A digital pressurization control system for a twin-fuselage aircraft

Abstract

The application belongs to the field of aircraft environmental control system, and particularly relates to a digital pressurization control system for double air-tight cabins of an aircraft. The system comprises: a cockpit pressure sensor arranged inside a cockpit, a cargo cabin pressure sensor arranged inside a cargo cabin; a cockpit exhaust valve arranged on a cockpit wall panel, a cargo cabin exhaust valve arranged on a cargo cabin wall panel; an inter-cabin balance valve arranged on an inter-cabin partition; a cockpit safety valve arranged on the cockpit wall panel, a cargo cabin safety valve arranged on the cargo cabin wall panel; a cockpit negative pressure valve arranged on the cockpit wall panel, a cargo cabin negative pressure valve arranged on the cargo cabin wall panel; and a cockpit pressure regulation control computer for collecting pressure measured values fed back by the pressure sensors and controlling the exhaust valves and the inter-cabin balance valve. The application can meet the needs of pressurization control of the cockpit and the cargo cabin respectively.

Description

Technical Field

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

[0002] For fighter aircraft, both domestic and international cabin pressurization systems utilize pneumatic pressure regulation. For transport aircraft, cabin pressurization control systems have evolved through pneumatic, electro-pneumatic, and electro-electric stages, entering the fully digital era. Pneumatic cabin pressure regulation systems utilize pneumatic control signals and pneumatic exhaust valves. Electro-pneumatic cabin pressure regulation systems are characterized by first converting electric control signals into pneumatic control signals, which then control the pneumatic exhaust valves. Digital cabin pressure regulation systems integrate a high degree of functionality, including operation, control, display, alarms, maintenance, and information input and output. Their core component is the control software. Currently, all major international passenger aircraft cabin pressurization systems utilize digital systems.

[0003] The actuator of the digital cabin pressure regulation system is an electric exhaust valve. Traditional pneumatic exhaust valves are structurally composed of a bellows, diaphragm, valve seat, spring, and calibrated orifice. The electric exhaust valve operates by rotating the valve plate through a motor and reduction mechanism via multiple controller channels. Cabin pressurization control systems on large European and American military transport aircraft, such as the C17, also generally utilize a digital cabin pressure regulation system. During sub-compartment pressurization, both the cockpit and cargo compartment are simultaneously depressurized, relying on personal protective equipment to meet the physiological needs of the crew and passengers. These systems feature single-compartment pressurization, digital control signals, and an electric exhaust valve. The system's multi-redundant design ensures the controller can control the exhaust valves through multiple channels. The Russian-made Il-76 transport aircraft utilizes a dual-compartment pneumatic pressure regulation system, allowing for separate pressurization of the cockpit and cargo compartments during sub-compartment pressurization. These systems feature dual-compartment control, a dual residual pressure system, a pneumatic control signal, and pneumatic exhaust valves.

[0004] Traditional aircraft cabin pressurization control systems are generally designed for a single airtight pressurized compartment. For example, on a typical airliner, the cockpit, passenger cabin, cargo hold, and electronics compartment are all located within a single airtight pressurized compartment, separated by several non-airtight structures. During cabin pressurization, each compartment maintains the same pressurized environment. Currently, most modern airliners utilize a single-cabin digital pressure regulation system for cabin pressurization. Some aircraft employ a dual-cabin structure with airtight pressure regulation to facilitate compartmentalized pressurization. This dual-cabin pneumatic pressure regulation system, however, has more design components than a digital pressure regulation system, is cumbersome to use, and offers slightly lower precision in pressurization parameter adjustment.

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

[0006] The purpose of this 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] A digital pressurization control system for a double-airtight cabin of an aircraft, the double-airtight cabin of the aircraft comprising a cockpit and a cargo hold, a cabin partition being provided between the cockpit and the cargo hold, the digital pressurization control system for the double-airtight cabin of the aircraft comprising:

[0009] Pressure sensors, including 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] Exhaust valves, including a cockpit exhaust valve and a cargo hold exhaust valve, wherein the cockpit exhaust valve is arranged on the cockpit wall panel, and the cargo hold exhaust valve is arranged on the cargo hold wall panel;

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

[0012] Safety valves, including a cockpit safety valve and a cargo hold safety valve, wherein 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;

[0013] Negative pressure valves, including a cockpit negative pressure valve and a cargo hold negative pressure valve, wherein 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;

[0014] The 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 provided in plurality inside the cockpit;

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

[0019] In at least one embodiment of the present application, the aircraft dual 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 a calculated cockpit pressure value in real time according to a preset algorithm, and controls the cockpit exhaust valve according to the difference between the calculated cockpit pressure value and the measured pressure value;

[0022] The cabin pressure control computer obtains a variety of flight parameter data and calculates the cargo hold pressure 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 value 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 pressure value of the cockpit and the actual 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 cabin pressure 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 actual measured pressure value of the cargo hold is greater than a 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 provided in plurality on the cockpit wall panel;

[0033] The cargo hold safety valve is provided 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 actual 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 provided in plurality on the cockpit wall panel;

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

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

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

[0042] Figure 1 This 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 This 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 solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments 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 the embodiments. 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 understood 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 this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and 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, be constructed and operated in a specific orientation. Therefore, it should not be understood as limiting the scope of protection of this application.

