Digital pressurization control system for double airtight cabins of airplane

Abstract

The invention belongs to the field of aircraft environment control systems, and particularly relates to a digital pressurization control system for double airtight cabins of an aircraft. According to the system, a cockpit pressure sensor is arranged in a cockpit, and a cargo hold pressure sensor is arranged in a cargo hold; the cockpit exhaust valve is arranged on the cockpit wall plate, and the cargo compartment exhaust valve is arranged on the cargo compartment wall plate; the inter-cabin balance valve is arranged on the inter-cabin partition plate; the cockpit safety valve is arranged on the cockpit wall plate, and the cargo hold safety valve is arranged on the cargo hold wall plate; the driving cabin negative pressure valve is arranged on the driving cabin wall plate, and the cargo cabin negative pressure valve is arranged on the cargo cabin wall plate; and the cabin pressure regulation control computer is used for collecting a pressure measured value fed back by the pressure sensor and controlling the exhaust valve and the inter-cabin balance valve. The requirement for respective pressurization control of the cockpit and the cargo hold can be met.

Description

Technical Field

[0001] The present application belongs to the field of aircraft environmental control systems, and in particular to a digital pressurization control system for a double airtight cabin of an aircraft. Background Art

[0002] For fighter jets, both domestic and foreign cabin pressurization adopts pneumatic pressure regulation structure. For transport aircraft, the cabin pressurization control system has gone through the development stages of pneumatic, electronic-pneumatic, and electronic-electric, and has entered the full digital era. The pneumatic cabin pressure regulation system adopts pneumatic control signals and pneumatic exhaust valves. The characteristic of the electronic pneumatic cabin pressure regulation system is that the electric control signal is first converted into a pneumatic control signal, and then the pneumatic exhaust valve is controlled. In the digital cabin pressure regulation system, the operation, control, display, alarm, maintenance, and input and output information of the cabin pressure control have been highly integrated, and its core part is the control software. At present, the cabin pressurization control of major foreign passenger aircraft all adopts a digital cabin pressure regulation system.

[0003] The actuator of the digital cabin pressure regulation system is an electric exhaust valve. The traditional pneumatic exhaust valve is composed of a diaphragm box, a diaphragm, a valve seat, a spring, a sizing hole, etc. The working mode of the electric exhaust valve is that the controller drives the valve plate to rotate through the motor and the reduction mechanism through multiple channels. The cabin pressurization control system of large military transport aircraft in Europe and the United States generally adopts a digital cabin pressure regulation system, such as C17. When performing the compartment pressurization task, the cockpit and the cargo compartment are depressurized at the same time, relying on personal protective equipment to meet the physiological needs of the crew and passengers. Its characteristics are single-cabin pressurization, digital control signal, electric exhaust valve, and the system's multi-redundancy design ensures that the controller can control the exhaust valve through multiple channels to complete the work. The Russian-made Il-76 transport aircraft adopts a dual-cabin pneumatic pressure regulation system. When performing the compartment pressurization task, the cockpit and the cargo compartment can be pressurized separately. Its characteristics are dual-cabin control, dual residual pressure system, pneumatic control signal, and pneumatic exhaust valve.

[0004] The traditional design of aircraft cabin pressurization control system is generally for a single airtight pressurized cabin. For example, in an ordinary passenger aircraft, the cockpit, passenger cabin, cargo cabin, electronic equipment cabin, etc. are all in an airtight pressurized cabin, but are separated by several non-airtight structures. When the cabin is pressurized, each compartment is in the same pressurized environment. At present, most modern passenger aircraft use a single-cabin digital pressure regulation system as a cabin pressurization design scheme. Some aircraft use a double airtight pressurized cabin structure to perform compartment pressurization tasks, and use a double-cabin pneumatic pressure regulation. Compared with the digital pressure regulation system, its system design has many accessories, cumbersome use, and the accuracy of pressurization parameter adjustment is slightly poor.

[0005] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0006] The purpose of the present application is to provide a digital pressurization control system for a double airtight cabin of an aircraft to solve at least one problem existing in the prior art.

