公开(公告)号：EP0889315A3

公开(公告)日：1999-05-19

申请号：EP98112406.8

申请日：1998-07-03

申请人： FINMECCANICA S.p.A.

发明人： Maino, Bruno ,  Bellazzi, Alberto

IPC分类号： G01M13/02

CPC分类号： F16H57/00 ,  B64C27/14 ,  F16H61/12 ,  G01M13/02

摘要： The method includes the steps of: acquiring a signal ( s(t) ) from an acceleration sensor; calculating the Fourier transform ( F(h) ) in the frequency domain of the signal ( s(t) ) to obtain a sequence of samples; acquiring from the sequence of samples a set of samples including samples at the meshing frequency of the gears monitored by the sensor, and samples at the harmonic frequencies of the meshing frequency; calculating the energies associated with the set of samples and the signal; calculating a noise energy parameter ( MFP ) correlated to the ratio between the energy of the set of samples and the energy of the signal; comparing the noise energy parameter ( MFP ) with at least one predetermined threshold ( TH1 ); and generating an alarm signal in the event the noise energy parameter ( MFP ) exceeds the threshold value ( TH1 ).

摘要翻译： 该方法包括以下步骤：从加速度传感器获取信号（s（t））; 计算信号（s（t））的频域中的傅立叶变换（F（h））以获得采样序列; 从所述样本序列中获取一组样本，所述样本组包括所述传感器监测的所述齿轮的啮合频率下的样本，以及所述啮合频率的谐波频率下的样本; 计算与该组样本和该信号相关联的能量; 计算与该组样本的能量与该信号的能量之间的比率相关的噪声能量参数（MFP）; 将噪声能量参数（MFP）与至少一个预定阈值（TH1）进行比较; 并且在噪声能量参数（MFP）超过阈值（TH1）的情况下产生警报信号。

公开(公告)号：EP0889316A2

公开(公告)日：1999-01-07

申请号：EP98112408.4

申请日：1998-07-03

申请人： FINMECCANICA S.p.A.

发明人： Maino, Bruno ,  Bellazzi, Alberto

IPC分类号： G01M13/02

CPC分类号： B64C27/14 ,  F16H57/00 ,  G01M13/028

摘要： The method includes the steps of: acquiring a signal ( s(t) ) from an acceleration sensor; calculating the Hilbert transform (H[T' 1m (i)]) of the signal filtered and sampled beforehand; defining a complex signal ( C 1m (i) ) having the filtered and sampled signal ( T' 1m (i) ) as the real part and the Hilbert transform ( H[T' 1m (i)] ) of the filtered and sampled signal ( T' 1m (i) ) as the imaginary part; calculating a phase signal ( FC(i) ) given by the difference between the phase of the complex signal ( C 1m (i) ) and a reference phase ( P(i)+P 0 ); calculating the variance ( V ) of the phase signal ( FC(i) ); comparing the variance ( V ) with at least one predetermined threshold ( TH1 ); and generating an alarm signal if the variance ( V ) exceeds the threshold value ( TH1 ).

摘要翻译： 该方法包括以下步骤：从在加速度传感器获取的信号（S（t））的; 计算希尔伯特变换滤波和预先采样的信号的（HÄT'1m（I）U）; - 定义的复信号（C1米（ⅰ）），其具有滤波和采样信号（T'1m（I））作为实部和滤波和采样信号的希尔伯特变换（HÄT'1m（ⅰ）Ü）（T' 1米（I））作为虚部; 计算由复数信号（C1米（I））的相位之间的差给出的相位信号（FC（i））和一个参考相位（P（I）+ P0）; 计算相位信号（FC（I））的方差（V）; 方差（V）与至少一个预定阈值（TH1）进行比较; 和报警信号的生成如果方差（V）超过阈值（TH1）。

公开(公告)号：EP0899553A3

公开(公告)日：1999-04-14

申请号：EP98112407.6

申请日：1998-07-03

申请人： FINMECCANICA S.p.A.

