Dynamic debugging and calibrating system of aero-engine telemetering system

Abstract

The invention provides a dynamic debugging calibration system of an aero-engine telemetering system. The dynamic debugging calibration system comprises an aero-engine rotation simulation device; the rotating shaft is driven by the aero-engine rotation simulation device to rotate at a specific rotating speed; the rotating shaft is provided with a first end and a second end; the aero-engine telemetering system is arranged at the first end of the rotating shaft and is driven by the rotating shaft to rotate at a specific rotating speed; the slip ring device is arranged at the second end of the rotating shaft and is driven by the rotating shaft to rotate at a specific rotating speed; the slip ring device is electrically connected with the aero-engine telemetering system; wherein the slip ring device accesses a standard test signal and transmits the standard test signal to the aero-engine telemetering system; the aero-engine telemetry system outputs telemetry signals. According to the invention, dynamic debugging and calibration of the aero-engine telemetering system can be realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero-engine test, in particular to a dynamic debugging and calibration system of aero-engine telemetry system. BACKGROUND

[0002] In the design and manufacture of aero-engine, the test of strain and temperature sensing of rotating parts is an important means to verify the safety performance of engine rotor, and in this process, a telemetry system is used as an intermediate signal transmission device. The strain refers to the local relative deformation of an object under the action of external force and non-uniform temperature field and other factors.

[0003] In order to obtain real measurement data in the test, the effectiveness and accuracy of the test signal transmission need to be evaluated, and the calibration of the telemetry system test equipment before the test is an important way to achieve the evaluation. In this case, how to realize the dynamic debugging and calibration of the aero-engine telemetry system is a problem to be solved. SUMMARY

[0004] The technical problem to be solved by the present application is to provide a dynamic debugging and calibration system of aero-engine telemetry system, to realize the dynamic debugging and calibration of aero-engine telemetry system, and to improve the integrity and effectiveness of the debugging and calibration process of aero-engine telemetry system.

[0005] To solve the above technical problem, the present application provides a dynamic debugging and calibration system of aero-engine telemetry system, comprising: an aero-engine rotating simulation device; a rotating shaft driven by the aero-engine rotating simulation device to rotate at a certain speed; the rotating shaft has a first end and a second end; an aero-engine telemetry system installed on the first end of the rotating shaft and driven by the rotating shaft to rotate at a certain speed; a slip ring device installed on the second end of the rotating shaft and driven by the rotating shaft to rotate at a certain speed; the slip ring device is electrically connected with the aero-engine telemetry system; wherein the slip ring device is connected with a standard test signal and transmitted to the aero-engine telemetry system; the aero-engine telemetry system outputs a telemetry signal.

[0006] In an embodiment of the present application, the aero-engine telemetry system comprises a telemetry rotor module and a telemetry stator module; the slip ring device comprises a brush ring and a brush wire electrically connected; the brush wire of the slip ring device is connected with a standard test signal; the brush ring of the slip ring device is connected with the telemetry rotor module.

[0007] In an embodiment of the present application, the aero-engine rotating simulation device comprises a motor device and a corresponding rotating output shaft; the rotating output shaft is in transmission connection with the rotating shaft.

[0008] In an embodiment of the present application, the rotating output shaft is connected to the rotating shaft through a gear box.

[0009] In an embodiment of the present application, a coupling is further arranged between the slip ring device and the second end of the rotating shaft to achieve elastic connection and synchronous rotation of the rotating shaft and the slip ring device.

[0010] In an embodiment of the present application, the dynamic debugging and calibration system of the aero-engine telemetry system further comprises an output calibration module connected to the aero-engine telemetry system; the output calibration module is configured to perform a telemetry system strain calibration operation and a telemetry system temperature calibration operation under different rotating speed conditions.

[0011] In an embodiment of the present application, the aero-engine telemetry system comprises a telemetry rotor module and a telemetry stator module; the output calibration module is connected to the telemetry rotor module; the telemetry stator module is configured to send the calibrated telemetry signal to a telemetry signal receiving end.

