公开(公告)号：US20160375994A1

公开(公告)日：2016-12-29

申请号：US15152721

申请日：2016-05-12

申请人： AIRBUS HELICOPTERS

发明人： Regis ROSSOTTO

IPC分类号： B64C27/14 ,  B64D27/10 ,  B64D27/24

CPC分类号： B64C27/14 ,  B64C27/12 ,  B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  B64D2027/026 ,  Y02T50/64

摘要： A method of driving rotation of a rotor of an aircraft, said aircraft having at least two fuel-burning engines and an electric motor suitable for driving rotation of said rotor. Said rotor is driven by using said engines together. An authorization is generated only during at least one predetermined stage of flight, said authorization authorizing the use of the electric motor in order to drive said rotor in rotation. While said authorization is valid and if one of said engines has failed, then an operation order is generated to require said electric motor to operate. While said operation order is valid, said rotor is driven by each engine that has not failed together with said electric motor.

摘要翻译： 一种驱动飞行器的转子的旋转的方法，所述飞行器具有至少两个燃料燃烧发动机和适于驱动所述转子的旋转的电动机。 所述转子通过一起使用所述发动机来驱动。 仅在至少一个预定的飞行阶段期间产生授权，所述授权授权使用电动机以驱动所述转子旋转。 虽然所述授权有效，并且如果所述发动机之一发生故障，则产生操作命令以要求所述电动机操作。 当所述操作顺序有效时，所述转子由与所述电动机一起没有失效的每个发动机驱动。

公开(公告)号：US20160311547A1

公开(公告)日：2016-10-27

申请号：US15083533

申请日：2016-03-29

申请人： AIRBUS HELICOPTERS

发明人： Regis ROSSOTTO ,  Jean-Francois PICCONE

IPC分类号： B64D31/06 ,  F02C9/26 ,  B64C27/46 ,  F02C3/10

CPC分类号： B64D31/06 ,  B64C27/46 ,  F01D21/00 ,  F02C3/10 ,  F02C9/00 ,  F02C9/263 ,  F05D2220/329 ,  Y02T50/671

摘要： A method of stopping a turboshaft engine in flight. During a power reduction step, a current power of the engine for stopping is reduced to reach zero power, and a current speed of rotation of the gas generator of the engine for stopping is reduced to reach a predetermined intermediate speed when the current power becomes zero. During a temperature stabilization step, the current speed of rotation remains equal to the intermediate speed. During a shutdown step, the current speed of rotation is reduced to reach zero speed.

摘要翻译： 一种在飞行中停止涡轮轴发动机的方法。 在功率降低步骤中，用于停止的发动机的当前功率被降低以达到零功率，并且当当前功率变为零时，用于停止的发动机的气体发生器的当前转速被降低以达到预定的中间速度 。 在温度稳定步骤期间，当前的旋转速度保持等于中间速度。 在关机步骤中，当前的旋转速度降低到零速度。

公开(公告)号：US20160376017A1

公开(公告)日：2016-12-29

申请号：US15182663

申请日：2016-06-15

申请人： AIRBUS HELICOPTERS

发明人： Regis ROSSOTTO

IPC分类号： B64D31/06 ,  B64C27/04 ,  B64D35/08 ,  F02C6/02 ,  F02C6/20

CPC分类号： B64D31/06 ,  B64C27/04 ,  B64C27/12 ,  B64D35/08 ,  F02C6/02 ,  F02C6/206 ,  F02C9/42 ,  F05D2220/329 ,  F05D2270/023 ,  F05D2270/052 ,  F05D2270/13 ,  Y02T50/671

摘要： A power plant comprising two engine groups and a main power transmission gearbox. Each engine group drives the main gearbox mechanically in order to rotate a main rotor of an aircraft at a frequency of rotation NR. A first engine group comprising two main engines is regulated on a first setpoint NR* for the frequency of rotation NR, while a second engine group comprising a secondary engine is regulated on a second setpoint W2* for power of the second engine group. In addition, each engine operates with margins relative to operating limits. The second setpoint W2* for power is determined so that each secondary engine operates with a lowest second margin that is equal to the lowest first margin of the first engine group.

