An electronic aircraft cockpit emergency exit system inspection device

Abstract

The invention discloses an electronic aircraft cockpit emergency exit system inspection device, comprising a vehicle body system, an air pressure system, an instrument control and electrical system, and an onboard pressure monitoring and deflation system. The vehicle body system comprises: a chassis, a box body connected to the chassis, the four end faces of the box body are connected to each other in a hinged manner and are provided with maintenance doors, a handle is provided on the left side of the box body, two universal wheels and two directional wheels are symmetrically provided on the chassis, the air pressure system comprises: a nitrogen charging interface, a one-way valve connected to the nitrogen charging interface, an empty first metering interface connected to the one-way valve, a first pressure sensor connected to a primary safety valve, a first solenoid valve and a first stop valve connected to the primary safety valve, and a pressure reducing valve connected to the first solenoid valve and the first stop valve, the instrument control and electrical system comprises: an electrical control cabinet and an operation panel, and the onboard pressure monitoring and deflation system comprises a third rubber hose and a third pressure sensor connected to the third rubber hose.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft cockpit emergency exit systems, and in particular to electronic aircraft cockpit emergency exit system inspection equipment. Background Art

[0002] As an important measure for pilots to escape, the detection of its technical indicators has become an important part of the aircraft assembly process. With the improvement of relevant inspection requirements, the current support equipment cannot meet the requirements of high-precision and automated inspection and testing, and an electronic aircraft cockpit emergency exit system inspection equipment is also needed. For this purpose, an electronic aircraft cockpit emergency exit system inspection equipment is specially designed for use. Summary of the invention

[0003] The purpose of the present invention is to provide an electronic aircraft cockpit emergency exit system inspection device to solve the shortcomings of the existing emergency exit system inspection device, such as low measurement accuracy and no automation function, and to provide an electronic aircraft cockpit emergency exit system inspection device with a reasonable structure, complete functions, and real-time data curve and historical data query functions, so as to inspect the functional performance index parameters of the aircraft cockpit emergency exit system.

[0004] The object of the present invention is achieved through the following technical solutions: an electronic aircraft cockpit emergency exit system inspection equipment, including a body system, an air pressure system, an instrument control and electrical system, an onboard pressure monitoring and venting system;

[0005] The vehicle body system comprises: a chassis and a vehicle body connected to the chassis.

[0006] The four end faces of the box body are hingedly connected to each other to form a maintenance door, and a handle is provided on the left side of the box body;

[0007] Two universal wheels and two fixed wheels are symmetrically arranged on the chassis.

[0008] The air pressure system includes: a nitrogen charging interface, a one-way valve connected to the nitrogen charging interface, a first metering interface connected to the one-way valve, a first pressure sensor connected to a primary safety valve, a first solenoid valve and a first stop valve connected to the primary safety valve, and a pressure reducing valve connected to the first solenoid valve and the first stop valve;

[0009] The instrument control and electrical system includes: an electrical control cabinet and an operation panel;

[0010] The onboard pressure monitoring and deflation system comprises a third rubber hose and a third pressure sensor connected to the third rubber hose.

[0011] Further, the pressure reducing valve is connected to the secondary safety valve, the stop valve, and the third solenoid valve;

[0012] A first speed regulating valve, a second speed regulating valve and a third speed regulating valve connected to the secondary safety valve, the third stop valve and the third solenoid valve;

[0013] The first speed regulating valve, the second speed regulating valve and the third speed regulating valve are arranged in parallel.

[0014] Further, the first speed regulating valve is connected in series to the second solenoid valve, the second speed regulating valve is connected in series to the fourth solenoid valve, and the second speed regulating valve is connected in series to the second solenoid valve.

[0015] The second solenoid valve and the second stop valve are connected in parallel on the pipeline where the first speed regulating valve is located;

[0016] The fifth solenoid valve is connected in parallel with the fourth stop valve and is located on the pipeline where the second speed regulating valve is located.