[0012] In an embodiment of the present application, the telemetry system strain calibration operation comprises a gain measurement error calibration operation, a dynamic strain linear error calibration operation and / or a frequency response consistency calibration operation.

[0013] The telemetry system temperature calibration operation comprises a temperature measurement error calibration operation.

[0014] In an embodiment of the present application, the telemetry rotor module comprises a first transmitting module corresponding to the telemetry system strain calibration operation and a second transmitting module corresponding to the telemetry system temperature calibration operation; the first transmitting module comprises a combined impedance R i and a trend impedance R Bias ; a second end of the combined impedance R i is connected to a second end of the trend impedance R Bias ; the trend impedance R Bias is used to pass an alternating current signal through a direct current path to stabilize the signal state.

[0015] In an embodiment of the present application, the output calibration module comprises a function signal generator U g and a test bridge resistance R1, a test bridge voltage dividing resistance R gage and a lead resistance R wire connected in sequence; a first end of the function signal generator U g is connected to a first end of the test bridge resistance R1; a second end of the function signal generator U g is connected to a second end of the trend impedance R Bias ; a second end of the combined impedance R ia second end of the test bridge resistance R1 and a first end of the test bridge voltage dividing resistance R gage a second end of the test bridge resistance R1.

[0016] In an embodiment of the present application, the output calibration module comprises a process verifier connected to the second transmitting module; the process verifier provides a reference temperature reference value; the telemetry rotor module further comprises a temperature compensation thermistor R connected to the second transmitting module to access a compensation current.

[0017] In an embodiment of the present application, the gain measurement error in the gain measurement error calibration operation is obtained by the following way:

[0018]

[0019] wherein Δε is the gain measurement error, U out1 is the potential peak value measured by the telemetry signal receiving end; ε is the theoretical gain, U g1 is the adjusting potential of the function signal generator. g

[0020] In an embodiment of the present application, the dynamic strain linear error in the dynamic strain linear error calibration operation is obtained by the following way:

[0021]

[0022] wherein ε L is the dynamic strain linear error, Δε is the gain measurement error; Δε = ε max - ε min , ε max is the maximum value of the gain measurement within the range, ε min is the minimum value of the gain measurement within the range.

[0023] In an embodiment of the present application, the frequency response error in the frequency response consistency calibration operation is obtained by the following way:

[0024]

[0025] wherein Δδ L is the frequency response error, ε' is the gain at each frequency response point, and ε0 is the gain corresponding to the dynamic strain measurement at the frequency of 1 KHz.

[0026] In an embodiment of the present application, the temperature measurement error in the temperature measurement error calibration operation is obtained by the following way:

[0027]

[0028] ​Wherein, Δt is temperature measurement error, U out2 is the direct current potential value measured by the telemetry signal receiving end; E is thermoelectric potential sensitivity, t in is the temperature value corresponding to the standard temperature analog signal accessed by the second transmitting module.

[0029] Compared with the prior art, the application has the following advantages: the technical solution of the application can simulate the dynamic transmission state corresponding to different working conditions of the telemetry system under ground conditions, and realize dynamic debugging and calibration of the aero-engine telemetry system under different rotating speed conditions. BRIEF DESCRIPTION OF DRAWINGS

[0030] The accompanying drawings are included to provide a further understanding of the application, and are incorporated in and constitute apart of this application, illustrate embodiments of the application, and together with the description serve to explain the principles of the application.

[0031] In the drawings:

[0032] Figure 1 is a dynamic debugging and calibration system composition schematic diagram of the aero-engine telemetry system of an embodiment of the application.

[0033] Figure 2 is a partial composition schematic diagram of the dynamic debugging and calibration system of the aero-engine telemetry system of an embodiment of the application.

[0034] Figure 3 is a composition schematic diagram of the aero-engine telemetry system of an embodiment of the application.

[0035] Figure 4 is a dynamic debugging and calibration principle schematic diagram of the aero-engine telemetry system of an embodiment of the application.

