CN108082494A - Aircraft body cabin internal pressure regulator control system - Google Patents
Aircraft body cabin internal pressure regulator control system Download PDFInfo
- Publication number
- CN108082494A CN108082494A CN201611023575.0A CN201611023575A CN108082494A CN 108082494 A CN108082494 A CN 108082494A CN 201611023575 A CN201611023575 A CN 201611023575A CN 108082494 A CN108082494 A CN 108082494A
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- CN
- China
- Prior art keywords
- pressure
- cockpit
- control
- linkage door
- regulating device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
Abstract
Aircraft body cabin internal pressure regulator control system belongs to internal pressure control technique field more particularly to a kind of aircraft body cabin internal pressure is adjusted and controlled.It is adjusted and controlled that the present invention provides a kind of aircraft body cabin internal pressure that can improve flight safety.The present invention includes cockpit pressure regulating device and executing agency, and structural feature cockpit pressure regulating device adjusts cockpit pressure by changing the open amount of control valve sum；Cabin air is vented linkage door epicoele from the metering hole on exhaust linkage door into people, by conduit person who lives in exile's controller, flows to the capacity of air with highly automated adjusting control chamber by control valve, control chamber is made to change by predetermined pressure rule；Cavity pressure and exhaust linkage door open amount are controlled simultaneously.
Description
Technical field
The invention belongs to internal pressure control technique field more particularly to a kind of aircraft body cabin internal pressure are adjusted and controlled.
Background technology
Loss of cabin pressurization is exactly that the pressure difference of interior of aircraft and aircraft exterior is zero, that is, aircraft is not pressurized.Usual feelings
Condition, with the rising of aircraft altitude, the pressure charging system of aircraft can slowly give aircraft supercharging, make the passenger on aircraft be unlikely to because
For high altitude pressure is small uncomfortable sensation is generated with oxygen deficiency.Positive pressure cabin can be that pilot's creation meets physiological requirement
Environment.With aeronautical technology, advanced radar detection and the development of precision Guidance Technique, air-combat tactics Concept Change, over the horizon is made
Warrior becomes the principal mode of Future Air Combat.As remote missile launching platform, the high-level performance of aircraft is paid attention to.Have
Super high altitude flight, landing flexibly, over the horizon the features such as aircraft appearance, pilot's positive pressure cabin environment is proposed it is higher will
It asks.Altitude decompression sickness is human body after the reduction of high-altitude flight environmental pressure, and ambient pressure decrease speed and amplitude are more than a fixed limit
Degree causes the inert gas dissolved originally in body tissue to dissociate for gas phase, and the nitrogen supersaturation dissolved in vivo, effusion forms gas
Bubble.Bubble is being organized and is being distributed in body fluid or is gathered in a certain position.
The content of the invention
The present invention addresses the above problem, provides a kind of aircraft body cabin internal pressure regulation and control knot that can improve flight safety
Structure.
To achieve the above object, the present invention adopts the following technical scheme that, the present invention includes cockpit pressure regulating device and holds
Row mechanism, structural feature cockpit pressure regulating device adjust cockpit pressure by changing the open amount of control valve sum；Seat
Cabin air is vented linkage door epicoele from the metering hole on exhaust linkage door into people, by conduit person who lives in exile's controller, by control valve
The capacity of air is flowed to highly automated adjusting control chamber, control chamber is made to change by predetermined pressure rule；Control chamber pressure simultaneously
Power and exhaust linkage door open amount；
Cockpit set temperature control system, it is temperature-resistant in control cabinet in pressure control procedure；It is vented linkage door control cockpit
Pressure；
The driving input terminal of the control chamber volume is connected with the output terminal of exhaust linkage door and control valve；Control valve passes through
Control chamber flows into air；
Compared with setting pressure with cockpit to overbottom pressure in engine base cabin, control exhaust linkage door open amount；It is imitative by dynamic
Very, cockpit overbottom pressure and flight course cabin ambient, the output quantity of control pressure regulating device are compared.
As a preferred embodiment, cockpit setup pressure value of the present invention is 34.4kPa.
As another preferred embodiment, the pressure signal of the present invention for being vented linkage door and being provided according to controller changes
Open amount changes the air capacity of discharge.
