A temperature sensor detection device and method for an aircraft system

Abstract

The application provides a temperature sensor detection device and method for an airplane whole system, and belongs to the technical field of airplane detection.The temperature sensor detection device comprises a hydraulic system and a control system, wherein the hydraulic system is used for providing a liquid medium environment and a temperature range of an airplane subsystem where a temperature sensor to be detected is located, the control system is used for managing and controlling the hydraulic system, automatic detection of the temperature sensor is realized, the liquid medium environment comprises hydraulic oil, fuel oil, lubricating oil and cooling liquid, and the temperature range is -60 DEG C to 200 DEG C.The device is simple to operate, only needs to insert the temperature sensor to be detected into the device, input the required liquid medium environment and temperature range, the detection device can automatically construct the environment required by the user, and detection of the temperature sensor to be detected is started.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft detection, and relates to a temperature sensor detection device and method for an aircraft system. BACKGROUND

[0002] Temperature sensors play a crucial role in aircrafts. They monitor and record temperature changes in various parts of the aircraft, ensuring that they operate within normal operating ranges and avoid damage caused by overheating or overcooling. For example, temperature sensors monitor the temperature of various components in the engine system, including turbines, combustion chambers, etc., to ensure that the engine operates within an appropriate temperature range to ensure its performance and reliability. For example, temperature sensors monitor the temperature of the liquid in the hydraulic system to ensure that the hydraulic oil operates within an appropriate temperature range to prevent system failure or liquid performance degradation due to excessive or insufficient temperature; temperature sensors in the environmental control system monitor the temperature changes inside the aircraft to ensure the comfort of the pilot cabin and adjust the air conditioning system to adapt to different flight conditions.

[0003] In an aircraft, the working environment and temperature range of temperature sensors in each system are different, so there is currently no device that can detect temperature sensors in all aircraft subsystems. Each subsystem has its unique working conditions and temperature requirements, for example, the engine system may require high temperature resistance, while the flight control system may require low temperature resistance. In order to solve this problem, it is necessary to build a device that can detect all temperature sensors in the aircraft system, such a device needs to have compatibility and flexibility, to be able to construct the working environment and temperature range of different subsystems, and to provide reliable data acquisition and monitoring functions to ensure the normal operation of the aircraft and the safety of the pilot. SUMMARY

[0004] The present application provides a temperature sensor detection device and method for an aircraft system, which can construct the working environment and temperature range of each subsystem of the aircraft, and provide reliable data acquisition and monitoring functions. Specifically, the device of the present application can construct the liquid medium environment and temperature range of the aircraft subsystem where the temperature sensor is located, wherein the liquid medium environment includes hydraulic oil, fuel, lubricating oil, and coolant; the temperature range is -60℃ to 200℃.

[0005] The technical solution adopted by the present application is as follows:

[0006] A temperature sensor detection device for an aircraft system, the temperature sensor detection device comprising a hydraulic system and a control system, wherein the hydraulic system is used to provide the liquid medium environment and temperature range of the aircraft subsystem where the temperature sensor to be detected is located, and the control system is used to manage and control the hydraulic system to realize automatic detection of the temperature sensor. Specifically:

[0007] The hydraulic system comprises an oil tank group, a reversing valve, a filter, a hydraulic pump, a throttle valve, a relief valve, a unloading valve, a waste oil tank and a temperature tank; a plurality of oil tanks storing different liquid media are connected in parallel in the oil tank group to provide different liquid media in each subsystem of the aircraft; the oil tank group is provided with a reversing valve at the oil outlet end for controlling the flow of the target liquid medium; the filter is connected to the oil outlet end of the reversing valve for filtering impurities in the liquid medium; the hydraulic pump is connected to the oil outlet end of the filter for providing power to extract and transport the liquid medium for the temperature sensor detection device; the throttle valve is connected to the oil outlet end of the hydraulic pump for adjusting the flow of the liquid medium; the temperature tank is connected to the oil outlet end of the throttle valve for adjusting the ambient temperature, and a temperature sensor interface is arranged in the temperature tank for connecting the temperature sensor to be measured; the unloading valve is connected to the oil outlet end of the temperature tank for discharging the liquid medium in the pipeline, and the discharged liquid medium flows into the waste oil tank connected to the outlet end of the unloading valve; the relief valve is used to relieve the system load, and the inlet end and the oil outlet end thereof are connected with the hydraulic pump and the waste oil tank respectively.

