CN117382887A - Pneumatic cabin pressure regulating system based on digital control for aircraft - Google Patents
Pneumatic cabin pressure regulating system based on digital control for aircraft Download PDFInfo
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- CN117382887A CN117382887A CN202311347640.5A CN202311347640A CN117382887A CN 117382887 A CN117382887 A CN 117382887A CN 202311347640 A CN202311347640 A CN 202311347640A CN 117382887 A CN117382887 A CN 117382887A
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- pressure regulator
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- 230000001105 regulatory effect Effects 0.000 title claims abstract description 40
- 230000007246 mechanism Effects 0.000 claims abstract description 29
- 230000001276 controlling effect Effects 0.000 claims abstract description 8
- 230000001012 protector Effects 0.000 claims description 4
- 230000005856 abnormality Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 description 8
- 230000002159 abnormal effect Effects 0.000 description 6
- 230000008569 process Effects 0.000 description 5
- 238000007689 inspection Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004513 sizing Methods 0.000 description 2
- 238000013024 troubleshooting Methods 0.000 description 2
- 239000006096 absorbing agent Substances 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000005389 magnetism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Fluid Pressure (AREA)
Abstract
The invention discloses a pneumatic cabin pressure regulating system based on digital control for an aircraft. Comprises a cabin pressure controller, an electric air pressure regulator, a two-position three-way electromagnetic valve, a pneumatic cabin pressure regulator and an exhaust valve; the electric air pressure regulator comprises a control valve and a limited angle motor mechanism for controlling the opening degree of the control valve; the electric air pressure regulator is respectively and electrically connected with the control ends of the limited-angle motor mechanism and the two-position three-way electromagnetic valve, and the feedback end of the limited-angle motor mechanism is also electrically connected with the electric air pressure regulator through the position feedback component; two passages of the two-position three-way electromagnetic valve are respectively communicated with a control cavity of the exhaust valve through a control valve and a pneumatic cabin pressure regulator. The invention can realize the taking-off and landing of airports with different heights, does not need the ground crew to manually switch the pressure system before taking off, and greatly improves the attendance efficiency of the airplane.
Description
Technical Field
The invention belongs to the technical field of aviation cabin pressure control, and particularly relates to a pneumatic cabin pressure regulating system based on digital control for an aircraft.
Background
The cabin pressure condition system for the prior aircraft adopts a pneumatic structure, namely, the cabin pressure is regulated by sensing pressure through bellows and mechanical parts of a diaphragm in an absolute pressure regulating mechanism and a residual pressure regulating mechanism, as shown in figure 1. The following problems exist in the use process: 1. and when the pressure of the cabin is abnormal, the fault position cannot be accurately judged, products related to the cabin air tightness are all required to be checked once, and after the products of the pressure regulating system are changed, the faults are still present, so that the troubleshooting period is long. 2. The pressure regulating system is mostly single margin, when the product fails, the task is interrupted, and when serious, the cabin is out of secret. 3. The products have a 'plateau' gear and a 'plain' gear, but the aircraft is required to be operated by ground staff before taking off during switching, so that the attendance efficiency of the aircraft is reduced. 4. The aircraft continuously accelerates and decelerates in the plane, which can cause the pressure change of the cabin to exceed 6kPa and easily cause the problem of 'ear pressing'.
Disclosure of Invention
The purpose of the invention is that: a digital control based pneumatic cabin pressure regulation system for an aircraft is provided. The invention can realize the taking-off and landing of airports with different heights, does not need the ground crew to manually switch the pressure system before taking off, and greatly improves the attendance efficiency of the airplane.
