CN105716890A - Airplane temperature compensator test system and test method - Google Patents
Airplane temperature compensator test system and test method Download PDFInfo
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- CN105716890A CN105716890A CN201511034037.7A CN201511034037A CN105716890A CN 105716890 A CN105716890 A CN 105716890A CN 201511034037 A CN201511034037 A CN 201511034037A CN 105716890 A CN105716890 A CN 105716890A
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention provides an airplane temperature compensator test system and test method. A temperature compensator comprises a push rod. The system comprises a temperature control module, a sensor group, a data processing module and a pressure block, wherein the temperature control module sets different temperatures and is used for simulating a work environment of the temperature compensator at an airplane engine servo apparatus; the sensor group is used for detecting temperature change of the work environment, detecting displacement of the push rod and pressure change of the pressure block, and outputting sensor signals; and the data processing module receives the sensor signals, performs analysis processing on the sensor signals and outputs a performance analysis result of the temperature compensator. According to the invention, the work environment of the temperature sensor is simulated through an automation mode, and sensors are taken as data acquisition devices, performance is analyzed based on data output by the sensors, and a performance analysis structure is obtained finally, the performance of the temperature compensator is automatically detected, the operation is simple, and the detection efficiency is high.
Description
Technical field
The present invention relates to technical field of aerospace, particularly relate to temperature compensator test system and the method for testing of a kind of aircraft.
Background technology
Aircraft fuel oil servosystem humidity control system is the important component part of modern fuel servo system, and the good and bad direct relation of its service behaviour the safety of whole airplane.In use whether the service behaviour of temperature compensator reaches technology requirement, it is necessary to carry out product quality detection.In correlation technique, the detection of temperature compensator adopts water bath heating heating-up temperature compensator mostly, push rod stroke again through displacement sensor temperature compensator, but the temperature of this measuring method controls accurate not, cause that the thrust measurement that push rod is produced is not accurate enough, it is impossible to truly reflect product quality.Additionally, the method for testing in correlation technique, complicated operation, repeatability is low, detection efficiency is low.
Summary of the invention
In view of this, the present invention provides temperature compensator test system and the method for testing of a kind of aircraft, it is achieved the performance of Aulomatizeted Detect temperature compensator, simple to operate, detection efficiency is high.
Specifically, the present invention is achieved through the following technical solutions:
According to an aspect of the present invention, the temperature compensator test system of a kind of aircraft is provided, described temperature compensator includes push rod, described system includes temperature control modules, sensor group, data processing module and pressure block, wherein, described temperature control modules is set with different temperature, for simulating the described temperature compensator working environment at described aircraft engine servomechanism installation；Described sensor group is for detecting the variations in temperature of described working environment, and detects the displacement of described push rod and the pressure change of described pressure block output sensor signal；Described data processing module receives described sensor signal, is analyzed described sensor signal processing, exports the results of performance analysis of described temperature compensator.
Exemplarily, described system also includes data acquisition module, sensor signal for described sensor group is exported carries out signal processing, described signal processing includes described sensor signal is returned to zero, at least one of processing and amplifying and Filtering Processing, and the sensor signal after processing is carried out analog digital conversion becomes digital signal, described digital signal is sent to described data processing module.
Exemplarily, described temperature control modules includes temperature detecting unit, heating unit and control unit, and wherein, described temperature detecting unit is used for detecting current environmental temperature；Described control unit is used for judging that whether described current environmental temperature is lower than preset temperature threshold value, if lower than, then control described heating unit and be heated.
Exemplarily, described control unit is additionally operable to, when described Current Temperatures rises to described preset temperature threshold value under the effect of described heating unit, control described heating unit and quit work.
Exemplarily, described system also includes installing stand, is used for installing described temperature compensator and described sensor group.
Exemplarily, described sensor group includes temperature sensor, displacement transducer and pressure transducer.
Exemplarily, described system also includes display module, for showing the results of performance analysis of described temperature compensator that described data processing module exports.
Exemplarily, described system also includes alarm module, and described alarm module is configured at least one of voice unit and display unit, for when the performance of described temperature compensator is not up to standard, sending alarm signal.
