A hydraulic pressure tester for aircraft hydraulic indicators and sensors

Abstract

The utility model belongs to the field of aircraft airborne equipment detection, concretely is a kind of hydraulic tester for aircraft hydraulic indicator and sensor.The tester includes case and integrated in its power module, control module;And be located at the hydraulic pressure source of case exterior, precision pressure gauge, digital multimeter;Case front panel is equipped with voltmeter, ammeter, digital pressure gauge, function selection switch, pointer selection switch, signal adjusting knob, total power switch, calibration interface and pilot lamp;Rear panel is equipped with ac power input socket, special indicator interface socket, sensor interface socket, safety tube group.The utility model is designed to the specific interface and parameter of target model, can avoid repeatedly erecting and disassembling test circuit, only needs to connect measured piece by standard cable, can complete all test items according to standardization process, can significantly improve the detection efficiency and quality of certain type aircraft double combination hydraulic indicator and hydraulic sensor.

Description

Technical Field

[0001] This utility model relates to the field of airborne equipment testing technology, specifically a hydraulic tester for aircraft hydraulic indicators and sensors. Background Technology

[0002] In the field of aircraft maintenance, hydraulic indicators and pressure sensors are important components for monitoring the status of aircraft hydraulic systems. The performance testing of key components such as hydraulic indicators and sensors is crucial and directly affects flight safety.

[0003] For a certain type of aircraft equipped with dual combined hydraulic indicators and separate left and right wheel brake pressure sensors, existing testing methods have obvious shortcomings: using general-purpose instruments to build temporary test circuits is cumbersome, complex to connect, and prone to errors; moreover, existing general-purpose hydraulic testing equipment often cannot truly simulate the working parameters and signal characteristics of the aircraft's hydraulic system, resulting in incomplete testing items, insufficient accuracy, and low efficiency, which cannot meet the requirements for consistency and periodicity in batch maintenance. Summary of the Invention

[0004] To overcome the shortcomings of existing technologies, this utility model provides a hydraulic testing device for aircraft hydraulic indicators and sensors. By integrating power supply, signal simulation, pressure measurement, electrical parameter measurement, mode control, and interfaces into a standard chassis, and designing it for the specific interfaces and parameters of the target aircraft model, it can avoid repeated assembly and disassembly of test circuits. All test items can be completed according to a standardized process simply by connecting the test component through a standard cable. This can significantly improve the testing efficiency and quality of dual-combination hydraulic indicators and hydraulic sensors for a certain type of aircraft.

[0005] The technical solution of this utility model is:

[0006] A hydraulic tester for aircraft hydraulic indicators and sensors, characterized in that it comprises: a chassis, and a power module and a control module integrated within the chassis; and a hydraulic pressure source, a precision pressure gauge, and a digital multimeter located outside the chassis; the hydraulic pressure source is an external hydraulic source used to test pressurization when testing brake pressure sensors, and the precision pressure gauge is located at the interface of the hydraulic pressure source to accurately display the pressure of the external hydraulic source;

[0007] The chassis has a front panel and a rear panel;

[0008] The front panel of the chassis is a human-machine interface, and the following components are arranged on the front panel of the chassis according to functional zones:

[0009] Display area: includes DC voltmeters and DC ammeters for monitoring power output parameters, and digital pressure gauges for real-time monitoring of system pressure;

[0010] Operation area: includes a main power switch for controlling the on / off of the equipment, a function selection band switch for switching test modes, an illumination pointer selection band switch for controlling the on / off of the illumination, a voltage test band switch for switching the output voltage, a left / right pointer selection band switch for switching the left and right test systems, and a signal adjustment potentiometer for adjusting the analog pressure signal.

[0011] Test and calibration area: includes test holes and calibration switches for DC voltmeter, digital pressure gauge, etc., for equipment self-test; and signal voltage test hole for connecting the digital multimeter to measure the output signal of the sensor.