In addition, control chamber air quality of the present invention is mutually made by metering hole circulation area, metering hole circulation area
About controlled.
Advantageous effect of the present invention.
The present invention ensures that body with the ability remained to after cabin decompression in high-altitude flight, ensures air superiority, cockpit pressure
Force environment must meet requirements at the higher level.The present invention is based on decompression sickness deliberated indexes and explosive decompression deliberated index, it is proposed that 44.4kPa
High overbottom pressure cockpit pressure control program.
The present invention combines body flight profile, mission profile, carries out dynamic simulation to cockpit pressure regulating system, compares overbottom pressure
The influence of 29.4kPa, 34.4kPa and 44.4kPa to flight course cabin ambient, the result shows that, 44.4kPa overbottom pressure cockpit pressures
Meet strategy and tactics transformation requirement, can ensure air superiority.
Description of the drawings
In order to which technical problem solved by the invention, technical solution and advantageous effect is more clearly understood, below in conjunction with
The drawings and the specific embodiments, the present invention will be described in further detail.It should be appreciated that specific embodiment party described herein
Formula is only used to explain the present invention, is not intended to limit the present invention.
Fig. 1 is present system structure diagram.
Fig. 2 is present invention exhaust linkage door structure diagram.
In figure, 1 it is valve, 2 is housing, 3 is spring, 4 is diaphragm, 5 is support plate, 6 is pressure body.
Specific embodiment
As shown in the figure, the present invention includes cockpit pressure regulating device and executing agency, cockpit pressure regulating device is by changing
Become the open amount of control valve sum to adjust cockpit pressure；Cabin air is vented into people from the metering hole on exhaust linkage door and links
Door epicoele, by conduit person who lives in exile's controller, is flowed to the capacity of air with highly automated adjusting control chamber by control valve, makes control
Chamber processed is changed by predetermined pressure rule；Cavity pressure and exhaust linkage door open amount are controlled simultaneously.
Cockpit set temperature control system, it is temperature-resistant in control cabinet in pressure control procedure；It is vented linkage door control
Cockpit pressure.
The driving input terminal of the control chamber volume is connected with the output terminal of exhaust linkage door and control valve；Control valve
Air is flowed by control chamber.
Compared with setting pressure with cockpit to overbottom pressure in engine base cabin, control exhaust linkage door open amount；By dynamic
State emulates, comparison cockpit overbottom pressure and flight course cabin ambient, the output quantity of control pressure regulating device.
The cockpit setup pressure value is 34.4kPa.
The pressure signal that the exhaust linkage door is provided according to controller, changes open amount, changes the air capacity of discharge.
The control chamber air quality is mutually restricted and controlled by metering hole circulation area, metering hole circulation area.
Altitude decompression sickness is human body after the reduction of high-altitude flight environmental pressure, and ambient pressure decrease speed and amplitude are more than one
Fixed limit degree causes the inert gas dissolved originally in body tissue to dissociate for gas phase, and the nitrogen supersaturation dissolved in vivo escapes shape
Into bubble.Bubble organize and body fluid in be distributed or be gathered in a certain position altitude decompression sickness be human body in high-altitude flight environment pressure
After power reduces, ambient pressure decrease speed and amplitude are more than certain limit, cause the inert gas dissolved originally in body tissue
Dissociate for gas phase, the nitrogen supersaturation dissolved in vivo, effusion forms bubble.Bubble is being organized and distribution in body fluid or aggregation Mr. Yu
One position.
Control chamber volume changes with exhaust linkage door and the movement of control valve.To consider in analysis and Control chamber characteristic
The variation of control chamber volume.
Experiment proves, using overbottom pressure 44.4kPa, flies in cruising altitude 19000m, pilot can be made to be exposed to 5500m
Below the height of cabin.According to the altitude decompression sickness deliberated index that Haldane is established, supersaturation coefficient is less than 1.60 License Values.
It during cruising altitude flight, is generated in vivo without microbubble, can guarantee that body remains to the long period in high-altitude after having cabin decompression
The ability of flight ensure that wartime air superiority, and the strategy and tactics transformation that satisfaction " decline lifesaving " develops into " continuing to fly " will
It asks.