Exemplarily, described system also includes memory module, is used for storing under different temperatures environment, the results of performance analysis of described temperature compensator.
According to another aspect of the present invention, the temperature compensator method of testing of a kind of aircraft is provided, described temperature compensator includes push rod, described method of testing includes: being placed on by described temperature compensator and control the described temperature compensator of simulation in the working environment of described aircraft engine servomechanism installation by temperature control modules, described temperature control modules controls the ambient temperature of described working environment；Detected the variations in temperature of described working environment by sensor group, and the pressure detecting the displacement of described push rod and the pressure block of test changes, and output sensor signal；Described sensor signal is transferred to data processing module, is analyzed processing to described sensor signal by described data processing module, exports the results of performance analysis of described temperature compensator.
The application embodiment of the present invention, working environment by automatization's mode analog temperature sensor, with sensor for data acquisition device, data based on sensor output carry out performance evaluation, finally give performance evaluation structure, realizing the performance of Aulomatizeted Detect temperature compensator, simple to operate, detection efficiency is high.
Accompanying drawing explanation
Fig. 1 is the schematic diagram that the present invention one exemplary embodiment illustrates temperature compensator；
Fig. 2 is the schematic block diagram of the temperature compensator test system of a kind of aircraft shown in the present invention one exemplary embodiment；
Fig. 3 is the exemplary process diagram of the temperature compensator method of testing of a kind of aircraft shown in the present invention one exemplary embodiment.
Detailed description of the invention
Here in detail exemplary embodiment being illustrated, its example representation is in the accompanying drawings.When as explained below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawings represents same or analogous key element.Embodiment described in following exemplary embodiment does not represent all embodiments consistent with the present invention.On the contrary, they only with in appended claims describe in detail, the present invention some in the example of consistent apparatus and method.
The term used in the present invention is only merely for the purpose describing specific embodiment, and is not intended to be limiting the present invention." one ", " described " and " being somebody's turn to do " of the singulative used in the present invention and appended claims is also intended to include most form, unless context clearly shows that other implications.It is also understood that term "and/or" used herein refers to and comprises any or all of one or more project of listing being associated and be likely to combination.
Although should be appreciated that and be likely to adopt term first, second, third, etc. to describe various information in the present invention, but these information should not necessarily be limited by these terms.These terms are only used for being distinguished from each other out same type of information.Such as, without departing from the present invention, the first information can also be referred to as the second information, and similarly, the second information can also be referred to as the first information.Depend on linguistic context, word as used in this " if " can be construed to " ... time " or " when ... " or " in response to determining ".
Fig. 1 is the schematic diagram that the present invention one exemplary embodiment illustrates temperature compensator.As shown in Figure 1, temperature compensator is made up of housing, temperature sensing material, push rod etc., it it is the key element of humidity control system, it can correct sense ambient temperature, and path increment and thrust accurately can be produced, temperature-sensing element therein can absorb the heat of fuel oil, produces volumetric expansion, regulating sleeve is promoted to regulate the flow of the cold and hot fuel oil of import, so that it is guaranteed that oil temperature remains in a safety range in electromotor.In embodiments of the present invention, it is provided that a kind of system and method for detecting temperature compensator performance, make temperature compensator detect automatization, improve detection efficiency.
Fig. 2 is the schematic block diagram of the temperature compensator test system of a kind of aircraft shown in the present invention one exemplary embodiment.In embodiments of the present invention, temperature compensator includes but not limited to push rod and pressure block.As in figure 2 it is shown, the temperature compensator test system of this aircraft can include temperature control modules, sensor group, data processing module and pressure block.
Wherein, temperature control modules is set with different temperature, for simulating the described temperature compensator working environment at described aircraft engine servomechanism installation, sensor group is for detecting the variations in temperature of working environment, and the pressure change of the displacement of detection push rod and described pressure block, and output sensor signal, data processing module receives described sensor signal, it is analyzed sensor signal processing, exports the results of performance analysis of described temperature compensator.Temperature sensor can include temperature sensor, displacement transducer and pressure transducer.