摘要翻译： 一个发电厂，包括两个发动机组和一个主动力传动齿轮箱。 每个发动机组以机械方式驱动主变速箱，以便以旋转频率NR旋转飞行器的主转子。 包括两个主发动机的第一发动机组在第一设定点NR *上针对旋转频率NR进行调节，而包括二次发动机的第二发动机组被调节在第二设定点W2 *上，用于第二发动机组的功率。 此外，每个发动机的运行边际相对于运行极限。 确定用于功率的第二设定点W2 *，使得每个次级发动机以等于第一发动机组的最低第一余量的最低第二余量运行。

公开(公告)号：US20160035203A1

公开(公告)日：2016-02-04

申请号：US14809876

申请日：2015-07-27

申请人： AIRBUS HELICOPTERS

发明人： Regis ROSSOTTO ,  Emmanuel CAMHI

IPC分类号： G08B19/02 ,  B64D15/20

CPC分类号： G08B19/02 ,  B64D15/20

摘要： A method of detecting that an aircraft is flying in icing conditions. A processor unit determines a real power developed by the turboshaft engine and a theoretical power that the engine can develop in theory, the theoretical power being determined using a theoretical model supplying a power as a function at least of a speed of rotation of a gas generator of the engine. The processor unit determines a difference between the real power and the theoretical power. The processor unit generates a warning to indicate the presence of icing conditions when the power difference is greater than a predetermined power threshold for a length of time longer than a time threshold, and when a temperature outside the aircraft lies between a low temperature threshold and a high temperature threshold.

摘要翻译： 一种检测飞机在结冰条件下飞行的方法。 处理器单元确定由涡轮轴发动机开发的实际功率和发动机在理论上可以发展的理论功率，理论功率使用理论模型来确定，该理论模型至少提供气体发生器的旋转速度的功率 的发动机。 处理器单元确定实际功率和理论功率之间的差异。 当功率差大于预定功率阈值大于时间阈值的时间长度时，处理器单元产生警告以指示结冰条件的存在，并且当飞机外的温度位于低温阈值和 高温阈值。

公开(公告)号：US20170025032A1

公开(公告)日：2017-01-26

申请号：US15290441

申请日：2016-10-11

申请人： AIRBUS HELICOPTERS

发明人： Guillaume DUMAR ,  Regis ROSSOTTO ,  Hilario VIEIRA

IPC分类号： G09B9/46 ,  G09B9/08 ,  G09B9/44

CPC分类号： G09B9/46 ,  G09B9/085 ,  G09B9/44

摘要： A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.

摘要翻译： 一种在实现模拟旋翼航空器中的一个发动机的故障的飞行中模拟模式的同时驱动旋翼航空器的主转子旋转的方法。 在模拟模式中，当主转子的当前旋转速度（NR）被检测为低于预定的阈值旋转速度（S）时，模拟模式保持活动，并且产生调节命令以执行 控制操作（A）通过授权超过在模拟模式下调节发动机运转的设定值（OEI / 2）施加的限制来逐渐增加发动机所输送的功率。 所述逐渐增加的动力被飞行员停留在训练中，并且操作主转子叶片的集体桨距操纵器，以主旋转的旋转方式以预定的阈值速度旋转。

公开(公告)号：US20140302461A1

公开(公告)日：2014-10-09

申请号：US14247459

申请日：2014-04-08

申请人： AIRBUS HELICOPTERS

发明人： Guillaume DUMUR ,  Regis ROSSOTTO ,  Hilario VIEIRA

IPC分类号： G09B9/46

CPC分类号： G09B9/46

摘要： A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.

