阅读说明：本技术 用于飞机发动机附件在转速急降时的油压采集与判定系统 (Oil pressure acquisition and judgment system for aircraft engine accessory in rotating speed emergency landing ) 是由 吕浩 于 2021-06-30 设计创作，主要内容包括：本发明提供了一种用于飞机发动机附件在转速急降时的油压采集与判定系统,包括：数据采集及电控子系统分别实时采集燃油子系统的压力和传动子系统的转速信号；测控子系统用于对数据采集及电控子系统采集到的压力和转速信号进行判断,并将判断结果传输至安全管理子系统；安全管理子系统接收判断信号,并根据判断结果,发出控制信号至所述的数据采集及电控子系统,并分别监控燃油子系统和传动子系统中的数值参数,当数值参数超出预设值时发出警示信息；数据采集及电控子系统根据所述控制信号控制所述传动子系统的转速,以及控制燃油子系统压力、流向和通断。本系统可实现转速、燃油压力的自动控制。(The invention provides an oil pressure acquisition and judgment system for an aircraft engine accessory in the process of rotating speed sudden drop, which comprises: the data acquisition and electric control subsystem respectively acquires the pressure of the fuel subsystem and the rotating speed signal of the transmission subsystem in real time; the measurement and control subsystem is used for judging the pressure and rotating speed signals collected by the data collection and electric control subsystem and transmitting the judgment result to the safety management subsystem; the safety management subsystem receives the judgment signal, sends a control signal to the data acquisition and electric control subsystem according to the judgment result, respectively monitors the numerical parameters in the fuel subsystem and the transmission subsystem, and sends out warning information when the numerical parameters exceed the preset values; and the data acquisition and electric control subsystem controls the rotating speed of the transmission subsystem according to the control signal and controls the pressure, the flow direction and the on-off of the fuel subsystem. The system can realize automatic control of the rotating speed and the fuel pressure.)

1. An oil pressure collection and determination system for an aircraft engine accessory during a speed dip, comprising: the system comprises a measurement and control subsystem, a data acquisition and electric control subsystem, a fuel subsystem, a transmission subsystem and a safety management subsystem;

the measurement and control subsystem is respectively in circuit connection with the data acquisition and electric control subsystem and the safety management subsystem, the data acquisition and electric control subsystem is respectively in circuit connection with the fuel subsystem, the transmission subsystem and the safety management subsystem, and the safety management subsystem is respectively in circuit connection with the fuel subsystem and the transmission subsystem;

the data acquisition and electric control subsystem respectively acquires the pressure of the fuel subsystem and the rotating speed signal of the transmission subsystem in real time;

the measurement and control subsystem is used for judging the pressure and rotating speed signals collected by the data collection and electric control subsystem and transmitting the judgment result to the safety management subsystem;

the safety management subsystem receives the judgment signal, sends a control signal to the data acquisition and electric control subsystem according to the judgment result, respectively monitors the numerical parameters in the fuel subsystem and the transmission subsystem, and sends out warning information when the numerical parameters exceed preset values;

and the data acquisition and electric control subsystem controls the rotating speed of the transmission subsystem according to the control signal and controls the pressure, the flow direction and the on-off of the fuel subsystem.

2. The system of claim 1 wherein the fuel subsystem is configured to provide a one way supply pressure, a two way supply pressure, and a return pressure for engine accessory testing.

3. The system of claim 1, wherein the drive subsystem is configured to provide a drive to the engine accessory, wherein the rotational speed is controlled to a precision of less than or equal to 1r/min, and wherein the rate of change of the rotational speed is adjustable.

4. The system of claim 1, wherein the instrumentation subsystem compiles test software via labview software.

5. The system of claim 1, wherein the test software controls the fuel system to have a first oil supply pressure of 4.9MPa, a second oil supply pressure of 0.659MPa and an oil return pressure of 0.2MPa through the data acquisition and electronic control subsystem, and the test software sets the initial rotation speed of the transmission subsystem to be 3800r/min and the changed rotation speed to be 2540 r/min; the test software sets the speed change time to 1 second.

