CN212340563U - Air tightness checking system for aircraft - Google Patents
Air tightness checking system for aircraft Download PDFInfo
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- CN212340563U CN212340563U CN202021013332.0U CN202021013332U CN212340563U CN 212340563 U CN212340563 U CN 212340563U CN 202021013332 U CN202021013332 U CN 202021013332U CN 212340563 U CN212340563 U CN 212340563U
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Abstract
The utility model discloses an air tightness checking system for an aircraft, which comprises a front end pressure processing device and a rear end air tightness checking device, wherein the front end pressure processing device is used for cleaning and filtering the pressure provided by an air source and guiding and storing the high-pressure gas; the rear-end air tightness checking device comprises an airplane cabin air tightness checking module, a radar air tightness checking module and a fuel system air tightness checking module, adjusts the pressure of the gas output by the front-end pressure processing device to a target value, and respectively inputs the target value into the airplane cabin air tightness checking module, the radar air tightness checking module and the fuel system air tightness checking module to check the air tightness of the airplane cabin, the radar and the fuel system.
Description
[ technical field ] A method for producing a semiconductor device
The utility model belongs to aeronautical instrument field, concretely relates to combination formula gas tightness detecting system of aircraft cabin gas tightness, radar gas tightness, fuel oil system gas tightness.
[ background of the invention ]
The air tightness inspection of the aircraft cabin, the radar and the fuel system is an important item for the ground guarantee inspection of the aircraft, and the air tightness inspection method aims to perform in-situ inspection on the air tightness of the aircraft cabin system, the radar equipment and the fuel system, prejudge the tightness of the cabin, the radar and the fuel system and prevent the occurrence of air leakage or oil leakage caused by poor air tightness of an oil circuit of the fuel system of the cabin and the radar cavity. At present aircraft cabin, the radar, fuel oil system gas tightness inspection mode is through a movable gas cylinder, link to each other through hose and a pointer manometer, connect the aircraft cabin of hose connection again, the radar, the valve of fuel oil meter, open gas cylinder pressure, give certain pressure value back through aerifing, close the gas cylinder, look over the manometer pressure drop and judge the gas tightness by the mode, its accuracy and reliability are not enough, and to the cabin, the radar, fuel oil system's gas tightness inspection device is independent separately, lack one set of combination formula gas tightness detecting system.
[ Utility model ] content
An object of the utility model is to provide an air tightness detecting system for aircraft for solve the air tightness detecting device of passenger cabin, radar, the fuel oil system of aircraft among the prior art all independent problem separately.
In order to realize the above-mentioned purpose, implement the utility model discloses a gas tightness inspection system for aircraft includes that the pressure that is used for providing the air supply cleans and filters and carries out water conservancy diversion energy storage's front end pressure processing apparatus and rear end gas tightness inspection device to high-pressure gas, rear end gas tightness inspection device includes aircraft cabin gas tightness inspection module, radar gas tightness inspection module and fuel oil system gas tightness inspection module to rear end gas tightness inspection device adjusts the pressure of the gas of front end pressure processing apparatus output to the target value, and inputs aircraft cabin gas tightness inspection module, radar gas tightness inspection module and fuel oil system gas tightness inspection module respectively.
According to the main characteristics, the front end pressure processing device is connected with an air source and comprises an inflation connector, an air filter, a one-way valve, a main switch, an air storage tank, a one-way valve and a switch which are connected in series, wherein the air source is a 10MPa movable nitrogen cylinder, the inflation connector is connected with the air source, the specification of the inflation connector is designed according to the standard of ground support equipment of the airplane, the air filter is arranged at the rear end of the inflation connector and used for filtering various fine impurities in the air source, the one-way valve is arranged at the rear end of the air filter and used for ensuring the one-way flow of the cleaned air in cooperation with the air filter, the main switch is arranged at the rear end of the one-way valve and used for controlling the on-off of an air path at the rear end of the cleaned air source, the air storage tank is used for storing pressure and providing buffer for a rear end system, the one-way valve is arranged, the check valve is arranged at the pressure gauge and is provided with a metering interface for calibrating the pressure gauge.