发明人： Maino, Bruno ,  Bellazzi, Alberto

IPC分类号： G01M13/02 ,  G01H1/00

CPC分类号： G01M13/028 ,  G01H1/003

摘要： The monitoring method includes the steps of: acquiring a signal ( s(t) ) from an acceleration sensor associated with an epicyclic assembly; sampling the signal ( s(t) ) at a predetermined sampling frequency ( FS ) to obtain an initial sequence of samples ( T 1 (i) ); dividing the samples ( T 1 (i) ) in the initial sequence into groups, each defined by a predetermined number ( NJ ) of samples; acquiring predetermined groups of samples; filtering the acquired groups of samples to obtain an intermediate sequence of samples ( T f (i) ); processing the intermediate sequence of samples ( T f (i) ) to obtain a final sequence of samples ( ET J,K (i) ); calculating a sixth-order moment ( M6A ) of the final sequence of samples ( ET J,K (i) ); and comparing the sixth-order moment ( M6A ) with at least one predetermined threshold ( TH1 ) to detect any vibrational irregularity in the epicyclic assembly of the helicopter.

摘要翻译： 监视方法包括以下步骤：从与行星组件相关联的加速度传感器获取信号（s（t））; 以预定采样频率（FS）对信号（s（t））进行采样以获得初始采样序列（T1（i））; 将初始序列中的样本（T1（i））划分成组，每个组由预定数目（NJ）的样本限定; 获取预定的样本组; 对所获取的样本组进行过滤以获得中间样本序列（Tf（i））; 处理中间样本序列（Tf（i））以获得最终样本序列（ETJ，K（i））; 计算最终样本序列（ETJ，K（i））的六阶矩（M6A）; 以及将六阶矩（M6A）与至少一个预定阈值（TH1）进行比较以检测直升机的周转组件中的任何振动不规则性。

公开(公告)号：EP0899553A2

公开(公告)日：1999-03-03

申请号：EP98112407.6

申请日：1998-07-03

申请人： FINMECCANICA S.p.A.

发明人： Maino, Bruno ,  Bellazzi, Alberto

IPC分类号： G01M13/02 ,  G01H1/00

CPC分类号： G01M13/028 ,  G01H1/003

摘要： The monitoring method includes the steps of: acquiring a signal ( s(t) ) from an acceleration sensor associated with an epicyclic assembly; sampling the signal ( s(t) ) at a predetermined sampling frequency ( FS ) to obtain an initial sequence of samples ( T 1 (i) ); dividing the samples ( T 1 (i) ) in the initial sequence into groups, each defined by a predetermined number ( NJ ) of samples; acquiring predetermined groups of samples; filtering the acquired groups of samples to obtain an intermediate sequence of samples ( T f (i) ); processing the intermediate sequence of samples ( T f (i) ) to obtain a final sequence of samples ( ET J,K (i) ); calculating a sixth-order moment ( M6A ) of the final sequence of samples ( ET J,K (i) ); and comparing the sixth-order moment ( M6A ) with at least one predetermined threshold ( TH1 ) to detect any vibrational irregularity in the epicyclic assembly of the helicopter.

摘要翻译： 监视方法包括以下步骤：获取信号从在含有行星组件相关联的加速度传感器（S（t））的; 以预定的采样频率（FS）进行采样的信号（S（t）的），以获得在样品的初始序列（T 1（I））; 将所述样品（T 1（i））的初始序列分成组，每个组由样本的预定数目（新泽西州）所定义; 获取的样品的预定组; 过滤样品所获取的基团，以获得在样品（T F（i））的中间体序列; 处理样品的中间序列（T F（I）），以获得样品（ET J，K（I））的最终序列; 计算样品（ET J，K（I））的最终序列的六阶矩（M6A）; 和第六阶矩（M6A）与至少一个预定阈值（TH1）进行比较，以检测在所述直升机的行星组件的任何振动不规则性。

公开(公告)号：EP0889316A3

公开(公告)日：1999-05-19

申请号：EP98112408.4

申请日：1998-07-03

申请人： FINMECCANICA S.p.A.

发明人： Maino, Bruno ,  Bellazzi, Alberto

IPC分类号： G01M13/02

CPC分类号： B64C27/14 ,  F16H57/00 ,  G01M13/028

摘要： The method includes the steps of: acquiring a signal ( s(t) ) from an acceleration sensor; calculating the Hilbert transform (H[T' 1m (i)]) of the signal filtered and sampled beforehand; defining a complex signal ( C 1m (i) ) having the filtered and sampled signal ( T' 1m (i) ) as the real part and the Hilbert transform ( H[T' 1m (i)] ) of the filtered and sampled signal ( T' 1m (i) ) as the imaginary part; calculating a phase signal ( FC(i) ) given by the difference between the phase of the complex signal ( C 1m (i) ) and a reference phase ( P(i)+P 0 ); calculating the variance ( V ) of the phase signal ( FC(i) ); comparing the variance ( V ) with at least one predetermined threshold ( TH1 ); and generating an alarm signal if the variance ( V ) exceeds the threshold value ( TH1 ).

