Aircraft dual cabin pressure simulation and control device

Abstract

The application belongs to the technical field of aircraft cabin pressure control, and particularly relates to a kind of aircraft double cabin pressure simulation and control device. The host computer of the application combines the simulated flight environment height, calculates the flight environment pressure according to the atmospheric pressure schedule table, simultaneously calculates the simulated cockpit pressure command value and cargo cabin pressure command value through the flight environment height, cabin pressure and exhaust valve opening angle, and controls the output pressure through the double-channel cabin pressure controller, collects the cabin pressure through the cockpit pressure sensor and cargo cabin pressure sensor, thereby quickly simulating the aircraft cockpit pressure and cargo cabin pressure. The aircraft double cabin pressure simulation and control device of the application can quickly verify the function and performance of the digital cabin pressure control system, and meets the demand of quickly delivering the cabin pressure control system for installation.

Description

Technical Field

[0001] This application belongs to the field of aircraft cabin pressure control technology, and specifically relates to an aircraft dual-cabin pressure simulation and control device. Background Technology

[0002] The cockpit pressure control system is a critical core system of large aircraft, and the loss of some of its key functions could cause irreparable and fatal harm to the personnel on board. Therefore, the cockpit pressure control system needs to undergo acceptance testing of its control functions before installation to ensure that the system indicators meet the design requirements.

[0003] Currently, the functional performance of cockpit pressure control systems is primarily tested using simulated cockpits and high-altitude simulators. Simulated cockpits are generally required to have a volume similar to that of an aircraft cockpit, and the cabin pressure control system regulates the cabin pressure under simulated aircraft environmental control system air supply conditions. High-altitude simulators primarily simulate the changes in flight environment pressure caused by aircraft flight, providing simulated flight environment pressure for the adjustment of the aircraft cockpit's exhaust valves. For large aircraft, both simulated cockpits and high-altitude simulators are large pieces of equipment. Using them for functional performance testing of cockpit pressure control systems involves long environmental preparation times, high risk levels, high environmental noise, complex product installation, numerous on-site operators, high testing costs, and long testing cycles, which cannot meet the demand for rapid delivery and installation of cockpit pressure control systems.

[0004] Therefore, it is desirable to have a technical solution to overcome or at least mitigate one of the aforementioned defects of the prior art. Utility Model Content

[0005] The purpose of this application is to provide an aircraft dual-cabin pressure simulation and control device to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] An aircraft dual-cabin pressure simulation and control device includes:

[0008] A main control computer, used to generate cockpit pressure command values ​​and cargo hold pressure command values;

[0009] A dual-channel cockpit pressure controller includes a pressure control module, a first output air path, and a second output air path. Both the first and second output air paths are connected to an air pump. The pressure control module is connected to the main control computer and is used to control the output pressure of the first output air path according to the cockpit pressure command value, and also to control the output pressure of the second output air path according to the cargo hold pressure command value.

[0010] A multi-port pressure testing device, comprising a cockpit pressure pipeline and a cargo hold pressure pipeline, wherein the input port of the cockpit pressure pipeline is connected to the first output air path and the cockpit pressure pipeline is provided with multiple cockpit pressure testing ports, and the input port of the cargo hold pressure pipeline is connected to the second output air path and the cargo hold pressure pipeline is provided with multiple cargo hold pressure testing ports.

[0011] A cockpit pressure sensor is installed on the cockpit pressure test interface and is connected to the main control computer to upload cockpit pressure signals to the main control computer.

[0012] A cargo hold pressure sensor is installed on the cargo hold pressure test interface and is connected to the main control computer for uploading cargo hold pressure signals to the main control computer.

[0013] The cockpit exhaust valve is connected to the main control computer and is used to upload the cockpit exhaust valve opening angle signal to the main control computer.

[0014] Cargo hold exhaust valve, which is connected to the main control computer, is used to upload the cargo hold exhaust valve opening angle signal to the main control computer;

[0015] The power supply control module is used to supply power to the dual-channel cabin pressure controller, the air pump, the cockpit pressure sensor, the cargo hold pressure sensor, the cockpit exhaust valve, and the cargo hold exhaust valve.

