CN113466682A - Airplane product pressure given test equipment and test method - Google Patents
Airplane product pressure given test equipment and test method Download PDFInfo
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- CN113466682A CN113466682A CN202110636942.9A CN202110636942A CN113466682A CN 113466682 A CN113466682 A CN 113466682A CN 202110636942 A CN202110636942 A CN 202110636942A CN 113466682 A CN113466682 A CN 113466682A
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- 238000009530 blood pressure measurement Methods 0.000 claims description 3
- 230000008569 process Effects 0.000 description 6
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- 239000003921 oil Substances 0.000 description 2
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- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/327—Testing of circuit interrupters, switches or circuit-breakers
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
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Abstract
The invention relates to the technical field of airplane product equipment detection, in particular to airplane product pressure setting test equipment and a test method, wherein the test equipment comprises an industrial computer, a power supply module and a display which are connected with the industrial computer, a data acquisition board card connected with the industrial computer, a voltage transmitter and a current transmitter connected with the data acquisition board card, a test circuit module connected with the voltage transmitter and the current transmitter, and a product interface circuit connected with the test circuit module, wherein the data acquisition board card, the voltage transmitter and the test circuit module are respectively connected with the power supply module; the industrial computer is connected with a dynamic and static pressure detection system, and the dynamic and static pressure detection system comprises an ARM processor connected with the industrial computer and a power module, an acquisition circuit connected with the ARM processor, and a test gas circuit connected with the acquisition circuit. The invention solves the problems of time and labor consumption, large test error and the like in manual test.
Description
Technical Field
The invention relates to the technical field of airplane product equipment detection, in particular to airplane product pressure given testing equipment and a testing method.
Background
The pressure relay detection equipment (hereinafter referred to as detection equipment) is designed according to the repair technical conditions of an XXX type pressure relay comprehensive measuring instrument (hereinafter referred to as pressure relay), and meets the requirement of the pressure relay on periodic off-position inspection. The pressure relay does not work for a long time when the airplane normally flies at ordinary times and is only used for outputting an electric signal to the seat guide plate blasting valve when the seat is ejected, so that the function or performance of the product is difficult to find out in daily airplane and ground maintenance; the pressure relay ensures that the pilot is not blown by airflow to be injured when the high-speed ejection lifesaving is carried out; when the medium-low speed ejection lifesaving device is used for lifesaving, the guide plate does not extend out, so that the reliability of people/chair separation is prevented from being influenced by the extension of the guide plate. The product is closely related to the life of a pilot, and the working performance of the product is ensured to be normal; the pressure relay has inherent law of performance reduction (such as component aging, parameter drift and the like) along with the increase of calendar age, and the pressure relay is required to be regularly detected.
However, the conventional means for detecting the pressure relay of the type is manual test, and the defects are mainly as follows: 1. the time and the labor are consumed, the testing process is more, the air pressure requirement precision is high, and the manual testing error is larger; 2. under the condition that the given air pressure value is low according to the test requirement, the pressure precision requirement is high, and the existing means is difficult to slowly and accurately pressurize the product; 3. in the product detection process, the closing of the control electromagnetic valve is completely manually guided, and time delay exists, so that the validity of the detection result is inconsistent.
After investigation, all systems and repair shops at present have no automatic test equipment. Therefore, the method for testing the pressure setting of the aircraft product is provided, and an automatic testing device is developed to meet the requirement that the pressure relay is required to be periodically subjected to off-position inspection.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a device and a method for testing the pressure setting of an aircraft product.
The technical problem to be solved by the invention is realized by adopting the following technical scheme:
the aircraft product pressure setting test equipment comprises an industrial computer, a power module and a display, wherein the power module and the display are connected with the industrial computer, the aircraft product pressure setting test equipment also comprises a data acquisition board card connected with the industrial computer, a voltage transmitter and a current transmitter connected with the data acquisition board card, a test circuit module connected with the voltage transmitter and the current transmitter, and a product interface circuit connected with the test circuit module, wherein the data acquisition board card, the voltage transmitter and the test circuit module are respectively connected with the power module;
the industrial computer is connected with a dynamic and static pressure detection system, the dynamic and static pressure detection system comprises an ARM processor connected with the industrial computer and a power module, an acquisition circuit connected with the ARM processor, and a test gas circuit connected with the acquisition circuit, and the test gas circuit comprises static pressure output and dynamic pressure output connected with a pressure relay.
