公开(公告)号：US20060027701A1

公开(公告)日：2006-02-09

申请号：US11020066

申请日：2004-12-23

申请人： Paul Eglin

发明人： Paul Eglin

IPC分类号： B64C27/00

CPC分类号： B64C27/001

摘要： A method and a device allow for reducing the vibration generated on the structure 17 of a helicopter 2 by the air flow through the main rotor 5 and by the air flow along the fuselage 3. The device 1 includes: at least one sensor 18, 19, 20 measuring the vibration generated on the structure 17; and computer element 30 responsive to the measurements to determine a variation in angle of incidence for a stabilizer 39 of the helicopter 2 that is suitable for generating a vertical opposing force {right arrow over (TZ)} for opposing the vertical vibration, with the variation in angle of incidence as determined in this way being transmitted to a system 10 for controlling the angle of incidence of the stabilizer 39.

摘要翻译： 一种方法和装置允许通过主转子5的空气流和沿着机身3的空气流减少在直升机2的结构17上产生的振动。 装置1包括：测量在结构17上产生的振动的至少一个传感器18,19,20。 以及响应于测量的计算机元件30，以确定直升机2的稳定器39的入射角的变化，其适于产生垂直相反的力（右侧箭头（用于相对垂直振动的TZ，与角度的变化 以这种方式确定的发射率被传输到用于控制稳定器39的入射角的系统10。

公开(公告)号：US06745114B2

公开(公告)日：2004-06-01

申请号：US10272293

申请日：2002-10-17

申请人： Paul Eglin

发明人： Paul Eglin

IPC分类号： G06F1518

CPC分类号： G05D1/0825

摘要： A device for determining in real time the behavior of a craft may include a first device for determining, from a current linear model modeling the behavior of the craft, a vector &lgr; illustrating an equilibrium state. A second device is connected to the first device for determining from vector &lgr; the values at equilibrium of parameters of the linear model. A third device is connected to the second device for calculating, from at least some of the parameter values, the dynamic component of the behavior of the craft. A fourth device is connected to the first and third devices for introducing the dynamic component into the linear model so as to obtain a new current linear model and to deduce the behavior of the craft therefrom.

摘要翻译： 用于实时地确定飞行器的行为的装置可以包括第一装置，用于根据当前线性模型来确定飞行器的行为，示出平衡状态的矢量λ。 第二设备连接到第一设备，用于从向量λ确定线性模型的参数平衡处的值。 第三设备连接到第二设备，用于从至少一些参数值计算飞行器的行为的动态分量。 第四装置连接到第一和第三装置，用于将动态分量引入到线性模型中，以便获得新的当前线性模型并推导出该装置的行为。

公开(公告)号：US08843252B2

公开(公告)日：2014-09-23

申请号：US13551021

申请日：2012-07-17

申请人： Paul Eglin

发明人： Paul Eglin

IPC分类号： G06F19/00 ,  B64C27/00 ,  B64D45/00 ,  G05D1/06

CPC分类号： B64D45/00 ,  G05D1/0676

摘要： A piloting assistance device (5) comprising a calculation unit (10) and a display unit (20). The calculation unit (10) executes stored instructions to determine at least one thrust margin for a propeller between a current thrust being exerted by said propeller and a threshold thrust corresponding to a negative power limit (Pmin), and to determine a main minimum total ground slope that can be followed by the aircraft in descent as a function of said thrust margin. Finally, the calculation unit presents a main symbol (25) on a display unit (20), the main symbol (25) representing the minimum total ground slope that can be followed by the aircraft (1) in descent, the main symbol (25) appearing superimposed on a representation (21) of the surroundings that exist in front of the aircraft (1).

摘要翻译： 一种引导辅助装置（5），包括计算单元（10）和显示单元（20）。 计算单元（10）执行存储的指令，以确定由所述螺旋桨施加的当前推力与对应于负功率极限（Pmin）的阈值推力之间的螺旋桨的至少一个推力裕度，并且确定主要最小总地面 作为所述推力边缘的函数，下降中的飞机可以跟随的斜坡。 最后，计算单元在显示单元（20）上呈现主符号（25），主符号（25）表示飞机（1）在下降时可以遵循的最小总地面坡度，主符号（25） ）叠加在存在于飞机（1）前面的环境的表示（21）上。