[0016] In at least one embodiment of this application, the main control computer generates the cockpit pressure command value based on the flight environment pressure, the cockpit pressure signal, and the cockpit exhaust valve opening angle signal, and generates the cargo hold pressure command value based on the flight environment pressure, the cargo hold pressure signal, and the cargo hold exhaust valve opening angle signal.

[0017] In at least one embodiment of this application, the pressure control module is connected to the host computer via an RS232 bus.

[0018] In at least one embodiment of this application, the first output gas path and the second output gas path are connected to the air pump via rubber gas pipelines.

[0019] In at least one embodiment of this application, the cockpit pressure line is connected to the first output air line via a rubber gas line, and the cargo hold pressure line is connected to the second output air line via a rubber gas line.

[0020] In at least one embodiment of this application,

[0021] The cockpit pressure pipeline is equipped with four cockpit pressure test ports, and the cockpit pressure sensor is installed on the cockpit pressure test ports via threaded connection.

[0022] The cargo hold pressure pipeline is equipped with four cargo hold pressure test ports, and the cargo hold pressure sensor is installed on the cargo hold pressure test ports via threaded connection.

[0023] In at least one embodiment of this application, the cockpit exhaust valve is connected to the main control computer via an ARINC429 bus.

[0024] In at least one embodiment of this application, the cargo compartment exhaust valve is connected to the main control computer via an ARINC429 bus.

[0025] The utility model has at least the following beneficial technical effects:

[0026] The dual-cabin pressure simulation and control device of this application can simulate flight environment pressure and cabin pressure to conduct functional performance tests of the cabin pressure control system. It has a short environmental preparation time, convenient, simple and flexible operation process, few test personnel required, low test cost, high test efficiency, and no large equipment hazards or environmental noise. It can realize the rapid verification of the functional performance of digital cabin pressure control system and meet the needs of rapid delivery and installation of cabin pressure control system. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of an aircraft dual-cabin pressure simulation and control device according to one embodiment of this application.

[0028] in:

[0029] 1-Main control computer; 2-Dual-channel cabin pressure controller; 3-Air pump; 4-Multi-interface pressure testing device; 5-Cockpit pressure sensor; 6-Cargo hold pressure sensor; 7-Cockpit exhaust valve; 8-Cargo hold exhaust valve; 9-Rubber gas pipeline; 10-Power supply control module. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0031] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0032] The following is in conjunction with the appendix Figure 1 This application will be described in further detail.

[0033] This application provides an aircraft dual-cabin pressure simulation and control device to replace existing simulated cockpits and high-altitude simulated cockpits, enabling rapid verification of the functional performance of a digital cockpit pressure control system. The aircraft dual-cabin pressure simulation and control device includes: a main control computer 1, a dual-channel cockpit pressure controller 2, an air pump 3, a multi-interface pressure testing device 4, a cockpit pressure sensor 5, a cargo hold pressure sensor 6, a cockpit exhaust valve 7, a cargo hold exhaust valve 8, rubber gas pipelines 9, and a power supply control module 10.

[0034] Specifically, such as Figure 1As shown, the main control computer 1 generates cockpit pressure command values ​​and cargo hold pressure command values, and sends these values ​​to the pressure control module of the dual-channel cockpit pressure controller 2 via an RS232 bus. The main control computer 1 calculates the flight environment altitude based on the simulated takeoff airport altitude and aircraft vertical speed, and calculates the flight environment pressure using linear interpolation according to the atmospheric pressure table, simulating the flight environment pressure value. The main control computer 1 generates the required simulated cockpit pressure command value based on the flight environment pressure, cockpit pressure signal, and cockpit exhaust valve opening angle signal, and generates the required simulated cargo hold pressure command value based on the flight environment pressure, cargo hold pressure signal, and cargo hold exhaust valve opening angle signal.