6. The system of claim 1, wherein the test software further displays the pressure at the pressure measuring point of the engine speed sensor Pno, the test software can change the rotating speed from 3800r/min to 2540r/min within a set time of 1s after pressing the start test button, record Pno pressure values of the rotating speed 3638r/min and 2972r/min when the rotating speed changes, calculate the pressure difference of the lower Pno of the two rotating speeds and the time interval Δ T, the test software records the test process through an oscillogram, generates a curve of the pressure changing along with the rotating speed in 1s, further determines, and determines that the pressure difference Pno is less than 0.5MPa and the time interval Δ T is less than 0.8s, and determines that the pressure is qualified if the pressure difference Pno is less than 0.5MPa and the time interval Δ T is less than 0.8s, otherwise, determines that the pressure is not qualified.

Technical Field

The invention relates to the field of aviation equipment detection, in particular to an oil pressure acquisition and judgment system for aircraft engine accessories during rotating speed sudden drop.

Background

In the prior art, some accessories of a rotating speed sensor of an aircraft engine fuel system are still mechanical, the rotating speed needs to be converted into fuel pressure, and the rotating speed and the fuel pressure change synchronously. The difficulty of the test is that the rapid change of the rotating speed needs to be accurately controlled, the fuel pressure is collected in the rotating speed changing process, and the sensitivity of the accessory conversion pressure is judged according to the collected fuel pressure. The aircraft engine fuel system can automatically judge whether the accessory meets the requirements according to the acquired pressure. The technology relates to the rotating speed sudden drop and fuel pressure acquisition and automatic judgment of an aircraft engine accessory, and a reasonable test method and an accurate test result of the technical scheme are important bases for judging whether the accessory can work normally and deducing fault reasons, and have important significance for safe flight of an aircraft.

The existing test device for controlling the rotating speed has two modes: one way is to control the drop in rotational speed by manually adjusting a potentiometer; the other mode is that the rotating speed is adjusted to two rotating speed points of rotating speed conversion, and the rotating speed is suddenly reduced by controlling instantaneous switching through a relay. However, the manual regulation of the rotating speed in the prior art cannot accurately control the rotating speed; the switching mode of the relay cannot control the time of the reduction of the rotating speed. Due to the fact that the pressure collection is delayed, the fuel pressure at the corresponding rotating speed cannot be accurately read.

Therefore, a need exists for an oil pressure collection and determination system for aircraft engine accessories during a rapid speed drop.

Disclosure of Invention

The invention provides an oil pressure acquisition and judgment system for an aircraft engine accessory during a rapid rotating speed drop, which aims to solve the problems of inaccurate test results caused by manual rotating speed adjustment, low rotating speed control precision and asynchronism of rotating speed acquisition and pressure acquisition in the prior art.

In order to achieve the purpose, the invention adopts the following technical scheme.

An oil pressure collection and determination system for an aircraft engine accessory during a speed dip, comprising: the system comprises a measurement and control subsystem, a data acquisition and electric control subsystem, a fuel subsystem, a transmission subsystem and a safety management subsystem;

the measurement and control subsystem is respectively in circuit connection with the data acquisition and electric control subsystem and the safety management subsystem, the data acquisition and electric control subsystem is respectively in circuit connection with the fuel subsystem, the transmission subsystem and the safety management subsystem, and the safety management subsystem is respectively in circuit connection with the fuel subsystem and the transmission subsystem;

the data acquisition and electric control subsystem respectively acquires the pressure of the fuel subsystem and the rotating speed signal of the transmission subsystem in real time;

the measurement and control subsystem is used for judging the pressure and rotating speed signals collected by the data collection and electric control subsystem and transmitting the judgment result to the safety management subsystem;

the safety management subsystem receives the judgment signal, sends a control signal to the data acquisition and electric control subsystem according to the judgment result, respectively monitors the numerical parameters in the fuel subsystem and the transmission subsystem, and sends out warning information when the numerical parameters exceed preset values;

and the data acquisition and electric control subsystem controls the rotating speed of the transmission subsystem according to the control signal and controls the pressure, the flow direction and the on-off of the fuel subsystem.

Preferably, the fuel subsystem is adapted to provide a one way supply pressure, a two way supply pressure and a return pressure required for engine accessory testing.

Preferably, the transmission subsystem is used for providing a driving device for the engine accessories, the rotating speed control precision is less than or equal to 1r/min, and the rotating speed change rate is adjustable.

Preferably, the test software is edited by the measurement and control subsystem through labview software.

