Mounting structure of intelligent oxygen terminal monitoring system of aircraft unit

Abstract

The utility model discloses a mounting structure of an intelligent oxygen terminal monitoring system of an airplane unit, a pressure sensor, an electromagnetic actuator, a display module and a control module are integrally mounted on an integrated block, and a switch module is independently mounted near the integrated block; the integrated block is provided with an oxygen inlet channel used for being externally connected with a unit oxygen terminal, an oxygen supply channel used for being externally connected with a unit passenger oxygen supply front end, a communication channel communicated with the oxygen inlet channel and the oxygen supply channel, a sensor installation cavity used for installing a pressure sensor, a circuit part used for installing a display module and a core piece installation cavity used for installing a control module. The air inlet channel is communicated with the oxygen supply channel and the sensor installation cavity, a piston rod assembly is arranged in the communication channel, the electromagnetic actuator is installed outside the integrated block and connected with one end of the piston rod assembly, and the electromagnetic actuator drives the piston rod assembly to move to achieve opening and closing of the communication channel so as to achieve opening and closing of oxygen supply. And a display screen of the display module is arranged outside the integrated block. The structure saves space and is convenient to maintain.

Description

Technical Field

[0001] The utility model relates to oxygen supply for aircraft crew, and particularly to an installation structure of an intelligent terminal monitoring system for aircraft crew oxygen. Background Art

[0002] When the aircraft crew supplies oxygen to the crew members, it is best to use an intelligent terminal monitoring system for aircraft crew oxygen to monitor and control the oxygen supply pressure. Since a set of intelligent terminal monitoring system for aircraft crew oxygen is required at each crew member's position, and the space inside the aircraft is limited, in order to save space, the intelligent terminal monitoring system for aircraft crew oxygen is preferably of a small and compact installation structure. At present, the intelligent terminal monitoring system for aircraft crew oxygen is a newly emerged facility, and its installation structure needs to be newly designed to meet the small and compact requirements. Content of the Utility Model

[0003] The purpose of the utility model is to provide an installation structure of an intelligent terminal monitoring system for aircraft crew oxygen, which saves space and is convenient for maintenance.

[0004] The technical solution adopted by the utility model is as follows:

[0005] An installation structure of an intelligent terminal monitoring system for aircraft crew oxygen. The intelligent terminal monitoring system for aircraft crew oxygen includes a pressure sensor, an electromagnetic actuator, a display module, a control module, and a switch module; the pressure sensor, the electromagnetic actuator, the display module, and the control module are integrally installed on an integrated block, and the switch module is independently installed near the integrated block; the integrated block is provided with an oxygen inlet channel for externally connecting to the crew oxygen terminal, an oxygen supply channel for externally connecting to the oxygen supply front end of the crew member, a communication channel connecting the oxygen inlet channel and the oxygen supply channel, a sensor installation cavity for installing the pressure sensor, a circuit part installation cavity for installing the display module, and a core component installation cavity for installing the control module, an air inlet channel connecting the oxygen supply channel and the sensor installation cavity. A piston rod assembly is arranged in the communication channel, the electromagnetic actuator is installed outside the integrated block and connected to one end of the piston rod assembly, and the electromagnetic actuator drives the piston rod assembly to move to realize the opening and closing of the communication channel and thus realize the opening and closing of oxygen supply. The display screen of the display module is arranged outside the integrated block.

[0006] Preferably, the piston rod assembly includes a plug and a perforated plug respectively sealed and installed at the front and rear opening ends of the communication channel through static seals, a piston rod located in the communication channel, a front seal arranged in the front section position of the communication channel, and a rear seal arranged at the rear end of the piston rod. The front end of the piston rod is provided with a ventilation hole, the front part is slidably matched with the front seal, the middle part is slidably matched with the communication channel through a piston capable of ventilating, and the rear end is slidably and sealingly inserted into the hole of the plug through the rear seal and then connected to the electromagnetic actuator. When the electromagnetic actuator drives the piston rod to move, the opening and closing of the communication channel are realized by changing the position of the ventilation hole at the front end of the piston rod.

[0007] Preferably, the electromagnetic actuator includes a valve body mounted on the integrated block, a cover for closing the non-mounted end of the valve body, a coil assembly located inside the valve body, a valve core located inside the valve body and passing through the coil assembly, and a spring located inside the valve body and pressing between the cover and the valve core. The valve core is connected to the piston rod assembly at the mounted end of the valve body. When the coil assembly works, it drives the valve core to overcome the spring force to move the piston rod assembly outward to realize the conduction of the communication channel. When the coil assembly does not work, the spring resets and drives the piston rod assembly to move inward through the valve core to realize the blockage of the communication channel.

[0008] Preferably, the openings of the sensor installation cavity and the core component installation cavity are arranged on the same side of the integrated block and are installed and closed by the same cover plate. The core component installation cavity is provided with an electrical external connection port.

