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1. 发明授权

US06739550B2 Flight control surface control unit 有权
标题翻译：飞行控制面控制单元
公开(公告)号：US06739550B2
公开(公告)日：2004-05-25
申请号：US10266291
申请日：2002-10-08
申请人： Takashi Koizumi , Toshio Kamimura
发明人： Takashi Koizumi , Toshio Kamimura
IPC分类号： B64C1324
CPC分类号： B64C13/34 , B64C9/02 , B64C13/24 , B64C13/28 , B64C13/50 , F16H1/46 , Y02T50/44
摘要： A flight control surface control unit controls a swinging angle of a flight control surface of an aircraft by providing a swinging force to the flight control surface and swinging the flight control surface about a pivot. The flight control surface control unit comprises an actuator mounted on an airframe of the aircraft with a final output shaft of the actuator positioned coaxially with the pivot of the flight control surface. The final output shaft of the actuator and the flight control surface are connected to each other. The flight control surface is formed with a recess in the vicinity of the pivot thereof and the actuator is accommodated in the recess.
摘要翻译：飞行控制表面控制单元通过向飞行控制表面提供摆动力并围绕枢轴摆动飞行控制表面来控制飞机的飞行控制表面的摆动角度。飞行控制表面控制单元包括安装在飞行器的机身上的致动器，致动器的最终输出轴与飞行控制表面的枢轴同轴地定位。执行器的最终输出轴和飞行控制表面相互连接。飞行控制表面在其枢轴附近形成有凹部，并且致动器容纳在凹部中。

2. 发明授权

US06371415B1 Aerodynamic component with a leading edge flap 失效
标题翻译：具有前缘皮瓣的气动元件
公开(公告)号：US06371415B1
公开(公告)日：2002-04-16
申请号：US09658905
申请日：2000-09-11
申请人： Thomas Lorkowski , Frank Hermle , Peter Jaenker
发明人： Thomas Lorkowski , Frank Hermle , Peter Jaenker
IPC分类号： B64C1324
CPC分类号： B64C27/001 , B64C27/615 , B64C2027/7283 , Y02T50/34
摘要： An aerodynamic component such as a helicopter rotor blade has an aerodynamic flow profile, a free end and a mounting end forming a blade root for attachment to a rotor mast. A blade section between the root and the free end has a leading edge and a trailing edge as viewed in the flow or chord direction. The blade is enclosed on its suction side and its pressure side with a respective skin. A nose flap or leading edge flap is secured to the leading edge by a bearing or hinge. The blade tilting angle is adjustable by piezo-drive elements arranged in at least one pair forming an actuator for each nose flap. The piezo-elements of a pair are arranged in the chord direction one behind the other and the pair is secured to the body of the blade by a fixed point positioned between the elements of a pair. The expansion and contraction from the piezo-element closer to the trailing edge is transmitted to the flap by a push rod. The expansion and contraction of the piezo-element closer to the leading edge is transmitted to the flap by a pronged pull-fork. The push rod and the pull-fork drive a free end of a lever secured to the flap, whereby a displacement of the push rod or of the pull fork causes the tilting adjustment of the flap by a push-pull action.
摘要翻译：诸如直升机转子叶片的空气动力学部件具有空气动力学流动分布，自由端和形成用于附接到转子桅杆的叶片根部的安装端。根部和自由端之间的叶片部分具有从流动或弦向方向观察的前缘和后缘。叶片在其吸力侧和其压力侧被封闭，并具有相应的皮肤。鼻翼或前缘皮瓣通过轴承或铰链固定到前缘。刀片倾斜角度可以通过布置在至少一对中的压电驱动元件来调节，形成每个鼻翼的致动器。一对的压电元件沿着弦方向一个在另一个之上布置，并且该对被固定在一对位置的元件之间的固定点。来自压电元件的靠近后缘的膨胀和收缩通过推杆传递到翼片。靠近前缘的压电元件的膨胀和收缩通过叉形叉子传递到翼片。推杆和拉叉驱动固定到翼片的杠杆的自由端，由此推杆或拉叉的位移通过推拉动作导致翼片的倾斜调节。

3. 发明授权

US06345792B1 Actuating device with at least three stable positions 有权
公开(公告)号：US06345792B1
公开(公告)日：2002-02-12
申请号：US09803300
申请日：2001-03-09
申请人： Alan J. Bilanin , Robert M. McKillip, Jr.
发明人： Alan J. Bilanin , Robert M. McKillip, Jr.
IPC分类号： B64C1324
摘要： A mechanical actuating device for moving an aerodynamic or hydrodynamic surface includes plural flexure members confined in an elastically deformed condition. The flexure members are movable against the force generated by their elastic deformation to move the device into one of at least three stable positions, in which the device, and therefore the aerodynamic or hydrodynamic surface, are held by the force generated by elastic deformation of the flexure members. Since the flexure members are always elastically deformed, the device “snaps” between discrete, stable positions and is held firmly in each. In another embodiment more flexure members can be used to provide additional stable positions. In one application, the actuating device is used as a trailing edge tab for a helicopter or tiltrotor blade to reduce 1/rev vibrations. The device can be actuated manually or electrically using shape-memory alloy wires to snap the flexure members into their various stable positions.