[0007] The technical solution of this application is:

[0008] An aircraft double airtight cabin digital pressurization control system, the aircraft double airtight cabin comprising a cockpit and a cargo cabin, a cabin partition is provided between the cockpit and the cargo cabin, the aircraft double airtight cabin digital pressurization control system comprising:

[0009] A pressure sensor, comprising a cockpit pressure sensor and a cargo hold pressure sensor, wherein the cockpit pressure sensor is disposed inside the cockpit, and the cargo hold pressure sensor is disposed inside the cargo hold;

[0010] An exhaust valve, comprising a cockpit exhaust valve and a cargo hold exhaust valve, wherein the cockpit exhaust valve is arranged on the cockpit wall plate, and the cargo hold exhaust valve is arranged on the cargo hold wall plate;

[0011] An inter-cabin balancing valve, the inter-cabin balancing valve being arranged on the cabin bulkhead;

[0012] A safety valve, comprising a cockpit safety valve and a cargo hold safety valve, wherein the cockpit safety valve is arranged on the cockpit wall plate, and the cargo hold safety valve is arranged on the cargo hold wall plate;

[0013] A negative pressure valve, comprising a cockpit negative pressure valve and a cargo hold negative pressure valve, wherein the cockpit negative pressure valve is arranged on the cockpit wall plate, and the cargo hold negative pressure valve is arranged on the cargo hold wall plate;

[0014] A cabin pressure regulation control computer is used to collect the actual pressure value fed back by the pressure sensor and control the exhaust valve and the inter-cabin balance valve.

[0015] In at least one embodiment of the present application, a pressure control panel is provided inside the cockpit, and the cabin pressure regulation control computer realizes data interaction with the pressure sensor, the exhaust valve and the inter-cabin balance valve through the pressure control panel.

[0016] In at least one embodiment of the present application,

[0017] The cockpit pressure sensor is arranged in plurality inside the cockpit;

[0018] A plurality of cargo hold pressure sensors are disposed inside the cargo hold.

[0019] In at least one embodiment of the present application, the aircraft double airtight cabin digital pressurization control system adopts a triple-redundant working mode, including two identical and independent automatic control channels and an independent manual control channel.

[0020] In at least one embodiment of the present application,

[0021] The cockpit pressure control computer acquires a variety of flight parameter data, and calculates the cockpit pressure calculated value in real time according to a preset algorithm, and controls the cockpit exhaust valve according to the difference between the cockpit pressure calculated value and the pressure measured value;

[0022] The cabin pressure control computer acquires a variety of flight parameter data, and calculates the calculated pressure value of the cargo hold in real time according to a preset algorithm, and controls the cargo hold exhaust valve according to the difference between the calculated pressure value of the cargo hold and the actual pressure value.

[0023] In at least one embodiment of the present application, the flight parameter data includes atmospheric data, flight management data, door closing data, engine throttle lever data, landing gear wheel load data and flight attitude data.

[0024] In at least one embodiment of the present application, the cabin pressure regulation control computer controls the inter-cabin balancing valve according to the difference between the actual measured pressure value of the cockpit and the actual measured pressure value of the cargo hold.

[0025] In at least one embodiment of the present application,

[0026] When the measured pressure value of the cockpit exceeds a first preset pressure range, the cockpit pressure regulation control computer issues an alarm;

[0027] When the actual measured pressure value of the cargo hold exceeds a second preset pressure range, the cabin pressure regulation control computer issues an alarm.

[0028] In at least one embodiment of the present application,

[0029] When the measured pressure value of the cockpit is greater than a first positive pressure threshold, the cockpit safety valve opens;

[0030] When the actually measured pressure value of the cargo hold is greater than the second positive pressure threshold, the cargo hold safety valve opens.

[0031] In at least one embodiment of the present application,

[0032] The cockpit safety valve is arranged in plurality on the cockpit wall panel;

[0033] The cargo hold safety valve is arranged in plurality on the cargo hold wall panel.

