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1.发明申请SYSTEM FOR CONTROLLING PITCH VARIATION OF THE BLADES OF A PROPELLER, A PROPELLER, AND AN AIRCRAFT 有权用于控制螺旋桨，螺旋桨和飞机的叶片的倾斜变化的系统公开(公告)号：US20130078096A1
公开(公告)日：2013-03-28
申请号：US13617544
申请日：2012-09-14
申请人： Gérard Couderc , Mathilde Chouteau , Romuald Biest
发明人： Gérard Couderc , Mathilde Chouteau , Romuald Biest
IPC分类号： F01D7/00
摘要： A system (10) having a control plate (15) for controlling the pitch of the blades (5) of a propeller, a power block (20), and a directional control valve (30) for feeding said power block (20) with fluid. The power block (20) is sealed and includes at least a body in which at least one piston (22) that is secured to a piston rod (25) projecting from said body (21) is movable in translation, a repeater rod (50) connecting said piston rod (25) to said control plate (15). The control valve (30) is sealed and comprises a stationary manifold (35) and a movable manifold (40) that is movable in rotation, said stationary manifold (35) being controlled by a control lever (31) connected by repeater means (32) to said repeater rod (50). A respective pipe (60) connects each chamber (23, 24) of said power block (20) to said movable manifold (40).
摘要翻译： 一种具有控制板（15）的系统（10），用于控制螺旋桨叶片（5）的间距，动力块（20）和方向控制阀（30），用于将所述动力块（20）与 流体。 动力块（20）被密封并且包括至少一个主体，其中固定到从所述主体（21）突出的活塞杆（25）的至少一个活塞（22）能够平移地移动，中继杆（50） ）将所述活塞杆（25）连接到所述控制板（15）。 控制阀（30）被密封并且包括可旋转移动的固定歧管（35）和可移动歧管（40），所述固定歧管（35）由控制杆（31）控制，所述控制杆通过中继器装置 ）到所述中继棒（50）。 相应的管道（60）将所述动力块（20）的每个室（23,24）连接到所述可移动歧管（40）。
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2.发明授权System for controlling pitch variation of the blades of a propeller, a propeller, and an aircraft 有权用于控制螺旋桨，螺旋桨和飞行器的叶片的桨距变化的系统公开(公告)号：US09284042B2
公开(公告)日：2016-03-15
申请号：US13617544
申请日：2012-09-14
申请人： Gérard Couderc , Mathilde Chouteau , Romuald Biest
发明人： Gérard Couderc , Mathilde Chouteau , Romuald Biest
摘要： A system (10) having a control plate (15) for controlling the pitch of the blades (5) of a propeller, a power block (20), and a directional control valve (30) for feeding said power block (20) with fluid. The power block (20) is sealed and includes at least a body in which at least one piston (22) that is secured to a piston rod (25) projecting from said body (21) is movable in translation, a repeater rod (50) connecting said piston rod (25) to said control plate (15). The control valve (30) is sealed and comprises a stationary manifold (35) and a movable manifold (40) that is movable in rotation, said stationary manifold (35) being controlled by a control lever (31) connected by repeater means (32) to said repeater rod (50). A respective pipe (60) connects each chamber (23, 24) of said power block (20) to said movable manifold (40).
摘要翻译： 一种具有控制板（15）的系统（10），用于控制螺旋桨叶片（5）的间距，动力块（20）和方向控制阀（30），用于将所述动力块（20）与 流体。 动力块（20）被密封并且包括至少一个主体，其中固定到从所述主体（21）突出的活塞杆（25）的至少一个活塞（22）能够平移地移动，中继杆（50） ）将所述活塞杆（25）连接到所述控制板（15）。 控制阀（30）被密封并且包括可旋转移动的固定歧管（35）和可移动歧管（40），所述固定歧管（35）由控制杆（31）控制，所述控制杆通过中继器装置 ）到所述中继棒（50）。 相应的管道（60）将所述动力块（20）的每个室（23,24）连接到所述可移动歧管（40）。
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3.发明授权Control lever for controlling a rotary wing, a mechanical control system including said control lever, and an aircraft 有权用于控制旋转翼的控制杆，包括所述控制杆的机械控制系统和飞行器公开(公告)号：US09150306B2
公开(公告)日：2015-10-06
申请号：US13437420
申请日：2012-04-02
申请人： Gérard Couderc , Romuald Biest
发明人： Gérard Couderc , Romuald Biest
摘要： A control lever (10) provided with a stick (11) extending axially from a stand (11′) towards grip means (11″) and with a carrier structure (20) for said stick (11) that is hinged about a first hinge axis (AX1) and about a second hinge axis (AX2). The control lever (10) includes phasing means (30) constrained to move in rotation with said stick (11) about said first hinge axis (AX1) and about said second hinge axis (AX2), said phasing means (30) comprising at least three main arms (31, 32, 33), each for controlling a respective power member (8′, 8″, 8″′) that is connected to a set (6) of swashplates for controlling a rotary wing (2).