The technical scheme of the invention is as follows: a pneumatic cabin pressure regulating system based on digital control for an aircraft comprises a cabin pressure controller, an electric air pressure regulator, a two-position three-way electromagnetic valve, a pneumatic cabin pressure regulator and an exhaust valve; the electric air pressure regulator comprises a control valve and a limited angle motor mechanism for controlling the opening degree of the control valve; the electric air pressure regulator is respectively and electrically connected with the control ends of the limited-angle motor mechanism and the two-position three-way electromagnetic valve, and the feedback end of the limited-angle motor mechanism is also electrically connected with the electric air pressure regulator through the position feedback component; two passages of the two-position three-way electromagnetic valve are respectively communicated with a control cavity of the exhaust valve through a control valve and a pneumatic cabin pressure regulator.
In the pneumatic cabin pressure regulating system based on digital control for the airplane, the rest passage of the two-position three-way electromagnetic valve is communicated with the atmosphere through a cabin altitude protection device.
In the pneumatic cabin pressure regulating system based on digital control for the aircraft, the cabin altitude protection device is used for ensuring that the absolute pressure in the cabin is not lower than 36kPa.
The pneumatic cabin pressure regulating system based on digital control for the airplane further comprises a safety valve for ensuring that the residual pressure of the cabin is not more than 39 kPa.
In the pneumatic cabin pressure regulating system based on digital control for the aircraft, the signal output by the electric air pressure regulator to the control end of the limited angle motor mechanism is a current signal which is less than or equal to 100mA, and the signal output by the electric air pressure regulator to the control end of the two-position three-way electromagnetic valve is a voltage signal of 28V.
In the pneumatic cabin pressure regulating system based on digital control for the aircraft, when the cabin pressure is abnormal, the cabin height protection device is also used for ensuring that the cabin height is not more than 8km.
In the pneumatic cabin pressure regulating system based on digital control for the aircraft, the cabin pressure controller is also electrically connected with the cabin pressure sensor.
In the pneumatic cabin pressure regulating system based on digital control for the aircraft, the cabin pressure controller is also electrically connected with an atmospheric pressure sensor.
The invention has the advantages that:
1. the invention has two parts of electric regulation and pneumatic regulation, which are mutually backup. Both have the functions of completely regulating the pressure of the cabin, controlling the pressure change rate of the cabin, taking off and landing on the plateau, protecting the cabin height and the like. The electric regulation can collect cabin and atmospheric pressure signals on the machine and automatically control cabin pressure through the operation of the controller. The pneumatic regulating part senses the atmospheric pressure and the cabin pressure through parts such as a corrugated pipe, a diaphragm, a spring and the like in the absolute pressure regulating mechanism and the residual pressure regulating mechanism, so that the cabin pressure is controlled. When the controller or the pressure signal is abnormal, the system can be automatically switched to the pneumatic adjusting part, and the pneumatic adjusting part can realize the functions of complete cabin pressure system control, cabin pressure change rate control, high protection and the like. When the aircraft enters environments such as strong magnetism and the like and the power of the onboard controller is in fault and the like, the aircraft needs to be switched to the pneumatic adjusting part, the aircraft can be manually switched to the pneumatic adjusting part through the onboard control panel.
2. The electric air pressure regulator of the system is provided with the position feedback component, the working state of the control valve can be fed back in real time, the controller judges the working state of a product according to the feedback signal, and the pressure of the control cavity of the product can be monitored in real time by the aid of the pressure sensor arranged on the exhaust valve in the system so as to assist in judging the working state of the product. When the pressure of the cabin is abnormal, the working state of the pressure regulating system can be judged through the two signals, so that the time for checking the pressure regulating system is reduced, and the outfield troubleshooting period is greatly reduced.
3. Previous products were subject to fly acceleration and deceleration in the aircraft resulting in cabin pressure swings approaching 6kPa (test curves are shown in fig. 3). According to the system, through matching and coordination among the electric air pressure regulator, the control valve and the cabin pressure controller, the cabin pressure floating is reduced to 2kPa (test curve is shown in fig. 4) due to the flat flight acceleration and deceleration of the aircraft at different flying heights, and the comfort of a pilot is greatly improved.