[0034] In at least one embodiment of the present application,

[0035] When the measured pressure value of the cockpit is less than a first negative pressure threshold, the cockpit negative pressure valve opens;

[0036] When the actually measured pressure value of the cargo hold is less than the second negative pressure threshold, the cargo hold negative pressure valve opens.

[0037] In at least one embodiment of the present application,

[0038] The cockpit negative pressure valve is arranged in plurality on the cockpit wall panel;

[0039] The cargo hold negative pressure valve is arranged in plurality on the cargo hold wall panel.

[0040] The invention has at least the following beneficial technical effects:

[0041] The aircraft double airtight cabin digital pressurization control system of the present application is suitable for aircraft with double airtight structural cabins, and can meet the needs of separate pressurization control of the cockpit and the cargo cabin when performing compartment pressurization tasks; it adopts digital pressure regulation system technology for double cabin pressurization control to meet the digital control and communication needs of the entire aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 It is a schematic diagram of a digital pressurization control system for a double airtight cabin of an aircraft according to one embodiment of the present application;

[0043] Figure 2 It is a schematic diagram of a digital pressurization control system for a double airtight cabin of an aircraft according to one embodiment of the present application. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0045] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0046] The following is combined with Figure 1 to Figure 2 This application is described in further detail.

[0047] The present application provides a digital pressurization control system for a double airtight cabin of an aircraft. The double airtight cabin of the aircraft includes a cockpit and a cargo cabin. A cabin partition is provided between the cockpit and the cargo cabin. The digital pressurization control system for the double airtight cabin of the aircraft includes: a pressure sensor, an exhaust valve, an inter-cabin balance valve, a safety valve, a negative pressure valve and a cabin pressure regulation control computer.

[0048] Specifically, Figure 1 As shown, the pressure sensor includes a cockpit pressure sensor and a cargo hold pressure sensor. The cockpit pressure sensor is arranged inside the cockpit, and the cargo hold pressure sensor is arranged inside the cargo hold. The pressure sensors are used to collect pressure signals and provide the cockpit and cargo hold pressure signals to the cabin pressure regulation control computer.

[0049] The exhaust valve includes a cockpit exhaust valve and a cargo hold exhaust valve. The cockpit exhaust valve is arranged on the cockpit wall panel. The cockpit exhaust valve is used to receive instructions from the cabin pressure regulation control computer and control the air flow discharged out of the cockpit. The cargo hold exhaust valve is arranged on the cargo hold wall panel. The cargo hold exhaust valve is used to receive instructions from the cabin pressure regulation control computer and control the air flow discharged out of the cargo hold.

[0050] The inter-cabin balancing valve is set on the cabin bulkhead and is used to connect or disconnect the cockpit and cargo hold according to the instructions of the cabin pressure regulation control computer.

[0051] The safety valves include a cockpit safety valve and a cargo hold safety valve. The cockpit safety valve is arranged on the cockpit wall panel, and the cargo hold safety valve is arranged on the cargo hold wall panel. The safety valves can protect the cockpit and cargo hold structures from being subjected to excessive positive pressure loads. The negative pressure valves include a cockpit negative pressure valve and a cargo hold negative pressure valve. The cockpit negative pressure valve is arranged on the cockpit wall panel, and the cargo hold negative pressure valve is arranged on the cargo hold wall panel. The negative pressure valves can protect the cockpit and cargo hold structures from being subjected to excessive negative pressure loads.

[0052] The cabin pressure control computer is used to collect the actual pressure values ​​fed back by the pressure sensor and control the exhaust valve and the inter-cabin balance valve.

[0053] In a preferred embodiment of the present application, a pressure control panel is provided inside the cockpit, and the cabin pressure control computer realizes data interaction with the pressure sensor, the exhaust valve and the inter-cabin balance valve through the pressure control panel. The pressure control panel serves as the crew operation interface, and can perform automatic, manual and emergency operations. Preferably, multiple cockpit pressure sensors are provided inside the cockpit; multiple cargo compartment pressure sensors are provided inside the cargo compartment to realize redundancy control. The multi-redundant design is used to ensure that the control computer can control the exhaust valve through multiple channels to complete the work. In this embodiment, the aircraft double airtight cabin digital pressurization control system adopts a triple-redundant working mode, including two identical and independent automatic control channels and one independent manual control channel.