公开(公告)号：US20140034774A1

公开(公告)日：2014-02-06

申请号：US13592772

申请日：2012-08-23

申请人： Jean-Jacques Ferrier ,  Paul Eglin

发明人： Jean-Jacques Ferrier ,  Paul Eglin

IPC分类号： B64C27/08 ,  B64C27/26

CPC分类号： B64C27/08 ,  B64C27/26 ,  B64C27/28

摘要： An aircraft (1) comprising a fuselage (2), a rotary wing (10) having two contrarotating main rotors (12) arranged in tandem above the fuselage (2), at least one propulsion member (20), and a power plant (30). Each propulsion member (20) is carried by a rear portion (3) of the fuselage. The aircraft (1) includes an interconnection system (40) providing a permanent connection between the power plant (30) and the rotary wing (10), except in the event of a failure or during training, the aircraft (1) having differential control means (50) for controlling the cyclic pitch of the blades of the main rotors (12) to control the aircraft (1) in yaw, and inhibition means (60) for inhibiting each propulsion member (20).

摘要翻译： 包括机身（2）的飞机（1），具有在机身（2）上串联布置的两个反转主转子（12）的旋转翼（10），至少一个推进构件（20）和发电厂 30）。 每个推进构件（20）由机身的后部（3）承载。 飞机（1）包括互连系统（40），其在发电厂（30）和旋转翼（10）之间提供永久连接，除非发生故障或训练期间，飞机（1）具有差速控制 用于控制主转子（12）的叶片的循环间距以控制飞行器（1）偏航的装置（50），以及用于抑制每个推进构件（20）的禁止装置（60）。

公开(公告)号：US08568096B2

公开(公告)日：2013-10-29

申请号：US12769912

申请日：2010-04-29

申请人： Paul Eglin

发明人： Paul Eglin

IPC分类号： B64C27/00

CPC分类号： B64C27/22 ,  G05D1/0858

摘要： The present invention relates to a control and regulation method for a rotorcraft having at least one variable-pitch propulsive propeller driven by at least one power source, said method consisting in generating at least one mean pitch setpoint βtcl* for the propeller(s) as a function of a thrust variation control order Tcl, wherein the method consists in defining a plurality of operating modes, including: a direct mode in which the value of the mean pitch value is a direct result of the control order Tcl; a forced mode in which the mean pitch is automatically forced to a calculated pitch value; a regulated mode in which the power of the propulsive propeller(s) is regulated as a function of a power setpoint from a pilot and of servo-controlling the mean pitch of the propeller(s); and a protected mode.

摘要翻译： 本发明涉及一种用于具有由至少一个动力源驱动的至少一个可变桨距推进螺旋桨的旋翼航空器的控制和调节方法，所述方法包括为螺旋桨生成至少一个平均桨距设定值（a） 推力变化控制顺序Tcl的函数，其中该方法包括定义多个操作模式，包括：直接模式，其中平均间距值的值是控制顺序Tcl的直接结果; 强制模式，其中平均音高被自动强制为计算的音调值; 推进式螺旋桨的功率被调节为来自飞行员的功率设定点的函数和伺服控制螺旋桨的平均桨距的调节模式; 和保护模式。

公开(公告)号：US08915464B2

公开(公告)日：2014-12-23

申请号：US13592772

申请日：2012-08-23

申请人： Jean-Jacques Ferrier ,  Paul Eglin

发明人： Jean-Jacques Ferrier ,  Paul Eglin

IPC分类号： B64C27/22 ,  B64C29/00 ,  B64C27/08 ,  B64C27/26 ,  B64C27/28

CPC分类号： B64C27/08 ,  B64C27/26 ,  B64C27/28

摘要： An aircraft (1) comprising a fuselage (2), a rotary wing (10) having two contrarotating main rotors (12) arranged in tandem above the fuselage (2), at least one propulsion member (20), and a power plant (30). Each propulsion member (20) is carried by a rear portion (3) of the fuselage. The aircraft (1) includes an interconnection system (40) providing a permanent connection between the power plant (30) and the rotary wing (10), except in the event of a failure or during training, the aircraft (1) having differential control means (50) for controlling the cyclic pitch of the blades of the main rotors (12) to control the aircraft (1) in yaw, and inhibition means (60) for inhibiting each propulsion member (20).