[0035] The dual-channel cabin pressure controller 2 includes a pressure control module, a first output air path, and a second output air path. Both the first and second output air paths are connected to an air pump 3, which provides pressure and vacuum. The pressure control module is connected to the main control computer 1 via an RS232 bus and controls the output pressure of the first output air path according to the cockpit pressure command value, and also controls the output pressure of the second output air path according to the cargo hold pressure command value. The pressure control module receives two cabin pressure command values ​​from the main control computer 1 and controls the air pump 3 in real time to generate two pressure sources with the same command values, quickly controlling the output pressure of the two independent output air paths to the cockpit pressure command value and the cargo hold pressure command value. In a preferred embodiment of this application, the input interfaces of both the first and second output air paths are connected to the air pump 3 via rubber gas pipes 9.

[0036] The multi-port pressure testing device 4 includes two independent pressure lines: a cockpit pressure line and a cargo hold pressure line. The input port of the cockpit pressure line is connected to the output port of the first output air line, and multiple cockpit pressure testing ports are provided on the cockpit pressure line. The input port of the cargo hold pressure line is connected to the output port of the second output air line, and multiple cargo hold pressure testing ports are provided on the cargo hold pressure line.

[0037] In a preferred embodiment of this application, the cockpit pressure line is connected to the first output air line via a rubber gas line 9, and the cargo hold pressure line is connected to the second output air line via a rubber gas line 9. In this embodiment, the cockpit pressure line is provided with four cockpit pressure test ports, and the cockpit pressure sensor 5 is installed on the cockpit pressure test ports via threaded connections; the cargo hold pressure line is provided with four cargo hold pressure test ports, and the cargo hold pressure sensor 6 is installed on the cargo hold pressure test ports via threaded connections.

[0038] The cockpit pressure sensor 5 is used to measure the pressure of the cockpit pressure line. The four cockpit pressure sensors 5 are respectively installed on the corresponding cockpit pressure test interface through threaded connection. The cockpit pressure sensor 5 is connected to the main control computer 1 to upload the cockpit pressure signal to the main control computer 1. The cargo hold pressure sensor 6 is used to measure the pressure of the cargo hold pressure line. The four cargo hold pressure sensors 6 are respectively installed on the corresponding cargo hold pressure test interface through threaded connection. The cargo hold pressure sensor 6 is connected to the main control computer 1 to upload the cargo hold pressure signal to the main control computer 1.

[0039] The cockpit exhaust valve 7 is connected to the main control computer 1 and is used to upload the cockpit exhaust valve opening angle signal to the main control computer 1; the cargo hold exhaust valve 8 is connected to the main control computer 1 and is used to upload the cargo hold exhaust valve opening angle signal to the main control computer 1. In this embodiment, both the cockpit exhaust valve 7 and the cargo hold exhaust valve 8 are connected to the main control computer 1 via the ARINC429 bus, and the opening angles of the cockpit exhaust valve 7 and the cargo hold exhaust valve 8 are sent to the main control computer 1 in real time via the ARINC429 bus.

[0040] The power supply control module 10 is connected to the dual-channel cabin pressure controller 2, air pump 3, cockpit pressure sensor 5, cargo hold pressure sensor 6, cockpit exhaust valve 7, and cargo hold exhaust valve 8 via power supply cables, and is used to provide power to each electronic component.

[0041] This application discloses an aircraft dual-cabin pressure simulation and control device. The main control computer 1 calculates the flight environment pressure based on the simulated flight altitude and atmospheric pressure table. Simultaneously, it calculates the required cockpit and cargo hold pressure command values ​​using the flight environment altitude, cabin pressure, and exhaust valve opening angle. The output pressure is controlled by a dual-channel cabin pressure controller 2, and cabin pressure is collected by cockpit pressure sensors 5 and cargo hold pressure sensors 6, thus rapidly simulating aircraft cockpit and cargo hold pressure. This application can simulate flight environment pressure and cabin pressure for functional performance testing of the cabin pressure control system. It features short environmental preparation time, convenient, simple, and flexible operation, low personnel requirements, low testing costs, high testing efficiency, and no large equipment hazards or environmental noise. It enables rapid verification of the functional performance of digital cabin pressure control systems, meeting the need for rapid delivery and installation of cabin pressure control systems.

