Method and apparatus for monitoring aircraft components

• US 5,483,833 A
• Filed: 03/22/1994
• Issued: 01/16/1996
• Est. Priority Date: 03/22/1994
• Status: Expired due to Term

• Current Assignee: Martin Marietta Energy Systems, Inc. (Martin Marietta Corporation)
• Original Assignee: Martin Marietta Energy Systems, Inc. (Martin Marietta Corporation)
• Inventors: Ayers, Curtis W., Dickens, Larry M., Haynes, Howard D.
• Primary Examiner(s): Chilcot, Richard
• Assistant Examiner(s): NOORI, MAX H
• Application Number:
  US08/216,227
• Time in Patent Office: 665 Days
• Field of Search: 73/579, 73/583, 73/457, 73/462, 73/865.9, 73/2, 73/460, 73/459, 324/722
• US Class Current: 73/583
• CPC Class Codes: G01H 1/003 of rotating machines G01H1/10 takes precedence
• CPC Class Codes: G01M 15/12 by monitoring vibrations

Abstract

Operability of aircraft mechanical components is monitored by analyzing the voltage output of an electrical generator of the aircraft. Alternative generators, for a turbine-driven rotor aircraft, include the gas producer turbine tachometer generator, the power turbine tachometer generator, and the aircraft systems power producing starter/generator. Changes in the peak amplitudes of the fundamental frequency and its harmonics are correlated to changes in condition of the mechanical components.

Claims

1. An apparatus for monitoring an aircraft having a mechanical system and an electrical system, comprising:

means for obtaining an electrical signal from a component of the electrical system, the electrical signal varying in accordance with movement of at least one component of the mechanical system; and

means for correlating changes in the electrical signal to changes in condition of the at least one component,

wherein the electrical signal is a voltage signal, and wherein the means for producing the voltage signal comprises at least one of a gas producer turbine tachometer generator, a power turbine tachometer generator, a rotor tachometer generator, and an aircraft systems power producing starter/generator.

2. An apparatus according to claim 1, wherein the electrical signal is a voltage signal and wherein the correlating means includes means for producing a frequency-domain spectrum of the voltage signal during operation of the aircraft, the voltage signal exhibiting a fundamental frequency having a peak amplitude, and a plurality of harmonics, each having a peak amplitude.

3. An apparatus according to claim 2, wherein the correlating means includes means for determining a baseline fundamental frequency having a corresponding peak amplitude, means for monitoring the fundamental frequency and its corresponding peak amplitude during operation of the aircraft, and means for comparing the monitored peak amplitude to the baseline peak amplitude.

4. An apparatus according to claim 3, wherein the means for producing a voltage signal comprises an aircraft systems power producing starter/generator.

5. An apparatus according to claim 2, wherein the correlating means includes means for determining changes in the peak amplitudes of the harmonic frequencies relative to changes in the peak amplitude of the fundamental frequency.

6. An apparatus according to claim 2, wherein the correlating means includes means for determining changes in relative harmonic peak magnitude for at least the first several harmonics.

7. An apparatus according to claim 5, wherein the correlating means includes

means for determining a baseline fundamental frequency having a corresponding peak amplitude, and baseline harmonics, each having a corresponding peak amplitude,

means for monitoring, during operation of the aircraft, the fundamental frequency and its corresponding peak amplitude, and the harmonics, each having a corresponding peak amplitude,

means for normalizing the monitored and baseline fundamental and harmonic peak amplitudes, and

means for determining a ratio of the baseline normalized fundamental and harmonic peak amplitudes to the monitored normalized fundamental and harmonic peak amplitudes.

8. An apparatus according to claim 7, further comprising means for determining an average change in relative harmonic peak magnitudes for at least the first several harmonics.

9. An apparatus according to claim 1, wherein the correlating means comprises a computer.

10. An apparatus according to claim 8, further comprising a voltage splitter disposed between the computer and the means for producing a voltage signal.