According to the main characteristics, the airplane cabin air tightness inspection module comprises a pressure regulator, a normally open electromagnetic valve, a switch, a one-way valve, a pressure gauge, an airplane cabin, a pressure sensor, a one-way valve and a controller, wherein one end of the pressure regulator is connected with the front end pressure processing device, the pressure of gas output by the front end pressure processing device is reduced to 1.5MPa after passing through the pressure regulator, the normally open electromagnetic valve is installed at the rear end of the pressure regulator and can be closed when being in an open state in a normal state and receiving a command of the controller, the switch is installed at the rear end of the electromagnetic valve and controls the on-off of the gas, the pressure gauge is installed at the front end of the airplane cabin and is used for indicating the pressure of the gas entering the cabin, the one-way valve is installed at the other end of the pressure gauge and is provided with a metering, the aircraft cabin air tightness checking module is used for controlling the on-off of the normally open electromagnetic valve, and further comprises a safety valve and an air release switch which are installed at the pressure release end of the aircraft cabin.
According to the main characteristics, the radar air tightness checking module comprises a pressure regulator, a normally open electromagnetic valve, a switch, a one-way valve, a pressure sensor, a controller and a safety valve, wherein one end of the pressure regulator is connected with the front end pressure processing device, the pressure of gas output by the front end pressure processing device is reduced to 0.3MPa after passing through the pressure regulator, the normally open electromagnetic valve is installed at the rear end of the pressure regulator and is in an open state in a normal state and can be closed when receiving a command of the controller, the switch is installed at the rear end of the electromagnetic valve to control the on-off of the gas, the pressure sensor is installed at the front end of the radar, the sensor is connected with the controller, the controller can collect and process a signal output by the pressure sensor to control the on-off of the normally open electromagnetic valve, the.
According to the main characteristics, the fuel system air tightness checking module comprises a pressure regulator, a normally open electromagnetic valve, a switch, a one-way valve, a pressure sensor, a controller and a safety valve, wherein one end of the pressure regulator is connected with the front end pressure processing device, the pressure of gas output by the front end pressure processing device is reduced to 1.5MPa after passing through the pressure regulator, the normally open electromagnetic valve is installed at the rear end of the pressure regulator and is in an open state in a normal state and can be closed when receiving a command of the controller, the switch is installed at the rear end of the electromagnetic valve and controls the on-off of the gas, the pressure sensor is installed at the front end of the fuel system, the sensor is connected with the controller, the controller can collect and process a signal output by the pressure sensor and control the on-off of the normally open electromagnetic valve, the.
Compared with the prior art, implement the utility model discloses an air tightness checking system for aircraft detects the integration with aircraft cabin, radar, fuel oil system's gas tightness, so through one set of measurement system alright realize the detection to three module.
[ description of the drawings ]
Fig. 1 is a schematic view of a configuration of a front-end pressure processing device for implementing an air tightness inspection system for an aircraft according to the present invention.
Fig. 2 is a schematic structural view of an aircraft cabin air-tightness inspection module implementing the air-tightness inspection system for aircraft of the present invention.
Fig. 3 is a schematic structural diagram of a radar airtightness detection module for implementing the airtightness inspection system for aircraft according to the present invention.
Fig. 4 is a schematic structural diagram of a fuel system airtightness detection module of an aircraft airtightness inspection system according to the present invention.
[ detailed description ] embodiments
The air tightness checking system for the aircraft comprises a front end pressure processing device and a rear end air tightness checking device, wherein the front end pressure processing device is used for cleaning and filtering the pressure provided by an air source and conducting flow guide and energy storage on high-pressure air; the rear-end air tightness checking device comprises an airplane cabin air tightness checking module, a radar air tightness checking module and a fuel system air tightness checking module, adjusts the pressure of the gas output by the front-end pressure processing device to a target value, and respectively inputs the target value into the airplane cabin air tightness checking module, the radar air tightness checking module and the fuel system air tightness checking module to check the air tightness of the airplane cabin, the radar and the fuel system.
