Conveyor cabin differential pressure control signal ground power-on inspection device

Abstract

The utility model belongs to the field of electromechanical systems-environment control systems, and relates to a transport plane cabin differential pressure control signal ground power-on inspection device, which comprises an air extractor, a differential pressure sensor, a differential pressure gauge, a cargo hold door control circuit and a test lamp, and is characterized in that the air extractor is respectively connected with the differential pressure sensor and the differential pressure gauge through airtight hoses; the pressure difference sensor is electrically connected with the cargo hold door control circuit through the butt joint socket, a first branch of the cargo hold door control circuit is electrically connected with the test lamp, a second branch of the cargo hold door control circuit is electrically connected with the cargo hold door control system through the switch, and during ground inspection, pressure sensing components and circuits can be inspected.

Description

TECHNICAL FIELD

[0001] The utility model belongs to electromechanical system - environmental control system field relates to a kind of transport machine seat cabin pressure difference control signal ground power-on inspection device. BACKGROUND

[0002] During the whole process of airplane take-off, flight, landing, the atmospheric pressure in the airplane cabin changes due to the change of airplane height. To ensure that the cabin personnel can work smoothly in the cabin and to ensure the safety and comfort of the cabin personnel, and to avoid injury due to pressure change in the cabin. The current airplane generally has a bleed air system and a cabin pressure regulating system to adjust the pressure difference between the inside and outside of the cabin. However, there is currently a lack of cabin pressure inspection, transmission and control device and related methods when the cabin pressure changes. SUMMARY

[0003] The utility model solves the technical problem: a kind of transport machine seat cabin pressure difference control signal ground power-on inspection device, ground inspection, can be tested to pressure sensing component and circuit.

[0004] TECHNICAL SCHEME

[0005] A kind of transport machine seat cabin pressure difference control signal ground power-on inspection device, including air extraction device, pressure difference sensor, differential pressure gauge, cargo door control circuit, test lamp, the air extraction device is connected with pressure difference sensor, differential pressure gauge respectively by airtight hose, the pressure difference sensor is electrically connected with cargo door control circuit by butt socket, the first branch of cargo door control circuit is electrically connected with test lamp, the second branch of cargo door control circuit is electrically connected with cargo door control system by switch.

[0006] Further, the air extraction device is a handheld micro-pressure pump.

[0007] Further, the handheld micro-pressure pump includes a cavity, one end of the cavity is provided with a pressure increasing / decreasing hand wheel 4a, for realizing the air extraction function, the other end is provided with two quick-release connectors 1a, two quick-release connectors 1a are connected with pressure difference sensor and differential pressure gauge respectively through airtight hose one by one, a fine adjustment hand wheel 3a is arranged on the cavity, for high-precision adjustment of cavity output pressure.

[0008] Further, the cargo door control circuit includes a switch, a plug CZ and a cable, the plug CZ is provided with a number of 1-4 jack, the switch is connected with the 1 and 3 hole of the plug CZ through the cable, the 2 hole of the plug CZ1 is connected with the safety valve circuit, and the 4 hole of the plug CZ is connected with the cargo bridge lock normal control hydraulic electromagnetic valve plug, and the cargo bridge lock normal control hydraulic electromagnetic valve plug is connected with the test lamp.

[0009] Furthermore, the differential pressure sensor is equipped with a micro switch, which includes two pairs of contacts, namely a pair of contacts numbered 1 and 2 and a pair of contacts numbered 3 and 4, and also includes a spring plate. The spring plate is connected to contacts 1 and 2 or contacts 3 and 4 according to the pressure change inside the differential pressure sensor.

[0010] Furthermore, contacts 1 to 4 inside the micro switch are connected one-to-one with holes 1 to 4 of the plug CZ.

[0011] Beneficial effects

[0012] This invention proposes a ground-based power-on inspection device for differential pressure control signals in transport aircraft cabins. It employs suitable pressure-sensing components and connects these components to the aircraft's existing circuitry. The differential pressure sensors indirectly control a specific circuit on the aircraft, thereby achieving cabin pressure control. During ground inspections, detailed checks can be performed on the selected pressure-sensing components and circuitry. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the CG-1 differential pressure sensor structure;

[0014] Figure 2 Top view of the CG-1 differential pressure sensor structure;

[0015] Figure 3 Schematic diagram of the internal microswitch of the CG-1 differential pressure sensor;

[0016] Figure 4 This is a schematic diagram of the differential pressure handheld micro-pressure pump of this utility model;

[0017] Figure 5 This is a schematic diagram showing the connection of a micro-pressure pump, a differential pressure sensor, and a differential pressure gauge.

