit latching by spreading of the wing tip. The inhibitor is linked to a valve to shift the valve and thereby cause hydraulic pressure to be supplied to extend the latch pin. When the locks are in their looked positions, the secondary locks mechanically block the primary locks from moving out of their locked positions. The secondary locks are biased into their locked positions. During flight, the latch pins and locks are isolated from hydraulic pressure. Spreading, latching, and locking procedures are carried out automatically following manual actuation of a control member. A hydraulic actuator that moves the wing-tip between folded and spread positions acts as a strut to hold the wing tip in the folded position.
摘要翻译： 多个闩锁销通过主锁和辅助锁锁定到闩锁位置。 当主锁定在其锁定位置之外时，每个主锁定机械地阻止其相应辅助锁的移动进入辅助锁的锁定位置。 辅助锁合在一起，使它们一起移入和移出其锁定位置。 后续开关感测组合机构的运动。 闩锁销抑制器阻止闩锁销移动到闩锁位置并且被移开以允许通过翼尖的扩展来锁定。 抑制剂连接到阀门以移动阀门，从而导致液压被提供以延伸闩锁销。 当锁位于其看起来的位置时，辅助锁将机械地阻挡主锁从其锁定位置移出。 辅助锁被偏置到其锁定位置。 在飞行过程中，闩锁销和锁与液压隔离。 手动驱动控制构件后，会自动执行扩展，锁定和锁定程序。 将翼尖在折叠位置和扩展位置之间移动的液压致动器用作支柱以将翼尖保持在折叠位置。
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公开(公告)号：US07641152B2
公开(公告)日：2010-01-05
申请号：US11734842
申请日：2007-04-13
申请人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
发明人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
IPC分类号： G05D1/00
摘要： The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.
摘要翻译： 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用改变飞行器条件的输入，如高度，马赫数，重量，重心，垂直速度和飞行阶段。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。
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公开(公告)号：US08447445B2
公开(公告)日：2013-05-21
申请号：US12620698
申请日：2009-11-18
申请人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
发明人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
IPC分类号： B64C13/00
摘要： The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.
摘要翻译： 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用高度，马赫数，重量，重心（CG），垂直速度和飞行阶段等改变飞机状态的输入。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。
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公开(公告)号：US20100152926A1
公开(公告)日：2010-06-17
申请号：US12620698
申请日：2009-11-18
申请人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
发明人： Dan Onu , John D. Winter , Candy L. Carr , Paul M. Vijgen , Gary A. Emch , Michael E. Renzelmann
IPC分类号： G05D1/00
摘要： The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.
摘要翻译： 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用高度，马赫数，重量，重心（CG），垂直速度和飞行阶段等改变飞机状态的输入。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。
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公开(公告)号：US20100100355A1
公开(公告)日：2010-04-22
申请号：US12253747
申请日：2008-10-17
申请人： Alan D. Marx , Gary A. Emch , Mark J. Gardner , Richard I. Apfel , Michael E. Renzelmann , Christopher D. Feet , Michael R. Finn , Mark S. Good , Gregory J. Seehusen
发明人： Alan D. Marx , Gary A. Emch , Mark J. Gardner , Richard I. Apfel , Michael E. Renzelmann , Christopher D. Feet , Michael R. Finn , Mark S. Good , Gregory J. Seehusen
IPC分类号： G06F15/00
CPC分类号： B64D45/0005 , B64D2045/001
摘要： A method for detecting freewheeling skew failures in the wing flaps of an aircraft includes measuring the outputs of flap skew sensors when the aircraft is in flight (IF) and the flaps are extended to a selected position, and when the aircraft is next on the ground (OG) and the flaps are extended to the selected position. The respective differences between the IF and OG outputs of symmetrical pairs of the flap skew sensors are computed, and then the respective difference between the computed IF output difference and the computed OG output difference of each symmetrical pair of the sensors is computed. The computed IF and OG difference of each symmetrical pair of the sensors is then compared with each of predetermined maximum and minimum threshold value to determine whether a freewheeling skew failure exists in any of the flaps of the aircraft.
摘要翻译： 一种用于检测飞行器翼片中的续流偏斜故障的方法，包括当飞机处于飞行中（IF）时测量襟翼歪斜传感器的输出，并且襟翼延伸到选定的位置，并且当飞机在地面上时 （OG），并且襟翼延伸到所选位置。 计算襟翼偏斜传感器的对称对的IF和OG输出之间的各自的差异，然后计算计算的IF输出差和每对传感器对的计算的OG输出差的相应差。 然后将每个对称的传感器对的计算的IF和OG差与预定的最大和最小阈值中的每一个进行比较，以确定是否存在飞行器的任何襟翼中的空转歪斜故障。
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公开(公告)号：US4483423A
公开(公告)日：1984-11-20
申请号：US420727
申请日：1982-09-21
摘要： A torque isolation device for a force-sensitive load having a safe force limit to be imposed thereon, configured to transmit upstream rotational force within the limit to the load and transmit any force in excess thereof to a load-isolated path, is comprised of a radially displaceable driving coupling which includes a cam member having a dwell and bi-directional, outwardly oriented camming surfaces bounding same receiving a cam follower secured to a pivotal drive arm radially extensible from a biased primary transmission position, wherein the cam follower is disposed within the dwell, to an extended overload position in engagement with mechanical ground wherein the cam follower is displaced along the camming surface.
摘要翻译： 一种用于对其施加安全力极限的力敏感载荷的扭矩隔离装置，其构造成将负载极限内的上游旋转力传递到负载并且将超过其的任何力传递到负载隔离路径，由 径向可移动的驱动联接器，其包括具有驻留和双向的向外定向的凸轮表面的凸轮构件，所述凸轮构件接合同一接收固定到从偏置的主变速器位置可径向延伸的枢转驱动臂的凸轮从动件，其中所述凸轮从动件设置在 停留在与机械接地接合的延伸的过载位置，其中凸轮从动件沿着凸轮表面移位。
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