초록
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Helicopters and rotary wing aircraft vibration control system for controlling rotating machinery vibrations are provided for rotating machinery vibrations correlating with operational rotating frequencies. The vibration control system includes a first imbalance rotor with a first mass concentration, the first imbalance rotor driven to rotate with a first controllable phase, a second imbalance rotor with a second mass concentration, the second imbalance rotor driven to rotate with a second controllable phase, a third imbalance rotor with a third mass conc...
Helicopters and rotary wing aircraft vibration control system for controlling rotating machinery vibrations are provided for rotating machinery vibrations correlating with operational rotating frequencies. The vibration control system includes a first imbalance rotor with a first mass concentration, the first imbalance rotor driven to rotate with a first controllable phase, a second imbalance rotor with a second mass concentration, the second imbalance rotor driven to rotate with a second controllable phase, a third imbalance rotor with a third mass concentration, the third imbalance rotor driven to rotate with a third controllable phase, a fourth imbalance rotor with a fourth mass concentration, the fourth imbalance rotor driven to rotate with a fourth controllable phase. The vibration control system includes vibration sensors for monitoring the vibration and outputting vibration signals. The vibration control system includes a controller, the controller receiving an operational rotating frequency reference signal, the controller also receiving the vibration sensor signals with the controller controlling the first imbalance rotor first controllable phase, the second imbalance rotor second controllable phase, the third imbalance rotor third controllable phase, and the fourth imbalance rotor fourth controllable phase relative to the rotating frequency reference signal to produce a biaxial force which reduces the vibration signals outputted from the vibration sensors.
대표
청구항
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1. A rotary wing aircraft, having an aircraft body interior cabin space supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency, said rotary wing aircraft having a persistent operational rotating frequency vibration, said rotary wing aircraft including: an operational rotating frequency reference sensor, said operational rotating frequency reference sensor outputting a rotating frequency signal indicative of the rotary wing system operational rotating frequency,a first imbalance rotor havi...
1. A rotary wing aircraft, having an aircraft body interior cabin space supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency, said rotary wing aircraft having a persistent operational rotating frequency vibration, said rotary wing aircraft including: an operational rotating frequency reference sensor, said operational rotating frequency reference sensor outputting a rotating frequency signal indicative of the rotary wing system operational rotating frequency,a first imbalance rotor having a first mass concentration, said first imbalance rotor driven to rotate with a first controllable phase (φ_1_1),a second imbalance rotor having a second mass concentration, said second imbalance rotor driven to rotate with a second controllable phase (φ_1_2),a third imbalance rotor having a third mass concentration, said third imbalance rotor driven to rotate with a third controllable phase (φ_1_3),a fourth imbalance rotor having a fourth mass concentration, said fourth imbalance rotor driven to rotate with a fourth controllable phase (φ_1_4),a plurality of vibration sensors for monitoring said vibration and outputting vibration signals,a system controller, said system controller receiving said outputted rotating frequency signal, said system controller also receiving said vibration sensor signals wherein said system controller independently and automatically controls each of said first imbalance rotor first controllable phase (φ_1_1), said second imbalance rotor second controllable phase (φ_1_2), said third imbalance rotor third controllable phase (φ_1_3), and said fourth imbalance rotor fourth controllable phase (φ_1_4), relative to said rotating frequency reference signal with said first phase (φ_1_1), said second phase (φ_1_2), said third phase (φ_1_3), and said fourth phase(φ_1_4) not in a fixed phase relationship to produce a first biaxial force and a moment which reduces the vibration signals outputted from said vibration sensors. 2. A rotary wing aircraft as claimed in claim 1, having an aircraft body structure between said body interior cabin space, said exterior space and said rotary wing system rotating with said operational rotating frequency, said first imbalance rotor, and said second imbalance rotor mounted to said aircraft body structure as a first co-rotating coaxial pair with said first imbalance rotor electromagnetically motor driven at a first rotational clockwise rotational direction to rotate with the first controllable phase (φ_1_1) and said second imbalance rotor electromagnetically motor driven at a second rotational clockwise rotational direction to rotate with the second controllable phase (φ_1_2) , said third imbalance rotor, and said fourth imbalance rotor are mounted to said aircraft body structure as a second co-rotating coaxial pair with said third imbalance rotor electromagnetically motor driven at a third rotational counter clockwise rotational direction to rotate with the third controllable phase (φ_1_3) and said fourth imbalance rotor electromagnetically motor driven at a fourth rotational counter clockwise rotational direction to rotate with the fourth controllable phase (φ_1_4), wherein said first biaxial force and said moment are inputted into said rotary wing aircraft through said aircraft body structure. 