摘要翻译： 一种在实现模拟旋翼航空器中的一个发动机的故障的飞行中模拟模式的同时驱动旋翼航空器的主转子旋转的方法。 在模拟模式中，当主转子的当前旋转速度（NR）被检测为低于预定的阈值旋转速度（S）时，模拟模式保持活动，并且产生调节命令以执行 控制操作（A）通过授权超过在模拟模式下调节发动机运转的设定值（OEI / 2）施加的限制来逐渐增加发动机所输送的功率。 所述逐渐增加的动力被飞行员停留在训练中，并且操作主转子叶片的集体桨距操纵器，以主旋转的旋转方式以预定的阈值速度旋转。

公开(公告)号：US20170066541A1

公开(公告)日：2017-03-09

申请号：US15175269

申请日：2016-06-07

申请人： AIRBUS HELICOPTERS

发明人： Regis ROSSOTTO

IPC分类号： B64D31/06 ,  B64D35/08 ,  B64C27/06

CPC分类号： B64D31/06 ,  B64C27/06 ,  B64C27/12 ,  B64D35/08 ,  F02C6/206 ,  F02C9/42 ,  F05D2220/329 ,  Y02T50/671

摘要： A power plant comprising two engine groups and a main power transmission gearbox. Each engine group drives the main gearbox mechanically in order to rotate a main rotor of an aircraft at a frequency of rotation NR. A first engine group comprising two main engines is regulated on a first setpoint NR* for the frequency of rotation NR, while a second engine group comprising a secondary engine is regulated on a second setpoint W2* for power. The second setpoint W2* for power is determined so that each secondary engine operates only when a flight power Wvol necessary for the flight of the aircraft is greater than the sum of the main maximum powers WMax1 from each main engine.

摘要翻译： 一个发电厂，包括两个发动机组和一个主动力传动齿轮箱。 每个发动机组以机械方式驱动主变速箱，以便以旋转频率NR旋转飞行器的主转子。 包括两个主发动机的第一发动机组在第一设定点NR *上针对旋转频率NR进行调节，而包括二次发动机的第二发动机组被调节在第二设定点W2 *上用于动力。 确定功率的第二设定点W2 *，使得每个次级发动机仅在飞行器飞行所需的飞行功率Wvol大于来自每个主发动机的主最大功率WMax1的总和时才起作用。

公开(公告)号：US20150028153A1

公开(公告)日：2015-01-29

申请号：US14333765

申请日：2014-07-17

申请人： AIRBUS HELICOPTERS

发明人： Regis ROSSOTTO ,  Hanno BOIE

IPC分类号： B64D31/06 ,  B64C27/00

CPC分类号： B64D31/06 ,  B64C27/00 ,  B64C27/12 ,  B64D35/08 ,  F02C9/42 ,  F05D2220/329 ,  F05D2270/05 ,  F05D2270/053 ,  Y02T50/671

摘要： A power plant (1) having two engine groups (10, 20) and a main gearbox (MGB) (2), and a rotary wing aircraft (30) having such a power plant (1). Each engine group (10, 20) drives said MGB (2) mechanically to rotate a main outlet shaft (3) and, consequently, a main rotor (31) of said aircraft (30) at a frequency of rotation NR. A first engine group (10) has two main engines (11, 12) and is by a first setpoint NR* for said frequency of rotation NR, while a second engine group (20) has one secondary engine (21) and is regulated by a second setpoint W1* for power from said second engine group (20). The first engine group (10) is also regulated by a third setpoint W2f* for anticipating power such that said first engine group (10) and said second engine group (20) deliver the power needed at said main rotor (31).

摘要翻译： 具有两个发动机组（10,20）和主变速箱（MGB）（2）的发电厂（1）和具有这种动力装置（1）的旋翼机（30）。 每个发动机组（10,20）以机械方式驱动所述MGB（2），以使旋转频率NR旋转主出口轴（3），从而旋转所述飞机（30）的主转子（31）。 第一发动机组（10）具有两个主发动机（11,12），并且具有用于所述转速NR的第一设定点NR *，而第二发动机组（20）具有一个二次发动机（21）并由 来自所述第二发动机组（20）的功率的第二设定点W1 *。 第一发动机组（10）也由第三设定点W2f *调节以预测功率，使得所述第一发动机组（10）和所述第二发动机组（20）传递所述主转子（31）所需的功率。