4. When the system is electrically regulated, the pressure system can be automatically switched through the wheel-mounted signal and the takeoff/landing airport height input by the control panel, so that the comfort of passengers is improved. Meanwhile, the pressure system does not need to be manually switched by ground staff before the aircraft takes off, so that the attendance efficiency of the aircraft is greatly improved. When in pneumatic adjustment, the system is provided with an airtight switching device, and the airtight condition of the control cavity is controlled through an electromagnetic valve to control whether the product works or not. The airport take-off and landing at different heights are realized, the ground staff is not required to manually switch the pressure system before taking off the aircraft, and the attendance efficiency of the aircraft is greatly improved.
Drawings
FIG. 1 is a block diagram of a conventional pressure regulating system;
FIG. 2 is a block diagram of the structure of the present invention;
FIG. 3 is a conventional press debugging test curve;
FIG. 4 is a graph of the test of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without making any inventive effort are intended to fall within the scope of the present invention.
Features and exemplary embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by showing examples of the invention. The present invention is in no way limited to any particular arrangement and method set forth below, but rather covers any adaptations, alternatives, and modifications of structure, method, and device without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques have not been shown in detail in order not to unnecessarily obscure the present invention.
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other, and the embodiments may be referred to and cited with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
Example 1. The pneumatic cabin pressure regulating system based on digital control for the aircraft is shown in figure 2, and comprises a cabin pressure controller 1, an electric air pressure regulator 3, a two-position three-way electromagnetic valve 5, a pneumatic cabin pressure regulator 6 and an exhaust valve 7; the electric air pressure regulator 3 comprises a control valve 3.2 and a limited angle motor mechanism 3.1 for controlling the opening degree thereof; the electric air pressure regulator 3 is respectively and electrically connected with the control ends of the limited angle motor mechanism 3.1 and the two-position three-way electromagnetic valve 5, and the feedback end of the limited angle motor mechanism 3.1 is also electrically connected with the electric air pressure regulator 3 through the position feedback component 2; two passages of the two-position three-way electromagnetic valve 5 are respectively communicated with a control cavity 7.2 of the exhaust valve 7 through a control valve 3.2 and a pneumatic cabin pressure regulator 6.
The remaining passage of the two-position three-way electromagnetic valve 5 is communicated with the atmosphere through the cabin altitude protector 4.
The cabin altitude protector 4 described above is used to ensure that the absolute pressure in the cabin is not less than 36kPa.
The pneumatic cabin pressure regulating system based on digital control for the airplane further comprises a safety valve 8 for ensuring that the residual pressure of the cabin is not more than 39 kPa.
The signal output by the electric air pressure regulator 3 to the control end of the limited angle motor mechanism 3.1 is a current signal which is less than or equal to 100mA, and the signal output by the electric air pressure regulator to the control end of the two-position three-way electromagnetic valve 5 is a voltage signal of 28V.
The cabin altitude protection device 4 also serves to ensure that the cabin altitude does not exceed 8km when an abnormality occurs in the cabin pressure.
The cabin pressure controller 1 described above is also electrically connected to a cabin pressure sensor 9.
The cabin pressure controller 1 described above is also electrically connected to an atmospheric pressure sensor 10.
The cabin pressure controller 1 collects signals collected by the cabin pressure sensor 9 and the atmospheric pressure sensor 10, processes the signals, outputs an electric signal for controlling the electric pressure regulator 3, and transmits the electric signal to the limited angle motor mechanism 3.1.
The cabin pressure controller 1 has the functions of power-on self-inspection and flight inspection, can monitor the working state of the pressure regulating mechanism in real time before taking off and in the flight process, and has higher safety.
The cabin pressure controller 1 receives the position signal fed back by the position feedback component 2, and judges whether the position of the control valve 3.2 is correct, thereby judging whether the pneumatic pressure regulator 3 is faulty.