3. A rotary wing aircraft as claimed in claim 2, including a fifth imbalance rotor having a fifth mass concentration, a sixth imbalance rotor having a sixth mass concentration, said fifth imbalance rotor and said sixth imbalance rotor mounted to said aircraft body structure as a third co-rotating coaxial pair, said fifth imbalance rotor electromagnetically motor driven at a fifth rotational clockwise rotational direction to rotate with a fifth controllable phase (φ_2_1) and said sixth imbalance rotor electromagnetically motor driven at a sixth rotational clockwise rotational direction to rotate with the sixth controllable phase (φ_2_2) ,a seventh imbalance rotor having a seventh mass concentration,an eighth imbalance rotor having a eighth mass concentration, said seventh imbalance rotor and said eighth imbalance rotor mounted to said aircraft body structure as a fourth co-rotating coaxial pair with said seventh imbalance rotor electromagnetically motor driven at a seventh rotational counter clockwise rotational direction to rotate with the seventh controllable phase (φ_2_3) and said eighth imbalance rotor electromagnetically motor driven at a eighth rotational counter clockwise rotational direction to rotate with the eighth controllable phase (φ_2_4),wherein said fifth imbalance rotor, said sixth imbalance rotor, said seventh imbalance rotor, and said eighth imbalance rotor are mounted to said aircraft body structure at a second location and orientation relative to said mounted first imbalance rotor, said mounted second imbalance rotor, said mounted third imbalance rotor, and said mounted fourth imbalance rotor,wherein said fifth imbalance rotor fifth controllable phase (φ_2_1), said sixth imbalance rotor sixth controllable phase (φ_2_2), said seventh imbalance rotor seventh controllable phase(φ_2_3), and said eighth imbalance rotor eight controllable phase (φ_2_4) are independently controlled relative to said rotating frequency reference signal in a non-fixed phase relationship to one another to produce a second biaxial force at a distal second vibration control system actuator mounting location which reduces the vibration signals outputted from said vibration sensors. 4. A rotary wing aircraft, having an aircraft body interior cabin space supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency, said rotary wing aircraft having a persistent operational rotating frequency vibration, said rotary wing aircraft including: an operational rotating frequency reference sensor, said operational rotating frequency reference sensor outputting a rotating frequency signal indicative of the rotary wing system operational rotating frequency;a first imbalance rotor having a first mass concentration, said first imbalance rotor driven to rotate with a first controllable phase (φ_1_1);a second imbalance rotor having a second mass concentration, said second imbalance rotor driven to rotate with a second controllable phase (φ_1_2);a third imbalance rotor having a third mass concentration, said third imbalance rotor driven to rotate with a third controllable phase (φ_1_3);a fourth imbalance rotor having a fourth mass concentration, said fourth imbalance rotor driven to rotate with a fourth controllable phase (φ_1_4);a plurality of vibration sensors for monitoring said vibration and outputting vibration signals, said vibration sensors being accelerometers; anda system controller, said system controller receiving said outputted rotating frequency signal, said system controller also receiving said vibration sensor signals wherein said system controller independently controls said first imbalance rotor first controllable phase (φ_1_1), said second imbalance rotor second controllable phase (φ_1_2), said third imbalance rotor third controllable phase (φ_1_3), and said fourth imbalance rotor fourth controllable phase (φ_1_4), relative to said rotating frequency reference signal with said first phase (φ_1_1), said second phase (φ_1_2), said third phase (φ_1_3), and said fourth phase(φ_1_4) not in a fixed phase relationship to produce a first biaxial force and a moment which reduces the vibration signals outputted from said vibration sensors. 5. A rotary wing aircraft vibration control system comprising: a rotary wing aircraft having an aircraft body interior cabin space supported by a rotary wing system rotating with an operational rotating frequency;a persistent operational rotating frequency vibration associated with the rotary wing aircraft;an operational rotating frequency reference sensor, the operational rotating frequency reference sensor producing a rotating frequency signal indicative of the operational rotating frequency;a first imbalance rotor having a first mass concentration and, the first imbalance rotor driven to rotate with a first controllable phase (φ_1_1);a second imbalance rotor having a second mass concentration, the second imbalance rotor driven to rotate with a second controllable phase (φ_1_2);a third imbalance rotor having a third mass concentration, the third imbalance rotor driven to rotate with a third controllable phase (φ_1_3);a fourth imbalance rotor having a fourth mass concentration, the fourth imbalance rotor driven to rotate with a fourth controllable phase (φ_1_4);a plurality of vibration sensors for monitoring the operational rotating frequency vibration and producing vibration signals, said vibration sensors being accelerometers,a system controller receiving the rotating frequency signal, the system controller also receiving the vibration signals; andwherein said system controller independently and separately controls each of the first imbalance rotor first controllable phase (φ_1_1), the second imbalance rotor second controllable phase (φ_1_2), the third imbalance rotor third controllable phase (φ_1_3), and the fourth imbalance rotor fourth controllable phase (φ_1_4), wherein the control is relative to the rotating frequency signal with the first phase (φ_1_1), the second phase (φ_1_2), the third phase (φ_1_3), and the fourth phase(φ_1_4) not being in a fixed phase relationship relative to each other, thereby producing a first biaxial force and a moment, and reducing the vibration signals from the vibration sensors.