Exemplarily, temperature control modules can include temperature detecting unit, heating unit and control unit, and wherein, temperature detecting unit is used for detecting current environmental temperature；Control unit is used for judging that whether described current environmental temperature is lower than preset temperature threshold value, if lower than, then control described heating unit and be heated.Further, control unit is additionally operable to when Current Temperatures rises to preset temperature threshold value under the effect of heating unit, controls heating unit and quits work.
Exemplarily, data acquisition module is for carrying out signal processing to the sensor signal of sensor group output, signal processing includes sensor signal is returned to zero, at least one of processing and amplifying and Filtering Processing, and the sensor signal after processing is carried out analog digital conversion becomes digital signal, digital signal is sent to data processing module.For example, owing to the sensor signal of sensor output different in sensor group is respectively not desired to him, in order to meet the output data demand of Data Data processing module, such as, require the voltage signal of output 0 ~ 5V, after data acquisition module receives sensor signal, first the sensor signal of each different sensor output is processed, all the sensors signal is adjusted to the voltage signal of 0 ~ 5V, additionally, in order to eliminate Hz noise, unwanted frequency signal of decaying, suppressing interference and noise, sensor signal can be filtered processing by data acquisition module.If the sensor signal of sensor output is more weak, sensor signal can also be amplified by data acquisition module and zeroing processes.After completing above-mentioned process, data acquisition module can be sent to data processing module after sensor signal is carried out analog digital conversion, so that data processing module carries out Data Analysis Services according to the digital signal of the sensor signal received.
An example according to the present invention, the temperature compensator test system of this aircraft can also include installing stand, is used for installing temperature compensator and sensor group.Temperature control modules can be arranged in a casing, environment in this casing is the working environment of the temperature compensator of simulation, temperature control modules controls the temperature that it is internal, after temperature compensator and sensor group being arranged on installation stand, put into above-mentioned casing in the lump, perform the detection operation of temperature compensator further.
According to another example of the present invention, the temperature compensator test system of aircraft can also include display module, for the results of performance analysis of the temperature compensator of video data processing module output.This analysis result can be the tables of data form of EXCEL, it is also possible to be chart format, for instance, draw out the displacement curve of temperature curve and push rod, as long as analysis result can be presented intuitively.Exemplarily, the temperature compensator test system of aircraft can also include alarm module, and described alarm module is configured at least one of voice unit and display unit, for when the performance of temperature compensator is not up to standard, sending alarm signal.The temperature compensator test system of aircraft can also include memory module, is used for storing under different temperatures environment, the results of performance analysis of temperature compensator.
Fig. 3 is the exemplary process diagram of the temperature compensator method of testing of a kind of aircraft shown in the present invention one exemplary embodiment.As it is shown on figure 3, the temperature compensator method of testing of this aircraft is implemented based on aforementioned test system, comprise the steps:
Step 110, is placed on temperature compensator and controls the temperature compensator of simulation in the working environment of aircraft engine servomechanism installation by temperature control modules.Wherein, temperature control modules controls the ambient temperature of working environment.
Step 120, detects the variations in temperature of working environment and the pressure change of the displacement of detection push rod and pressure block output sensor signal by sensor group.
Step 130, is transferred to data processing module by sensor signal, is analyzed processing to sensor signal by data processing module, the results of performance analysis of output temperature compensator.
The application embodiment of the present invention, working environment by automatization's mode analog temperature sensor, with sensor for data acquisition device, data based on sensor output carry out performance evaluation, finally give performance evaluation structure, realizing the performance of Aulomatizeted Detect temperature compensator, simple to operate, detection efficiency is high.
For embodiment of the method, owing to it corresponds essentially to system embodiment, so relevant part illustrates referring to the part of system embodiment.Device embodiment described above is merely schematic, and the unit illustrated as separating component described in system can be or may not be physically separate, the parts shown as unit can be or may not be physical location, namely may be located at a place, or can also be distributed on multiple NE.Some or all of module therein can be selected according to the actual needs to realize the purpose of the present invention program.Those of ordinary skill in the art, when not paying creative work, are namely appreciated that and implement.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within the scope of protection of the invention.