公开(公告)号：EP0889313A2

公开(公告)日：1999-01-07

申请号：EP98112392.0

申请日：1998-07-03

申请人： FINMECCANICA S.p.A.

发明人： Maino, Bruno ,  Bellazzi, Alberto

IPC分类号： G01M13/02

CPC分类号： G01M13/028 ,  B64C27/14 ,  F16H57/00

摘要： The monitoring method includes the steps of: acquiring a first signal ( s(t) ) from an acceleration sensor; calculating a transform in the frequency domain of the first signal ( s(t) ) to obtain an initial sequence of samples ( S 1 ), each of the samples having a respective amplitude and a respective frequency; processing the initial sequence of samples ( S 1 ) to obtain a final sequence of samples ( S 3 ); calculating a sixth-order moment ( M6A ) of the final sequence of samples ( S 3 ); and comparing the sixth-order moment ( M6A ) with at least one predetermined threshold ( TH1 ) to detect any vibrational irregularity in the helicopter transmission assembly.

摘要翻译： 监视方法包括以下步骤：在从加速度传感器获得的第一信号（S（t））的; 计算所述第一信号（S（t））的频域的变换，以获得在样品（S1）的初始序列，每一个都具有respectivement振幅和频率respectivement的样本; 处理样品的起始序列（S 1）以获得采样（S3）的最终序列; 计算样品（S3）的最终序列的六阶矩（M6A）; 和第六阶矩（M6A）与至少一个预定阈值（TH1）进行比较，以检测在所述直升机传动组件的任何振动不规则性。

公开(公告)号：EP0889314A3

公开(公告)日：1999-05-19

申请号：EP98112404.3

申请日：1998-07-03

申请人： FINMECCANICA S.p.A.

发明人： Maino, Bruno ,  Bellazzi, Alberto

IPC分类号： G01M13/02

CPC分类号： B64C27/14 ,  F16H57/00 ,  G01H1/003 ,  G01M13/028

摘要： The monitoring method includes the steps of: acquiring a signal ( s(t) ) from an acceleration sensor; calculating a transform in the frequency domain of the signal ( s(t) ) to obtain a sequence of samples; acquiring a sample ( F(2) ) in the sequence of samples; calculating an actual amplitude value ( C2 ) of the acquired sample ( F(2) ); calculating a relative deviation ( RC2 ) between the actual amplitude value ( C2 ) of the acquired sample ( F(2) ) and a reference amplitude value ( C2 ref ); and comparing the relative deviation ( RC2 ) with at least one predetermined threshold ( TH1 ) to immediately detect any irregularity in, and so prevent in-flight failure of, the helicopter transmission assembly.

摘要翻译： 该监视方法包括以下步骤：从加速度传感器获取信号（s（t））; 计算信号（s（t））的频域变换以获得样本序列; 获取样本序列中的样本（F（2））; 计算所获取的样本（F（2））的实际幅度值（C2）; 计算获取的采样（F（2））的实际幅度值（C2）与参考幅度值（C2ref）之间的相对偏差（RC2）; 并且将所述相对偏差（RC2）与至少一个预定阈值（TH1）进行比较以立即检测所述直升机变速器组件中的任何不规则性并且因此防止飞行中故障。

公开(公告)号：EP0889313A3

公开(公告)日：1999-05-19

申请号：EP98112392.0

申请日：1998-07-03

申请人： FINMECCANICA S.p.A.

发明人： Maino, Bruno ,  Bellazzi, Alberto

IPC分类号： G01M13/02

CPC分类号： G01M13/028 ,  B64C27/14 ,  F16H57/00

摘要： The monitoring method includes the steps of: acquiring a first signal ( s(t) ) from an acceleration sensor; calculating a transform in the frequency domain of the first signal ( s(t) ) to obtain an initial sequence of samples ( S 1 ), each of the samples having a respective amplitude and a respective frequency; processing the initial sequence of samples ( S 1 ) to obtain a final sequence of samples ( S 3 ); calculating a sixth-order moment ( M6A ) of the final sequence of samples ( S 3 ); and comparing the sixth-order moment ( M6A ) with at least one predetermined threshold ( TH1 ) to detect any vibrational irregularity in the helicopter transmission assembly.