[0017] Furthermore, the first solenoid valve, the fourth solenoid valve, the fifth solenoid valve, the second stop valve, and the fourth stop valve are connected to the second pressure sensor, the three-way ball valve, and the second metering interface.

[0018] Furthermore, the three-way ball valve is connected to the first rubber hose and the second rubber hose, and the first rubber hose and the second rubber hose are arranged in parallel.

[0019] Furthermore, the electrical control cabinet includes: a programmable controller, an expansion module, a relay, a miniature circuit breaker, and a fuse;

[0020] The programmable controller, expansion module, relay, miniature circuit breaker and fuse are located in the box and are electrically connected through connecting wires.

[0021] Further, the operation panel includes: a power start switch, a power stop switch, an emergency stop switch, an audible and visual alarm, and a human-machine interface;

[0022] The human-machine interface is electrically connected to the electrical control cabinet. The human-machine interface is located in the middle of the end face of the box body, and a gas source pressure and output pressure sensor is fixedly provided on one side of the human-machine interface. A gas source switch, a deflation switch, a fast pressurization switch, and a slow pressurization switch are fixedly provided below the human-machine interface in sequence.

[0023] A power start switch, a power stop switch, an emergency stop switch, and an audible and visual alarm are fixedly arranged on a side away from the gas source pressure and output pressure sensor;

[0024] Gas or nitrogen pipeline switches are fixedly provided at the air release switch and the rapid pressure increase switch.

[0025] Furthermore, the human-machine interface functions include clamp spring lock unlocking inspection, release mechanism inspection, locking connection lock inspection, and actuator piston rod inspection. By entering the required test function interface and clicking the start button, the control programs can be automatically executed respectively.

[0026] Furthermore, the on-board pressure monitoring and deflation system is connected to the on-board actuator, and an indicator detection system is installed on the on-board actuator fixture.

[0027] Furthermore, the electrical control cabinet is connected to a power line and a signal line to connect the nitrogen truck to the flange pipe opening of the inspection equipment.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] a. Simple operation, strong visibility, and real-time and historical data playback functions;

[0030] b. Light weight, compact structure and low maintenance cost;

[0031] c. It has stable working performance, high reliability and low noise, and can be used under the same environmental conditions as aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a three-dimensional schematic diagram of the present invention;

[0033] Figure 2 It is a schematic diagram of the internal connection of the present invention;

[0034] Figure 3 It is a schematic diagram of the principle of the present invention. DETAILED DESCRIPTION

[0035] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0036] like Figure 1-3 As shown, an electronic aircraft cockpit emergency exit system inspection equipment includes a body system, an air pressure system, an instrument control and electrical system, an onboard pressure monitoring and venting system;

[0037] The vehicle body system comprises: a chassis and a vehicle body connected to the chassis.

[0038] The four end faces of the box body are hingedly connected to each other to form a maintenance door, and a handle is provided on the left side of the box body;

[0039] Two universal wheels and two fixed wheels are symmetrically arranged on the chassis.

[0040] The air pressure system includes: a nitrogen charging interface 2, a one-way valve 3 connected to the nitrogen charging interface 2, an air filter 4 connected to the one-way valve 3, a first metering interface 5 and a first pressure sensor 6 connected to the air filter 4, a primary safety valve connected to the first metering interface 5 and the first pressure sensor 6, a first solenoid valve 8 and a first stop valve 9 connected to the primary safety valve, and a pressure reducing valve 11 connected to the first solenoid valve 8 and the first stop valve 9;

[0041] The instrument control and electrical system includes: an electrical control cabinet and an operation panel;

[0042] The onboard pressure monitoring and deflation system includes a third hose 27 and a third pressure sensor 28 connected to the third hose 27 .

[0043] In order to facilitate linkage control in the use state, a further preferred embodiment of the present invention is that the pressure reducing valve 11 is connected to the secondary safety valve 14, the stop valve 16, and the third solenoid valve 17;

[0044] The first speed regulating valve 13, the second speed regulating valve 15 and the third speed regulating valve 18 connected to the secondary safety valve 14, the third stop valve 16 and the third solenoid valve 17;

[0045] The first speed regulating valve 13 , the second speed regulating valve 15 , and the third speed regulating valve 18 are arranged in parallel.