[0054] In the aircraft double airtight cabin digital pressurization control system of the present application, the cabin pressure adjustment control computer obtains a variety of flight parameter data, and calculates the cockpit pressure calculation value in real time according to a preset algorithm, and controls the cockpit exhaust valve according to the difference between the cockpit pressure calculation value and the pressure measured value; the cabin pressure adjustment control computer obtains a variety of flight parameter data, and calculates the cargo hold pressure calculation value in real time according to a preset algorithm, and controls the cargo hold exhaust valve according to the difference between the cargo hold pressure calculation value and the pressure measured value. Among them, the flight parameter data includes atmospheric data, flight management data, cabin door closing data, engine throttle lever data, landing gear wheel load data and flight attitude data. The cabin pressure adjustment control computer receives the cabin pressure and converts it into an electric signal, and at the same time receives a variety of flight parameter data, continuously calculates the cabin pressure and the rate of change, so that it meets the requirements of the predetermined program, and controls the exhaust valve in real time according to the difference between the pressure calculation value and the pressure measured value.

[0055] In a preferred embodiment of the present application, the system has a dual-cabin balancing function, and the cabin pressure control computer controls the inter-cabin balancing valve according to the difference between the actual measured pressure value of the cockpit and the actual measured pressure value of the cargo hold.

[0056] In a preferred embodiment of the present application, the system has an alarm function. When the actual measured pressure value in the cockpit exceeds the first preset pressure range, the cabin pressure regulation control computer issues an alarm; when the actual measured pressure value in the cargo hold exceeds the second preset pressure range, the cabin pressure regulation control computer issues an alarm.

[0057] In a preferred embodiment of the present application, when the measured pressure value of the cockpit is greater than the first positive pressure threshold, the cockpit safety valve opens; when the measured pressure value of the cargo hold is greater than the second positive pressure threshold, the cargo hold safety valve opens. There are multiple cockpit safety valves on the cockpit wall; there are multiple cargo hold safety valves on the cargo hold wall.

[0058] In a preferred embodiment of the present application, when the measured pressure value of the cockpit is less than the first negative pressure threshold, the cockpit negative pressure valve opens; when the measured pressure value of the cargo hold is less than the second negative pressure threshold, the cargo hold negative pressure valve opens. There are multiple cockpit negative pressure valves on the cockpit wall; there are multiple cargo hold negative pressure valves on the cargo hold wall.

[0059] The aircraft double airtight cabin digital pressurization control system of the present application is suitable for large military transport aircraft. The double airtight cabin digital pressurization control system technology is applied to the design of the cabin pressurization control system, which can realize separate pressurization control of the cockpit and cargo compartment, realize the monitoring and adjustment of the cabin pressure, and has cabin safety protection and alarm functions.

[0060] The aircraft double airtight cabin digital pressurization control system of the present application has the following beneficial effects compared with the prior art:

[0061] The double-cabin pressurization control can meet the needs of the aircraft to perform normal transportation and compartment pressurization tasks;

[0062] Digital control and communication can minimize crew misoperation and improve system operation safety and passenger comfort.

[0063] The redundant design of the cabin pressure control computer and the multi-channel electric exhaust valve makes the cabin pressure control system more reliable.