[0012] Status indicator area: includes a 220V AC power indicator and a 28V DC power indicator;

[0013] The rear panel of the chassis is equipped with interface units and protective components, including: a power socket for connecting an external AC power supply, an indicator interface socket for connecting the tested dual-combination hydraulic indicator, a sensor interface socket for connecting the left and right wheel brake pressure sensors; and multiple fuse holders and grounding terminals for providing overcurrent protection for the internal DC power supply circuits and AC input circuits.

[0014] The power module is electrically connected to the power input socket, control module, operation display unit and interface unit, and is used to provide various DC operating voltages required by the equipment.

[0015] The control module is electrically connected to the function selection band switch, the pointer selection band switch, the signal conditioning potentiometer, and the interface unit, and is used to control the signal path and test logic according to the operation instructions.

[0016] Furthermore, the multiple fuse holders on the rear panel of the chassis are respectively for installing fuse holders for protecting 5V DC circuits, fuse holders for installing fuse holders for protecting 8V DC circuits, fuse holders for installing fuse holders for protecting 15V DC circuits, fuse holders for installing fuse holders for protecting 28V DC circuits, and fuse holders for installing fuse holders for protecting 220V AC input circuits.

[0017] Furthermore, both the sensor interface socket and the indicator interface socket are aviation sockets that conform to airborne equipment interface standards.

[0018] Furthermore, when the function selection band switch is in indicator test mode, the signal adjustment potentiometer is used to manually adjust the analog sensor voltage signal output to the indicator interface socket to drive the hydraulic indicator pointer to deflect.

[0019] Furthermore, the internal working principle of the tester is as follows: An external AC220V power supply is converted by the power module to generate various regulated DC currents required by the equipment; the control module receives power from the switches on the front panel and switches the correct power and signal paths to the corresponding interface sockets; when testing the indicator, the operating signal adjustment potentiometer generates an adjustable analog voltage signal to simulate the actual sensor output, driving the indicator pointer to move, and comparing the value of the digital pressure gauge on the tester with the value of the indicator pointer to determine if it meets the technical specifications; when testing the sensor or performing a joint test, a standard pressure is provided by an external hydraulic source and applied to the sensor, comparing the value of the digital pressure gauge on the tester with the pressure value at the test point in the process manual to determine if it meets the technical specifications; the sensor output electrical signal is measured through the signal voltage test hole, and comparing the voltage measurement value with the check point voltage value in the process manual to determine if it meets the technical specifications.

[0020] Beneficial effects:

[0021] This invention provides a hydraulic testing apparatus for aircraft hydraulic indicators and sensors. By integrating power supply, signal simulation, pressure measurement, electrical parameter measurement, mode control, and interfaces into a standard chassis, and designing it for the specific interfaces and parameters of the target aircraft model, it avoids the need for repeated assembly and disassembly of test circuits. All test items can be completed according to a standardized process simply by connecting the test component through a standard cable. This significantly improves the testing efficiency and quality of dual-combination hydraulic indicators and hydraulic sensors for a certain type of aircraft. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the front panel structure of the tester according to an embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of the rear panel structure of the tester according to an embodiment of the present invention;

[0024] Figure 3 This is a wiring diagram of the rear panel socket of the tester according to an embodiment of the present invention;

[0025] Figure 4 This is a schematic diagram showing the pin connections between the rear panel of the tester and the indicator and sensor according to an embodiment of the present invention.

[0026] Figure 5 This is a block diagram illustrating the principle of the testing apparatus according to an embodiment of the present invention.

[0027] In the diagram: 1-DC voltmeter, 2-DC voltmeter calibration test hole, 3-DC voltmeter calibration switch, 4-DC ammeter, 5-DC ammeter calibration test hole, 6-DC ammeter calibration switch, 7-Digital pressure gauge, 8-Digital pressure gauge calibration test hole, 9-Digital pressure gauge calibration switch, 10-Left / right pointer selection band switch, 11-Signal voltage test hole, 12-220V AC power indicator light, 13-Main power switch, 14-28V DC power indicator light, 15-Voltage test band switch, 16-Illumination pointer selection band 17-Function selection band switch; 18-Signal adjustment potentiometer; 19-Reserved label mounting position; 20-Fuse holder for 5V DC circuit fuse; 21-Fuse holder for 8V DC circuit fuse; 22-Fuse holder for 15V DC circuit fuse; 23-Fuse holder for 28V DC circuit fuse; 24-Fuse holder for 220V AC circuit fuse; 25-220V AC power input socket; 26-Sensor interface socket; 27-Spare socket; 28-Indicator interface socket; 29-Grounding terminal. Detailed Implementation