[0008] The control system comprises four modules: a parameter input module, a hardware control module, a data collection module and a result analysis module; the parameter input module is used for inputting the required detection parameter conditions, including the liquid medium environment and the temperature range required by the temperature sensor to be measured; the hardware control module is used for regulating and controlling the key hardware in the hydraulic system to reach the required parameters, including the temperature tank, the reversing valve, the hydraulic pump and the like; the data collection module is used for collecting the temperature values of the temperature sensor to be measured at different times; and the result analysis module is used for analyzing the temperature values measured by the temperature sensor and evaluating the health status of the temperature sensor.

[0009] In an embodiment of the present application, a plurality of hydraulic oil tanks, fuel oil tanks, lubricating oil tanks and cooling liquid tanks are connected in parallel in the oil tank group, which can provide four different liquid media of hydraulic oil, fuel oil, lubricating oil and cooling liquid to create the liquid medium environment required by each subsystem of the aircraft, such as the electromechanical system, the avionics system, the environmental control system, the engine system and the flight control system, and the detection temperature ranges of each liquid medium are different, specifically: for hydraulic oil, the detection temperature range is -60℃ to 200℃; for fuel oil, the temperature range is -60℃ to 150℃; for lubricating oil, the temperature range is -55℃ to 180℃; and for cooling liquid, the temperature range is -55℃ to 180℃.

[0010] In an embodiment of the present application, the temperature accuracy error of the temperature tank in the hydraulic system is ±1℃.

[0011] In an embodiment of the present application, one or more temperature sensor interfaces are arranged in the temperature tank in the hydraulic system, and a plurality of temperature sensor interfaces are connected in parallel, so that parallel testing of a plurality of temperature sensors can be performed.

[0012] The application also provides a temperature sensor detection method for an aircraft system, which is realized based on the temperature sensor detection device.

[0013] Step 1, insert the temperature sensor to be detected into the temperature sensor interface reserved in the temperature box; start the control system and the hydraulic system.

[0014] Step 2, input the liquid medium environment and the environmental temperature range required by the temperature sensor to be detected into the parameter input module in the control system.

[0015] Step 3, the hardware control module in the control system controls the related components in the hydraulic system, so that the hydraulic system provides the liquid medium environment and the environmental temperature input in step 2.

[0016] Step 4, after the liquid medium environment and the environmental temperature are stable, the data collection module in the control system collects the temperature values of the temperature sensor to be detected at different times, and the result analysis module analyzes the collected temperature values to determine the health condition of the temperature sensor.

[0017] The application has the advantages that the device is easy to operate, only needs to insert the temperature sensor to be detected into the device, input the required liquid medium environment and temperature range, and the detection device can automatically construct the environment required by the user and start to detect the temperature sensor to be detected. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 It is the structural diagram of the detection device;

[0019] Figure 2 It is the operation flow chart of the detection device;

[0020] Figure 3 It is the result chart of the temperature sensor measurement temperature value;

[0021] In the figure: 1 hydraulic system; 2 reversing valve; 3 filter; 4 hydraulic pump; 5 throttle valve; 6 overflow valve; 7 unloading valve; 8 waste oil tank; 9 temperature box; 10 control system; 11 temperature sensor interface; 12 hydraulic oil tank; 13 fuel oil tank; 14 cooling liquid oil tank; 15 lubricating oil tank. DETAILED DESCRIPTION

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. The drawings in the following description are only some embodiments of the application, and for those skilled in the art, other drawings can also be obtained without creative labor under the premise of these drawings.

[0023] A temperature sensor detection device for an aircraft system, the temperature sensor detection device comprising a hydraulic system 1 and a control system 10, as shown in Figure 1 .