[0036] Figure 5 is a dynamic debugging and calibration principle schematic diagram of the aero-engine telemetry system of another embodiment of the application. DETAILED DESCRIPTION

[0037] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiment description. Obviously, the drawings in the following description are only some examples or embodiments of the application, and for those skilled in the art, the application can also be applied to other similar scenarios without creative labor. Unless it is obvious from the language environment or otherwise stated, the same reference numbers in the drawings represent the same structure or operation.

[0038] As used in this application and the appended claims, the singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise. Thus, for example, reference to "a" or "the" component can include more than one such component unless the context clearly indicates otherwise. Similarly, the terms "another" and "at least one" are used interchangeably, and include the meaning of one or more. As used herein, the term "includes" and / or "including" means including, but not limited to.

[0039] The relative arrangement of parts and steps, numerical expressions, and numerical values set forth in the examples are not intended to limit the scope of the present application unless specifically so stated. It is also to be understood that the dimensions of the various parts shown in the drawings are not necessarily to scale. Techniques, methods, and apparatus known to those of ordinary skill are not discussed in detail, but are to be considered part of the present application as described herein. In all examples shown and discussed herein, any specific values are to be interpreted as merely exemplary and not limiting. Thus, other examples of the exemplary embodiments can have different values. It is noted that like numbers and letters refer to like elements throughout the several views of the drawings and, as such, no further discussion with regard thereto is deemed necessary.

[0040] Embodiments of the present application describe a dynamic debug calibration system for an aircraft engine telemetry system.

[0041] Figure 1 is a schematic diagram of a dynamic debug calibration system for an aircraft engine telemetry system according to an embodiment of the present application. Figure 2 is a schematic diagram of a dynamic debug calibration system for an aircraft engine telemetry system according to an embodiment of the present application. Figure 3 is a schematic diagram of an aircraft engine telemetry system according to an embodiment of the present application.

[0042] Referring to Figures 1 to 3 , the dynamic debug calibration system 100 for the aircraft engine telemetry system 111 includes an aircraft engine rotation simulation device 101, a rotation shaft 110, the aircraft engine telemetry system 111, and a slip ring device 112. Figure 1 and Figure 2 The support base 150 is also shown in

[0043] The rotating shaft 110 is driven by the aero-engine rotating simulation device 101 to rotate at a specific rotating speed. The rotating shaft 110 has a first end and a second end. The aero-engine telemetry system 111 is installed on the first end of the rotating shaft 110 and is driven by the rotating shaft 110 to rotate at a specific rotating speed. The aero-engine rotating simulation device 101 can set the corresponding simulation rotating speed according to the rotating speed point required by the aero-engine for testing. The aero-engine rotating simulation device 101 in the scheme can also be in other forms, for example, realized by a gas turbine.

[0044] The slip ring device 112 is installed on the second end of the rotating shaft 110 and is driven by the rotating shaft 110 to rotate at a specific rotating speed. The slip ring device 112 is electrically connected with the aero-engine telemetry system 111. The slip ring device 112 can transmit signals for a rotating body. Specifically, the slip ring device 112 accesses the standard test signal and transmits it to the aero-engine telemetry system 111. The aero-engine telemetry system 111 outputs the telemetry signal.

[0045] The aero-engine telemetry system 111 includes a telemetry rotor module 301 and a telemetry stator module 302. The slip ring device 112 includes a brush ring and a brush wire electrically connected. The brush wire of the slip ring device 112 is connected with the standard test signal, which is accessed, for example, through the test signal input module 212. The brush ring of the slip ring device 112 is connected with the telemetry rotor module 301. The telemetry rotor module 301 and the telemetry stator module 302 output data, for example, through wireless communication.

[0046] In some embodiments, the aero-engine rotating simulation device 101 includes a motor device 102 and a corresponding rotating output shaft 103. The rotating output shaft 103 is in driving connection with the rotating shaft 110. In some embodiments, the rotating output shaft 103 is in driving connection with the rotating shaft 110 through a gear box 131.

[0047] In some embodiments, a shaft coupling 121 is further arranged between the slip ring device 112 and the second end of the rotating shaft 110 to realize the elastic connection and synchronous rotation of the rotating shaft 110 and the slip ring device 112. The brush ring and the brush wire of the slip ring device 112 can also be regarded as the rotor and the stator of the slip ring device 112. The brush ring can be sleeved with the rotating shaft 110. When the shaft coupling 121 is arranged between the slip ring device 112 and the second end of the rotating shaft 110, the brush ring can be sleeved with one end of the shaft coupling 110.

