UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPPRESSION
First Claim
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1. A vibration control system for a rotorcraft, comprising:
- at least one of an integrated actuator and an intermediate actuator associated with a first source of vibration;
a sensor configured to sense vibration from the first source of vibration;
a dedicated actuator configured for association with a fuselage; and
a controller configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.
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Abstract
A vibration control system for a rotorcraft includes at least one of an integrated actuator and an intermediate actuator associated with a first source of vibration, a sensor configured to sense vibration from the first source of vibration, a dedicated actuator configured for association with a fuselage, and a controller configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.
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Citations
20 Claims
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1. A vibration control system for a rotorcraft, comprising:
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at least one of an integrated actuator and an intermediate actuator associated with a first source of vibration; a sensor configured to sense vibration from the first source of vibration; a dedicated actuator configured for association with a fuselage; and a controller configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A method, comprising:
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operating a first source of vibration of a rotorcraft; sensing vibration attributable to the first source of vibration; to reduce at least one of a vibration and an audible noise associated with a fuselage of the rotorcraft, operating a controller to receive the sensed vibration, control at least one of an integrated actuator associated with the first source of vibration and an intermediate actuator associated with the first source of vibration, and control at least one of (1) an integrated actuator associated with a second source of vibration and an intermediate actuator associated with the second source of vibration and (2) a dedicated actuator associated with a fuselage of the rotorcraft. - View Dependent Claims (9, 10, 11, 12, 13, 14, 15)
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16. A helicopter, comprising:
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a main rotor system; a fuselage; a pylon mount system connected between the main rotor system and the fuselage; at least two of an integrated actuator associated with the main rotor system, an intermediate actuator associated with the main rotor system, and a dedicated actuator associated with the fuselage; a sensor configured to sense vibration generated by the main rotor system; and a controller configured to receive information from the sensor and configured to control at least two of the integrated actuator associated with the main rotor system, the intermediate actuator associated with the main rotor system, and the dedicated actuator associated with the fuselage. - View Dependent Claims (17, 18, 19, 20)
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Specification