Furthermore, the acquisition circuit comprises a sensor acquisition circuit connected with the ARM processor, a static pressure sensor and a dynamic pressure sensor which are connected with the sensor acquisition circuit, and the static pressure sensor and the dynamic pressure sensor are respectively connected with the test gas circuit.
Furthermore, the test gas circuit comprises a pressure source, a pressure buffer connected with the pressure source and a manual pressure switch connected with the pressure buffer, the static pressure output and the dynamic pressure output are respectively connected with the manual pressure switch, the static pressure sensor is connected between the static pressure output and the manual pressure switch, and the dynamic pressure sensor is connected between the dynamic pressure output and the manual pressure switch.
Further, the pressure source includes vacuum pump and the negative pressure gas holder that is used for testing static pressure, a force pump and the malleation gas holder that are used for testing the dynamic pressure, the force pump is connected with pump control circuit, malleation gas tank connection has pressure sensor, pressure sensor and pump control circuit are connected, pump control circuit has and controls the force pump according to set pressure measured value and set pressure value and open and stop the function, negative pressure gas holder, malleation gas holder are connected with pressure buffer.
Further, the manual pressure switch comprises an evacuation switch connected between the negative pressure gas storage tank and the pressure buffer, a pressurizing switch connected between the positive pressure gas storage tank and the pressure buffer, a combined switch connected with the vacuum pump and the pressure pump, and an air release switch respectively connected with the vacuum pump and the pressure pump, wherein the static pressure sensor is connected between the static pressure output and the evacuation switch, and the dynamic pressure sensor is connected between the dynamic pressure output and the pressurizing switch.
A test method for applying pressure to given test equipment of an aircraft product comprises automatic test and manual test, wherein the automatic test comprises the following specific steps:
the method comprises the following steps that (I) equipment is powered on, all modules are completely and correctly connected, test software is started, and a system and a serial port are initialized;
performing self-inspection on the hardware system of the equipment, calling a display interface if the self-inspection is passed, and returning to the step (I) for reinitialization if the self-inspection is not passed;
(III) selecting the test items, wherein the selection items comprise: allowable error and power test, dynamic pressure air tightness test and static pressure air tightness test;
(IV) clicking to select the allowable error and power test:
(a) the dynamic pressure output on the dynamic and static pressure system is communicated with a port P of the pressure relay through a connecting pipeline;
(b) communicating an electrical interface of an electrical system with a pressure relay through a cable;
(c) closing the combined switch and opening the pressure pump switch;
(d) when the pressure is slowly increased to a value X1kpa, the pressure relay is required to be operated, the signal lamp is extinguished, the power value is read and is not more than 0.5W, the pressure is continuously increased to X2kpa, the pressure is kept for 1min, then the pressure is reduced to (X1 +/-0.784) kpa, the pressure relay is required to be operated, the signal lamp is required to be lightened, and the power value is read and is not more than 2W;
(e) judging whether the test index is qualified or not by the software, if so, storing test data, and releasing pressure and exiting the software by the system; if not, the software forcibly stops testing, and the system releases pressure;
and (V) when a dynamic pressure airtightness test is selected by clicking:
(A) the dynamic pressure output on the dynamic and static pressure system is communicated with a port P of the pressure relay through a connecting pipeline;
(B) closing the combined switch and opening the pressure pump switch;
(C) slowly increasing the pressure to X3kpa, maintaining the pressure for 3min, wherein the pressure is not reduced;
(D) judging whether the test index is qualified or not by the software, if so, storing test data, and releasing pressure and exiting the software by the system; if not, the software forcibly stops testing, and the system releases pressure;
and (VI) clicking to select the static pressure airtightness test:
(S1) communicating the dynamic pressure output on the dynamic and static pressure system with the port P and the port S of the pressure relay through a connecting pipeline;
(s2) closing the combination switch and opening the pressure pump switch;
(s3) slowly increasing the pressure to X4kpa, and keeping the pressure for 2min, wherein the pressure should not be reduced;
(s4) judging whether the test index is qualified by the software, if so, storing test data, and releasing pressure of the system and exiting the software; if not, the software forcibly stops testing, and the system is decompressed.
