초록 ▼

An Active Structural Control (ASC) system (10) and method which includes a plurality of Active Vibration Absorbers (AVAs) (40) attached to a yoke (32) included within a pylon structure (28) preferably comprising a spar (38) and a yoke (32) which is located intermediate between an aircraft fuselage (

An Active Structural Control (ASC) system (10) and method which includes a plurality of Active Vibration Absorbers (AVAs) (40) attached to a yoke (32) included within a pylon structure (28) preferably comprising a spar (38) and a yoke (32) which is located intermediate between an aircraft fuselage (20) and an aircraft engine (18) for controlling acoustic noise and/or vibration generated within the aircraft's cabin (44) due to unbalances in the aircraft engine (18). The ASC system (10) includes a plurality of error sensors (42) for providing error signals, and at least one reference sensor (49 or 50) for providing reference signals indicative of the N1 and/or N2 engine rotations and/or vibrations, and a preferably digital electronic controller (46) for processing the error and reference signal information to provide output signals to drive the plurality of AVAs (40) attached to the yoke (32). The AVAs (40) preferably act in a radial, tangential, or fore and aft directions and may be preferably located at the terminal end and/or at the base portion of the yoke (32). Further, the AVAs (40) may be Single Degree Of Freedom (SDOF) or Multiple Degree Of Freedom (MDOF) and may be tuned to have a passive resonance which substantially coincides with the N1 and/or N2 engine rotation and/or vibrations. In another aspect, reference signal processing is described which includes a modulo counter, a lookup table, and a digital IO.

대표청구항 ▼

[ What is claimed is:] [1.] An Active Structural Control (ASC) system for controlling acoustic noise and/or vibration generated within an aircraft cabin that results from vibration generated by at least one engine attached to a pylon structure by mounts, said vibration being transmitted into said py

[ What is claimed is:] [1.] An Active Structural Control (ASC) system for controlling acoustic noise and/or vibration generated within an aircraft cabin that results from vibration generated by at least one engine attached to a pylon structure by mounts, said vibration being transmitted into said pylon structure which attaches between said at least one engine and an aircraft fuselage, said pylon structure preferably including a yoke and a spar, and causes vibration of said aircraft fuselage, thereby generating said acoustic noise and/or vibration within said aircraft cabin, said ASC system comprising:(a) a plurality of error sensors for providing a plurality of error signals,(b) at least one reference sensor associated with said at least one engine for providing at least one reference signal selected from a group consisting of:(i) a first reference signal indicative of an N1 engine rotation, and(ii) a second reference signal indicative of an N2 engine rotation,(c) a plurality of Active Vibration Absorbers (AVAs) attached to said yoke at positions other thanthrough said mounts, wherein said plurality of active vibration absorbers are further comprised of:a Single Degree Of Freedom (SDOF) AVA located at at least one of a first and a second terminal end portion of said yoke and which is tuned to exhibit a resonant frequency which substantially coincides with an N2 engine rotation frequency and which acts in a substantially radial direction, andat least four Single Degree Of Freedom (SDOF) AVAs located on said yoke at a base portion thereof where said yoke connects to said spar wherein at least one of said at least four SDOF AVAs is tuned such that it exhibits a natural frequency which substantially coincides with an N1 engine rotation frequency; and(d) a controller for processing said at least one selected from said group consisting of said first reference signal and said second reference signal and said plurality of error signals and providing a plurality of output signals to said plurality of AVAs to effectuate vibration of said yoke and resultantly control acoustic noise within said aircraft cabin.