[0028] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments:

[0029] One embodiment of this utility model is, for example... Figure 1 As shown, a hydraulic testing apparatus for aircraft hydraulic indicators and sensors is characterized by comprising: a chassis, a power module and a control module integrated within the chassis, and a hydraulic pressure source, a precision pressure gauge, and a digital multimeter located outside the chassis; the hydraulic pressure source is an external hydraulic source used to test pressurization when testing brake pressure sensors, and the precision pressure gauge is located at the interface of the hydraulic pressure source to accurately display the pressure of the external hydraulic source;

[0030] The chassis has a front panel and a rear panel, such as Figure 1 and Figure 2 As shown;

[0031] like Figure 1 As shown, the front panel of the chassis is a human-computer interaction interface, and the following components are arranged on the front panel of the chassis according to functional zones:

[0032] Display area: includes DC voltmeter 1, DC ammeter 4, and digital pressure gauge 7. DC voltmeter 1 is used to monitor power output in real time, DC ammeter 4 is used to monitor load current in real time, and digital pressure gauge 7 is used to monitor system pressure in real time.

[0033] Operating area: Includes a main power switch 13, a function selection band switch 17, an illumination pointer selection band switch 16, a voltage test band switch 15, a left / right pointer selection band switch 10, and a core signal adjustment potentiometer 18; the main power switch 13 is used to control the on / off state of the equipment, the function selection band switch 17 is used to switch test modes, the pointer selection band switch 16 is used to control the on / off state of the illumination when working in low-visibility environments at night, the voltage test band switch 15 is used to switch the output voltage, the left / right pointer selection band switch 10 is used to switch between detecting the left and right brake systems, and the signal adjustment potentiometer 18 is used to adjust the simulated pressure signal;

[0034] Test and calibration area: Includes test hole 2 and calibration switch 3 for DC voltmeter 1, test hole 5 and calibration switch 6 for DC ammeter 4, test hole 8 and calibration switch 9 for digital pressure gauge 7, used for equipment self-test; and signal voltage test hole 11, used for connecting an external digital multimeter to measure sensor output signals;

[0035] Status indicator area: Includes 220V AC power indicator 12 and 28V DC power indicator 14;

[0036] like Figure 2 As shown, interface units and protective components are arranged on the rear panel of the chassis, including: a power socket 25 for connecting to an external AC power supply; an indicator interface socket 28 for connecting to the tested dual-combination hydraulic indicator; a sensor interface socket 26 for connecting the left and right wheel brake pressure sensors; a spare socket 27 for subsequent expansion; and a fuse holder 20 for installing a fuse protecting the 5V DC circuit; a fuse holder 21 for installing a fuse protecting the 8V DC circuit; a fuse holder 22 for installing a fuse protecting the 15V DC circuit; a fuse holder 23 for installing a fuse protecting the 28V DC circuit; a fuse holder 24 for installing a fuse protecting the 220V AC input circuit; and a grounding terminal 29. The sensor interface socket 26, indicator interface socket 28, and spare interface socket 27 are all aviation sockets that conform to airborne equipment interface standards.

[0037] The power module is electrically connected to the power input socket, control module, operation display unit and interface unit, and is used to provide various DC operating voltages required by the equipment.

[0038] The control module is electrically connected to the function selection band switch, the pointer selection band switch, the signal conditioning potentiometer, and the interface unit, and is used to control the signal path and test logic according to the operation instructions.