[0009] The beneficial effects of the present utility model are as follows:

[0010] The integrated block can integrate the pressure sensor, the electromagnetic actuator, the display module and the control module together, saving space and being convenient for maintenance. Since the switch module is an operation end, it is installed separately; the integrated block can externally connect the oxygen terminal of the unit and the front end of the crew oxygen supply of the unit at the same time and use the piston rod assembly inside to control the on-off of the two, with a clever structure. Description of the Drawings

[0011] Figure 1 is the structural block diagram of the aircraft crew oxygen intelligent terminal monitoring system in the embodiment of the present utility model.

[0012] Figure 2 is the schematic diagram of the installation structure of the aircraft crew oxygen intelligent terminal monitoring system in the embodiment of the present utility model.

[0013] Figure 3 is Figure 2 the sectional view at A-A in

[0014] Figure 4 is Figure 2 the sectional view at B-B in

[0015] Figure 5 is Figure 2 the sectional view at C-C in

[0016] Figure 6 is the sectional view of the integrated block in the embodiment of the present utility model.

[0017] Figure 7 is the sectional view of the electromagnetic actuator in the embodiment of the present utility model.

[0018] In the figure: 1 - integrated circuit block; 2 - cover plate; 3 - electromagnetic actuator; 4 - switch module; 5 - pressure sensor; 6 - sensor installation cavity; 7 - core component installation cavity; 8 - display module; 9 - control module; 10 - static sealing ring; 11 - plug cap; 12 - front sealing ring; 13 - piston rod; 14 - rear sealing ring; 15 - plug; 16 - air inlet channel; 17 - oxygen inlet channel; 18 - oxygen supply channel; 19 - communication channel; 20 - valve core; 21 - valve body; 22 - coil assembly; 23 - spring; 24 - sealing cover. Detailed implementation manners

[0019] The present utility model will be further described below in conjunction with the accompanying drawings and embodiments.

[0020] The present utility model discloses an installation structure for intelligent terminal monitoring of aircraft crew oxygen, as Figure 1 shown. The intelligent terminal monitoring system for aircraft crew oxygen includes a pressure sensor 5, an electromagnetic actuator 3, a display module 8, a control module 9, and a switch module 4; as Figures 2 to 6 shown, the pressure sensor 5, the electromagnetic actuator 3, the display module 8, and the control module 9 are integrally installed on the integrated circuit block 1, and the switch module 4 is independently installed near the integrated circuit block 1; as Figures 3 to 6 shown, the integrated circuit block 1 is provided with an oxygen inlet channel 17 for externally connecting to the crew oxygen terminal, an oxygen supply channel 18 for externally connecting to the oxygen supply front end of the crew members, a communication channel 19 connecting the oxygen inlet channel 17 and the oxygen supply channel 18, a sensor installation cavity 6 for installing the pressure sensor 5, a core component installation cavity 7 for installing the circuit part of the display module 8 and the control module 9, an air inlet channel 16 connecting the oxygen supply channel 17 and the sensor installation cavity 6. A piston rod assembly is provided in the communication channel 19. The electromagnetic actuator 3 is installed outside the integrated circuit block 1 and connected to one end of the piston rod assembly. The electromagnetic actuator 3 drives the piston rod assembly to move to realize the opening and closing of the communication channel 19, thereby realizing the opening and closing of oxygen supply. The display screen of the display module 8 is arranged outside the integrated circuit block 1.

[0021] In the above solution: The integrated circuit block 1 can integrate the pressure sensor 5, the electromagnetic actuator 3, the display module 8, and the control module 9 together, saving space and being convenient for maintenance. Since the switch module 4 is an operation end, it is installed separately; the integrated circuit block 1 can externally connect to the crew oxygen terminal and the oxygen supply front end of the crew members at the same time and use the internal piston rod assembly to control the on-off of the two, with a clever structure.

[0022] As Figures 2 to 6As shown in the figure, the oxygen inlet channel 17 and the oxygen supply channel 18 are arranged in parallel at the lower part of the integrated block 1 with their external interfaces facing downward, and the communication channel 19 horizontally penetrates through the middle of the integrated block 1. The sensor installation cavity 6 is located at the upper left part of the integrated block 1, the core component installation cavity 7 is located at the upper right part of the integrated block 1, the control module 9 is installed directly below the circuit part of the display module 8, and the electromagnetic actuator 3 is installed on the right side outside the integrated block 1 and is located at the right end of the communication channel 19. The pressure sensor 5 can adopt a silicon piezoresistive diaphragm sensor. The oxygen supply of the unit enters the sensor installation cavity 6 through the oxygen inlet channel 17 and the air inlet channel 16. After the diaphragm of the pressure sensor 5 is stressed, the resistance value changes, and thus the change in pressure is measured.

[0023] As Figures 2 to 6 shown, in this embodiment, preferably: the openings of the sensor installation cavity 6 and the core component installation cavity 7 are arranged on the same side of the integrated block 1 and are installed and sealed through the same cover plate 2. The core component installation cavity 7 is provided with an electrical external connection port.

