公开(公告)号：US08186629B2

公开(公告)日：2012-05-29

申请号：US12724453

申请日：2010-03-16

申请人： Nicolas Queiras ,  Marc Salesse-Lavergne ,  Paul Eglin

发明人： Nicolas Queiras ,  Marc Salesse-Lavergne ,  Paul Eglin

IPC分类号： G01D1/00 ,  G01D1/08 ,  B64C27/22

CPC分类号： B64C27/26 ,  B64C2027/8272

摘要： A method of optimizing the operation of left and right propellers disposed on either side of the fuselage of a rotorcraft including a main rotor. Left and right aerodynamic surfaces include respective left and right flaps suitable for being deflected, yaw stabilization of the rotorcraft being achieved via first and second pitches respectively of the left and right propellers, and the deflection angles of the left and right flaps are adjusted solely during predetermined stages of flight in order to minimize a differential pitch of the left and right propellers so as to optimize the operation of the left and right propellers, the predetermined stages of flight including stages of flight at low speed performed at an indicated air speed (IAS) of the rotorcraft that is below a predetermined threshold, and stages of yaw-stabilized flight at high speed performed at an indicated air speed of the rotorcraft greater than the predetermined threshold.

摘要翻译： 一种优化设置在包括主转子的旋翼飞机的机身的任一侧的左右推进器的操作的方法。 左右空气动力学表面包括适于偏转的相应的左和右翼片，分别由左和右螺旋桨经由第一和第二桨距实现的旋翼航空器的偏航稳定性，左右翼片的偏转角度仅在 预定的飞行阶段，以便最小化左右推进器的差速器间距，从而优化左右螺旋桨的运行，包括以指定空气速度（IAS）执行的包括低速飞行阶段的预定飞行阶段 ），并且在所述旋翼航空器的指示的空气速度下执行的高速的偏航稳定飞行阶段大于预定阈值。

公开(公告)号：US08376266B2

公开(公告)日：2013-02-19

申请号：US12774283

申请日：2010-05-05

申请人： Bernard Gemmati ,  Nicolas Queiras ,  Paul Eglin

发明人： Bernard Gemmati ,  Nicolas Queiras ,  Paul Eglin

IPC分类号： B64C27/54 ,  B64C27/82

CPC分类号： B64C27/22

摘要： A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the fuselage, each half-wing being provided with a respective first or second propeller. The hybrid helicopter has a thrust control suitable for modifying the first pitch of the first blades of the first propeller and the second pitch of the second blades of the second propeller by the same amount. The hybrid helicopter includes yaw control elements for generating an original order for modifying the yaw attitude of the hybrid helicopter by increasing the pitch of the blades of one propeller and decreasing the pitch of the blades of the other propeller, the original order is optimized as a function of the position of the thrust control to obtain an optimized yaw control order that is applied to the first and second blades.

摘要翻译： 一种控制混合式直升机的偏航姿态的方法，该混合式直升机包括机身和设置有从机身的任一侧延伸的第一和第二半翼的附加升降面，每个半翼设置有相应的第一或第二螺旋桨。 混合动力直升机具有适于将第一螺旋桨的第一叶片的第一桨距和第二桨叶的第二叶片的第二桨距改变相同量的推力控制。 混合动力直升机包括偏航控制元件，用于产生用于通过增加一个螺旋桨的叶片的桨距并且减小另一个螺旋桨的叶片桨距来改变混合直升机的偏航姿态的原始顺序，原始顺序被优化为 推力控制的位置的功能，以获得施加到第一和第二叶片的优化的偏航控制顺序。

公开(公告)号：US08583295B2

公开(公告)日：2013-11-12

申请号：US13088493

申请日：2011-04-18

申请人： Paul Eglin ,  Nicolas Queiras ,  André Barraco ,  Francois Malburet

发明人： Paul Eglin ,  Nicolas Queiras ,  André Barraco ,  Francois Malburet

IPC分类号： B64C27/57

CPC分类号： B64C27/26 ,  B64C2027/8281

摘要： A method of controlling and regulating a rotorcraft presenting a speed of advance that is high and stabilized, the rotorcraft including at least a main lift rotor (10), at least one variable pitch propulsion propeller (6), and at least one power plant for driving the main rotor(s) (10) and at least one propeller (6), said method consisting in using a first loop for regulating pitch or attitude, and a second loop for regulating speed by means of a control over the mean pitch of the propulsion propeller(s) (6), wherein the method further consists in controlling the deflection angle of a horizontal tailplane (30, 25, 35) by using a third loop for controlling and regulating said deflection angle of the horizontal tailplane (30, 25, 35) in order to minimize the total power consumed by the main rotor (10) and the propulsive propeller(s) (6), for a given speed and attitude.