The cabin pressure controller 1 receives the abnormal position signal fed back by the position feedback component 2, the cabin pressure controller 1 can automatically switch on the two-position three-way electromagnetic valve 5, cut off the output signal of the control valve 3.2 in the electric air pressure regulator 3, and simultaneously switch on the output signal of the pneumatic cabin pressure regulator 6 to regulate the cabin pressure, so as to ensure the normal regulation of the cabin pressure pressing force system curve. And transmits the fault information to the upper computer.
The cabin pressure controller 1 has the functions of power-on self-inspection and flight inspection, can monitor the working state of the pressure regulating mechanism in real time before taking off and in the flight process, and has higher safety.
The cabin pressure controller 1 can automatically switch cabin pressure systems according to the altitude of a take-off/landing airport, and is beneficial to improving the comfort of passengers.
The pneumatic cabin pressure regulator 6 has an absolute pressure regulating mechanism 6.1, a residual pressure regulating mechanism 6.2, and a damper 6.3. When the electric regulation is failed, the pneumatic cabin pressure regulator 6 automatically regulates the cabin pressure according to a preset pressure system curve, and simultaneously ensures that the cabin pressure increase rate is not more than 0.67kPa/s and the cabin pressure decrease rate is not more than 1.33kPa/s.
The aforementioned electric air pressure regulator 3 can convert the electric signal output from the cabin pressure controller 1 into an air-powered signal.
The exhaust valve 7 comprises a sizing hole 7.1, a control cavity 7.2 and an exhaust assembly 7.3. The sizing hole 7.1 is used for limiting the flow of cabin air supply and then entering the control cavity 7.2, the control cavity 7.2 is used for transmitting pneumatic signals to the electric air pressure regulator 3 and the pneumatic cabin pressure regulator 6, the electric air pressure regulator 3 or the pneumatic cabin pressure regulator 6 is used for feeding back processed pressure signals to the control cavity 7.2, the control cavity 7.2 is used for controlling the opening of the exhaust assembly 7.3 according to the processed pressure signals, the cabin exhaust amount is controlled, and the cabin pressure is ensured to meet a preset pressure system curve.
The two-position three-way electromagnetic valve 5 has two states, and outputs a signal controlled by the electric pressure regulator 3 when not energized, and cuts off the signal of the electric pressure regulator 3 after energized, and outputs a signal of the pneumatic cabin pressure regulator 6.
The cabin altitude protector 4 described above ensures that the cabin altitude does not exceed a predetermined value (typically 8 km) when an abnormality occurs in cabin pressure.
The safety valve 8 ensures that the pressure of the cabin does not exceed a specified value and ensures the safety of the aircraft structure.
The cabin pressure sensor 9 described above acquires cabin pressure in real time and transmits a pressure signal to the cabin pressure controller 1.
The aforementioned barometric pressure sensor 10 collects the barometric pressure in real time and transmits a pressure signal to the cabin pressure controller 1.
Specifically, the working process of the invention is as follows:
during normal operation, the two-position three-way electromagnetic valve 5 is electrified, at the moment, the pneumatic cabin pressure regulator 6 does not work, the cabin pressure controller 1 receives cabin pressure acquired in real time by the cabin pressure sensor 9, the atmospheric pressure acquired in real time by the atmospheric pressure sensor 10 is compared with a preset pressure system curve, an electric signal is output to the limited-angle motor mechanism 3.1 on the electric pressure regulator 3, and the limited-angle motor mechanism 3.1 controls the swing angle of the control valve 3.2 according to the electric signal to convert the electric signal of the cabin pressure controller 1 into a pneumatic signal. The position feedback component 2 collects the position information of the swing angle of the control valve 3.2 in real time and transmits the information to the cabin pressure controller 1, and the cabin pressure controller 1 compares the position information with the preset position requirement: when the position information is normal, the cabin pressure controller 1 continuously outputs an electric signal to the limited-angle motor mechanism 3.1, thereby controlling the swing angle of the control valve 3.2 in real time. The swing angle of the control valve 3.2 controls the pressure of the control cavity 7.2, and the control cavity 7.2 controls the lifting height of the exhaust assembly 7.3 according to the pressure, so as to control the exhaust capacity of the cabin and ensure that the pressure of the cabin meets a preset pressure system curve. When the position signal is abnormal, the cabin pressure controller 1 controls the two-position three-way electromagnetic valve 5 to switch on and switch off the operation of the pneumatic pressure regulator 3 and switch on the pneumatic cabin pressure regulator 6 to operate; at this time, the absolute pressure regulating mechanism 6.1, the residual pressure regulating mechanism 6.2 and the shock absorber 6.3 in the pneumatic cabin pressure regulator 6 start to automatically regulate the cabin pressure according to a preset pressure system curve, and meanwhile, the cabin pressure increasing rate is not more than 0.67kPa/s, and the cabin pressure decreasing rate is not more than 1.33kPa/s.