摘要翻译： 一种设置有从支架（11'）朝向夹紧装置（11“）轴向延伸并且具有用于所述棒（11）的托架结构（20）的杆（11）的控制杆（10），其围绕第一铰链 轴线（AX1）和约第二铰链轴线（AX2）。 所述控制杆（10）包括定位装置（30），所述定相装置（30）被限制为使所述杆（11）围绕所述第一铰链轴线（AX1）和所述第二铰链轴线（AX2）旋转移动，所述定相装置（30）至少包括 三个主臂（31,32,33）各自用于控制连接到用于控制旋转翼（2）的旋转盘组（6）的相应的动力构件（8'，8“，8”'）。
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4.发明授权Cyclic stick for mechanically transmitting commands for controlling a rotorcraft, the stick having a lever arm that is amplified selectively in the event of an emergency 有权用于机械传送用于控制旋翼航空器的命令的循环杆，该杆具有在紧急情况下被选择性放大的杆臂公开(公告)号：US08590843B2
公开(公告)日：2013-11-26
申请号：US13411950
申请日：2012-03-05
申请人： Romuald Biest , Robert Convers
发明人： Romuald Biest , Robert Convers
IPC分类号： B64C13/04
摘要： The invention provides a control mechanism for controlling flight of an aircraft, the control mechanism comprising a cyclic control stick (1) that is mounted to tilt (B1, B2) on a carrier structure (4) and that is in engagement with remote mechanical transmission members (2, 3). The stick (1) is arranged as a telescopic member provided with locking means (20) for locking it in a normal-use retracted position, and is equipped with deployment means (21). Unlocking of the locking means (20) and use of the deployment means (21) depend on an assistance device (17) associated with the stick (1) being in a defective state. In the event of such a defective state being detected, the stick (1) is suitable for being deployed so as to increase the comfort of the pilot while manipulating it.
摘要翻译： 本发明提供了一种用于控制飞行器飞行的控制机构，该控制机构包括一个循环控制杆（1），该循环控制杆安装成在载体结构（4）上倾斜（B1，B2）并与远程机械传动 会员（2,3）。 杆（1）被布置为具有用于将其锁定在正常使用的缩回位置的锁定装置（20）的伸缩构件，并且配备有展开装置（21）。 锁定装置（20）的解锁和展开装置（21）的使用取决于与棒（1）相关联的辅助装置（17）处于缺陷状态。 在检测到这样的缺陷状态的情况下，棒（1）适于被部署，以便在操纵该飞行员的同时增加飞行员的舒适性。
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5.发明授权Variable ratio crank for a manual flight control linkage of a rotary wing aircraft 有权用于旋翼飞机的手动飞行控制联动的可变比曲柄公开(公告)号：US08196857B2
公开(公告)日：2012-06-12
申请号：US12791216
申请日：2010-06-01
申请人： Bernard Gemmati , Romuald Biest , Carine Mirman
发明人： Bernard Gemmati , Romuald Biest , Carine Mirman
IPC分类号： B64C27/32
摘要： The present invention relates to a bellcrank (40) for a flight-attitude-changing linkage (27, 25A, 28A) of the variable gain type. The linkage (27, 25A, 28A) connects a manual flight control device of a rotary wing aircraft (1), e.g. a hybrid helicopter, to at least one airfoil of said aircraft (1) suitable for causing a change in flight attitude. Said bellcrank (40) includes first and second sliders (50, 52). Said first slider (50) is connected to a movable portion (57, 61) of a setpoint flight-attitude-changing linkage (24) that delivers a setpoint, with movements of said linkage causing the gain of said variable-gain linkage (27, 25A, 28A) to be adjusted, which gain is proportional to the position of said movable portion (57, 61).