Claims (10)
1. the temperature compensator test system of an aircraft, it is characterised in that described temperature compensator includes push rod, and described system includes temperature control modules, sensor group, data processing module and pressure block, wherein,
Described temperature control modules is set with different temperature, for simulating the described temperature compensator working environment at described aircraft engine servomechanism installation；
Described sensor group is for detecting the variations in temperature of described working environment, and detects the displacement of described push rod and the pressure change of described pressure block output sensor signal；
Described data processing module receives described sensor signal, is analyzed described sensor signal processing, exports the results of performance analysis of described temperature compensator.
2. system according to claim 1, it is characterized in that, described system also includes data acquisition module, sensor signal for described sensor group is exported carries out signal processing, described signal processing includes described sensor signal is returned to zero, at least one of processing and amplifying and Filtering Processing, and the sensor signal after processing is carried out analog digital conversion becomes digital signal, described digital signal is sent to described data processing module.
3. system according to claim 1, it is characterised in that described temperature control modules includes temperature detecting unit, heating unit and control unit, wherein,
Described temperature detecting unit is used for detecting current environmental temperature；
Described control unit is used for judging that whether described current environmental temperature is lower than preset temperature threshold value, if lower than, then control described heating unit and be heated.
4. system according to claim 3, it is characterised in that described control unit is additionally operable to, when described Current Temperatures rises to described preset temperature threshold value under the effect of described heating unit, control described heating unit and quit work.
5. system according to claim 1, it is characterised in that described system also includes installing stand, is used for installing described temperature compensator and described sensor group.
6. system according to claim 1, it is characterised in that described sensor group includes temperature sensor, displacement transducer and pressure transducer.
7. system according to claim 1, it is characterised in that described system also includes display module, for showing the results of performance analysis of described temperature compensator that described data processing module exports.
8. system according to claim 1, it is characterised in that described system also includes alarm module, and described alarm module is configured at least one of voice unit and display unit, for when the performance of described temperature compensator is not up to standard, sending alarm signal.
9. system according to claim 1, it is characterised in that described system also includes memory module, is used for storing under different temperatures environment, the results of performance analysis of described temperature compensator.
10. the temperature compensator method of testing of an aircraft, it is characterised in that described temperature compensator includes push rod and pressure block, and described method of testing includes:
Being placed on by described temperature compensator and control the described temperature compensator of simulation in the working environment of described aircraft engine servomechanism installation by temperature control modules, described temperature control modules controls the ambient temperature of described working environment；
Detected the variations in temperature of described working environment by sensor group, and detect the displacement of described push rod and the pressure change of described pressure block output sensor signal；
Described sensor signal is transferred to data processing module, is analyzed processing to described sensor signal by described data processing module, exports the results of performance analysis of described temperature compensator.
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| CN201511034037.7A CN105716890A (en) | 2015-12-30 | 2015-12-30 | Airplane temperature compensator test system and test method |
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| CN106568535A (en) * | 2016-10-10 | 2017-04-19 | 首凯汽车零部件（江苏）有限公司 | Precision detection system for motor vehicle exhaust emission temperature sensors |
| CN108803570A (en) * | 2018-06-21 | 2018-11-13 | 中国民航大学 | Air temperature control system fault test system based on signal converting technology |
| CN108829085A (en) * | 2018-06-21 | 2018-11-16 | 中国民航大学 | In-situ test platform based on air temperature control system functional simulation |
| CN113899554A (en) * | 2021-12-10 | 2022-01-07 | 中国飞机强度研究所 | Balance control method for slow-vehicle running environment field of laboratory aircraft engine |
| CN115950637A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | High altitude platform thrust measurement frock based on temperature compensation pole |
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| CN115950637A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | High altitude platform thrust measurement frock based on temperature compensation pole |
| CN115950637B (en) * | 2023-03-09 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | High altitude platform thrust measurement frock based on temperature compensation pole |
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