Further, the specific steps of manual testing are as follows:
(1) selecting to enter a manual test page;
(2) the system automatically clears the data format and sends an instruction for the first time;
(3) selecting to set dynamic pressure or total pressure according to requirements;
(4) after the sending setting is finished, selecting a specific set pressure value according to the test requirement, and executing;
(5) and after the test is finished, the system releases the pressure, initializes the content of the manual test item and exits from the manual test page.
The invention has the beneficial effects that:
1. the problems of time and labor consumption, large test error and the like in manual test are solved; 2. the automatic testing software is innovatively developed in combination with the product testing process, so that automatic testing is realized; 3. the core component with more reliable performance is innovatively selected, and the problem that under the condition of a given low air pressure value, the product is slowly and accurately pressurized through program control to meet the requirement of a test process is solved through upper computer software programming; 4. the key electromagnetic valve is controlled by innovatively using the solid-state relay with extremely low on-off delay, and the validity of a detection result caused by the closing time delay of the electric control electromagnetic valve in the product detection process is solved.
Drawings
The invention is further illustrated with reference to the following figures and examples:
FIG. 1 is a schematic diagram of the electrical system of the apparatus of the present invention;
FIG. 2 is a schematic diagram of the structure of the dynamic and static pressure detecting system according to the present invention;
FIG. 3 is a schematic diagram of a testing gas circuit of the dynamic and static pressure detection system of the present invention;
FIG. 4 is a flowchart of a main process of the testing method of the present invention;
FIG. 5 is a flow chart of an automatic test in the test method of the present invention;
FIG. 6 is a flow chart of a manual test in the test method of the present invention;
FIG. 7 is a schematic diagram of the allowable error and power test in the test method of the present invention;
FIG. 8 is a schematic view of a static pressure airtightness test in the test method of the present invention.
Detailed Description
In order to make the technical means, the creation features, the achievement purposes and the effects of the invention easy to understand, the invention is further explained in the following with the accompanying drawings and the embodiments.
As shown in fig. 1 to 3, an aircraft product pressure setting test device includes an industrial computer, a power module and a display connected to the industrial computer, and further includes a data acquisition board connected to the industrial computer, a voltage transmitter and a current transmitter connected to the data acquisition board, a test circuit module connected to the voltage transmitter and the current transmitter, and a product interface circuit connected to the test circuit module, where the data acquisition board, the voltage transmitter, and the test circuit module are respectively connected to the power module;
the industrial computer is connected with a dynamic and static pressure detection system, the dynamic and static pressure detection system comprises an ARM processor connected with the industrial computer and a power module, an acquisition circuit connected with the ARM processor, and a test gas circuit connected with the acquisition circuit, and the test gas circuit comprises static pressure output and dynamic pressure output connected with a pressure relay.
As a further improvement of the invention, the acquisition circuit comprises a sensor acquisition circuit connected with the ARM processor, a static pressure sensor and a dynamic pressure sensor which are connected with the sensor acquisition circuit, and the static pressure sensor and the dynamic pressure sensor are respectively connected with the test gas circuit.
As a further improvement of the invention, the test gas path comprises a pressure source, a pressure buffer connected with the pressure source and a manual pressure switch connected with the pressure buffer, wherein the static pressure output and the dynamic pressure output are respectively connected with the manual pressure switch, the static pressure sensor is connected between the static pressure output and the manual pressure switch, and the dynamic pressure sensor is connected between the dynamic pressure output and the manual pressure switch.
As a further improvement of the invention, the pressure source comprises a vacuum pump and a negative pressure air storage tank for testing static pressure, a pressure pump and a positive pressure air storage tank for testing dynamic pressure, the pressure pump is connected with a pump control circuit, the positive pressure air storage tank is connected with a pressure sensor, the pressure sensor is connected with the pump control circuit, the pump control circuit has a function of controlling the pressure pump to start and stop according to a set pressure measurement value and a set pressure value, and the negative pressure air storage tank and the positive pressure air storage tank are connected with a pressure buffer.
As a further improvement of the invention, the manual pressure switch comprises an evacuation switch connected between the negative pressure air storage tank and the pressure buffer, a pressurization switch connected between the positive pressure air storage tank and the pressure buffer, a combined switch for connecting the vacuum pump and the pressure pump, and an air release switch respectively connected with the vacuum pump and the pressure pump, wherein the static pressure sensor is connected between the static pressure output and the evacuation switch, and the dynamic pressure sensor is connected between the dynamic pressure output and the pressurization switch.