[0018] Figure 6 This is a schematic diagram illustrating the working principle of a differential pressure sensor circuit.

[0019] Figure 7 A schematic diagram of the connections of each component when the differential pressure sensor is powered on for inspection;

[0020] Among them, 1. Screw 1, 2. Spring, 3. Spring seat, 4. Adjusting screw, 5. Nut 1, 6. Bent pipe connector, 7. Sealing ring, 8. Nut 2, 9. Outer shell, 10. Top cover, 11. Washer, 12. Support rod, 13. Diaphragm, 14. Micro switch, 15. Screw 2, 16. Nut 3, 17. Screw 3, 18. Electrical plug socket; 1a. Quick release connector, 2a. Cavity, 3a. Fine adjustment handwheel, 4a. Pressure increase / decrease handwheel, 5a. Differential pressure gauge, 6a. Differential pressure sensor, 7a. Airtight hose, 8a. Cargo door operating circuit, 9a. Test lamp, 10a. Switch, 11a. Connecting socket. DETAILED DESCRIPTION

[0021] Features and illustrative embodiments of various aspects of the present application will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, it will be apparent to one of ordinary skill in the art that the present application can be practiced without some or all of these specific details. The description of the embodiments is merely illustrative of the present application and is not intended to limit the present application to any particular setting or method. Rather, the scope of the present application covers all modifications, equivalents, and alternatives falling within the spirit and scope of the present application. In the drawings and the following description, well-known structures and techniques have not been described in detail in order to avoid unnecessarily obscuring the present application.

[0022] It should be noted that the features of the embodiments of the present application and the embodiments can be combined with each other without conflict, and each embodiment can be mutually referred to and quoted. The present application will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.

[0023] As shown in Figures 1-3 The CG-1 differential pressure sensor to be functionally checked according to the present application mainly comprises an upper cover 10, a supporting ring 12, an outer shell 9, a pressure-sensitive sensing element, and two groups of identical micro switches 14 and electric plug-in sockets 18. The pressure-sensitive sensing element comprises a metal diaphragm 13 and a common cylindrical spiral compression spring 2, the two micro switches 14 are respectively fixed on the supporting ring 12 through two screws, and the two electric sockets 18 are respectively fixed on the outer shell 9 through four groups of screws 15 and nuts 16, and are respectively marked as CZ1, i.e. socket 1, and CZ2, i.e. socket 2.

[0024] The upper cover 10, the metal diaphragm 13, and the supporting ring 12 are fixed together through six screws 1, the upper cover 10 and the upper surface of the metal diaphragm 13 together form a sealed cavity, which is set as cavity A, the cavity A is communicated with the atmospheric pipeline on the airplane through an elbow joint 6, the pressure in the cavity is the same as the atmospheric static pressure, the metal diaphragm 13 and the shell form another sealed cavity, which is set as cavity B, the cavity B is communicated with the cabin of the airplane through a pipeline, and is used for sensing the pressure change in the cabin of the airplane.

[0025] The outer surface of the lower surface of the metal diaphragm 13 senses the cabin pressure, so that a differential pressure, i.e. cabin differential pressure, is formed on both sides of the metal diaphragm 13.

[0026] Its working principle is that the hard core of the metal diaphragm is in contact with the spring 2 on one side, and the other side is in contact with the external contact of the micro switch 14. The pressure difference of the differential pressure sensor micro switch is 980Pa±490Pa, the working pressure of the differential pressure sensor is 29.4KPa, and the maximum allowable pressure is 49.0KPa. The differential pressure sensor works by changing the pressure difference between the inside and outside. The inside cavity senses the outside atmospheric pressure, and the outside cavity senses the cabin pressure of the aircraft, so that a pressure difference is formed in the sensor. When the pressure difference is greater than 980Pa±490Pa, the hard core of the diaphragm compresses the spring piece and separates from the micro switch, the internal 3,4 contacts of the micro switch are disconnected, and the cargo compartment control system control circuit is powered off;

[0027] When the pressure difference is equal to or less than 980Pa±490Pa, the spring is stretched, the hard core of the diaphragm presses the external contact of the micro switch, the internal 3,4 contacts of the micro switch are connected, and the cargo compartment control system control circuit is connected.