11. An apparatus according to claim 1, wherein the electrical signal is a voltage signal, and wherein the apparatus further comprises signal conditioning means, disposed between the means for obtaining the voltage signal and the correlating means.

12. An apparatus according to claim 11, wherein the signal conditioning means comprises a high pass filter and an amplifier.

13. An apparatus according to claim 1, wherein the electrical signal is a voltage signal, and wherein the correlating means includes means for filtering the voltage signal, means for RMS-to-DC demodulating the filtered voltage signal, means for performing a fast Fourier transform (FFT) on the demodulated voltage signal, and means for comparing baseline specific frequency peaks to frequency peaks from the FFT.

14. An apparatus according to claim 1, wherein the electrical signal is a voltage signal, and wherein the correlating means includes means for performing a fast Fourier transform (FFT) on the voltage signal, means for performing digital mathematical frequency shifting on the FFT, and means for comparing baseline specific frequency peaks to frequency peaks from the mathematically frequency shifted FFT.

15. An apparatus according to claim 1, wherein the electrical signal is a voltage signal and wherein the correlating means includes means for RMS-to-DC demodulating the voltage signal, means for performing a fast Fourier transform (FFT) on the demodulated voltage signal, and means for comparing baseline specific frequency peaks to frequency peaks from the FFT.

16. A method for monitoring an aircraft having a mechanical system and an electrical system, comprising the steps of:

obtaining an electrical signal from a component of the electrical system, the electrical signal varying in accordance with movement of at least one component of the mechanical system; and

correlating changes in the electrical signal to changes in condition of the at least one component,

wherein the electrical signal is a voltage signal and wherein the correlating step includes producing a frequency-domain spectrum of the voltage signal during operation of the aircraft, the voltage signal exhibiting a fundamental frequency having a peak amplitude, and a plurality of harmonics, each having a peak amplitude, and

wherein the correlating step further includes determining a baseline fundamental frequency having a corresponding peak amplitude, monitoring the fundamental frequency and its corresponding peak amplitude during operation of the aircraft, and comparing the monitored peak amplitude to the baseline peak amplitude.

17. A method according to claim 16, wherein the step of producing a voltage signal comprises attaching a lead to an aircraft systems power producing starter/generator.

18. A method according to claim 16, wherein the correlating step includes determining changes in the peak amplitudes of the harmonic frequencies relative to changes in the peak amplitude of the fundamental frequency.

19. A method according to claim 16, wherein the correlating step includes determining changes in relative harmonic peak magnitude for at least the first several harmonics.

20. A method according to claim 19, wherein the correlating step includes

determining a baseline fundamental frequency having a corresponding peak amplitude, and baseline harmonics, each having a corresponding peak amplitude,

monitoring, during operation of the aircraft, the fundamental frequency and its corresponding peak amplitude, and the harmonics, each having a corresponding peak amplitude,

normalizing the monitored and baseline fundamental and harmonic peak amplitudes, and

determining a ratio of the baseline normalized fundamental and harmonic peak amplitudes to the monitored normalized fundamental and harmonic peak amplitudes.

21. A method for monitoring an aircraft mechanical system, comprising the steps of:

producing a voltage signal which varies in accordance with movement of at least one component of the mechanical system; and

correlating changes in the voltage signal to changes in condition of the at least one component,

wherein the step of producing a voltage signal comprises attaching a lead to at least one of a gas producer turbine tachometer generator, a power turbine tachometer generator, a rotor tachometer generator, and an aircraft systems power producing starter/generator.