Fig. 1 is a schematic view showing a structure of a front end pressure processing device of an air tightness inspection system for an aircraft according to the present invention. The front end pressure processing device is connected with an air source 11 and comprises an inflation connector 12, an air filter 13, a one-way valve 14, a main switch 15, an air storage tank 16, a one-way valve 17 and a switch 110 which are connected in series, wherein the air source 11 is a 10MPa movable nitrogen cylinder, the inflation connector 12 is connected with the air source 11, the specification of the inflation connector 12 is designed according to the standard of airplane ground support equipment, the air filter 13 is arranged at the rear end of the inflation connector 12 and is used for filtering various fine impurities in the air source, the one-way valve 14 is arranged at the rear end of the air filter 13 and is matched with the air filter 13 to ensure the one-way flow of the cleaned air, the main switch 15 is arranged at the rear end of the one-way valve 14 and is used for controlling the on-off of an air path at the rear end of the cleaned air source, the air storage tank 16 is used for storing pressure and providing buffering for a rear end system, the one-, wherein the pressure gauge 18 is used for measuring the air pressure at the rear end of the air storage tank 16, and the one-way valve 19 is arranged at the pressure gauge 18 and is provided with a metering interface for calibrating the pressure gauge.
Fig. 2 is a schematic structural diagram of an aircraft cabin air tightness checking module for implementing the air tightness checking system for aircraft according to the present invention. The airplane cabin air tightness checking module comprises a pressure regulator 21, a normally open electromagnetic valve 22, a switch 23, a one-way valve 24, a pressure gauge 25, a pressure sensor 27, a one-way valve 28 and a controller 29, wherein one end of the pressure regulator 21 is connected with the front end pressure processing device, the pressure of gas output by the front end pressure processing device is reduced to 1.5MPa after passing through the pressure regulator 21, the normally open electromagnetic valve 22 is installed at the rear end of the pressure regulator 21 and is in an open state in a normal state and can be closed after receiving an instruction of the controller 29, the switch 23 is installed at the rear end of the normally open electromagnetic valve 22 and controls the on-off of the gas, the pressure gauge 25 is installed at the front end of the airplane cabin and is used for indicating the pressure of the gas entering an airplane cabin 26, the one-way valve 24 is installed at the other end of the pressure gauge, the controller 29 collects and processes the signal output by the pressure sensor 27 to control the on/off of the normally open solenoid valve 22, and the cabin airtightness checking module further includes a safety valve 210 and a bleed switch 211 installed at a pressure discharge end (not numbered) of the cabin 26.
Please refer to fig. 3, in order to implement the structural schematic diagram of the radar air tightness detecting module of the air tightness detecting system for aircraft of the present invention, the radar air tightness detecting module includes a pressure regulator 31, a normally open solenoid valve 32, a switch 33, a check valve 34, a pressure sensor 35, a controller 36 and a safety valve 37, wherein one end of the pressure regulator 31 is connected to the front end pressure processing device, the pressure of the gas output by the front end pressure processing device is reduced to 0.3MPa after passing through the pressure regulator 31, the normally open solenoid valve 32 is installed at the rear end of the pressure regulator 31, the normal state is an open state, and the switch 33 can be closed when receiving the instruction of the controller 36, the switch 33 is installed at the rear end of the normally open solenoid valve 32 to control the on-off of the gas, the pressure sensor 35 is installed at the front end of the radar 38, the pressure sensor, the normal open electromagnetic valve 32 is controlled to be switched on and off, the check valve 34 is installed at the other end of the pressure sensor 35, a metering interface is reserved, and the safety valve 37 is installed at the front end of the radar 38 and has an overflow function.
Please refer to fig. 4, which is a schematic structural diagram of a fuel system air-tightness detection module of an air-tightness inspection system for an aircraft according to the present invention. The fuel system air tightness checking module comprises a pressure regulator 41, a normally open electromagnetic valve 42, a switch 43, a check valve 44, a pressure sensor 45, a controller 46 and a safety valve 47, wherein one end of the pressure regulator 41 is connected with the front end pressure processing device, the pressure of gas output by the front end pressure processing device is reduced to 1.5MPa after passing through the pressure regulator 41, the normally open electromagnetic valve 42 is installed at the rear end of the pressure regulator 41 and is in an open state in a normal state and can be closed when receiving an instruction of the controller 46, the switch 43 is installed at the rear end of the normally open electromagnetic valve 42 and controls the on-off of the gas, the pressure sensor 45 is installed at the front end of the fuel system 48, the pressure sensor 45 is connected with the controller 46, the controller 46 can collect and process signals output by the pressure sensor 45 and control the on-off of the normally open electromagnetic valve 42, the check valve 44, has the function of overflow.
