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公开(公告)号：US11203419B2
公开(公告)日：2021-12-21
申请号：US15962258
申请日：2018-04-25
申请人： AIRBUS HELICOPTERS
发明人： Setareh Taheri , Nicolas Certain
摘要： A regulator device for regulating a control setpoint for a speed of rotation, written NR, for at least one main rotor of a rotorcraft, the rotorcraft including at least one measurement member for taking measurements representative of a current vertical elevation of the rotorcraft relative to a reference level Ref; and measurement means serving to measure at least one vertical component of a travel speed of the rotorcraft relative to the air surrounding the rotorcraft, the regulator device for regulating the control setpoint of the speed including management means for automatically controlling the control setpoint for the speed in accordance with at least two predetermined control relationships that are distinct from each other.
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公开(公告)号：US09815561B2
公开(公告)日：2017-11-14
申请号：US15272898
申请日：2016-09-22
申请人： AIRBUS HELICOPTERS
摘要： A device for regulating the speed of rotation of at least one main rotor of a rotorcraft, which speed is known as the speed NR. Such a rotorcraft comprises at least one manual flight control member for delivering a collective pitch control setpoint C for the blades of the at least one main rotor, the control setpoint C being a function of a current position of the at least one control member; and detector means enabling a current state to be detected from at least two distinct states of the rotorcraft, namely a “ground” state in which the rotorcraft is in contact with the ground, at least in part, and a “flight” state in which the rotorcraft is at least being sustained in the air.
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3.发明授权Method of regulating the speed of rotation of the main rotor of a multi-engined rotorcraft in the event of one of the engines failing 有权在发动机发动机发生故障的情况下，调节多发旋翼航空器的主转子的旋转速度的方法公开(公告)号：US09463874B2
公开(公告)日：2016-10-11
申请号：US14788114
申请日：2015-06-30
申请人： AIRBUS HELICOPTERS
CPC分类号： B64C27/57 , B64C27/32 , G05D1/0072 , G05D1/0858
摘要： A method of regulating the speed of rotation of at least one main rotor of a multi-engined rotorcraft, which rotor is driven at variable speed. In the event of a failure of one of the main engines of the rotorcraft, a control unit generates an NR setpoint that is not less than the nominal drive speed (NRnom) of the main rotor. Thereafter, a calculator acts iteratively to determine a target speed (NRobj) for driving the main rotor to obtain stabilized lift of the rotorcraft by balancing between the torque developed by the main rotor and the rate of increase of its drive speed. The autopilot then causes the pitch of the blades of the main rotor to vary so as to obtain the iteratively calculated target speed (NRobj) until stabilized lift of the rotorcraft is obtained.
摘要翻译： 一种调节多发旋翼航空器的至少一个主转子的旋转速度的方法，该转子以可变速度驱动。 在旋翼航空器的主发动机之一发生故障的情况下，控制单元产生不小于主转子的额定驱动速度（NRnom）的NR设定点。 此后，计算器迭代地确定用于驱动主转子的目标速度（NRobj），以通过平衡由主转子产生的转矩和其驱动速度的增加速率来获得旋翼航空器的稳定升力。 自动驾驶仪然后使得主转子的叶片的桨距变化，以获得迭代计算的目标速度（NRobj），直到获得旋翼航空器的稳定升力。
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公开(公告)号：US09815568B2
公开(公告)日：2017-11-14
申请号：US15007298
申请日：2016-01-27
申请人： AIRBUS HELICOPTERS
摘要： A method of monitoring a power transmission system of an aircraft, the aircraft including at least one main rotor driven in rotation by a rotor mast and an auxiliary unit having an auxiliary rotor. Control means control the auxiliary rotor. A power relationship is determined providing a first reduced power parameter of the auxiliary unit as a function of a position (POS) of the control means. A setpoint limit is set for a second power parameter for the rotor mast. A current position (POSACTU) of the control means is determined and a calculated value (Vcal) is also determined at least by applying the current position (POSACTU) to the power relationship. A limit value that is not to be exceeded by a power plant is determined, with the limit value being equal to the sum at least of the setpoint limit plus the calculated value.
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公开(公告)号：US09676490B2
公开(公告)日：2017-06-13
申请号：US14948530
申请日：2015-11-23
申请人： AIRBUS HELICOPTERS
CPC分类号： B64D31/06 , F02C9/42 , F05D2220/329 , F05D2270/093
摘要： A method of assisting the piloting of a multi-engined rotorcraft in the event of an engine failure. A main rotor of the rotorcraft is driven at a variable NR speed under the control of a control unit. Calculation means identify an authorized margin of mechanical power usable by the pilot depending on a rating for regulating the operation of each of the engines under the control of a regulator unit. Outside an engine-failure situation, and providing the main rotor is being driven at a low NR speed, the mechanical power margin that is usable by the pilot and that is displayed on a screen, is in fact a limited margin of a value less than the authorized margin. Under such conditions, and in an engine-failure situation, the mechanical power reserve that is actually available enables the pilot to counter rapidly the sudden drop in the NR speed of rotation of the main rotor as induced by the engine failure.
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公开(公告)号：US10752342B2
公开(公告)日：2020-08-25
申请号：US15835575
申请日：2017-12-08
申请人： AIRBUS HELICOPTERS
发明人： Setareh Taheri , Nicolas Certain
摘要： A regulator device for regulating a speed of rotation, of a shaft of a gas generator of at least one turboshaft engine of a rotorcraft. The rotorcraft has at least one main rotor for regulating at least lift and/or propulsion for said rotorcraft in the air; a control member for controlling a collective pitch of the blades of said at least one main rotor, said control member serving to generate a control setpoint for said collective pitch; at least one turboshaft engine suitable for driving rotation of said at least one main rotor, said at least one engine producing, at least temporarily, a drive torque that is transmitted to said at least one main rotor; and measurement means for taking at each instant a measurement of said drive torque transmitted by said at least one engine to said at least one main rotor.
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7.发明授权公开(公告)号：US09409655B1
公开(公告)日：2016-08-09
申请号：US14607162
申请日：2015-01-28
申请人： AIRBUS HELICOPTERS
摘要： A flight instrument that displays the rotational speed of a main rotor of a rotary-wing aircraft, with the flight instrument including display means, a first indicator of a setpoint for the rotational speed of the main rotor, a second indicator of the first current value of the rotational speed of the main rotor, and third and fourth indicators of the limit values of the rotational speed. The setpoint for the rotational speed of the main rotor is variable and the first indicator is stationary on the display means, with the second, third and fourth indicators being movable in relation to the first indicator.
摘要翻译： 一种飞行仪器，其显示旋翼飞行器的主转子的旋转速度，飞行仪器包括显示装置，用于主转子的转速的设定点的第一指示器，第一电流值的第二指示器 的主转子的旋转速度，以及转速的极限值的第三和第四指示器。 主转子的旋转速度的设定值是可变的，并且第一指示器在显示装置上是静止的，其中第二，第三和第四指示器可相对于第一指示器移动。
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