Vibration analyzer

• US 4,977,395 A
• Filed: 01/31/1989
• Issued: 12/11/1990
• Est. Priority Date: 01/31/1989
• Status: Expired due to Fees

• Current Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Original Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Inventors: Bozeman, Richard J. Jr.
• Primary Examiner(s): Orsino, Joseph A.
• Assistant Examiner(s): NOT, DEFINED
• Application Number:
  US07/304,154
• Time in Patent Office: 679 Days
• Field of Search: 340/683, 340/529, 73/660, 73/659, 73/658
• US Class Current: 340/683
• CPC Class Codes: G01H 1/00 Measuring characteristics of vibrations in solids by using direct conduction to the detector G01H9/00, G01H11/00 take precedence

Abstract

The invention relates to monitoring circuitry for the real time detection of vibrations of a predetermined frequency and which are greater than a predetermined magnitude. The circuitry produces an instability signal in response to such detection. The circuitry is particularly adapted for detecting instabilities in rocket thrusters, but may find application with other machines such as expensive rotating machinery, turbines, etc. The monitoring circuitry identifies when vibration signals are present having a predetermined frequency of a multi-frequency vibration signal which has an RMS energy level greater than a predetermined magnitude. It generates an instability signal only if such a vibration signal is identified. The circuitry includes a delay circuit which responds with an alarm signal only if the instability signal continues for a predetermined time period. When used with a rocket thruster, the alarm signal may be used to cut off the thruster if such thruster is being used in flight. If the circuitry is monitoring testing of the thruster, it generates signals to change the thruster operation, for example, from pulse mode to continuous firing to determine if the instability of the thruster is sustained once it has been detected.

Claims

1. Monitoring apparatus for detecting high magnitude vibration of a machine during its operation comprising

accelerometer means for generating a vibration signal representative of multi-frequency vibrations of said machine during its operation,

analog detecting circuit means responsive to said vibration signal for determining the presence of at lease on machine vibration of a predetermined frequency, when said vibration signal is greater than a predetermined magnitude and for producing a machine instability signal if such machine vibration is detected, and

high-pass filter means disposed between said accelerometer means and said detecting circuit means for substantially blocking vibration signals below a predetermined filter frequency thereby producing a filtered signal representative of vibrations characterized by frequencies above said filter frequency, wherein said detecting circuit means includes

magnitude level circuit means for adjusting the magnitude of said filtered signal to produce an adjusted magnitude filtered signal, and

phase locked loop means responsive to said adjusted magnitude filtered signal and enabled only if said adjusted magnitude filtered signal is greater than a predetermined root mean squared level of said filtered signal and for generating said machine instability signal only if said vibration of said predetermined frequency is present in said adjusted magnitude filtered signal.

2. Apparatus for detecting instability of a rocket thruster during firing comprising,

accelerometer means for generating a vibration signal representative of thruster vibrations during thruster firing,

analog detecting circuit means responsive to said vibration signal for detecting the presence of any one or more of a plurality of thruster instability vibrations, each of said vibrations characterized by a predetermined frequency when said vibration signal has a magnitude greater than a predetermined magnitude, and for generating a thruster instability signal if any one or said instability vibrations is detected,

delay circuit means responsive to said thruster instability signal for generating a delay signal if said thruster instability signal continues for a predetermined time period, wherein, said detecting circuit means includes

amplitude level circuit means for adjusting the magnitude of said filtered signal to produce an adjusted magnitude filtered signal, and

phase locked loop means responsive to said adjusted magnitude filtered signal and enabled only if said adjusted magnitude filtered signal is greater than a predetermined root mean squared level of said filtered signal and for generating said machine instability signal only if said vibration of said predetermined frequency is present in said adjusted magnitude filtered signal.

3. The apparatus of claim 2 wherein said thruster firing is operating in a pulsed mode in response to a pulse train signal, said apparatus further comprising,

means responsive to said delay signal for disabling said pulse train signal and replacing it with a continuous thruster firing signal for operating said thruster in a continuous mode.

4. The apparatus of claim 3 further comprising high-pass filter means disposed between said accelerometer means and said detecting circuit means for substantially blocking vibration signals frequencies below a filter frequency thereby producing a filtered signal representation of vibrations characterized by frequencies above said filter frequency.

5. The apparatus of claim 2 further comprising

means responsive to said delay signal for terminating firing of said rocket thruster.

6. Monitoring apparatus for detecting high magnitude vibration of a machine during its operation comprising,

accelerometer means for generating a vibration signal representative of multi-frequency vibrations of said machine during its operation,

analog circuit means responsive to said vibration signal for determining the presence of at least one machine vibration of a predetermined frequency, only when said vibration signal is greater than a predetermined magnitude and for producing a machine instability signal if such machine vibration is detected, and

additional circuit means responsive to said vibration signal for determining the presence of additional machine vibrations at each of additional predetermined frequencies only when said vibration signal is greater than predetermined magnitudes and for producing said machine instability signal if any one or more of said additional machine vibrations is detected.

7. Apparatus for detecting instability of a rocket thruster during firing comprising,

accelerometer means for generating a vibration signal representative of thruster vibrations during thruster firing,

analog detecting circuit means responsive to said vibration signal for detecting the presence of any one or more of a plurality of thruster instability vibrations, each of said vibrations characterized by a predetermined frequency when said vibration signal has a magnitude greater than a predetermined magnitude, and for generating a thruster instability signal if any one or said instability vibrations is detected, wherein said detecting circuit means includes

amplitude level circuit means for adjusting the magnitude of said filtered signal to produce an adjusted magnitude filtered signal, and

phase locked loop means responsive to said adjusted magnitude filtered signal and enabled only if said adjusted magnitude filtered signal is greater than a predetermined root mean squared level of said filtered signal and for generating said machine instability signal only if said vibration of said predetermined frequency is present in said adjusted magnitude filtered signal.

8. Monitoring apparatus for detecting high magnitude vibration of a machine during its operation comprising,

accelerometer means for generating a vibration signal representative of multi-frequency vibrations of said machine during its operation,

detecting circuit means responsive to said vibration signal for detecting the presence of at least one machine vibration of a predetermined frequency, when said vibration signal is greater than a predetermined magnitude and for producing a machine instability signal if such machine vibration is detected,

high pass filter means disposed between said accelerometer means and said detecting circuit means for substantially blocking vibration signals below a predetermined filter frequency thereby producing a filtered signal representative of vibrations characterized by frequencies above said filter frequency, wherein said detecting circuit means includes

amplitude level circuit means for adjusting the magnitude of said filtered signal to produce an adjusted magnitude filtered signal, and

phase locked loop means responsive to said adjusted magnitude filtered signal and enabled only if said adjusted magnitude filtered signal is greater than a predetermined root mean squared level of said filtered signal and for generating said machine instability signal only if said vibration of said predetermined frequency is present in said adjusted magnitude filtered signal.

9. The apparatus of claim 8 further comprising,

delay circuit means responsive to said machine instability signal for generating a delay signal if said machine instability signal continues being generated after a predetermined time period.

10. The apparatus of claim 8 wherein said machine is a rocket thruster and said machine instability signal is a rocket thruster instability signal.

11. The apparatus of claim 10 wherein said add machine operation is thruster firing in a pulsed mode in response to a pulse train signal, said apparatus further comprising,

means responsive to said delay signal for disabling said pulse train signal and replacing it with a continuous thruster firing signal for operating said thruster in a continuous mode.

12. The apparatus of claim 10 further comprising

means responsive to said delay signal for terminating firing of said rocket thruster.