Preferably, the test software controls one path of oil supply pressure of the fuel system to be 4.9MPa, two paths of oil supply pressure to be 0.659MPa and oil return pressure to be 0.2MPa through the data acquisition and electronic control subsystem, and sets 3800r/min of initial rotation speed and 2540r/min of changed rotation speed of the transmission subsystem; the test software sets the speed change time to 1 second.

Preferably, the test software can also display the pressure of the pressure point of the engine speed sensor Pno, the test software can change the rotating speed from 3800r/min to 2540r/min within a set time 1s after pressing a test starting button, simultaneously record Pno pressure values of the rotating speed 3638r/min and the rotating speed 2972r/min when the rotating speed changes, calculate the pressure difference and the time interval delta T of the lower Pno of the two rotating speeds, record the test process through an oscillogram, generate a curve of the pressure changing along with the rotating speed within 1 second, further judge, when the Pno pressure difference is less than 0.5MPa and the time interval delta T is less than 0.8s, the judgment is qualified, and otherwise, the judgment is unqualified.

According to the technical scheme provided by the oil pressure acquisition and judgment system for the aircraft engine accessory during the rotating speed sudden drop, the initial rotating speed, the rotating speed after the change and the dropping time are set through software, and meanwhile, the pressure value is acquired in real time, so that the change result of the pressure along with the rotating speed can be obtained in real time.

Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a schematic diagram of an oil pressure collection and determination system for an aircraft engine accessory during a rapid speed drop according to an embodiment;

FIG. 2 is a schematic diagram of a fuel subsystem and a transmission subsystem of an engine accessory oil pressure acquisition and determination test technique during a sudden drop in rotational speed according to an embodiment of the present invention;

fig. 3 is a functional software and an oscillography diagram for a test method for collecting and determining oil pressure when the rotating speed of an engine rotating speed sensor suddenly drops according to an embodiment of the present invention.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.

As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, and/or groups thereof. It should be understood that the term "and/or" as used herein includes any and all combinations of one or more of the associated listed items.

It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.

For the convenience of understanding of the embodiments of the present invention, the following description will be further explained by taking several specific embodiments as examples with reference to the drawings, and the embodiments of the present invention are not limited thereto.

Examples

Fig. 1 is a schematic diagram of an oil pressure collecting and determining system for an aircraft engine accessory in a rapid speed drop according to the embodiment, and with reference to fig. 1, the system includes: the system comprises a measurement and control subsystem 1.1, a data acquisition and electric control subsystem 1.2, a fuel subsystem 1.4, a transmission subsystem 1.3 and a safety management subsystem 1.5.

The measurement and control subsystem 1.1 is respectively in circuit connection with the data acquisition and electric control subsystem 1.2 and the safety management subsystem 1.5, the data acquisition and electric control subsystem 1.2 is respectively in circuit connection with the fuel subsystem 1.4, the transmission subsystem 1.3 and the safety management subsystem 1.5, and the safety management subsystem 1.5 is respectively in circuit connection with the fuel subsystem 1.4 and the transmission subsystem 1.3.

The data acquisition and electric control subsystem 1.2 respectively acquires the pressure of the fuel subsystem 1.4 and the rotating speed signal of the transmission subsystem 1.3 in real time;

the measurement and control subsystem 1.1 is used for judging the pressure and rotating speed signals collected by the data collection and electric control subsystem 1.2 and transmitting the judgment result to the safety management subsystem 1.5;

the safety management subsystem 1.5 receives the judgment signal, sends a control signal to the data acquisition and electric control subsystem 1.2 according to the judgment result, respectively monitors the numerical parameters in the fuel subsystem 1.4 and the transmission subsystem 1.3, and sends out warning information when the numerical parameters exceed the preset values;

the data acquisition and electric control subsystem 1.2 controls the rotating speed of the transmission subsystem 1.3 according to the control signal and controls the pressure, the flow direction and the on-off of the fuel subsystem 1.4.

And each system is subjected to safety protection, and alarm information is sent out when the pressure, the rotating speed and other parameters in the system exceed specified values.

The fuel subsystem 1.4 is used to provide the one way supply pressure, the two way supply pressure and the return pressure required for engine accessory testing.

The transmission subsystem 1.3 is used for providing a driving device for engine accessories, and the rotating speed control precision is less than or equal to

1r/min, and the change rate of the rotating speed is adjustable.

And the measurement and control subsystem 1.1 edits the test software through labview software.