[0024] As Figure 5 shown, in this embodiment, preferably: the piston rod assembly includes a plug cap 11 and a perforated plug head 15 that are respectively sealed and installed at the front and rear opening ends of the communication channel 19 through static seals 10, a piston rod 13 located in the communication channel 19, a front seal 12 arranged in the front section of the communication channel 19, and a rear seal 14 arranged at the rear end of the piston rod 13. The front end of the piston rod 13 is provided with a ventilation hole, the front part is slidably matched with the front seal 12, the middle part is slidably matched with the communication channel 19 through a piston that can conduct air, and the rear end is slidably and sealingly inserted into the hole of the plug head 15 through the rear seal 14 and then connected to the electromagnetic actuator 3. When the electromagnetic actuator 3 drives the piston rod 13 to move, the conduction and blockage of the communication channel 19 are realized through the change of the position of the ventilation hole at the front end of the piston rod 13. The plug cap 11 and the plug head 15 are installed by screws, and the static seal 10 can ensure their sealed installation. When the ventilation hole at the front end of the piston rod 13 moves backward, the ventilation hole can conduct both sides of the front seal 12. When the ventilation hole at the front end of the piston rod 13 moves forward, it is on one side of the front seal 12, and the communication channel 19 is in a blocked state. The rear seal 14 can ensure the isolation between the outside and the communication channel 19 when the piston rod 13 is in an active state.

[0025] As Figure 7As shown, in this embodiment, preferably: The electromagnetic actuator 3 includes a valve body 21 mounted on the integrated block 1, a cover 24 closing the non-mounted end of the valve body 21, a coil assembly 22 located within the valve body 21, a valve core 20 located within the valve body 21 and passing through the coil assembly 22, and a spring 23 located within the valve body 21 and abutting between the cover 24 and the valve core 20. The valve core 20 is connected to the piston rod assembly at the mounted end of the valve body 21. When the coil assembly 22 operates, it drives the valve core 20 to overcome the spring force and move the piston rod assembly outward to achieve the conduction of the communication channel. When the coil assembly 22 does not operate, the spring 23 resets and drives the piston rod assembly to move inward through the valve core 20 to block the communication channel 19. The valve body 21 can be installed on the integrated block 1 with screws, and there is no need for a sealed installation.

[0026] The embodiments described above are some, but not all, of the embodiments of the present application. The detailed description of the embodiments of the present application is not intended to limit the scope of the present application claimed, but merely represents selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts fall within the scope of protection of the present application.

Claims

1. An installation structure of an aircraft crew oxygen intelligent terminal monitoring system, the aircraft crew oxygen intelligent terminal monitoring system comprising a pressure sensor, an electromagnetic actuator, a display module, a control module and a switch module; characterized in that: The pressure sensor, electromagnetic actuator, display module and control module are integrated and installed on the integrated block, and the switch module is independently installed near the integrated block; the integrated block is provided with an oxygen inlet channel for an externally connected crew oxygen terminal, an oxygen supply channel for an externally connected crew member oxygen supply front end, a connecting channel connecting the oxygen inlet channel and the oxygen supply channel, a sensor installation cavity for installing the pressure sensor, a core installation cavity for installing the circuit part of the display module and the control module, an air intake channel connecting the oxygen supply channel and the sensor installation cavity, a piston rod assembly is provided in the connecting channel, the electromagnetic actuator is installed outside the integrated block and connected to one end of the piston rod assembly, the electromagnetic actuator realizes the conduction and blockage of the connecting channel by driving the piston rod assembly to move, and thus realizes the opening and closing of the oxygen supply, and the display screen of the display module is arranged outside the integrated block.

2. The installation structure of the aircraft crew oxygen intelligent terminal monitoring system according to claim 1, characterized in that: The piston rod assembly includes a plug cap and a plug with a hole, which are respectively installed on the front and rear opening ends of the connecting channel through static sealing rings, a piston rod located in the connecting channel, a front sealing ring arranged in the front section of the connecting channel, and a rear sealing ring arranged at the rear end of the piston rod. The front end of the piston rod is provided with a vent hole, the front part slides with the front sealing ring, the middle part slides with the connecting channel through a ventilated piston, and the rear end is connected to the electromagnetic actuator after sealing the hole of the plug through the rear sealing ring. When the electromagnetic actuator drives the piston rod to move, the connection and blockage of the connecting channel are realized by changing the position of the vent hole at the front end of the piston rod.

3. The installation structure of the aircraft crew oxygen intelligent terminal monitoring system according to claim 1, characterized in that: The electromagnetic actuator includes a valve body installed on the integrated block, a cover that closes the non-installation end of the valve body, a coil assembly located in the valve body, a valve core located in the valve body and passing through the coil assembly, and a spring located in the valve body and resting between the cover and the valve core. The valve core is connected to the piston rod assembly at the installation end of the valve body. When the coil assembly is working, it drives the valve core to overcome the spring force and move the piston rod assembly outward to achieve conduction of the connecting channel. When the coil assembly is not working, the spring resets and drives the piston rod assembly inward through the valve core to achieve blocking of the connecting channel.

4. The installation structure of the aircraft crew oxygen intelligent terminal monitoring system according to claim 1, characterized in that: The openings of the sensor installation cavity and the core installation cavity are arranged on the same side of the integrated block and are installed and closed by the same cover plate. The core installation cavity is provided with an electrical external connection through port.

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