[0048] In some embodiments, the dynamic debugging and calibration system 100 of the aero-engine telemetry system 111 further includes an output calibration module 211. The output calibration module 211 is connected with the aero-engine telemetry system 111. The output calibration module 211 is configured to perform a telemetry system strain calibration operation and a telemetry system temperature calibration operation under different rotating speed conditions.

[0049] Figure 4 This is a schematic diagram illustrating the dynamic debugging and calibration principle of an aero-engine telemetry system according to an embodiment of this application. Figure 5 This is a schematic diagram illustrating the dynamic debugging and calibration principle of an aero-engine telemetry system according to another embodiment of this application.

[0050] refer to Figures 1 to 5 The aero-engine telemetry system 111 includes a telemetry rotor module 301 and a telemetry stator module 302. An output calibration module 211 is connected to the telemetry rotor module 301. The telemetry stator module 302 is configured to send calibrated telemetry signals to a telemetry signal receiver 403. Figure 4 and Figure 5 The 402 in the diagram indicates the signal transmission channel, specifically including the telemetry static module 302 transmitting the calibrated telemetry signal to the telemetry signal receiver 403 via wireless communication.

[0051] In some embodiments, the telemetry system strain calibration operation includes a gain measurement error calibration operation, a dynamic strain linearity error calibration operation, and / or a frequency response consistency calibration operation. The telemetry system temperature calibration operation includes a temperature measurement error calibration operation.

[0052] In some embodiments, the telemetry rotor module 301 includes a first transmitting module 401 corresponding to the telemetry system strain calibration operation and a second transmitting module 501 corresponding to the telemetry system temperature calibration operation.

[0053] The first transmitting module 401 includes a combined impedance R i and trend resistance R Bias Combined impedance R i The second end and the trend resistance R Bias The second end is connected. Trend impedance R Bias Used to pass AC signals through a DC path to stabilize the signal state. Output calibration module 211 includes a function signal generator U. g The test bridge resistor R1 and the test bridge voltage divider resistor R are connected in sequence. gage and lead resistance R wire Function signal generator U g The first terminal is connected to the first terminal of the test bridge resistor R1. Function signal generator U g The second end is connected to the trend impedance R Bias The second end. Combined impedance R i The first terminal is connected to the second terminal of the test bridge resistor R1 and the test bridge voltage divider resistor R. gage The first end.

[0054] In some embodiments, the output calibration module 211 comprises a process verifier connected to the second transmitting module 501. The process verifier provides a reference temperature reference value, for example, 0°C. The telemetry rotor module 301 further comprises a temperature compensation thermistor R connected to the second transmitting module 501 to access a compensation current.

[0055] In some embodiments, the gain measurement error in the gain measurement error calibration operation is obtained by:

[0056]

[0057] wherein Δε is the gain measurement error, U out1 is the potential peak value measured by the telemetry signal receiving end 403. ε is the theoretical gain, U g1 is the adjustment potential of the function signal generator U g .

[0058] In some embodiments, the dynamic strain linear error in the dynamic strain linear error calibration operation is obtained by:

[0059]

[0060] wherein ε L is the dynamic strain linear error, Δε is the gain measurement error. Δε = ε max - ε min , ε max is the maximum value of the gain measurement within the range, ε min is the minimum value of the gain measurement within the range.

[0061] In some embodiments, the frequency response error in the frequency response consistency calibration operation is obtained by:

[0062]

[0063] wherein Δδ L is the frequency response error, ε' is the gain at each frequency response point, and ε0 is the gain corresponding to the dynamic strain measurement at the frequency of 1 KHz.

[0064] In some embodiments, the temperature measurement error in the temperature measurement error calibration operation is obtained by:

[0065]

[0066] wherein Δt is the temperature measurement error, U out2 is the direct current potential value measured by the telemetry signal receiving end 403. E is the thermoelectric potential sensitivity, t inThe temperature value corresponding to the standard temperature analog signal accessed by the second transmitting module 501.