The test software controls one path of oil supply pressure of the fuel system to be 4.9MPa, two paths of oil supply pressure to be 0.659MPa and oil return pressure to be 0.2MPa through the data acquisition and electronic control subsystem, the test software sets 3800r/min of initial rotation speed of the transmission subsystem and 2540r/min of rotation speed after change; the test software sets the speed change time to 1 second.

The test software can also display the pressure of a pressure point measured by the engine speed sensor Pno, the test software can change the rotating speed from 3800r/min to 2540r/min within a set time 1s after pressing a test start button, simultaneously record Pno pressure values of the rotating speed 3638r/min and the rotating speed 2972r/min when the rotating speed changes, calculate the pressure difference and the time interval delta T of lower Pno of the two rotating speeds, record the test process through an oscillogram, generate a curve of the pressure changing along with the rotating speed in 1 second, further judge, and judge that the test is qualified when the pressure difference of Pno is less than 0.5MPa and the time interval delta T is less than 0.8s, otherwise, judge that the test is not qualified.

The oscillogram is a record of the test process and can be used for judging whether the test is qualified or not.

Fig. 2 is a schematic diagram of a fuel subsystem and a transmission subsystem of an engine accessory oil pressure collection and determination test technology in a rapid drop of a rotating speed, which is provided by the embodiment of the invention, and comprises a 2.1 fuel subsystem and a 2.2 transmission subsystem.

A fuel system: the system comprises a 2101 oil tank, a 2102 booster pump, a 2103 overflow valve, a 2104 one-way pressure regulating valve, a 2105 two-way pressure regulating valve, a 2106 one-way oil supply pressure measurement, a 2107 two-way oil supply pressure measurement, a 2108 test piece, a 2109 outlet pressure measurement, a 2110 oil supply temperature measurement, a 2111 oil return pressure regulating valve and a 2112 radiator.

A transmission system: the motor is 2201, and the rotating speed is controlled by a motor driver.

During test, fuel is pressurized by a 2102 booster pump, one path of oil supply pressure is regulated by one path of pressure regulating valve 2104, two paths of oil supply pressure are regulated by two paths of pressure regulating valves 2105, and the pressure of one path of oil supply, two paths of oil supply and outlet pressure measurement is measured by 2106, 2107 and 2109 and displayed on software through data acquisition. After the rotational speed is set, 2201 the drive train motor is operated and 2109 the outlet pressure measurement is varied with the rotational speed. And the test software determines the test result.

Fig. 3 is a collection and determination function software and an oscillography function diagram of a method for collecting and determining oil pressure of an engine speed sensor during a sudden drop of a rotating speed, which are provided by the embodiment of the invention, and the collection and determination function software and the oscillography function diagram comprise test software and an oscillography function diagram.

Testing software:

the test software can set the oil supply pressure and the oil return pressure of the fuel system;

the test software can set the rotating speed and the time interval of the rapid reduction of the rotating speed;

the test software can automatically judge whether the test is qualified.

An oscillography functional diagram:

the software can automatically generate a curve graph of the change of the rotating speed along with time;

the software may automatically generate a graph of pressure versus time. Each system is controlled by data acquisition and electric control: controlling the rotating speed of a transmission system and collecting the rotating speed of the transmission system; and controlling the pressure, flow direction and on-off of the fuel system, and acquiring the pressure of the fuel system to realize the test process to obtain a result.

In conclusion, the system of the embodiment can realize automatic control of the rotating speed and the fuel pressure and automatically judge the test result; and realizing the transmitted information termination test in abnormal conditions. The embodiment of the invention realizes the accurate control and the rapid change of the rotating speed and accurately collects the fuel pressure in the process of the rapid reduction and change of the rotating speed. The software of the embodiment of the invention realizes the automatic judgment function and can display the process of the rapid change through the oscillographic graph. The invention provides an accurate test result for the rotating speed sensor.

The embodiment of the invention can fully meet the actual requirements of the test of the aircraft accessory maintenance factory, and simultaneously avoids the error results of the test data caused by the operation errors of personnel.

Those of ordinary skill in the art will understand that: the components in the devices in the embodiments may be distributed in the devices in the embodiments according to the description of the embodiments, or may be correspondingly changed in one or more devices different from the embodiments. The components of the above embodiments may be combined into one component, or may be further divided into a plurality of sub-components.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.