[0024] The hydraulic system 1 comprises an oil tank group, a reversing valve 2, a filter 3, a hydraulic pump 4, a throttle valve 5, a relief valve 6, an unloading valve 7, a waste oil tank 8 and a temperature tank 9; the oil tank group is connected in parallel with four oil tanks storing different liquid media, i.e., a hydraulic oil tank 12, a fuel oil tank 13, a cooling liquid tank 14 and a lubricating oil tank 15, to provide different liquid media for various subsystems of the aircraft; the oil tank group is provided with the reversing valve 2 at the oil outlet end for controlling the flow of the target liquid medium; the filter 3 is connected to the oil outlet end of the reversing valve 2 for filtering impurities in the liquid medium; the hydraulic pump 4 is connected to the oil outlet end of the filter 3 for providing power to extract and transport the liquid medium; the throttle valve 5 is connected to the oil outlet end of the hydraulic pump 4 for adjusting the flow of the liquid medium; the temperature tank 9 is connected to the oil outlet end of the throttle valve for adjusting the ambient temperature, and is provided with four parallel temperature sensor interfaces 11 inside for connecting multiple temperature sensors in parallel; the unloading valve 7 is connected to the oil outlet end of the temperature tank 9 for discharging the liquid medium in the pipeline, and the discharged liquid medium flows into the waste oil tank 8 connected to the outlet end of the unloading valve 7; the relief valve 6 is used to relieve the system load, and the inlet end and the oil outlet end thereof are connected to the hydraulic pump 4 and the waste oil tank 8, respectively.

[0025] The control system 10 comprises four modules: a parameter input module, a hardware control module, a data collection module and a result analysis module; the parameter input module is used to input the required detection parameter conditions, including the liquid medium environment and the temperature range required by the temperature sensor to be detected; the hardware control module is used to regulate and control the key hardware in the hydraulic system to achieve the required parameters, including the temperature tank, the reversing valve, the hydraulic pump, etc.; the data collection module is used to collect the temperature values of the temperature sensor to be detected at different times; and the result analysis module is used to analyze the temperature values measured by the temperature sensor and evaluate the health status of the temperature sensor.

[0026] In this embodiment, the temperature sensor detection device can provide four different liquid media, i.e., hydraulic oil, fuel oil, lubricating oil and cooling liquid, to create the required liquid medium environment for various subsystems of the aircraft, such as the electromechanical system, the avionics system, the environmental control system, the engine system and the flight control system, and the detection temperature range of each liquid medium is different, specifically: for the hydraulic oil, the detection temperature range is -60℃-200℃; for the fuel oil, the temperature range is -60℃-150℃; for the lubricating oil, the temperature range is -55℃-180℃; and for the cooling liquid, the temperature range is -55℃-180℃.

[0027] The embodiment also provides a temperature sensor detection method for an aircraft system, which is realized based on the temperature sensor detection device and has a flow as shown in the figure. Figure 2 The temperature sensor detection method can effectively construct the liquid medium environment and temperature range of each subsystem of the aircraft where the temperature sensor is located, does not need a complex temperature control system, and can obtain accurate and reliable detection results. The temperature sensor detection method comprises the following steps.

[0028] Step 1, insert the temperature sensor to be detected into the temperature sensor interface 11 reserved in the temperature box 9; start the control system 10 and the hydraulic system 1.

[0029] Step 2, input the required liquid medium environment and environmental temperature range of the temperature sensor to be detected into the parameter input module in the control system 10; for the temperature sensor detection device that needs to be cleaned, the residual liquid in the pipeline is discharged through the unloading valve 7 before detection, and the pipeline is flushed 3 times with the required liquid medium of the temperature sensor to be detected.

[0030] Step 3, the hardware control module in the control system 10 controls the related components in the hydraulic system 1, so that the hydraulic system 1 provides the liquid medium environment and environmental temperature input in step 2.

[0031] Step 4, after the liquid medium environment and environmental temperature are stable, the data collection module in the control system 10 collects the temperature values of the temperature sensor to be detected at different times, and the result analysis module analyzes the collected temperature values to judge the health condition of the temperature sensor.

[0032] Figure 3 The figure shows the measurement results of the temperature sensor to be detected under different environmental temperatures. The abscissa in the figure represents the environmental temperature set by the temperature box, and the ordinate represents the temperature value actually measured by the temperature sensor. The environmental temperature and the temperature value actually measured by the temperature sensor are almost the same, indicating that the temperature sensor can accurately reflect the environmental temperature in the whole temperature range, that is, the temperature sensor does not fail, and at the same time, the accuracy and reliability of the detection device are verified, which shows that the device can correctly detect and record the measurement data of the temperature sensor.

[0033] The above embodiment only expresses the implementation of the present application, but cannot be understood as the limitation of the scope of the present application. It should be pointed out that for those skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which all belong to the protection scope of the present application.