Specifically, the portable suitcase structure design is adopted on the whole equipment, and the portable suitcase has the characteristics of convenience in carrying, firm structure, strong adaptability to working environment and the like. The measurement and control software in the equipment is developed and designed by using LabWindows/CVI under a Windows7 operating system, and the software design meets the requirements of simple operation and convenient use.
The industrial computer, the power module, the display, the data acquisition board card, the voltage transmitter, the current transmitter, the test circuit module and the product interface circuit form an electrical system in the equipment, and the equipment is closely matched with the dynamic and static pressure detection system through the electrical system to complete the function test of the pressure relay.
The industrial computer adopts a porphyrized ARK-1122 series ultra-small size extensible low-power-consumption fan-free embedded industrial personal computer, the model adopts an Intel AtomN2600/N2800 dual-core processor (with the frequency of 1.6GHz or 1.8 GHz), and the power consumption is only 10 watts.
The dynamic and static pressure detection system further comprises an interface board, a display unit and a keyboard, the interface board adopts an MSP430+ FPGA platform, the MSP430 is provided with 4 RS232 ports, the FPGA selects EP1K30TI144 of Altera company, the testing requirements can be met, and the ARM processor is connected with an industrial computer through the RS232 ports.
The ARM processor has the advantages of high response speed, rich resources and good stability.
The vacuum pump is manufactured by KNF company and is of the model number NPK 813. The technical parameters of the vacuum pump are as follows: no oil pump; working voltage: 24 VDC; flow rate: 13L/min; working temperature: 0-40 ℃; weight: 2.4 kg; interface: 1/8 RC. The pressure pump is manufactured by KNF company, and has the model number: NPK09 DC.
The technical parameters of the pressure pump are as follows: no oil pump; working voltage: 24 VDC; flow rate: 15L/min; working temperature: 0-40 ℃; maximum pressure: 7 Bar; weight: 1.8 kg; interface: 1/8 RC.
The pressure sensor is used for measuring atmospheric pressure, and the key characteristics of the pressure sensor are high accuracy and working range of measurement. Silicon resonant pressure sensors of GE-DRUCK, USA, are selected.
The dynamic and static pressure detection system generates a pressure source required by system testing through a built-in vacuum pump and a pressure pump, and the system pressure is changed by adjusting the opening of a manual pressure switch to finish the testing work; the sensor acquisition circuit samples frequency signals of the static pressure sensor and the total pressure sensor, calculates the frequency signals into pressure values, transmits the pressure values to the ARM processor, and the ARM processor performs corresponding atmosphere calculation and transmits the pressure values to the display unit; the ARM processor coordinates all the peripheral equipment to receive input signals of the keyboard and completes data acquisition and display, working state indication and the like.
As shown in fig. 3, a vacuum pump and a pressure pump are arranged in the dynamic and static pressure detection system to provide a pressure source required by the system for testing, the vacuum pump is controlled by a pump switch, and after the switch is turned on, the vacuum pump discharges air in the negative pressure air storage tank; the pressure pump is controlled by a pump control circuit, a pressure sensor is designed at the end of the positive pressure gas storage tank and used for measuring the pressure in the positive pressure gas storage tank, the microcontroller carries out logic criterion and controls the start and stop of the pressure pump according to the pressure measurement value and a set pressure value, the pressure pump is started when the pressure value is less than 5.5kg, and the pressure pump is stopped when the pressure value is more than 6.5 kg; the pressure of static pressure output and dynamic pressure output can be adjusted by adjusting the pressurizing switch and the evacuating switch, and the pressure of static pressure output and dynamic pressure output can be communicated to the atmosphere by opening the deflating switch.