22. An apparatus for monitoring an aircraft having a mechanical system and an electrical system, comprising:

means for obtaining an electrical signal from a component of the electrical system, the electrical signal varying in accordance with movement of at least one component of the mechanical system; and

means for correlating changes in the electrical signal to changes in condition of the at least one component,

wherein the correlating means includes means for producing a frequency-domain spectrum of a voltage signal during operation of the aircraft, the voltage signal exhibiting a fundamental frequency having a peak amplitude, and a plurality of harmonics, each having a peak amplitude, and

wherein the correlating means includes means for determining a baseline fundamental frequency having a corresponding peak amplitude, means for monitoring the fundamental frequency and its corresponding peak amplitude during operation of the aircraft, and means for comparing the monitored peak amplitude to the baseline peak amplitude.

23. An apparatus for monitoring an aircraft having a mechanical system and an electrical system, comprising:

means for obtaining an electrical signal from a component of the electrical system, the electrical signal varying in accordance with movement of at least one component of the mechanical system; and

means for correlating changes in the electrical signal to changes in condition of the at least one component,

wherein the correlating means includes means for producing a frequency-domain spectrum of voltage signal during operation of the aircraft, the voltage signal exhibiting a fundamental frequency having a peak amplitude, and a plurality of harmonics, each having a peak amplitude, and

wherein the correlating means includes means for determining changes in the peak amplitudes of the harmonic frequencies relative to changes in the peak amplitude of the fundamental frequency.

24. An apparatus for monitoring an aircraft having a mechanical system and an electrical system, comprising:

means for obtaining an electrical signal from a component of the electrical system, the electrical signal varying in accordance with movement of at least one component of the mechanical system; and

means for correlating changes in the electrical signal to changes in condition of the at least one component,

wherein the correlating means includes means for producing a frequency-domain spectrum of a voltage signal during operation of the aircraft, the voltage signal exhibiting a fundamental frequency having a peak amplitude, and a plurality of harmonics, each having a peak amplitude, and

wherein the correlating means includes means for determining changes in relative harmonic peak magnitude for at least the first several harmonics.

25. An apparatus for monitoring an aircraft having a mechanical system and an electrical system, comprising:

means for obtaining an electrical signal from a component of the electrical system, the electrical signal varying in accordance with movement of at least one component of the mechanical system;

means for correlating changes in the electrical signal to changes in condition of the at least one component,

wherein the electrical signal is a voltage signal; and

signal conditioning means disposed between the means for obtaining a voltage signal and the correlating means.

26. An apparatus for monitoring an aircraft having a mechanical system and an electrical system, comprising;

means for obtaining an electrical signal from a component of the electrical system, the electrical signal varying in accordance with movement of at least one component of the mechanical system;

means for correlating changes in the electrical signal to changes in condition of the at least one component,

wherein the electrical signal is a voltage signal, and

wherein the correlating means includes means for filtering the voltage signal, means for RMS-to-DC demodulating the filtered voltage signal, means for performing a fast Fourier transform (FFT) on the demodulated voltage signa, and means for comparing baseline specific frequency peaks to frequency peaks from the FFT.

27. An apparatus for monitoring an aircraft having a mechanical system and an electrical system, comprising;

means for obtaining an electrical signal from a component of the electrical system, the electrical signal varying in accordance with movement of at least one component of the mechanical system;

means for correlating changes in the electrical signal to changes in condition of the at least one component,

wherein the electrical signal is a voltage signal, and

wherein the correlating means includes means for performing a fast Fourier transform (FFT) on the voltage signal, means for performing digital mathematical frequency shifting on the FFT, and means for comparing baseline specific frequency peaks to frequency peaks from the mathematically frequency shifted FFT.

28. An apparatus for monitoring an aircraft having a mechanical system and an electrical system, comprising:

means for obtaining an electrical signal from a component of the electrical system, the electrical signal varying in accordance with movement of at least one component of the mechanical system;

means for correlating changes in the electrical signal to changes in condition of the at least one component,

wherein the electrical signal is a voltage signal, and

wherein the correlating means includes means for RMS-to-DC demodulating the voltage signal, means for performing a fast Fourier transform (FFT) on the demodulated voltage signal, and means for comparing baseline specific frequency peaks to frequency peaks from the FFT.