摘要翻译： 该监测方法包括以下步骤：从加速度传感器获取第一信号（s（t））; 计算第一信号（s（t））的频域中的变换以获得样本的初始序列（S1），每个样本具有相应的幅度和相应的频率; 处理初始样本序列（S1）以获得最终样本序列（S3）; 计算最终样本序列（S3）的六阶矩（M6A）; 以及将六阶矩（M6A）与至少一个预定阈值（TH1）进行比较以检测直升机变速器组件中的任何振动不规则性。

公开(公告)号：EP0889315A2

公开(公告)日：1999-01-07

申请号：EP98112406.8

申请日：1998-07-03

申请人： FINMECCANICA S.p.A.

发明人： Maino, Bruno ,  Bellazzi, Alberto

IPC分类号： G01M13/02

CPC分类号： F16H57/00 ,  B64C27/14 ,  F16H61/12 ,  G01M13/02

摘要： The method includes the steps of: acquiring a signal ( s(t) ) from an acceleration sensor; calculating the Fourier transform ( F(h) ) in the frequency domain of the signal ( s(t) ) to obtain a sequence of samples; acquiring from the sequence of samples a set of samples including samples at the meshing frequency of the gears monitored by the sensor, and samples at the harmonic frequencies of the meshing frequency; calculating the energies associated with the set of samples and the signal; calculating a noise energy parameter ( MFP ) correlated to the ratio between the energy of the set of samples and the energy of the signal; comparing the noise energy parameter ( MFP ) with at least one predetermined threshold ( TH1 ); and generating an alarm signal in the event the noise energy parameter ( MFP ) exceeds the threshold value ( TH1 ).

摘要翻译： 该方法包括以下步骤：从在加速度传感器获取的信号（S（t））的; 计算傅立叶在信号（S（t））的以获得样本的序列的频域变换（F（H））; 从样本的序列的一组样品，包括在由所述传感器所监测的齿轮的啮合频率样本，并在啮合频率的谐波频率样本的获取; 计算与所述采样集合和所述信号相关联的能量; 计算相关于组样品和信号的能量的能量之间的比率的噪声能量参数（MFP）; 噪声能量参数（MFP）与至少一个预定阈值（TH1）进行比较; 和在该事件中的噪声能量参数（MFP）报警信号的产生超过阈值（TH1）。

公开(公告)号：EP0889314A2

公开(公告)日：1999-01-07

申请号：EP98112404.3

申请日：1998-07-03

申请人： FINMECCANICA S.p.A.

发明人： Maino, Bruno ,  Bellazzi, Alberto

IPC分类号： G01M13/02

CPC分类号： B64C27/14 ,  F16H57/00 ,  G01H1/003 ,  G01M13/028

摘要： The monitoring method includes the steps of: acquiring a signal ( s(t) ) from an acceleration sensor; calculating a transform in the frequency domain of the signal ( s(t) ) to obtain a sequence of samples; acquiring a sample ( F(2) ) in the sequence of samples; calculating an actual amplitude value ( C2 ) of the acquired sample ( F(2) ); calculating a relative deviation ( RC2 ) between the actual amplitude value ( C2 ) of the acquired sample ( F(2) ) and a reference amplitude value ( C2 ref ); and comparing the relative deviation ( RC2 ) with at least one predetermined threshold ( TH1 ) to immediately detect any irregularity in, and so prevent in-flight failure of, the helicopter transmission assembly.

摘要翻译： 监视方法包括以下步骤：在从加速度传感器获取的信号（S（t））的; 计算所述信号（S（t））的频域的变换以获得样本的序列; 获取样品（F（2））在样本序列; 实际振幅值的计算所获得的样品的（C2）（F（2））; 计算实际振幅值所获取的样品的（C2）之间的相对偏差（RC2）（F（2））和一个参考振幅值（C2ref）; 和相对偏差（RC2）与至少一个预定阈值（TH1）进行比较来立即检测任何不规则性，因此防止在飞行中发生故障时，直升机传动组件。