When the test method is specifically implemented, the utility model discloses a test method that air tightness inspection is carried out to aircraft cabin, radar and fuel oil system to air tightness inspection system for the aircraft is as follows.
The method for testing the air tightness of the aircraft cabin comprises the following steps: opening the gas source, the main switch 15 and the switch 110, closing the switch 33 and the switch 43, adjusting the pressure of the front end to 3.0MPa, enabling the high-pressure gas to flow out of the front-end pressure processing device to reach the pressure regulator 21, and reducing the pressure of the high-pressure gas passing through the pressure regulator 2 to 1.5 MPa; 1.5MPa compressed gas is led to an airplane cabin through a normally open electromagnetic valve, a switch 23 and a pressure 25 meter, the gas is led out after passing through the cabin and is connected with a pressure sensor 27 with display and feedback functions, when the pressure sensor detects that the gas pressure is greater than 0.037MPa, the sensor automatically sends an output signal to a controller 29, the controller outputs a control signal to close the normally open electromagnetic valve, at the moment, the pressure source of a cabin pressure measurement module is cut off, the time that the indication value of the pressure sensor 27 is reduced to 0.001MPa from 0.029MPa is measured by a stopwatch, no less than 5min is needed, and otherwise, the reason that the air tightness in the airplane cabin is poor is needed to be searched and eliminated.
The method for testing the air tightness of the radar comprises the following steps: and opening the gas source, the main switch 15 and the switches 1-10, closing the switch 23 and the switch 43, adjusting the pressure of the front end to 1.0MPa, enabling the high-pressure gas to flow out of the front end pressure processing device to reach the pressure regulator 31, and reducing the pressure of the high-pressure gas passing through the pressure regulator 31 to 0.3 MPa. The 0.3MPa compressed gas is led to an onboard radar system through a normally open electromagnetic valve 32, a switch 33, a pressure sensor 35 with display and feedback functions and a safety valve 37, when the pressure sensor 35 detects that the gas pressure is greater than 0.13MPa, the sensor automatically gives an output signal to a controller, the controller outputs a control signal to close the normally open electromagnetic valve 32, at the moment, the pressure source of the radar pressure measurement subsystem is cut off, the indicating value of the pressure sensor 35 is measured by a stopwatch, the pressure is kept for 30min, and the pressure drop is not greater than 0.015 MPa.
The method for testing the air tightness of the fuel system comprises the following steps: and opening the gas source, the main switch 15 and the switch 110, closing the switch 23 and the switch 33, adjusting the pressure of the front end to 3.0MPa, enabling the high-pressure gas to flow out of the front-end pressure processing device to reach the pressure regulator 41, and reducing the pressure of the high-pressure gas passing through the pressure regulator 41 to 1.5 MPa. 1.5MPa compressed gas leads to a fuel oil system through a normally open electromagnetic valve 42, a switch 43, a pressure sensor 45 with display and feedback functions and a safety valve 47, when the pressure sensor 45 detects that the gas pressure is greater than 0.86MPa, the sensor automatically gives an output signal to a controller, the controller outputs a control signal to close the normally open electromagnetic valve 42, at the moment, the pressure source of a radar pressure measurement subsystem is cut off, the indicating value of the pressure sensor 45 is measured by a stopwatch, the pressure is kept for 30min, and the pressure drop is not greater than 0.015 MPa.
Compared with the prior art, implement the utility model discloses an air tightness checking system for aircraft detects the integration with aircraft cabin, radar, fuel oil system's gas tightness, so through one set of measurement system alright realize the detection to three module. And simultaneously, implement the utility model discloses a gas tightness checking system for aircraft adopts sensor acquisition control module to realize the automatic control of measuring pressure to the safety overflow valve is installed to the measurement system rear end, prevents that the too big harm aircraft inner device of testing pressure, and moreover each manometer and sensor all leave metering interface, and the later stage of being convenient for is markd.
It should be understood that equivalent alterations and modifications can be made by those skilled in the art according to the technical solution of the present invention and the inventive concept thereof, and all such alterations and modifications should fall within the scope of the appended claims.