[0039] like Figure 5As shown, the internal working principle of this embodiment is as follows: The external AC220V power supply is converted by the power module to generate various regulated DC power required by the equipment, such as 28V, 8V, 5V, and 15V; the control module receives power from the switches on the front panel and switches the correct power and signal paths to the corresponding interface sockets, such as sockets 28 and 26; when testing the indicator, the operating signal adjustment potentiometer 18 generates an adjustable analog voltage signal to simulate the real sensor output, driving the indicator pointer to move, and comparing the value of the digital pressure gauge 7 on the tester with the value of the indicator pointer to determine whether it meets the technical specifications; when testing the sensor or performing joint testing, the pressure regulation system inside the equipment provides standard pressure from an external hydraulic source and applies it to the sensor, comparing the value of the digital pressure gauge 7 on the tester with the pressure value of the test point in the process manual to determine whether it meets the technical specifications; the sensor output electrical signal is measured through the signal voltage test hole 11, and the voltage measurement value is compared with the check point voltage value in the process manual to determine whether it meets the technical specifications.

[0040] The procedure for testing aircraft hydraulic indicators and sensors using the test apparatus of this embodiment is as follows:

[0041] Step 1: Connect the dual-combination hydraulic indicator under test to socket 28 on the rear panel using a dedicated cable. Connect the left and right wheel brake pressure sensors to socket 26 on the rear panel using a dedicated cable. The wiring and pin connections of the rear panel sockets in this embodiment are as follows: Figure 3 and Figure 4 As shown;

[0042] Step 2: Turn on the main power switch 13;

[0043] Step 3: Individually test the dual-combination hydraulic indicator, including operating voltage testing, indication range testing, and indication error testing. Specifically:

[0044] Working voltage test method: Select the "Indicator" mode through the function selection band switch 17, output 28V voltage through the voltage test switch 15, and observe the DC voltmeter 1. If the DC voltmeter 1 displays DC 28V±2.8V, it meets the technical specifications.

[0045] Indication range test method: Select the "left" position using the left and right pointer selection switch 10, slowly rotate the signal adjustment potentiometer 18, observe the pressure value displayed on the digital pressure gauge 7, and observe the position of the pointer of the indicator being tested. The indication range should be (0~120) kgf / cm². 2 This complies with technical specifications;

[0046] Indication error test method: Select the "left" position by using the left and right pointer selection band switch 10, slowly rotate the signal adjustment potentiometer 18, observe the pressure value displayed on the digital pressure gauge 7, and compare it with the pointer reading of the indicator under test to check whether the error meets the technical specifications.

[0047] Step 4: Test the brake pressure sensor individually, including operating voltage testing and indication error testing. Specifically:

[0048] Working voltage test method: Select "sensor" mode through function selection band switch 17, output 8V voltage through voltage test switch 15, observe DC voltmeter 1. If DC voltmeter 1 displays DC 8V±0.02V, it meets the technical specifications.

[0049] Indication error test method: Select the "right" position using the left and right pointer selector switch 10, open the valve of the external hydraulic source, and pressurize step by step. Record the pressure value of the digital pressure gauge 7 at the check point and compare it with the check point pressure value in the process manual. The error should meet the technical specifications. At the same time, connect a digital multimeter to the signal voltage test port 11 and test the signal voltage output port to obtain the corresponding voltage value. Compare it with the check point voltage value in the process manual. It should meet the technical specifications. When the pressure reaches the highest pressure point, depressurize in sequence and observe the error of the reverse stroke at each check point. It should meet the technical specifications.

[0050] Step 5: Conduct a joint test of the dual-combination hydraulic indicator and brake pressure sensor, mainly to test the indication error. Specifically:

[0051] Select the "right" position using the left and right pointers on band switch 10, and select the "joint test" mode using function selection band switch 17. Open the valve of the hydraulic tester and pressurize step by step. Record the pressure value of the digital pressure gauge 7 at the check point, which should meet the technical specifications. When the pressure reaches the highest pressure point, depressurize in sequence and observe the error of the reverse stroke at each check point, which should meet the technical specifications.

[0052] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention without departing from the principles and spirit of the present invention.