摘要翻译： 本发明涉及一种用于可变增益型飞行姿态改变联动装置（27,25A，28A）的曲拐（40）。 连杆机构（27,2AA，28A）连接旋翼机（1）的手动飞行控制装置， 一种混合式直升机，适用于适于引起飞行姿态改变的所述飞机（1）的至少一个翼型。 所述曲拐（40）包括第一和第二滑块（50,52）。 所述第一滑块（50）连接到传递设定点的设定点飞行姿态改变联动装置（24）的可移动部分（57,61），所述联动装置的运动导致所述可变增益联动装置（27）的增益 ，25A，28A），该增益与所述可动部分（57,61）的位置成比例。
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公开(公告)号：US08393569B2
公开(公告)日：2013-03-12
申请号：US12468285
申请日：2009-05-19
申请人： Bernard Gemmati , Philippe Vincent , Romuald Biest
发明人： Bernard Gemmati , Philippe Vincent , Romuald Biest
IPC分类号： B64C13/00
摘要： A breakable coupling device for coupling together first and second main transmission shafts stationary in translation along a longitudinal axis of rotation of the device comprises a blocking device having a discontinuous first housing and a continuous second housing forming a closed loop; a compression device; at least one drive device connecting the blocking device and the compression device together in rotation about the longitudinal axis below a predetermined torque, wherein the discontinuous first housing is configured to receive the at least one drive device below the predetermined torque; and a shifting device configured to shift the at least one drive device non-reversibly from the discontinuous first housing towards the continuous second housing when the torque exerted on the at least one drive device is greater than the predetermined torque.
摘要翻译： 一种用于将第一和第二主传动轴沿着装置的旋转纵向轴线平移地平滑连接在一起的可破坏的联接装置包括具有不连续的第一壳体和形成闭环的连续的第二壳体的阻挡装置; 压缩装置; 至少一个驱动装置，其将所述阻挡装置和所述压缩装置连接在一起围绕所述纵向轴线旋转低于预定扭矩，其中所述不连续的第一壳体构造成将所述至少一个驱动装置接收在所述预定扭矩以下; 以及移动装置，其构造成当施加在所述至少一个驱动装置上的扭矩大于所述预定扭矩时，使所述至少一个驱动装置不可逆地从所述不连续的第一壳体向所述连续的第二壳体移动。
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7.发明授权Rotary actuator incorporating a force relationship, and a method of reducing angular slack in such a rotary actuator 有权包含力关系的旋转致动器，以及减小这种旋转致动器中的角度松弛的方法公开(公告)号：US08181550B2
公开(公告)日：2012-05-22
申请号：US12622936
申请日：2009-11-20
申请人： Bernard Gemmati , Romuald Biest
发明人： Bernard Gemmati , Romuald Biest
IPC分类号： G05G1/00
CPC分类号： B64C13/28 , G05G5/03 , G05G5/05 , Y10T74/20006
摘要： A rotary actuator incorporating a force relationship includes a twistably-deformable structure having a first and a second end plate and a helical spring with a first and a second terminal end secured on the first and the second end plate, respectively, and wherein the first and the second end plate have a first and a second notch, respectively, and wherein the first and the second notch have a first and a second contact zone, respectively. The rotary actuator further includes an outlet shaft and a motor assembly having an outlet gear configured to drive the twistably-deformable structure so as to drive the outlet shaft in rotation, wherein the motor assembly, the twistably-deformable structure and the outlet shaft are disposed in succession. The rotary actuator has a first finger constrained to rotate with the outlet gear and a second finger constrained to rotate with the outlet shaft.
摘要翻译： 包括力关系的旋转致动器包括具有第一和第二端板的可扭转变形的结构和螺旋弹簧，第一和第二端部分别固定在第一和第二端板上，并且其中第一和第二端板 第二端板分别具有第一和第二凹口，并且其中第一和第二凹口分别具有第一和第二接触区域。 旋转致动器还包括出口轴和马达组件，其具有被配置为驱动可扭曲变形的结构以便驱动出口轴转动的出口齿轮，其中马达组件，可扭曲变形的结构和出口轴被设置 陆续。 旋转致动器具有被限制为与出口齿轮一起旋转的第一手指和被限制为与出口轴一起旋转的第二手指。
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8.发明申请CONTROL LEVER FOR CONTROLLING A ROTARY WING, A MECHANICAL CONTROL SYSTEM INCLUDING SAID CONTROL LEVER, AND AN AIRCRAFT 有权用于控制旋转翼的控制杆，包括控制杆的机械控制系统和飞机公开(公告)号：US20120255386A1
公开(公告)日：2012-10-11
申请号：US13437420
申请日：2012-04-02
申请人： Gèrard Couderc , Romuald Biest
发明人： Gèrard Couderc , Romuald Biest
IPC分类号： G05G9/04
摘要： A control lever (10) provided with a stick (11) extending axially from a stand (11′) towards grip means (11″) and with a carrier structure (20) for said stick (11) that is hinged about a first hinge axis (AX1) and about a second hinge axis (AX2). The control lever (10) includes phasing means (30) constrained to move in rotation with said stick (11) about said first hinge axis (AX1) and about said second hinge axis (AX2), said phasing means (30) comprising at least three main arms (31, 32, 33), each for controlling a respective power member (8′, 8″, 8″′) that is connected to a set (6) of swashplates for controlling a rotary wing (2).