[0046] In order to facilitate linkage control in use, a further preferred embodiment of the present invention is that the first speed control valve 13 is connected in series to the second solenoid valve 12, the second speed control valve 15 is connected in series to the fourth solenoid valve 19, and the second speed control valve 18 is connected in series to the second solenoid valve 21.

[0047] The second solenoid valve 12 is connected in parallel with the second stop valve 10 and is located on the pipeline where the first speed regulating valve 13 is located;

[0048] The fifth solenoid valve 21 is connected in parallel with the fourth stop valve 20 and is located on the pipeline where the second speed regulating valve 18 is located.

[0049] In order to facilitate the linkage control in use, a further preferred embodiment of the present invention is that the first solenoid valve 12, the fourth solenoid valve 19, the fifth solenoid valve 21, the second stop valve 10, and the fourth stop valve 20 are connected to the second pressure sensor 24, the three-way ball valve 23, and the second metering interface 22.

[0050] In order to facilitate effective docking transmission in use, a further preferred embodiment of the present invention is that the three-way ball valve 23 is connected to the first rubber hose 25 and the second rubber hose 26, and the first rubber hose 25 and the second rubber hose 26 are arranged in parallel.

[0051] In order to realize the automatic integrated operation, the present invention is particularly provided with an electrical control cabinet. A further preferred embodiment of the present invention is that the electrical control cabinet comprises: a programmable controller, an expansion module, a relay, a miniature circuit breaker, and a fuse;

[0052] The programmable controller, expansion module, relay, miniature circuit breaker and fuse are located in the box and are electrically connected through connecting wires.

[0053] In order to be able to operate the detection device through the artificial intelligence operation panel in the use state, a further preferred embodiment of the present invention is that the operation panel includes: a power start switch, a power stop switch, an emergency stop switch, an audible and visual alarm and a human-machine interface;

[0054] The human-machine interface is electrically connected to the electrical control cabinet. The human-machine interface is located in the middle of the end face of the box body, and a gas source pressure and output pressure sensor is fixedly provided on one side of the human-machine interface. A gas source switch, a deflation switch, a fast pressurization switch, and a slow pressurization switch are fixedly provided below the human-machine interface in sequence.

[0055] A power start switch, a power stop switch, an emergency stop switch, and an audible and visual alarm are fixedly arranged on a side away from the gas source pressure and output pressure sensor;

[0056] Gas or nitrogen pipeline switches are fixedly provided at the air release switch and the rapid pressure increase switch.

[0057] In order to be able to perform further inspections on the test vehicle body in advance when it is in use, a further preferred embodiment of the present invention is that the human-machine interface functions include clamp spring lock unlocking inspection, release mechanism inspection, locking connection lock inspection, and actuator piston rod inspection. By entering the required test function interface and clicking the start button, the control programs can be automatically executed respectively.

[0058] In order to facilitate the docking with the on-board actuator clamp through the on-board pressure monitoring and air release system when in use, a further preferred embodiment of the present invention is that the on-board pressure monitoring and air release system is docked with the on-board actuator, and an indicator detection system is installed on the on-board actuator clamp.

[0059] In order to facilitate effective docking of the external vehicle body system when in use, a further preferred embodiment of the present invention is that the electrical control cabinet is connected to the power line and the signal line to dock the nitrogen vehicle with the flange pipe opening of the inspection equipment.

[0060] The electronic aircraft cockpit emergency exit system inspection equipment is divided into two types: automatic control mode and manual control mode.

[0061] The procedure for using the automatic control mode of the electronic aircraft cockpit emergency exit system inspection equipment is as follows:

[0062] 1. Turn each valve on the operation panel to the "off" position; open the operation door of the inspection equipment, and connect the power cord and signal cord to the inspection equipment respectively.