[0067] The dynamic debugging and calibration system for the aero-engine telemetry system in the application can simulate the dynamic transmission state corresponding to different working conditions of the telemetry system under ground conditions, and realize dynamic debugging and calibration of the aero-engine telemetry system under different rotating speed conditions. Compared with static calibration, the application scheme can improve the integrity and effectiveness of the debugging and calibration process of the aero-engine telemetry system.

[0068] The technical scheme of the application can simulate engine working conditions of different rotating speeds, and through different test channels of the transmitting module of the telemetry system, different gain gears (corresponding to different types of calibration operations) are preset, then standard test signals are input, and the signal after actual output gain is measured at the receiving end, so as to verify whether the actual signal processing process is consistent with the expected setting of the telemetry system.

[0069] The above has described the basic concept, and obviously, the above-mentioned invention disclosure is only taken as an example for the person skilled in the art, and does not constitute a limitation on the application. Although it is not explicitly stated here, the person skilled in the art can make various modifications, improvements and corrections to the application. Such modifications, improvements and corrections are suggested in the application, so such modifications, improvements and corrections still belong to the spirit and scope of the exemplary embodiments of the application.

[0070] At the same time, specific words are used in the application to describe the embodiments of the application. As "one embodiment", "an embodiment", and / or "some embodiments" means a certain feature, structure or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that the "an embodiment" or "one embodiment" or "an alternative embodiment" mentioned in different positions in the specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the application can be properly combined.

[0071] Some aspects of the application can be completely executed by hardware, completely executed by software (including firmware, resident software, microcode, etc.), or executed by a combination of hardware and software. The above hardware or software can be referred to as "data block", "module", "engine", "unit", "component" or "system". The processor can be one or more application specific integrated circuits (ASIC), digital signal processors (DSP), digital signal processing devices (DAPD), programmable logic devices (PLD), field programmable gate arrays (FPGA), processors, controllers, microcontrollers, microprocessors or combinations thereof.

[0072] It should be noted that the foregoing description of the embodiments of the application has been presented for the purposes of illustration and description. It is not intended to be exhaustive or to limit the application to the precise form disclosed. Many modifications and variations are possible in light of the above teaching. It is intended that the scope of the application be limited not with this detailed description, but rather by the claims appended hereto.

[0073] While the application has been described with reference to the currently preferred embodiments, those skilled in the art will recognize various changes in form and equivalent substitutions without departing from the spirit of the application. Accordingly, the application is not limited to the embodiments described above, but rather the scope of the application is to be accorded the complete range of equivalents possible to the description and drawings thereof.

Claims

1. A dynamic debugging and calibration system of an aero-engine telemetry system, comprising: an aero-engine rotation simulation device; a rotation shaft driven by the aero-engine rotation simulation device to rotate at a specific speed; the rotation shaft having a first end and a second end; an aero-engine telemetry system installed at the first end of the rotation shaft and driven by the rotation shaft to rotate at a specific speed; a slip ring device installed at the second end of the rotation shaft and driven by the rotation shaft to rotate at a specific speed; the slip ring device is electrically connected with the aero-engine telemetry system; wherein the slip ring device is connected with a standard test signal and transmits the standard test signal to the aero-engine telemetry system; the aero-engine telemetry system outputs a telemetry signal.

2. The dynamic debug calibration system for an aeroengine telemetry system of claim 1, wherein, the aero-engine telemetry system comprises a telemetry rotor module and a telemetry stator module; the slip ring device comprises a brush ring and a brush wire electrically connected; the brush wire of the slip ring device is connected with a standard test signal; the brush ring of the slip ring device is connected with the telemetry rotor module.

3. The dynamic debug calibration system for an aeroengine telemetry system of claim 1, wherein, the aero-engine rotation simulation device comprises a motor device and a corresponding rotating output shaft; the rotating output shaft is in transmission connection with the rotation shaft.

4. The dynamic debug calibration system for an aeroengine telemetry system of claim 3, wherein, the rotating output shaft is in transmission connection with the rotation shaft through a gear box.