The above content is combine specific preferred embodiment to the further description of the invention made, it is impossible to assert this
The specific implementation of invention is confined to these explanations, for those of ordinary skill in the art to which the present invention belongs, not
On the premise of departing from present inventive concept, several simple deduction or replace can also be made, the present invention should be all considered as belonging to and be carried
The protection domain that claims of friendship determine.
Claims (4)
1. aircraft body cabin internal pressure regulator control system includes cockpit pressure regulating device and executing agency, it is characterised in that cockpit pressure tune
Regulating device adjusts cockpit pressure by changing the open amount of control valve sum；Cabin air from exhaust linkage door on metering hole
Linkage door epicoele is vented into people, by conduit person who lives in exile's controller, air is flowed to highly automated adjusting control chamber by control valve
Capacity, make control chamber by predetermined pressure rule change；Cavity pressure and exhaust linkage door open amount are controlled simultaneously；
Cockpit set temperature control system, it is temperature-resistant in control cabinet in pressure control procedure；It is vented linkage door control cockpit
Pressure；
The driving input terminal of the control chamber volume is connected with the output terminal of exhaust linkage door and control valve；Control valve passes through
Control chamber flows into air；
Compared with setting pressure with cockpit to overbottom pressure in engine base cabin, control exhaust linkage door open amount；It is imitative by dynamic
Very, cockpit overbottom pressure and flight course cabin ambient, the output quantity of control pressure regulating device are compared.
2. aircraft body cabin internal pressure regulator control system includes cockpit pressure regulating device and executing agency according to claim 1,
It is 34.4kPa to be characterized in that the cockpit setup pressure value.
3. aircraft body cabin internal pressure regulator control system includes cockpit pressure regulating device and executing agency according to claim 1,
It is characterized in that the pressure signal that the exhaust linkage door is provided according to controller, changes open amount, change the air capacity of discharge.
4. aircraft body cabin internal pressure regulator control system includes cockpit pressure regulating device and executing agency according to claim 1,
It is characterized in that the control chamber air quality is mutually restricted and controlled by metering hole circulation area, metering hole circulation area.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611023575.0A CN108082494A (en) | 2016-11-21 | 2016-11-21 | Aircraft body cabin internal pressure regulator control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611023575.0A CN108082494A (en) | 2016-11-21 | 2016-11-21 | Aircraft body cabin internal pressure regulator control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108082494A true CN108082494A (en) | 2018-05-29 |
Family
ID=62169535
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611023575.0A Pending CN108082494A (en) | 2016-11-21 | 2016-11-21 | Aircraft body cabin internal pressure regulator control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108082494A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275164A (en) * | 2022-01-18 | 2022-04-05 | 中国兵器工业集团第二一四研究所苏州研发中心 | High-altitude continuous oxygen supply pressure regulation and control system and method |
| CN114476078A (en) * | 2022-03-16 | 2022-05-13 | 湖南文理学院 | Integrated oxygen system in aircraft cabin |
| CN117302521A (en) * | 2023-11-28 | 2023-12-29 | 北京蓝天航空科技股份有限公司 | Pressure control method and device for civil aviation aircraft cabin, electronic equipment and storage medium |
-
2016
- 2016-11-21 CN CN201611023575.0A patent/CN108082494A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275164A (en) * | 2022-01-18 | 2022-04-05 | 中国兵器工业集团第二一四研究所苏州研发中心 | High-altitude continuous oxygen supply pressure regulation and control system and method |
| CN114275164B (en) * | 2022-01-18 | 2023-10-20 | 中国兵器工业集团第二一四研究所苏州研发中心 | High-altitude continuous oxygen supply pressure regulation and control system and method |
| CN114476078A (en) * | 2022-03-16 | 2022-05-13 | 湖南文理学院 | Integrated oxygen system in aircraft cabin |
| CN114476078B (en) * | 2022-03-16 | 2022-09-09 | 湖南文理学院 | Integrated oxygen system in aircraft cabin |
| CN117302521A (en) * | 2023-11-28 | 2023-12-29 | 北京蓝天航空科技股份有限公司 | Pressure control method and device for civil aviation aircraft cabin, electronic equipment and storage medium |
| CN117302521B (en) * | 2023-11-28 | 2024-03-01 | 北京蓝天航空科技股份有限公司 | Pressure control method and device for civil aviation aircraft cabin, electronic equipment and storage medium |
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Legal Events
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| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180529 |