4. 发明授权

US06817573B2 Aircraft 失效
标题翻译：飞机
公开(公告)号：US06817573B2
公开(公告)日：2004-11-16
申请号：US10186665
申请日：2002-07-02
申请人： Richard George Harrison , Terry Prendergast , Geoffrey Salkeld , Darren Holdcroft
发明人： Richard George Harrison , Terry Prendergast , Geoffrey Salkeld , Darren Holdcroft
IPC分类号： B64C1324
CPC分类号： B64C39/024 , B64C29/0075 , B64C2201/086 , B64C2201/088 , B64C2201/102 , B64C2201/104 , B64C2201/121 , B64C2201/127 , B64C2201/128 , B64C2201/165 , B64C2201/187
摘要： An aircraft 1 comprising interchangeable wings 5 detachedly connected to a fuselage 3, each wing 5 containing the fuel and flight systems 13,15 for engines 7 mounted to the wings 5, so that the fuselage 3 need contain no flight systems, simply a “bus” 23 for communication and the transfer of data between the wings.
摘要翻译：飞机1包括分离地连接到机身3的可互换翼5，每个翼5包含燃料和飞行系统13,15，用于安装到翼5上的发动机7，使得机身3不需要包含飞行系统，简单地是“总线 “23”用于沟通和传递数据之间的翅膀。

5. 发明授权

US06231013B1 Airfoil member with a piezoelectrically actuated servo-flap 失效
标题翻译：具有压电致动伺服襟翼的翼型件
公开(公告)号：US06231013B1
公开(公告)日：2001-05-15
申请号：US09334216
申请日：1999-06-16
申请人： Peter Jaenker
发明人： Peter Jaenker
IPC分类号： B64C1324
CPC分类号： B64C27/001 , B64C2027/7283 , Y02T50/34
摘要： An airfoil member, especially a rotor blade for a helicopter, includes an airfoil body and a servo-actuated flap tiltably connected to the airfoil body so as to form at least a portion of the trailing edge of the airfoil member. At least one piezoelectric actuator is arranged inside the airfoil member, and connected to the servo-flap via a transmission mechanism and a connecting rod linkage so as to tiltingly deflect the servo-flap as needed. Preferably, two counter-acting piezoelectric actuators are connected to the flap via respective transmission mechanisms and connecting rod linkages. An elongation of the piezoelectric actuators in the span width direction of the airfoil member is converted or redirected into an actuating motion in the chord length direction of the airfoil member by the transmission mechanisms. Orienting the actuators to have an elongation motion in the span width direction prevents the high centrifugal accelerations arising in the rotor blade from having negative influences on the operation of the actuators.
摘要翻译：机翼构件，特别是用于直升机的转子叶片包括翼型件本体和可倾斜地连接到翼型件主体的伺服驱动翼片，以便形成翼型构件的后缘的至少一部分。至少一个压电致动器设置在翼型构件的内部，并通过传动机构和连杆连杆与伺服翼连接，以便根据需要使伺服翼片倾斜偏转。优选地，两个反作用压电致动器经由相应的传动机构和连杆连杆连接到翼片。翼型构件的跨度宽度方向上的压电致动器的伸长率通过传动机构被转换或重定向到翼型构件的翼弦长度方向的致动运动。使致动器定向在跨度宽度方向上具有伸长运动，防止转子叶片中产生的高离心加速度对致动器的操作产生负面影响。

6. 发明授权

US06220550B1 Actuating device with multiple stable positions 有权
标题翻译：具有多个稳定位置的执行装置
公开(公告)号：US06220550B1
公开(公告)日：2001-04-24
申请号：US09282709
申请日：1999-03-31
申请人： Robert M. McKillip, Jr.
发明人： Robert M. McKillip, Jr.
IPC分类号： B64C1324
CPC分类号： B64C27/001 , B64C13/50 , F03G7/065
摘要： A mechanical actuating device for moving an aerodynamic or hydrodynamic surface includes at least one flexure member confined in an elastically deformed condition. The flexure member is movable against the force generated by its elastic deformation to move the device into one of a plurality of stable positions, in which the device, and therefore the aerodynamic or hydrodynamic surface, are held by the force generated by elastic deformation of the flexure member. Since the flexure member is always elastically deformed, it “snaps” between discrete, stable positions and is held firmly in each. In another embodiment more flexure members can be used to provide additional stable positions. In one application, the actuating device is used as a trailing edge tab for a helicopter or tiltrotor blade to reduce 1/rev vibrations. The device can be actuated manually or electrically using shape-memory alloy wires to snap the flexure members into their various stable positions.
摘要翻译：用于移动空气动力学或流体动力学表面的机械致动装置包括限制在弹性变形状态的至少一个挠曲构件。挠曲构件可抵抗由其弹性变形产生的力移动，以将装置移动到多个稳定位置中的一个，其中装置，因此空气动力学或流体动力学表面由通过弹性变形产生的力保持挠性构件。由于挠曲构件总是弹性变形，所以它在离散的稳定位置之间“卡扣”，并且牢固地保持在每个位置。在另一个实施方案中，可以使用更多的弯曲构件来提供额外的稳定位置。在一个应用中，致动装置用作用于直升机或倾斜转子叶片的后缘翼片，以减少1 / rev振动。可以使用形状记忆合金线手动地或电地致动该装置，以将挠曲构件卡扣到其各种稳定位置。

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