Process and device for reducing the spectral line noise inside an aircraft, especially a rotating-wing aircraft, in particular a helicopter
First Claim
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1. A process for reducing the spectral line noise inside a rotating-wing aircraft, in particular a helicopter, according to which process the following operations are carried out repetitively and automatically:
- a) for each of I points Mi, i varying form 1 to I, situated on said rotating-wing aircraft, the value P2mi of a vibratory and/or acoustic parameter which exists at said point Mi is measured, said vibratory and/or acoustic parameter being representative of a vibratory and/or acoustic effect of at least one source of noise of said aircraft;
b) for each of said I points Mi, a value P1i corresponding to the relation;
is measured in real time, in which relation;
P2i is representative of the value P2mi measured in the absence of active control;
Tj,i is a value for transferring between the value of a vibratory and/or acoustic parameter existing at the level of a controllable mechanical element (A), and the corresponding value existing at said point Mi; and
P3j is a value of said vibratory and/or acoustic parameter, due to the action of said mechanical element (A) and dependent on the control of the latter; and
c) on the basis of the values P1i measured in real time for all the I points Mi, a sum S is calculated, satisfying the relation;
d) said sum S is minimized so as to deduce therefrom control commands for said mechanical elements (A); and
e) the control commands thus deduced are applied to said mechanical elements (A), wherein, repetitively and automatically, in a preliminary step, the value of at least one reference parameter which is correlated with the noise from said source of noise is measured and, on the basis of said measured value of the reference parameter, a reference signal is determined, and in step d), said sum S is minimized by carrying out filtering with respect to said reference signal determined in said preliminary step.
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Abstract
Process and device for reducing the spectral line noise inside an aircraft, especially a rotating-wing aircraft, in particular a helicopter.
Said device (1) comprises sensors (Ca, Cb) for measuring the values of vibratory and/or acoustic parameters, controllable mechanical elements (A) forming secondary sources of noise, and a main computer (CAL) determining, on the basis of the values measured by the sensors (Ca, Cb), control commands for the mechanical elements (A), as well as at least one reference sensor (CO) for measuring a reference parameter which is correlated with the noise, and possibly an auxiliary computer (4) for calculating, on the basis of the values measured by the reference sensor (CO), a reference signal, and said main computer (CAL) determines the control commands by carrying out filtering with respect to the reference signal.
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Citations
13 Claims
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1. A process for reducing the spectral line noise inside a rotating-wing aircraft, in particular a helicopter, according to which process the following operations are carried out repetitively and automatically:
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a) for each of I points Mi, i varying form 1 to I, situated on said rotating-wing aircraft, the value P2mi of a vibratory and/or acoustic parameter which exists at said point Mi is measured, said vibratory and/or acoustic parameter being representative of a vibratory and/or acoustic effect of at least one source of noise of said aircraft;
b) for each of said I points Mi, a value P1i corresponding to the relation;
is measured in real time, in which relation;
P2i is representative of the value P2mi measured in the absence of active control;
Tj,i is a value for transferring between the value of a vibratory and/or acoustic parameter existing at the level of a controllable mechanical element (A), and the corresponding value existing at said point Mi; and
P3j is a value of said vibratory and/or acoustic parameter, due to the action of said mechanical element (A) and dependent on the control of the latter; and
c) on the basis of the values P1i measured in real time for all the I points Mi, a sum S is calculated, satisfying the relation;
d) said sum S is minimized so as to deduce therefrom control commands for said mechanical elements (A); and
e) the control commands thus deduced are applied to said mechanical elements (A), wherein, repetitively and automatically, in a preliminary step, the value of at least one reference parameter which is correlated with the noise from said source of noise is measured and, on the basis of said measured value of the reference parameter, a reference signal is determined, and in step d), said sum S is minimized by carrying out filtering with respect to said reference signal determined in said preliminary step. - View Dependent Claims (2, 3, 4, 5, 6)
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7. A device for reducing the spectral line noise inside a rotating-wing aircraft, especially a helicopter, said device (1) comprising:
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sensors (Ca, Cb) for measuring the values of vibratory and/or acoustic parameters representative of at least one vibratory and/or acoustic effect of at least one primary source of noise of said rotating-wing aircraft;
at least one reference sensor (CO) for measuring the values of at least one reference parameter which is correlated with the noise of said rotating-wing aircraft;
controllable mechanical elements (A) forming secondary sources of noise which are able to create, under the effect of control commands, loadings which are capable of reducing the vibratory and/or acoustic effect of said primary source of noise; and
a main computer (CAL) determining, on the basis of the values measured by said sensors (Ca, Cb) and said reference sensor (CO), control commands for said mechanical elements (A), with a view to reducing the spectral line noise inside said aircraft, wherein said main computer (CAL) determines said control commands by calculating a sum S satisfying the relation;
on the basis of I values P1i measured by said sensors (Ca, Cb) and by minimizing said sum S by means of filtering with respect to a reference signal which depends on the measured values of said reference parameter. - View Dependent Claims (8, 9, 10, 11, 12, 13)
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Specification
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Current AssigneeAirbus Helicopters
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Original AssigneeEurocopter
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InventorsDussac, Marc
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Granted Patent
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Time in Patent OfficeDays
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Field of Search
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US Class Current702/56
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CPC Class CodesG10K 11/17854 the filter being an adaptiv...G10K 11/17857 Geometric disposition, e.g....G10K 11/17879 using both a reference sign...