[0028] The utility model provides a kind of transport machine cabin pressure difference control signal ground power-on inspection device, including air extraction device, differential pressure sensor 6a, differential pressure gauge 5a, cargo compartment door control circuit 8a, test lamp 9a, the air extraction device is connected with differential pressure sensor 6a, differential pressure gauge 5a respectively by airtight hose 7a, the differential pressure sensor 6a is electrically connected with cargo compartment door control circuit 8a by butt socket 11a, the first branch of cargo compartment door control circuit 8a is electrically connected with test lamp 9a, the second branch of cargo compartment door control circuit 8a is electrically connected with cargo compartment door control system by switch 10a.

[0029] Among them, air extraction device is handheld micro pressure pump, and handheld micro pressure pump adopts mature piston hand pump on market, for example, mature products such as KZP12, SH series, CS series, piston hand pump is moved by handle, so that piston reciprocates in cavity, when piston moves to left, the volume of right end of cavity gradually expands, vacuum is formed, and air is extracted, when piston moves to right, the volume of right end of cavity is gradually compressed, and air is filled.

[0030] Among them, handheld micro pressure pump includes cavity 2a, and one end of cavity 2a is provided with pressure increasing / decreasing hand wheel 4a, for realizing air extraction function, and the other end is provided with two quick-release connectors 1a, two quick-release connectors 1a are connected with differential pressure sensor 6a and differential pressure gauge 5a respectively through airtight hose 7a one by one, and the cavity 2a is provided with fine adjustment hand wheel 3a, for high-precision adjustment of the pressure output from the cavity 2a to the quick-release connector 1a.

[0031] The cargo door control circuit 8a includes a switch, a plug CZ, and a cable. The plug CZ is provided with 1-4 jacks. The switch is connected to the 1 and 3 jacks of the plug CZ through the cable. The 2 jack of the plug CZ1 is connected to the safety valve circuit. The 4 jack of the plug CZ is connected to the cargo bridge lock normal control hydraulic electromagnetic valve plug. The cargo bridge lock normal control hydraulic electromagnetic valve plug is connected to the test lamp 9a.

[0032] The differential pressure sensor 6a is internally provided with a micro switch. The micro switch includes two pairs of contacts, i.e. a pair of 1 and 2 jacks and a pair of 3 and 4 jacks. The micro switch also includes a spring sheet. The spring sheet is connected to the 1 and 2 jacks or the 3 and 4 jacks according to the pressure change in the differential pressure sensor.

[0033] The 1-4 jacks in the micro switch are connected to the 1-4 jacks of the plug CZ one by one.

[0034] In use, the plug 1 of the differential pressure sensor 6a, i.e. the CZ1, is connected to the cable connection plug CZ of the cargo door control circuit 8a. The differential pressure sensor 6a is installed on the aircraft skin. The inner cavity on one side of the metal diaphragm 13 in the differential pressure sensor 6a, i.e. the A cavity, is connected to the atmosphere pipeline on the aircraft through the elbow joint 6. The pressure in the A cavity is the same as the atmospheric pressure. The B cavity on the other side of the metal diaphragm 13 in the differential pressure sensor 6a senses the cabin pressure. The test lamp 9a is connected to the first branch of the cargo door control circuit 8a through the cargo bridge lock normal control hydraulic electromagnetic valve plug. The air-tight hose 7a of the B cavity of the differential pressure sensor is connected to the other quick release joint 1a of the handheld micro pressure pump.

[0035] During ground inspection, the ground power supply provides 28V DC power to the aircraft and supplies power to the cargo door control system. The cargo door normal control switch is turned on. At this time, the 3 and 4 jacks of the micro switch in the differential pressure sensor 6a are connected. The cargo door control system is connected to the 3 jack of the plug CZ, the 3 and 4 jacks of the micro switch, the 4 jack of the plug CZ, the cargo bridge lock normal control hydraulic electromagnetic valve plug, and the test lamp 9a. The test lamp 9a should be lit. If the test lamp 9a is not lit, the cargo door control circuit 8a is not powered on. The cargo door control circuit 8a or the differential pressure sensor should be checked.