摘要翻译： 一种控制和调节具有高稳定性的前进速度的旋翼飞机的方法，所述旋翼航空器至少包括主提升转子（10），至少一个可变桨距推进推进器（6）和至少一个动力装置 驱动主转子（10）和至少一个螺旋桨（6），所述方法包括使用用于调节桨距或姿态的第一回路，以及用于通过对平均桨距的平均桨距的控制来调节速度的第二回路 推进螺旋桨（6），其中所述方法还包括通过使用第三回路来控制水平尾翼（30,25,35）的偏转角度，所述第三回路用于控制和调节所述水平尾翼（30,25,35）的所述偏转角， 以便以给定的速度和姿态来最小化主转子（10）和推进螺旋桨（6）所消耗的总功率。

公开(公告)号：US20120153072A1

公开(公告)日：2012-06-21

申请号：US13088493

申请日：2011-04-18

申请人： Paul Eglin ,  Nicolas Queiras ,  André Barraco ,  Francois Malburet

发明人： Paul Eglin ,  Nicolas Queiras ,  André Barraco ,  Francois Malburet

IPC分类号： B64C27/54

CPC分类号： B64C27/26 ,  B64C2027/8281

摘要： A method of controlling and regulating a rotorcraft presenting a speed of advance that is high and stabilized, the rotorcraft including at least a main lift rotor (10), at least one variable pitch propulsion propeller (6), and at least one power plant for driving the main rotor(s) (10) and at least one propeller (6), said method consisting in using a first loop for regulating pitch or attitude, and a second loop for regulating speed by means of a control over the mean pitch of the propulsion propeller(s) (6), wherein the method further consists in controlling the deflection angle of a horizontal tailplane (30, 25, 35) by using a third loop for controlling and regulating said deflection angle of the horizontal tailplane (30, 25, 35) in order to minimize the total power consumed by the main rotor (10) and the propulsive propeller(s) (6), for a given speed and attitude.

摘要翻译： 一种控制和调节具有高稳定性的前进速度的旋翼飞机的方法，所述旋翼航空器至少包括主提升转子（10），至少一个可变桨距推进推进器（6）和至少一个动力装置 驱动主转子（10）和至少一个螺旋桨（6），所述方法包括使用用于调节桨距或姿态的第一回路，以及用于通过对平均桨距的平均桨距的控制来调节速度的第二回路 推进螺旋桨（6），其中所述方法还包括通过使用第三回路来控制水平尾翼（30,25,35）的偏转角度，所述第三回路用于控制和调节所述水平尾翼（30,25,35）的所述偏转角， 以便以给定的速度和姿态来最小化主转子（10）和推进螺旋桨（6）所消耗的总功率。

公开(公告)号：US20130175385A1

公开(公告)日：2013-07-11

申请号：US13543957

申请日：2012-07-09

申请人： Paul Eglin

发明人： Paul Eglin

IPC分类号： B64C27/57 ,  B64D45/00

CPC分类号： B64C27/57 ,  B64C27/22 ,  B64D45/00 ,  G05D1/0858

摘要： An autopilot device (10) and method for automatically piloting a rotary wing aircraft (1), having at least one propulsion propeller (2), said rotary wing comprising at least one rotor (3) with a plurality of blades (3′), said device comprising a processor unit (15) co-operating with at least one collective control system (7) for controlling the collective pitch of said blades (3′). The device includes engagement means (20) connected to the processor unit (15) for engaging an assisted mode of piloting for maintaining an angle of attack, said processor unit (15) automatically controlling the collective pitch of the blades (3′) when the assisted mode of piloting for maintaining an angle of attack is engaged by controlling said collective control system to maintain an aerodynamic angle of attack (α) of the aircraft at a reference angle of attack (α*).