[0063] 2. Connect the nitrogen truck to the inspection equipment, click the "power button" to start the equipment, observe whether the instruments and touch screen display are normal, turn on the nitrogen truck inflation switch, and ensure that the "gas source pressure" of the inspection equipment is within the rated pressure range.

[0064] 3. Fix the indicator detection system on the actuator clamp on the machine and adjust the position; reliably connect the on-machine pressure monitoring and air release system with the on-machine actuator, and check whether the stop valve is closed.

[0065] 4. Enter the required test function interface through the human-machine interface function options (including "clip spring lock unlocking check", "release mechanism check", "locking connection lock check", "actuator piston rod check"), and click the start button to automatically execute the control program respectively.

[0066] 5. The human-machine interface displays the current pressure value in real time and the pressure curve of the inflation process at the same time.

[0067] 6. After the work is completed, click "Equipment Exhaust" on the screen. After the exhaust is completed, turn off the "Power Button", remove the pressure monitoring and venting system, hose, power cord, signal line, nitrogen truck connector and other components on the machine, and close the equipment door.

[0068] The procedure for using the manual control mode of the electronic aircraft cockpit emergency exit system inspection equipment is as follows:

[0069] 1. Turn each valve on the operation panel to the "off" position; open the operation door of the inspection equipment, and connect the power cord and signal cord to the inspection equipment respectively.

[0070] 2. Connect the nitrogen truck to the inspection equipment, click the "power button" to start the equipment, observe whether the instruments and touch screen display are normal, turn on the nitrogen truck inflation switch, and ensure that the "gas source pressure" of the inspection equipment is within the rated pressure range.

[0071] 3. Fix the indicator detection system on the actuator clamp on the machine and adjust the position; reliably connect the on-machine pressure monitoring and air release system with the on-machine actuator, and check whether the stop valve is closed.

[0072] 4. Turn the gas source switch stop valve on the operation panel to the "open" position, and turn the three-way ball valve to the "gas line" or "nitrogen line".

[0073] 5. Turn the slow pressure-boosting switch stop valve to the "open" position to supply gas at a certain gas supply speed. When the output pressure reaches the rated pressure, turn the slow pressure-boosting switch stop valve to the "closed" position to conduct a functional performance check in the first working condition.

[0074] 6. Turn the fast boost switch stop valve to the "open" position to supply gas at a certain gas supply speed. When the output pressure reaches the rated pressure, turn the fast boost switch stop valve to the "closed" position to perform the second working condition functional performance check.

[0075] 7. Turn the slow pressure-boosting switch stop valve to the "open" position to supply gas at a certain gas supply speed. When the output pressure reaches the rated pressure, turn the slow pressure-boosting switch stop valve to the "closed" position to conduct the third working condition functional performance check.

[0076] 8. After all working condition checks are completed, turn the vent switch stop valve to the "open" position to vent the equipment.

[0077] 9. After the work is completed, turn off the "power button", remove the pressure monitoring and venting system, hoses, power cord, signal line, nitrogen truck connector and other components on the machine, and close the equipment door.

[0078] As can be seen from the above, the electronic aircraft cockpit emergency exit system inspection equipment has two operation control modes: manual and automatic. In the automatic operation control mode, a variety of working conditions can be tested through simple operations. The supervision and analysis of the test process can be improved through historical, real-time data and curves; the accuracy of the pressure sensor is controlled between 0.5% and 1.0% to ensure the accuracy of the measured value.