Claims (7)
1. The air tightness checking system for the aircraft is characterized by comprising a front end pressure processing device and a rear end air tightness checking device, wherein the front end pressure processing device and the rear end air tightness checking device are used for cleaning and filtering pressure provided by a gas source and conducting diversion and energy storage on high-pressure gas, the rear end air tightness checking device comprises an aircraft cabin air tightness checking module, a radar air tightness checking module and a fuel oil system air tightness checking module, and the rear end air tightness checking device adjusts the pressure of the gas output by the front end pressure processing device to a target value and inputs the target value to the aircraft cabin air tightness checking module, the radar air tightness checking module and the fuel oil system air tightness checking module respectively.
2. The air tightness checking system for aircraft according to claim 1, wherein: front end pressure processing apparatus is connected with the air supply, including the inflation connector of establishing ties, the air filter, the check valve, master switch, the gas holder, check valve and switch, wherein the air supply is 10MPa movable nitrogen cylinder, the inflation connector is connected with the air supply, the air filter is installed in inflation connector rear end, the check valve is installed in the air filter rear end, the master switch is in the check valve rear end, the break-make of control clean air supply rear end gas circuit, the gas holder is used for providing the buffering for back-end system storage pressure, the check valve is installed in the gas holder rear end.
3. The air tightness checking system for aircraft according to claim 2, wherein: the front-end pressure processing device also comprises a pressure gauge and a one-way valve, wherein the pressure gauge is used for measuring the air pressure at the rear end of the air storage tank, and the one-way valve is arranged at the pressure gauge and is provided with a metering interface.
4. The air tightness checking system for aircraft according to claim 3, wherein: this aircraft cabin gas tightness inspection module includes voltage regulator, normally open solenoid valve, switch, check valve, manometer, aircraft cabin, pressure sensor, check valve, controller, wherein voltage regulator one end with front end pressure processing apparatus connects, the pressure drops to 1.5MPa behind the gas of front end pressure processing apparatus output through the voltage regulator, and normally open solenoid valve installs in the voltage regulator rear end, and the normality is the open mode, can close when receiving the controller instruction, and the switch mounting is in the solenoid valve rear end, and the manometer is installed in aircraft cabin front end, and the check valve is installed at the manometer other end, leaves the measurement interface, and pressure sensor is installed to the aircraft cabin other end to leave the measurement interface, sensor connection director.
5. The air tightness checking system for aircraft according to claim 4, wherein: the aircraft cabin air tightness checking module also comprises a safety valve and an air release switch which are arranged at the pressure release end of the aircraft cabin.
6. The air tightness checking system for aircraft according to claim 5, wherein: the radar gas tightness inspection module comprises a pressure regulator, a normally open electromagnetic valve, a switch, a one-way valve, a pressure sensor, a controller and a safety valve, wherein one end of the pressure regulator is connected with the front end pressure processing device, the pressure of gas output by the front end pressure processing device is reduced to 0.3MPa after passing through the pressure regulator, the normally open electromagnetic valve is installed at the rear end of the pressure regulator, the normally open electromagnetic valve is in an open state and can be closed when receiving a controller instruction, the switch is installed at the rear end of the electromagnetic valve to control the on-off of gas, the pressure sensor is installed at the front end of the radar, the sensor is connected with the controller, the one-way valve is installed at the.
7. The air tightness checking system for aircraft according to claim 6, wherein: the fuel system gas tightness inspection module comprises a pressure regulator, a normally open electromagnetic valve, a switch, a one-way valve, a pressure sensor, a controller and a safety valve, wherein one end of the pressure regulator is connected with the front end pressure processing device, the pressure of gas output by the front end pressure processing device is reduced to 1.5MPa after passing through the pressure regulator, the normally open electromagnetic valve is installed at the rear end of the pressure regulator and is in an open state in a normal state, the switch is installed at the rear end of the electromagnetic valve, the pressure sensor is installed at the front end of the fuel system, the sensor is connected with the controller, the one-way valve is installed at the other end of the sensor and is.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021013332.0U CN212340563U (en) | 2020-06-05 | 2020-06-05 | Air tightness checking system for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021013332.0U CN212340563U (en) | 2020-06-05 | 2020-06-05 | Air tightness checking system for aircraft |
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| CN212340563U true CN212340563U (en) | 2021-01-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202021013332.0U Active CN212340563U (en) | 2020-06-05 | 2020-06-05 | Air tightness checking system for aircraft |
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| CN (1) | CN212340563U (en) |
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- 2020-06-05 CN CN202021013332.0U patent/CN212340563U/en active Active
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