Claims

1. A hydraulic testing apparatus for aircraft hydraulic indicators and sensors, characterized in that: include: The chassis, and the power module and control module integrated within the chassis; The system also includes a hydraulic pressure source, a precision pressure gauge, and a digital multimeter located outside the chassis. The hydraulic pressure source is an external hydraulic source used to test the pressurization when testing the brake pressure sensor. The precision pressure gauge is located at the interface of the hydraulic pressure source and is used to accurately display the pressure of the external hydraulic source. The chassis has a front panel and a rear panel; The front panel of the chassis is a human-machine interface. The following components are arranged functionally on the front panel: Display area: including a DC voltmeter and a DC ammeter for monitoring power output parameters, and a digital pressure gauge for real-time system pressure monitoring; Operation area: including a main power switch for controlling the on / off state of the equipment, a function selection band switch for switching test modes, an illumination pointer selection band switch for controlling the on / off state of the lighting, a voltage test band switch for switching the output voltage, a left / right pointer selection band switch for switching the left and right pointers of the test system, and a signal adjustment potentiometer for adjusting the analog pressure signal; Test and verification area: including test ports and verification switches for the DC voltmeter, the digital pressure gauge, and for equipment self-testing; and a signal voltage test port for connecting an external digital multimeter to measure the sensor output signal; Status indication area: including a 220V AC power indicator and a 28V DC power indicator. The rear panel of the chassis is equipped with interface units and protective components, including: a power socket for connecting an external AC power supply, an indicator interface socket for connecting the tested dual-combination hydraulic indicator, and a sensor interface socket for connecting the left and right wheel brake pressure sensors. And multiple fuse holders and grounding terminals for providing overcurrent protection for the internal DC power supply circuits and AC input circuits; The power module is electrically connected to the power input socket, control module, operation display unit and interface unit, and is used to provide various DC operating voltages required by the equipment. The control module is electrically connected to the function selection band switch, the pointer selection band switch, the signal conditioning potentiometer, and the interface unit, and is used to control the signal path and test logic according to the operation instructions.

2. The hydraulic testing apparatus for aircraft hydraulic indicators and sensors according to claim 1, characterized in that: The multiple fuse holders on the rear panel of the chassis are respectively for installing fuse holders for protecting 5V DC circuits, fuse holders for installing fuse holders for protecting 8V DC circuits, fuse holders for installing fuse holders for protecting 15V DC circuits, fuse holders for installing fuse holders for protecting 28V DC circuits, and fuse holders for installing fuse holders for protecting 220V AC input circuits.

3. The hydraulic testing apparatus for aircraft hydraulic indicators and sensors according to claim 1, characterized in that: The sensor interface socket and indicator interface socket are both aviation sockets that conform to airborne equipment interface standards.

4. A hydraulic testing apparatus for aircraft hydraulic indicators and sensors according to claim 1, characterized in that: When the function selection band switch is in indicator test mode, the signal adjustment potentiometer is used to manually adjust the analog sensor voltage signal output to the indicator interface socket to drive the hydraulic indicator pointer to deflect.

5. A hydraulic testing apparatus for aircraft hydraulic indicators and sensors according to claim 1, characterized in that: The internal working principle of the tester is as follows: An external AC220V power supply is converted by the power module to generate various regulated DC power supplies required by the equipment; the control module receives power from the switches on the front panel and switches the correct power and signal paths to the corresponding interface sockets; when testing the indicator, the operating signal adjustment potentiometer generates an adjustable analog voltage signal to simulate the actual sensor output, driving the indicator pointer to move. The value of the digital pressure gauge on the tester is compared with the value of the indicator pointer to determine whether it meets the technical specifications; when testing the sensor or performing a joint test, a standard pressure is provided by an external hydraulic source and applied to the sensor. The value of the digital pressure gauge on the tester is compared with the pressure value at the test point in the process manual to determine whether it meets the technical specifications. The sensor output electrical signal is measured through the signal voltage test hole. The voltage measurement value is compared with the check point voltage value in the process manual to determine whether it meets the technical specifications.

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