A test method for applying pressure to given test equipment of an aircraft product comprises automatic test and manual test, wherein the automatic test comprises the following specific steps:
the method comprises the following steps that (I) equipment is powered on, all modules are completely and correctly connected, test software is started, and a system and a serial port are initialized;
performing self-inspection on the hardware system of the equipment, calling a display interface if the self-inspection is passed, and returning to the step (I) for reinitialization if the self-inspection is not passed;
(III) selecting the test items, wherein the selection items comprise: allowable error and power test, dynamic pressure air tightness test and static pressure air tightness test;
(IV) clicking to select the allowable error and power test:
(a) the dynamic pressure output on the dynamic and static pressure system is communicated with a port P of the pressure relay through a connecting pipeline;
(b) communicating an electrical interface of an electrical system with a pressure relay through a cable;
(c) closing the combined switch and opening the pressure pump switch;
(d) when the pressure is slowly increased to a value X1kpa, the pressure relay is required to be operated, the signal lamp is extinguished, the power value is read and is not more than 0.5W, the pressure is continuously increased to X2kpa, the pressure is kept for 1min, then the pressure is reduced to (X1 +/-0.784) kpa, the pressure relay is required to be operated, the signal lamp is required to be lightened, and the power value is read and is not more than 2W;
(e) judging whether the test index is qualified or not by the software, if so, storing test data, and releasing pressure and exiting the software by the system; if not, the software forcibly stops testing, and the system releases pressure;
and (V) when a dynamic pressure airtightness test is selected by clicking:
(A) the dynamic pressure output on the dynamic and static pressure system is communicated with a port P of the pressure relay through a connecting pipeline;
(B) closing the combined switch and opening the pressure pump switch;
(C) slowly increasing the pressure to X3kpa, maintaining the pressure for 3min, wherein the pressure is not reduced;
(D) judging whether the test index is qualified or not by the software, if so, storing test data, and releasing pressure and exiting the software by the system; if not, the software forcibly stops testing, and the system releases pressure;
and (VI) clicking to select the static pressure airtightness test:
(S1) communicating the dynamic pressure output on the dynamic and static pressure system with the port P and the port S of the pressure relay through a connecting pipeline;
(s2) closing the combination switch and opening the pressure pump switch;
(s3) slowly increasing the pressure to X4kpa, and keeping the pressure for 2min, wherein the pressure should not be reduced;
(s4) judging whether the test index is qualified by the software, if so, storing test data, and releasing pressure of the system and exiting the software; if not, the software forcibly stops testing, and the system is decompressed.
As a further improvement of the invention, the purpose of manual testing is to facilitate the testers to test the product independently and compare data conveniently, the manual testing adopts a control instruction generation mode, a single instruction executes a single step, the instruction is generated and sent to an industrial computer, and the industrial computer feeds back the generated instruction to a dynamic and static pressure system to set or give the corresponding air pressure.
The manual test comprises the following specific steps:
(1) selecting to enter a manual test page;
(2) the system automatically clears the data format and sends an instruction for the first time;
(3) selecting to set dynamic pressure or total pressure according to requirements;
(4) after the sending setting is finished, selecting a specific set pressure value according to the test requirement, and executing;
(5) and after the test is finished, the system releases the pressure, initializes the content of the manual test item and exits from the manual test page.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. The utility model provides an aircraft product pressure gives test equipment, includes industrial computer, the power module and the display that are connected with industrial computer, its characterized in that: the industrial computer power supply also comprises a data acquisition board card connected with the industrial computer, a voltage transmitter and a current transmitter connected with the data acquisition board card, a test circuit module connected with the voltage transmitter and the current transmitter, and a product interface circuit connected with the test circuit module, wherein the data acquisition board card, the voltage transmitter and the test circuit module are respectively connected with the power supply module;
the industrial computer is connected with a dynamic and static pressure detection system, the dynamic and static pressure detection system comprises an ARM processor connected with the industrial computer and a power module, an acquisition circuit connected with the ARM processor, and a test gas circuit connected with the acquisition circuit, and the test gas circuit comprises static pressure output and dynamic pressure output connected with a pressure relay.
2. An aircraft product pressure setting test apparatus as defined in claim 1, wherein: the acquisition circuit comprises a sensor acquisition circuit connected with the ARM processor, a static pressure sensor and a dynamic pressure sensor, wherein the static pressure sensor and the dynamic pressure sensor are connected with the sensor acquisition circuit and are respectively connected with the test gas circuit.
3. An aircraft product pressure setting test apparatus as defined in claim 2, wherein: the testing gas circuit comprises a pressure source, a pressure buffer connected with the pressure source and a manual pressure switch connected with the pressure buffer, wherein static pressure output and dynamic pressure output are respectively connected with the manual pressure switch, a static pressure sensor is connected between the static pressure output and the manual pressure switch, and a dynamic pressure sensor is connected between the dynamic pressure output and the manual pressure switch.