Claims

1. A temperature sensor detection device for an aircraft system, characterized in that The temperature sensor detection device comprises a hydraulic system (1) and a control system (10), wherein the hydraulic system (1) is used for providing a liquid medium environment and a temperature range of an aircraft subsystem where a temperature sensor to be detected is located, and the control system is used for managing and controlling the hydraulic system to realize automatic detection of the temperature sensor. The hydraulic system (1) comprises an oil tank group, a reversing valve (2), a filter (3), a hydraulic pump (4), a throttle valve (5), an overflow valve (6), an unloading valve (7), a waste oil tank (8) and a temperature tank (9); a plurality of oil tanks for storing different kinds of liquid media are connected in parallel in the oil tank group; the oil tank group is provided with the reversing valve (2) at an oil outlet end, which is used for controlling the flow of the target liquid medium; the filter (3) is connected at an oil outlet end of the reversing valve (2) and is used for filtering impurities in the liquid medium; the hydraulic pump (4) is connected at an oil outlet end of the filter (3) and is used for pumping and conveying the liquid medium; the throttle valve (5) is connected at an oil outlet end of the hydraulic pump (4) and is used for adjusting the flow of the liquid medium; the temperature tank (9) is connected at an oil outlet end of the throttle valve (5) and is used for adjusting the ambient temperature, and a temperature sensor interface (11) is arranged in the temperature tank (9) and is used for connecting the temperature sensor to be detected; the unloading valve (7) is connected at an oil outlet end of the temperature tank (9) and is used for discharging the liquid medium in the pipeline, and the discharged liquid medium flows into the waste oil tank (8) connected at an outlet end of the unloading valve (7); the overflow valve (6) is used for relieving the system load, and an inlet end and an oil outlet end of the overflow valve (6) are connected with the hydraulic pump (4) and the waste oil tank (8) respectively. The control system (10) comprises four modules: a parameter input module, a hardware control module, a data collection module and a result analysis module; the parameter input module is used for inputting the required detection parameter conditions; the hardware control module is used for regulating and controlling the related components in the hydraulic system (1) to reach the required parameters; the data collection module is used for collecting the temperature values of the temperature sensor to be detected at different time points; and the result analysis module is used for analyzing the temperature values measured by the temperature sensor and evaluating the health condition of the temperature sensor.

2. A temperature sensor detection device for an entire system of an aircraft according to claim 1, characterized in that, The oil tank group is connected in parallel with a hydraulic oil tank (12), a fuel oil tank (13), a lubricating oil tank (14) and a cooling liquid tank (15).

3. A temperature sensor detection device for an entire system of an aircraft according to claim 2, characterized in that, The detection temperature ranges of different liquid media are different, and specifically, the detection temperature range of the hydraulic oil is -60℃-200℃, the temperature range of the fuel oil is -60℃-150℃, the temperature range of the lubricating oil is -55℃-180℃, and the temperature range of the cooling liquid is -55℃-180℃.

4. The temperature sensor detection device for an entire system of an aircraft according to claim 1, wherein The temperature tank (9) in the hydraulic system (1) is provided with one or more temperature sensor interfaces (11).

5. A temperature sensor detection device for an entire system of an aircraft according to claim 4, characterized in that, The plurality of temperature sensor interfaces (11) are connected in parallel.

6. The temperature sensor detection device for an entire system of an aircraft according to claim 1, wherein The temperature accuracy error of the temperature tank (9) in the hydraulic system (1) is ±1℃.

7. A method for detecting a temperature sensor for an entire system of an aircraft, implemented based on the temperature sensor detection device according to any one of claims 1-6, characterized in that, The temperature sensor detection method comprises the following steps: Step 1: inserting the temperature sensor to be detected into the temperature sensor interface (11) reserved in the temperature tank (9); starting the control system (10) and the hydraulic system (1); Step 2, input the required liquid medium environment and the environmental temperature range of the temperature sensor to be tested in the parameter input module in the control system (10); Step 3, the hardware control module in the control system (10) regulates the related components in the hydraulic system (1), so that the hydraulic system (1) provides the liquid medium environment and the environmental temperature input in step 2; Step 4, after the liquid medium environment and the environmental temperature are stable, the data collection module in the control system (10) collects the temperature values of the temperature sensor to be tested at different times, and the result analysis module analyzes the collected temperature values to determine the health condition of the temperature sensor.

8. The method of claim 7, wherein, In step 2, for the temperature sensor detection device that needs to be cleaned, the residual liquid in the pipeline is discharged through the unloading valve (7) before detection, and the pipeline is flushed 3 times with the required liquid medium of the temperature sensor to be tested.

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