摘要翻译： 包括机身（2）的飞机（1），具有在机身（2）上串联布置的两个反转主转子（12）的旋转翼（10），至少一个推进构件（20）和发电厂 30）。 每个推进构件（20）由机身的后部（3）承载。 飞机（1）包括互连系统（40），其在发电厂（30）和旋转翼（10）之间提供永久连接，除非发生故障或训练期间，飞机（1）具有差速控制 用于控制主转子（12）的叶片的循环间距以控制飞行器（1）偏航的装置（50），以及用于抑制每个推进构件（20）的禁止装置（60）。

公开(公告)号：US07616130B2

公开(公告)日：2009-11-10

申请号：US11710549

申请日：2007-02-26

申请人： Jo{hacek over (e)}l Astruc ,  Paul Eglin

发明人： Jo{hacek over (e)}l Astruc ,  Paul Eglin

IPC分类号： G01C23/00

CPC分类号： G01C23/005

摘要： A method is provided for assisting the piloting of a rotorcraft in which vertical speed variation (DVZ) of the rotorcraft is determined as a function of a horizontal speed variation (DVH) of the aircraft and as a function of data representative of the power (W) absorbed for providing the rotorcraft with lift and forward advance, the ratio between variation speed vertical (DVZ) and the horizontal speed (VH) of the rotorcraft is calculated, and a piloting assistance symbol is presented on a display in a position (α) that is a function of the ratio.

摘要翻译： 提供了一种辅助驾驶飞行器的驾驶方法，其中旋翼航空器的垂直速度变化（DVZ）被确定为飞行器的水平速度变化（DVH）的函数，并且作为代表功率的数据（W 被吸收用于为旋翼航空器提供提升和前进提前，计算旋翼航空器的变速垂直（DVZ）与水平速度（VH）之间的比率，并且在位置（α）的显示器上呈现驾驶辅助符号， 这是该比率的函数。

公开(公告)号：US07461819B2

公开(公告)日：2008-12-09

申请号：US11019633

申请日：2004-12-23

申请人： Paul Eglin

发明人： Paul Eglin

IPC分类号： G05D1/00 ,  B64C13/00 ,  B64C11/00 ,  B64C27/78

CPC分类号： B64C27/001

摘要： A method and a device reduces the vibration generated on the structure 17 of a helicopter 2 by the flow of air through the main rotor 5 and by the flow of air along the fuselage 3. The device 1 includes: at least one sensor 18, 19, 20 measuring the vibration generated on the structure 17; and computer element 30 responsive to the vibration measurements to determine variation in the angle of incidence of a tail fin 9 of the helicopter 2 suitable for generating an opposing force {right arrow over (T1)}, {right arrow over (T2)} for opposing the vibration, and transmitting the variation in angle of incidence as determined in this way to a control system 10 for controlling the angle of incidence of the tail fin 9.

摘要翻译： 一种方法和装置通过空气通过主转子5的空气流以及沿着机身3的空气流减少在直升机2的结构17上产生的振动。装置1包括：至少一个传感器18,19 测量在结构17上产生的振动; 和响应于振动测量的计算机元件30，以确定直升机2的尾翼9适于产生相反的力{（T1）}上的右箭头（（T2）}的右箭头（T2）}的入射角的变化 相反的振动，并且以这种方式将入射角的变化传递到用于控制尾鳍9的入射角的控制系统10。

公开(公告)号：US07451949B2

公开(公告)日：2008-11-18

申请号：US11020066

申请日：2004-12-23

申请人： Paul Eglin

发明人： Paul Eglin

IPC分类号： G05D1/00 ,  B64C13/00 ,  B64C11/00 ,  B64C27/78

CPC分类号： B64C27/001

摘要： A method and a device allow for reducing the vibration generated on the structure 17 of a helicopter 2 by the air flow through the main rotor 5 and by the air flow along the fuselage 3. The device 1 includes: at least one sensor 18, 19, 20 measuring the vibration generated on the structure 17; and computer element 30 responsive to the measurements to determine a variation in angle of incidence for a stabilizer 39 of the helicopter 2 that is suitable for generating a vertical opposing force {right arrow over (TZ)} for opposing the vertical vibration, with the variation in angle of incidence as determined in this way being transmitted to a system 10 for controlling the angle of incidence of the stabilizer 39.

摘要翻译： 一种方法和装置允许通过主转子5的空气流和沿着机身3的空气流减少在直升机2的结构17上产生的振动。装置1包括：至少一个传感器18,19 测量在结构17上产生的振动; 以及响应于测量的计算机元件30，以确定直升机2的稳定器39的入射角的变化，其适于产生垂直相反的力（右侧箭头（用于相对垂直振动的TZ，与角度的变化 以这种方式确定的发射率被传输到用于控制稳定器39的入射角的系统10。