4. An aircraft product pressure setting test apparatus as defined in claim 3, wherein: the pressure source is including vacuum pump and the negative pressure gas holder that is used for testing static pressure, a force pump and the malleation gas holder that is used for testing the dynamic pressure, the force pump is connected with pump control circuit, malleation gas tank connection has pressure sensor, pressure sensor and pump control circuit are connected, pump control circuit has and controls the force pump according to setting for pressure measurement value and setting for the pressure value and open and stop the function, negative pressure gas holder, malleation gas holder are connected with pressure buffer.
5. An aircraft product pressure setting test apparatus as defined in claim 3, wherein: the manual pressure switch comprises an evacuation switch connected between the negative pressure gas storage tank and the pressure buffer, a pressurizing switch connected between the positive pressure gas storage tank and the pressure buffer, a combined switch connected with the vacuum pump and the pressure pump, and an air release switch respectively connected with the vacuum pump and the pressure pump, wherein the static pressure sensor is connected between the static pressure output and the evacuation switch, and the dynamic pressure sensor is connected between the dynamic pressure output and the pressurizing switch.
6. A test method using the aircraft product pressure setting test device of any one of claims 1 to 5, characterized by: the method comprises automatic testing and manual testing, wherein the automatic testing comprises the following specific steps:
the method comprises the following steps that (I) equipment is powered on, all modules are completely and correctly connected, test software is started, and a system and a serial port are initialized;
performing self-inspection on the hardware system of the equipment, calling a display interface if the self-inspection is passed, and returning to the step (I) for reinitialization if the self-inspection is not passed;
(III) selecting the test items, wherein the selection items comprise: allowable error and power test, dynamic pressure air tightness test and static pressure air tightness test;
(IV) clicking to select the allowable error and power test:
(a) the dynamic pressure output on the dynamic and static pressure system is communicated with a port P of the pressure relay through a connecting pipeline;
(b) communicating an electrical interface of an electrical system with a pressure relay through a cable;
(c) closing the combined switch and opening the pressure pump switch;
(d) when the pressure is slowly increased to a value X1kpa, the pressure relay is required to be operated, the signal lamp is extinguished, the power value is read and is not more than 0.5W, the pressure is continuously increased to X2kpa, the pressure is kept for 1min, then the pressure is reduced to (X1 +/-0.784) kpa, the pressure relay is required to be operated, the signal lamp is required to be lightened, and the power value is read and is not more than 2W;
(e) judging whether the test index is qualified or not by the software, if so, storing test data, and releasing pressure and exiting the software by the system; if not, the software forcibly stops testing, and the system releases pressure;
and (V) when a dynamic pressure airtightness test is selected by clicking:
(A) the dynamic pressure output on the dynamic and static pressure system is communicated with a port P of the pressure relay through a connecting pipeline;
(B) closing the combined switch and opening the pressure pump switch;
(C) slowly increasing the pressure to X3kpa, maintaining the pressure for 3min, wherein the pressure is not reduced;
(D) judging whether the test index is qualified or not by the software, if so, storing test data, and releasing pressure and exiting the software by the system; if not, the software forcibly stops testing, and the system releases pressure;
and (VI) clicking to select the static pressure airtightness test:
(S1) communicating the dynamic pressure output on the dynamic and static pressure system with the port P and the port S of the pressure relay through a connecting pipeline;
(s2) closing the combination switch and opening the pressure pump switch;
(s3) slowly increasing the pressure to X4kpa, and keeping the pressure for 2min, wherein the pressure should not be reduced;
(s4) judging whether the test index is qualified by the software, if so, storing test data, and releasing pressure of the system and exiting the software; if not, the software forcibly stops testing, and the system is decompressed.
7. A test method using an aircraft product pressure setting test device according to claim 6, wherein: the manual test comprises the following specific steps:
(1) selecting to enter a manual test page;
(2) the system automatically clears the data format and sends an instruction for the first time;
(3) selecting to set dynamic pressure or total pressure according to requirements;
(4) after the sending setting is finished, selecting a specific set pressure value according to the test requirement, and executing;
(5) and after the test is finished, the system releases the pressure, initializes the content of the manual test item and exits from the manual test page.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113867433A (en) * | 2021-11-09 | 2021-12-31 | 中国航空工业集团公司北京长城计量测试技术研究所 | Double-channel atmospheric parameter pressure control gas circuit and adjusting method |
| CN115656787A (en) * | 2022-12-21 | 2023-01-31 | 巨翊医疗科技(苏州)有限公司 | Testing device and method for PCBA with negative pressure sensor and infrared sensor |
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