[0064] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A digital pressurization control system for a double airtight cabin of an aircraft, wherein the double airtight cabin of the aircraft comprises a cockpit and a cargo cabin, and a cabin partition is provided between the cockpit and the cargo cabin, wherein: The aircraft double airtight cabin digital pressurization control system comprises: A pressure sensor, comprising a cockpit pressure sensor and a cargo hold pressure sensor, wherein the cockpit pressure sensor is disposed inside the cockpit, and the cargo hold pressure sensor is disposed inside the cargo hold; An exhaust valve, comprising a cockpit exhaust valve and a cargo hold exhaust valve, wherein the cockpit exhaust valve is arranged on the cockpit wall plate, and the cargo hold exhaust valve is arranged on the cargo hold wall plate; An inter-cabin balancing valve, the inter-cabin balancing valve being arranged on the cabin bulkhead; A safety valve, comprising a cockpit safety valve and a cargo hold safety valve, wherein the cockpit safety valve is arranged on the cockpit wall plate, and the cargo hold safety valve is arranged on the cargo hold wall plate; A negative pressure valve, comprising a cockpit negative pressure valve and a cargo hold negative pressure valve, wherein the cockpit negative pressure valve is arranged on the cockpit wall plate, and the cargo hold negative pressure valve is arranged on the cargo hold wall plate; A cabin pressure regulation control computer is used to collect the actual pressure value fed back by the pressure sensor and control the exhaust valve and the inter-cabin balance valve.

2. The aircraft double airtight cabin digital pressurization control system according to claim 1, characterized in that: A pressure control panel is provided inside the cockpit, and the cabin pressure regulation control computer realizes data interaction with the pressure sensor, the exhaust valve and the inter-cabin balance valve through the pressure control panel.

3. The aircraft double airtight cabin digital pressurization control system according to claim 2, characterized in that: The cockpit pressure sensor is arranged in plurality inside the cockpit; A plurality of cargo hold pressure sensors are disposed inside the cargo hold.

4. The aircraft double airtight cabin digital pressurization control system according to claim 3, characterized in that: The aircraft double airtight cabin digital pressurization control system adopts a triple-redundant working mode, including two identical and mutually independent automatic control channels and an independent manual control channel.

5. The aircraft double airtight cabin digital pressurization control system according to claim 1, characterized in that: The cockpit pressure control computer acquires a variety of flight parameter data, and calculates the cockpit pressure calculated value in real time according to a preset algorithm, and controls the cockpit exhaust valve according to the difference between the cockpit pressure calculated value and the pressure measured value; The cabin pressure control computer acquires a variety of flight parameter data, and calculates the calculated pressure value of the cargo hold in real time according to a preset algorithm, and controls the cargo hold exhaust valve according to the difference between the calculated pressure value of the cargo hold and the actual pressure value.

6. The aircraft double airtight cabin digital pressurization control system according to claim 5, characterized in that: The flight parameter data include atmospheric data, flight management data, door closing data, engine throttle lever data, landing gear wheel load data and flight attitude data.

7. The aircraft double airtight cabin digital pressurization control system according to claim 6, characterized in that: The cabin pressure regulating control computer controls the inter-cabin balancing valve according to the difference between the actual measured pressure value of the cockpit and the actual measured pressure value of the cargo hold.

8. The aircraft double airtight cabin digital pressurization control system according to claim 7, characterized in that: When the measured pressure value of the cockpit exceeds a first preset pressure range, the cockpit pressure regulation control computer issues an alarm; When the actual measured pressure value of the cargo hold exceeds a second preset pressure range, the cabin pressure regulation control computer issues an alarm.

9. The aircraft double airtight cabin digital pressurization control system according to claim 1, characterized in that: When the measured pressure value of the cockpit is greater than a first positive pressure threshold, the cockpit safety valve opens; When the actually measured pressure value of the cargo hold is greater than the second positive pressure threshold, the cargo hold safety valve opens.

10. The aircraft double airtight cabin digital pressurization control system according to claim 9, characterized in that: The cockpit safety valve is arranged in plurality on the cockpit wall panel; The cargo hold safety valve is arranged in plurality on the cargo hold wall panel.

11. The aircraft double airtight cabin digital pressurization control system according to claim 10, characterized in that: When the measured pressure value of the cockpit is less than a first negative pressure threshold, the cockpit negative pressure valve opens; When the actually measured pressure value of the cargo hold is less than the second negative pressure threshold, the cargo hold negative pressure valve opens.

12. The aircraft double airtight cabin digital pressurization control system according to claim 11, characterized in that: The cockpit negative pressure valve is arranged in plurality on the cockpit wall panel; The cargo hold negative pressure valve is arranged in plurality on the cargo hold wall panel.

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