[0079] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0080] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. An electronic aircraft cockpit emergency exit system inspection device, characterized in that: Including body system, air pressure system, instrument control and electrical system, onboard pressure monitoring and bleed system; The vehicle body system comprises: a chassis, a box body connected to the chassis; The four end faces of the box body are hingedly connected to each other to form a maintenance door, and a handle is provided on the left side of the box body; The chassis is symmetrically provided with two universal wheels and two fixed wheels; The air pressure system comprises: a nitrogen charging interface (2), a one-way valve (3) connected to the nitrogen charging interface (2), an air filter (4) connected to the one-way valve (3), a first metering interface (5) and a first pressure sensor (6) connected to the air filter (4), a primary safety valve connected to the first metering interface (5) and the first pressure sensor (6), a first solenoid valve (8) and a first stop valve (9) connected to the primary safety valve, and a pressure reducing valve (11) connected to the first solenoid valve (8) and the first stop valve (9); The instrument control and electrical system includes: an electrical control cabinet and an operation panel; The onboard pressure monitoring and deflation system comprises a third rubber hose (27) and a third pressure sensor (28) connected to the third rubber hose (27); The pressure reducing valve (11) is connected to a secondary safety valve (14), a stop valve (16), and a third solenoid valve (17); A first speed regulating valve (13), a second speed regulating valve (15), and a third speed regulating valve (18) connected to the secondary safety valve (14), the third stop valve (16), and the third solenoid valve (17); The first speed regulating valve (13), the second speed regulating valve (15), and the third speed regulating valve (18) are arranged in parallel; The first speed regulating valve (13) is connected in series with the second solenoid valve (12), the second speed regulating valve (15) is connected in series with the fourth solenoid valve (19), and the third speed regulating valve (18) is connected in series with the fifth solenoid valve (21); The second solenoid valve (12) is connected in parallel with the second stop valve (10) and is located on the pipeline where the first speed regulating valve (13) is located; The fifth solenoid valve (21) is connected in parallel with the fourth stop valve (20) and is located on the pipeline where the third speed regulating valve (18) is located; The first solenoid valve (8), the fourth solenoid valve (19), the fifth solenoid valve (21), the second stop valve (10), and the fourth stop valve (20) are connected to the second pressure sensor (24), the three-way ball valve (23), and the second metering interface (22); The electrical control cabinet comprises: a programmable controller, an expansion module, a relay, a miniature circuit breaker, and a fuse. The programmable controller, the expansion module, the relay, the miniature circuit breaker, and the fuse are located in the box and are electrically connected through a connecting line.

2. The electronic aircraft cockpit emergency exit system inspection device according to claim 1, characterized in that: The three-way ball valve (23) is connected to the first rubber hose (25) and the second rubber hose (26), and the first rubber hose (25) and the second rubber hose (26) are arranged in parallel.

3. The electronic aircraft cockpit emergency exit system inspection device according to claim 2, characterized in that: The operation panel includes: a power start switch, a power stop switch, an emergency stop switch, an audible and visual alarm and a human-machine interface; The human-machine interface is electrically connected to the electrical control cabinet. The human-machine interface is located in the middle of the end face of the box body, and a gas source pressure and output pressure sensor is fixedly provided on one side of the human-machine interface. A gas source switch, a deflation switch, a fast pressurization switch, and a slow pressurization switch are fixedly provided below the human-machine interface in sequence. A power start switch, a power stop switch, an emergency stop switch, and an audible and visual alarm are fixedly arranged on a side away from the gas source pressure and output pressure sensor; Gas or nitrogen pipeline switches are fixedly provided at the air release switch and the rapid pressure increase switch.

4. The electronic aircraft cockpit emergency exit system inspection device according to claim 3, characterized in that: The functions of the human-machine interface include the inspection of the clamp spring lock unlocking, the inspection of the release mechanism, the inspection of the locking connection lock, and the inspection of the actuator piston rod. By entering the required test function interface and clicking the start button, the control programs can be automatically executed respectively.

5. The electronic aircraft cockpit emergency exit system inspection device according to claim 4, characterized in that: The on-board pressure monitoring and deflation system is connected to the on-board actuator, and an indicator detection system is installed on the on-board actuator fixture.

6. The electronic aircraft cockpit emergency exit system inspection device according to claim 5, characterized in that: The electrical control cabinet is connected to the power line and the signal line, and the nitrogen truck is connected to the flange pipe opening of the inspection equipment.

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