摘要翻译： 一种用于自动驾驶具有至少一个推进推进器（2）的旋翼飞机（1）的自动驾驶仪（10）和方法，所述旋转翼包括具有多个叶片（3'）的至少一个转子（3） 所述设备包括与至少一个集体控制系统（7）协作的处理器单元（15），用于控制所述叶片（3'）的总体间距。 所述装置包括连接到处理器单元（15）的接合装置（20），用于接合用于维持迎角的辅助驾驶模式，所述处理器单元（15）当自动控制叶片（3'）的集体桨距时， 通过控制所述集体控制系统来维持飞行器的参考迎角（α*）的空气动力学攻角（α），从而进行用于维持攻角的辅助驾驶模式。

公开(公告)号：US20070273544A1

公开(公告)日：2007-11-29

申请号：US11710549

申请日：2007-02-26

申请人： Joel Astruc ,  Paul Eglin

发明人： Joel Astruc ,  Paul Eglin

IPC分类号： G08B29/00

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：US10023306B2

公开(公告)日：2018-07-17

申请号：US13543957

申请日：2012-07-09

申请人： Paul Eglin

发明人： Paul Eglin

IPC分类号： G05D1/08 ,  B64C27/57 ,  B64D45/00 ,  B64C27/22

摘要： An autopilot device (10) and method for automatically piloting a rotary wing aircraft (1), having at least one propulsion propeller (2), said rotary wing comprising at least one rotor (3) with a plurality of blades (3′), said device comprising a processor unit (15) co-operating with at least one collective control system (7) for controlling the collective pitch of said blades (3′). The device includes engagement means (20) connected to the processor unit (15) for engaging an assisted mode of piloting for maintaining an angle of attack, said processor unit (15) automatically controlling the collective pitch of the blades (3′) when the assisted mode of piloting for maintaining an angle of attack is engaged by controlling said collective control system to maintain an aerodynamic angle of attack (α) of the aircraft at a reference angle of attack (α*).

公开(公告)号：US09216820B2

公开(公告)日：2015-12-22

申请号：US12773965

申请日：2010-05-05

申请人： Paul Eglin

发明人： Paul Eglin

IPC分类号： B64C27/22 ,  B64C27/04 ,  B64C27/26 ,  B64C27/28 ,  B64D43/00

CPC分类号： B64C27/04 ,  B64C27/26 ,  B64C27/28 ,  B64D43/00

摘要： A piloting assistance device for a hybrid helicopter is provided with a rotary wing, two half-wings (8′, 8″) provided respectively with first and second propellers (6′, 6″), and an engine installation continuously driving the rotary wing (100) and the propellers by meshing with a mechanical interconnection system. Furthermore, the device is provided with computer element (40) for determining maximum mean pitch (max) applicable to the first and second propellers without exceeding the power available for the propellers, the computer element determining the maximum mean pitch (max) as a function of the current mean pitch of the blades of the first and second propellers as measured in real time, of a maximum power that can be delivered by the engine installation, of a current power being delivered by the engine installation, and of a relationship determining a power gradient (GRD) as a function of pitch for the first and second propellers.

摘要翻译： 用于混合直升机的驾驶辅助装置设置有旋翼，分别设置有第一和第二螺旋桨（6'，6“）的两个半翼（8'，8”），以及连续驱动旋翼 （100）和螺旋桨通过与机械互连系统啮合。 此外，该装置设置有计算机元件（40），用于确定适用于第一和第二螺旋桨的最大平均间距（max），而不超过可用于螺旋桨的功率，计算机元件确定最大平均间距（max）作为一个功能 当前由实际测量的第一和第二螺旋桨的叶片的当前平均间距，可由发动机安装可以传递的最大功率，由发动机设备输送的当前功率以及确定 功率梯度（GRD）作为第一和第二螺旋桨的沥青的函数。

公开(公告)号：US20130184902A1

公开(公告)日：2013-07-18

申请号：US13551021

申请日：2012-07-17

申请人： Paul Eglin

发明人： Paul Eglin

IPC分类号： B64D45/00

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：US20060097104A1

公开(公告)日：2006-05-11

申请号：US11019633

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： The present invention relates to a method and to a device for reducing 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. According to the invention, said device 1 comprises: at least one sensor 18, 19, 20 measuring the vibration generated on said structure 17; and computer means 30 responsive to said 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 said 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： 本发明涉及通过主转子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上产生的振动的方法和装置。根据本发明， 所述装置1包括：测量在所述结构17上产生的振动的至少一个传感器18,19,20。 以及响应于所述振动测量的计算机装置30，以确定直升机2的尾翼9的入射角的变化，适合于产生相反的力{（T 1）}上的右箭头，（T 2）上的右箭头 用于相对于所述振动，并且将以这种方式确定的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。