Claims (8)
1. The utility model provides a pneumatic type cabin pressure governing system based on numerical control for aircraft which characterized in that: comprises a cabin pressure controller (1), an electric air pressure regulator (3), a two-position three-way electromagnetic valve (5), a pneumatic cabin pressure regulator (6) and an exhaust valve (7); the electric air pressure regulator (3) comprises a control valve (3.2) and a limited angle motor mechanism (3.1) for controlling the opening degree of the control valve; the electric air pressure regulator (3) is respectively and electrically connected with the control ends of the limited-angle motor mechanism (3.1) and the two-position three-way electromagnetic valve (5), and the feedback end of the limited-angle motor mechanism (3.1) is also electrically connected with the electric air pressure regulator (3) through the position feedback component (2); two of the two-position three-way electromagnetic valve (5) are respectively communicated with a control cavity (7.2) of the exhaust valve (7) through a control valve (3.2) and a pneumatic cabin pressure regulator (6).
2. The aircraft digitally controlled pneumatic cabin pressure regulating system of claim 1, wherein: the rest passage of the two-position three-way electromagnetic valve (5) is communicated with the atmosphere through the cabin altitude protection device (4).
3. The aircraft digitally-controlled pneumatic cabin pressure regulating system of claim 2, wherein: the cabin altitude protector (4) is used for ensuring that the absolute pressure in the cabin is not lower than 36kPa.
4. The aircraft digitally controlled pneumatic cabin pressure regulating system of claim 1, wherein: also comprises a safety valve (8) for ensuring that the residual pressure of the cabin is not more than 39 kPa.
5. The aircraft digitally controlled pneumatic cabin pressure regulating system of claim 1, wherein: the signal output by the electric air pressure regulator (3) to the control end of the limited angle motor mechanism (3.1) is a current signal which is less than or equal to 100mA, and the signal output by the electric air pressure regulator to the control end of the two-position three-way electromagnetic valve (5) is a voltage signal of 28V.
6. The aircraft digitally-controlled pneumatic cabin pressure regulating system of claim 2, wherein: the cabin altitude protection device (4) also serves to ensure that the cabin altitude does not exceed 8km when an abnormality occurs in cabin pressure.
7. The aircraft digitally controlled pneumatic cabin pressure regulating system of claim 1, wherein: the cabin pressure controller (1) is also electrically connected with a cabin pressure sensor (9).
8. The aircraft digitally controlled pneumatic cabin pressure regulating system of claim 1, wherein: the cabin pressure controller (1) is also electrically connected to an atmospheric pressure sensor (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311347640.5A CN117382887A (en) | 2023-10-17 | 2023-10-17 | Pneumatic cabin pressure regulating system based on digital control for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311347640.5A CN117382887A (en) | 2023-10-17 | 2023-10-17 | Pneumatic cabin pressure regulating system based on digital control for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117382887A true CN117382887A (en) | 2024-01-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311347640.5A Pending CN117382887A (en) | 2023-10-17 | 2023-10-17 | Pneumatic cabin pressure regulating system based on digital control for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117382887A (en) |
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2023
- 2023-10-17 CN CN202311347640.5A patent/CN117382887A/en active Pending
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