摘要翻译： 一种设置有从支架（11'）朝向夹紧装置（11“）轴向延伸并且具有用于所述棒（11）的托架结构（20）的杆（11）的控制杆（10），其围绕第一铰链 轴线（AX1）和约第二铰链轴线（AX2）。 所述控制杆（10）包括定位装置（30），所述定相装置（30）被限制为使所述杆（11）围绕所述第一铰链轴线（AX1）和所述第二铰链轴线（AX2）旋转移动，所述定相装置（30）至少包括 三个主臂（31,32,33）各自用于控制连接到用于控制旋转翼（2）的旋转盘组（6）的相应的动力构件（8'，8“，8”'）。
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9.发明授权Mechanical device for combining first and second control orders, and an aircraft provided with such a device 有权用于组合第一和第二控制命令的机械装置，以及配备有这种装置的飞行器公开(公告)号：US08282035B2
公开(公告)日：2012-10-09
申请号：US12792080
申请日：2010-06-02
IPC分类号： B64C27/54
摘要： The present invention relates to a mechanical device (1) suitable for combining first and second pitch control orders for controlling the blade pitch of at least one rotary assembly, the device comprising a carrier structure (10) suitable for being fastened to a support (5) by at least one main fastener pin (13) about which said carrier structure (10) is capable of performing a pivoting movement. In addition, the device includes at least one connection lever (20, 30) per rotary assembly, and at least one secondary fastener pin (25, 35) per connection lever (20, 30), said secondary fastener pin (25, 35) being secured firstly to said carrier structure (10) and being fastened secondly by rotary means (26, 36) to the connection lever (20, 30).
摘要翻译： 本发明涉及适于组合用于控制至少一个旋转组件的叶片桨距的第一和第二俯仰控制次序的机械装置（1），该装置包括适于紧固到支撑件（5）的载体结构（10） ）通过至少一个主紧固件销（13），所述承载结构（10）能够围绕所述主紧固销（13）进行枢转运动。 另外，该装置包括每个旋转组件至少一个连接杆（20,30）和每个连接杆（20,30）的至少一个辅助紧固销（25,35），所述次级紧固销（25,35） 首先被固定到所述承载结构（10）上，并通过旋转装置（26,36）第二次固定到所述连接杆（20,30）上。
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10.发明申请公开(公告)号：US20120234985A1
公开(公告)日：2012-09-20
申请号：US13411950
申请日：2012-03-05
申请人： Romuald Biest , Robert Convers
发明人： Romuald Biest , Robert Convers
IPC分类号： B64C13/14
摘要： The invention provides a control mechanism for controlling flight of an aircraft, the control mechanism comprising a cyclic control stick (1) that is mounted to tilt (B1, B2) on a carrier structure (4) and that is in engagement with remote mechanical transmission members (2, 3). The stick (1) is arranged as a telescopic member provided with locking means (20) for locking it in a normal-use retracted position, and is equipped with deployment means (21). Unlocking of the locking means (20) and use of the deployment means (21) depend on an assistance device (17) associated with the stick (1) being in a defective state. In the event of such a defective state being detected, the stick (1) is suitable for being deployed so as to increase the comfort of the pilot while manipulating it.
摘要翻译： 本发明提供了一种用于控制飞行器飞行的控制机构，该控制机构包括一个循环控制杆（1），该循环控制杆安装成在载体结构（4）上倾斜（B1，B2）并与远程机械传动 会员（2,3）。 杆（1）被布置为具有用于将其锁定在正常使用的缩回位置的锁定装置（20）的伸缩构件，并且配备有展开装置（21）。 锁定装置（20）的解锁和展开装置（21）的使用取决于与棒（1）相关联的辅助装置（17）处于缺陷状态。 在检测到这样的缺陷状态的情况下，棒（1）适于被部署，以便在操纵该飞行员的同时增加飞行员的舒适性。
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