5. The dynamic debug calibration system for an aeroengine telemetry system of claim 1, wherein, a coupling is further arranged between the slip ring device and the second end of the rotation shaft to realize the elastic connection and synchronous rotation of the rotation shaft and the slip ring device.

6. The dynamic debug calibration system for an aeroengine telemetry system of claim 1, wherein, an output calibration module is further included, which is connected with the aero-engine telemetry system; the output calibration module is configured to perform a telemetry system strain calibration operation and a telemetry system temperature calibration operation under different rotation speed conditions.

7. The dynamic debug calibration system for an aeroengine telemetry system of claim 6, wherein, the aero-engine telemetry system comprises a telemetry rotor module and a telemetry stator module; the output calibration module is connected with the telemetry rotor module; the telemetry stator module is configured to send the calibrated telemetry signal to a telemetry signal receiving end.

8. The dynamic debug calibration system for an aeroengine telemetry system of claim 6, wherein, the telemetry system strain calibration operation comprises a gain measurement error calibration operation, a dynamic strain linear error calibration operation and / or a frequency response consistency calibration operation; the telemetry system temperature calibration operation comprises a temperature measurement error calibration operation.

9. The dynamic debug calibration system for an aeroengine telemetry system of claim 8, wherein, the telemetry rotor module comprises a first transmitting module corresponding to the telemetry system strain calibration operation and a second transmitting module corresponding to the telemetry system temperature calibration operation; The first transmitting module comprises a combined impedance R i and a trend impedance R Bias ; a second end of the combined impedance R i is connected with a second end of the trend impedance R Bias ; and the trend impedance R Bias is used for passing an alternating current signal through a direct current path to stabilize a signal state.

10. The dynamic debug calibration system for an aeroengine telemetry system of claim 9, wherein, The output calibration module comprises a function signal generator U g and a test bridge resistance R1, a test bridge voltage dividing resistance R gage and a lead resistance R wire ; the function signal generator U g is connected to a first end of the test bridge resistance R1; the function signal generator U g is connected to a second end of the trend impedance R Bias is connected to a second end of the test bridge resistance R1. The combination impedance R i The first end of the test bridge voltage divider resistance R gage The first end of the test bridge voltage divider resistance R 11. The dynamic debug calibration system for an aeroengine telemetry system of claim 9, wherein, the output calibration module comprises a process verifier connected to the second transmitting module; the process verifier provides a reference temperature reference value; the telemetry rotor module further comprises a temperature compensation thermistor R connected to the second transmitting module to access a compensation current.

12. The dynamic debug calibration system of an aeroengine telemetry system of claim 10, wherein, the gain measurement error in the gain measurement error calibration operation is obtained by the following way: wherein Δε is the gain measurement error, U out1 is the potential peak measured at the telemetry signal receiving end; ε is the theoretical gain, U g1 is the regulating potential of the function signal generator U g is the regulating potential of the function signal generator U 13. The dynamic debug calibration system for an aeroengine telemetry system of claim 12, wherein, the dynamic strain linear error in the dynamic strain linear error calibration operation is obtained by the following way: where ε L is the dynamic strain linear error, Δε is the gain measurement error; Δε = ε max - ε min , ε max is the maximum value of the gain measurement within the range, ε min is the minimum value of the gain measurement within the range.

14. The dynamic debug calibration system of an aeroengine telemetry system of claim 13, wherein, the frequency response error in the frequency response consistency calibration operation is obtained by the following way: where Δδ L is the frequency response error, ε' is the gain at each frequency response point, and ε0is the gain corresponding to the dynamic strain measurement at frequency 1 kHz.

15. The dynamic debug calibration system of an aeroengine telemetry system of claim 11, wherein, the temperature measurement error in the temperature measurement error calibration operation is obtained by the following way: Wherein, Δt is the temperature measurement error, U out2 is the direct current potential value measured by the telemetry signal receiving end; E is the thermoelectric potential sensitivity, t in is the temperature value corresponding to the standard temperature analog signal accessed by the second transmitting module.

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