[0042] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aircraft dual-cabin pressure simulation and control device, characterized in that, include: The main control computer (1) is used to generate cockpit pressure command values ​​and cargo hold pressure command values; A dual-channel cabin pressure controller (2) includes a pressure control module, a first output air path, and a second output air path. Both the first and second output air paths are connected to an air pump (3). The pressure control module is connected to the main control computer (1) and is used to control the output pressure of the first output air path according to the cockpit pressure command value, and also to control the output pressure of the second output air path according to the cargo hold pressure command value. A multi-port pressure testing device (4) includes a cockpit pressure pipeline and a cargo hold pressure pipeline. The input interface of the cockpit pressure pipeline is connected to the first output air path. The cockpit pressure pipeline is provided with multiple cockpit pressure testing interfaces. The input interface of the cargo hold pressure pipeline is connected to the second output air path. The cargo hold pressure pipeline is provided with multiple cargo hold pressure testing interfaces. The cockpit pressure sensor (5) is installed on the cockpit pressure test interface and is connected to the main control computer (1) to upload the cockpit pressure signal to the main control computer (1). Cargo hold pressure sensor (6), the cargo hold pressure sensor (6) is installed on the cargo hold pressure test interface, the cargo hold pressure sensor (6) is connected to the main control computer (1) and is used to upload the cargo hold pressure signal to the main control computer (1); The cockpit exhaust valve (7) is connected to the main control computer (1) and is used to upload the cockpit exhaust valve opening angle signal to the main control computer (1). Cargo hold exhaust valve (8), which is connected to the main control computer (1) and is used to upload the cargo hold exhaust valve opening angle signal to the main control computer (1); The power supply control module (10) is used to supply power to the dual-channel cabin pressure controller (2), the air pump (3), the cockpit pressure sensor (5), the cargo hold pressure sensor (6), the cockpit exhaust valve (7), and the cargo hold exhaust valve (8).

2. The aircraft dual-cabin pressure simulation and control device according to claim 1, characterized in that, The main control computer (1) generates the cockpit pressure command value based on the flight environment pressure, the cockpit pressure signal and the cockpit exhaust valve opening angle signal, and generates the cargo hold pressure command value based on the flight environment pressure, the cargo hold pressure signal and the cargo hold exhaust valve opening angle signal.

3. The aircraft dual-cabin pressure simulation and control device according to claim 1, characterized in that, The pressure control module is connected to the main control computer (1) via an RS232 bus.

4. The aircraft dual-cabin pressure simulation and control device according to claim 1, characterized in that, The first output air path and the second output air path are connected to the air pump (3) via rubber gas pipes (9).

5. The aircraft dual-cabin pressure simulation and control device according to claim 1, characterized in that, The cockpit pressure line is connected to the first output air line via a rubber gas line (9), and the cargo hold pressure line is connected to the second output air line via a rubber gas line (9).

6. The aircraft dual-cabin pressure simulation and control device according to claim 1, characterized in that, The cockpit pressure pipeline is provided with four cockpit pressure test ports, and the cockpit pressure sensor (5) is installed on the cockpit pressure test ports by threaded connection; The cargo hold pressure pipeline is provided with four cargo hold pressure test ports, and the cargo hold pressure sensor (6) is installed on the cargo hold pressure test ports by threaded connection.

7. The aircraft dual-cabin pressure simulation and control device according to claim 1, characterized in that, The cockpit exhaust valve (7) is connected to the main control computer (1) via the ARINC429 bus.

8. The aircraft dual-cabin pressure simulation and control device according to claim 1, characterized in that, The cargo compartment exhaust valve (8) is connected to the main control computer (1) via the ARINC429 bus.

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