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：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：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。