[0046] The following is combined with Figures 1 to 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 hold. A cabin partition is provided between the cockpit and the cargo hold. The digital pressurization control system for the double airtight cabin of the aircraft includes: a pressure sensor, an exhaust valve, an inter-cabin balancing valve, a safety valve, a negative pressure valve and a cabin pressure regulation control computer.

[0048] Specifically, such as 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 set 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 set 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 control computer.

[0051] The safety valves include cockpit safety valves and cargo hold safety valves. The cockpit safety valve is set on the cockpit wall panel, and the cargo hold safety valve is set on the cargo hold wall panel. The safety valves can protect the cockpit and cargo hold structures from bearing excessive positive pressure loads; the negative pressure valves include cockpit negative pressure valves and cargo hold negative pressure valves. The cockpit negative pressure valve is set on the cockpit wall panel, and the cargo hold negative pressure valve is set on the cargo hold wall panel. The negative pressure valves can protect the cockpit and cargo hold structures from bearing 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 achieve redundancy control. The multi-redundant design ensures 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] The present invention relates to a dual-cabin digital pressurization control system for an aircraft. The cabin pressure control computer (CPCC) acquires multiple flight parameter data and calculates a cockpit pressure value in real time based on a preset algorithm. The cockpit exhaust valve is controlled based on the difference between the calculated cockpit pressure value and the measured pressure value. The CPCC also acquires multiple flight parameter data and calculates a cargo hold pressure value in real time based on a preset algorithm. The cargo hold exhaust valve is controlled based on the difference between the calculated and measured pressure values. 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 CPCC receives cabin pressure and converts it into an electric signal. It also receives multiple flight parameter data and continuously calculates the cabin pressure and its rate of change to meet pre-programmed requirements. The exhaust valve is controlled in real time based on the difference between the calculated and measured pressure values.

[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 pressure measured in the cockpit and the actual pressure measured in the cargo hold.

[0056] In a preferred embodiment of the present application, the system has an alarm function. When the actual measured pressure value of the cockpit exceeds the first preset pressure range, the cabin pressure regulation control computer issues an alarm; when the actual measured pressure value of 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 cockpit pressure exceeds a first positive pressure threshold, the cockpit safety valve opens; when the measured cargo hold pressure exceeds a second positive pressure threshold, the cargo hold safety valve opens. Multiple cockpit safety valves are provided on the cockpit wall panel, and multiple cargo hold safety valves are provided on the cargo hold wall panel.

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

[0059] The aircraft dual-airtight cabin digital pressurization control system of the present application is suitable for large military transport aircraft. The dual-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 dual airtight cabin digital pressurization control system of the present application has the following beneficial effects compared with the prior art:

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

[0062] Digital control and communication minimize crew misoperation, improving system operation safety and passenger comfort;

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

[0064] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection 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 hold, and a cabin partition is provided between the cockpit and the cargo hold, characterized in that: The aircraft double airtight cabin digital pressurization control system includes: Pressure sensors, including 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; Exhaust valves, including a cockpit exhaust valve and a cargo hold exhaust valve, wherein the cockpit exhaust valve is arranged on the cockpit wall panel, and the cargo hold exhaust valve is arranged on the cargo hold wall panel; an inter-cabin balancing valve, the inter-cabin balancing valve being arranged on the cabin bulkhead; Safety valves, including a cockpit safety valve and a cargo hold safety valve, wherein 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; Negative pressure valves, including a cockpit negative pressure valve and a cargo hold negative pressure valve, wherein 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; a cabin pressure regulation control computer, the cabin pressure regulation control computer being used to collect the actual pressure value fed back by the pressure sensor and control the exhaust valve and the inter-cabin equalization valve; The cockpit pressure control computer acquires a variety of flight parameter data and calculates a calculated cockpit pressure value in real time according to a preset algorithm, and controls the cockpit exhaust valve according to the difference between the calculated cockpit pressure value and the measured pressure value; The cabin pressure control computer acquires a variety of flight parameter data and calculates a 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 and the measured pressure value of the cargo hold; 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; The cabin pressure adjustment control computer controls the inter-cabin balancing valve according to the difference between the actual pressure value of the cockpit and the actual pressure value of the cargo hold.

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 exchange with the pressure sensor, the exhaust valve and the inter-cabin balancing 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 provided in plurality inside the cockpit; A plurality of cargo hold pressure sensors are provided 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: When the measured pressure value of the cockpit exceeds a first preset pressure range, the cabin pressure 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.

6. 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 actual measured pressure value of the cargo hold is greater than a second positive pressure threshold, the cargo hold safety valve opens.

7. The aircraft double airtight cabin digital pressurization control system according to claim 6, characterized in that: The cockpit safety valve is provided in plurality on the cockpit wall panel; The cargo hold safety valve is provided in plurality on the cargo hold wall panel.

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 is less than a first negative pressure threshold, the cockpit negative pressure valve opens; When the actual measured pressure value of the cargo hold is less than the second negative pressure threshold, the cargo hold negative pressure valve opens.

9. The aircraft double airtight cabin digital pressurization control system according to claim 8, characterized in that: The cockpit negative pressure valve is provided in plurality on the cockpit wall panel; The cargo hold negative pressure valve is provided in plurality on the cargo hold wall panel.

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