[0036] Slowly rotate the handheld micro pressure pump's plus / minus pressure hand wheel 4a counterclockwise, and air is extracted from the pressure difference sensor B cavity. When the pressure difference between the inside and outside of the pressure difference sensor metal diaphragm 13 is 980Pa-6980Pa, the micro switch in the pressure difference sensor 6a switches to points 1, 2, and the cargo compartment door control system supplies power to the 1 hole of the socket CZ, the 1, 2 number contacts of the micro switch, and the 2 hole of the socket CZ to the safety valve circuit, and the cargo compartment door control circuit 8a should be disconnected, and the test lamp 9a should be extinguished. At this time, observe whether the value of the differential pressure gauge 5a is within the range of -980Pa-6980Pa; At this time, the pressure difference sensor 6a will have a micro switch connection click sound, proving that the micro switch has changed from connecting the 3, 4 number contacts to connecting the 1, 2 number contacts; If the test lamp 9a is still on, it indicates that the cargo compartment door control circuit is still in the on state, and the cargo compartment door control circuit 8a or the pressure difference sensor 6a should be checked.

[0037] Rotate the handheld micro pressure pump's plus / minus pressure hand wheel 4a clockwise to inflate the pressure difference sensor B cavity, and use the fine adjustment hand wheel 3a to fine tune the pressure value. When the pressure difference between the A, B cavities on both sides of the pressure difference sensor 6a metal diaphragm 13 is reduced to 980Pa±490Pa or less, the 3, 4 number contacts of the micro switch in the pressure difference sensor 6a are connected at this time, and the cargo compartment door control system supplies power to the 3 hole of the socket CZ, the 3, 4 number contacts of the micro switch, the 4 hole of the socket CZ, and the test lamp 9a through the plug of the normal cargo bridge lock control hydraulic electromagnetic valve. The test lamp 9a should be on, and at this time the pressure value of the differential pressure gauge can be observed to see if it is within the range of -(980Pa±490Pa).

[0038] Again, according to the same method, connect the plug 2 of the pressure difference sensor 6a, i.e. CZ2, with the cable connection plug CZ of the cargo compartment door control circuit 8a, and check again whether the pressure difference control signal is normally powered.

[0039] Finally, it should be noted that the above examples are only used to illustrate the technical solutions of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art can easily think of various equivalent modifications or replacements within the technical range disclosed by the present application, and these modifications or replacements should be covered within the protection scope of the present application.

Claims

1. A ground-based power-on inspection device for differential pressure control signals in a transport aircraft cabin, characterized in that, It includes an air extraction device, a differential pressure sensor, a differential pressure gauge, a cargo door control circuit, and a test light. The air extraction device is connected to the differential pressure sensor and the differential pressure gauge respectively through airtight hoses. The differential pressure sensor is electrically connected to the cargo door control circuit through a docking socket. The first branch of the cargo door control circuit is electrically connected to the test light, and the second branch of the cargo door control circuit is electrically connected to the cargo door control system through a switch.

2. The ground power supply inspection device for differential pressure control signals in a transport aircraft cabin according to claim 1, characterized in that, The air extraction device is a handheld micro-pressure pump.

3. The ground power supply inspection device for differential pressure control signals in a transport aircraft cabin according to claim 2, characterized in that, The handheld micro-pressure pump includes a cavity. One end of the cavity is equipped with a pressure increase / decrease handwheel for pumping air, and the other end is equipped with two quick-release connectors. The two quick-release connectors are respectively connected to a differential pressure sensor and a differential pressure gauge through airtight hoses. The air passages of the two quick-release connectors are connected. The cavity is equipped with a fine-tuning handwheel for high-precision adjustment of the cavity output pressure.

4. The ground power supply inspection device for differential pressure control signals in a transport aircraft cabin according to claim 2, characterized in that, The cargo door control circuit includes a switch, a plug CZ, and a cable. The plug CZ has holes numbered 1 to 4. The switch is connected to holes 1 and 3 of the plug CZ via the cable. Hole 2 of the plug CZ is connected to the safety valve circuit. Hole 4 of the plug CZ is connected to the plug of the cargo bridge lock normal operation hydraulic solenoid valve. The plug of the cargo bridge lock normal operation hydraulic solenoid valve is connected to the test light.

5. The ground power supply inspection device for differential pressure control signals in a transport aircraft cabin according to claim 4, characterized in that, The differential pressure sensor is equipped with a micro switch, which includes two pairs of contacts, namely a pair of contacts numbered 1 and 2 and a pair of contacts numbered 3 and 4, and also includes a spring plate. The spring plate is connected to contacts 1 and 2 or contacts 3 and 4 according to the pressure change inside the differential pressure sensor.

6. The ground power supply inspection device for differential pressure control signals in a transport aircraft cabin according to claim 5, characterized in that, The 1 to 4 contacts inside the micro switch are connected one-to-one with the 1 to 4 holes of the plug CZ.

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