CN102069909A - Electronic electrodynamic type cabinet pressure regulation system - Google Patents
Electronic electrodynamic type cabinet pressure regulation system Download PDFInfo
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- CN102069909A CN102069909A CN2010106177685A CN201010617768A CN102069909A CN 102069909 A CN102069909 A CN 102069909A CN 2010106177685 A CN2010106177685 A CN 2010106177685A CN 201010617768 A CN201010617768 A CN 201010617768A CN 102069909 A CN102069909 A CN 102069909A
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Abstract
The invention discloses an electronic electrodynamic type cabinet pressure regulation system, which comprises a cabinet pressure control selector, a cabinet pressure controller and a cabinet exhaust valve, wherein the cabinet pressure controller is connected with an output end of the cabinet pressure control selector, and the cabinet exhaust valve is connected with an output end of the cabinet pressure controller; the cabinet pressure control selector comprises a control input device and a selector, and an output end of the control input device is electrically connected with the selector; the cabinet pressure controller comprises two or more pressure sensors, and an automatic control module, a ground self-check module and a manual control module which are electrically connected with the cabinet pressure control selector and output ends of the pressure sensors respectively; and the cabinet exhaust valve comprises an exhaust valve execution module, and an alternating current actuator and a direct current actuator which are connected with two input ends of the exhaust valve execution module respectively. The electronic electrodynamic type cabinet pressure regulation system overcomes defects of the conventional pneumatic cabinet pressure regulation system, and has the advantages of high control accuracy, high response speed and high interchangeability.
Description
Technical field
The present invention relates to regulate the motor drive mechanism of aircraft cabin pressure, specifically a kind of electric and electrically operated aircraft cabin pressure control system.
Background technology
Support cabin pressure regulating system is used for the aircraft high-altitude flight, regulate suitable cockpit pressure and cockpit pressure rate of change, guarantee the a/s rate of change adjusting of cockpit pressure, keep the passenger cabin positive and negative pressure to prick in the scope of controllable variations, prevent that aircaft configuration from being damaged by abnormal pressure on the one hand, satisfy aviator and passenger adaptable range of pressure on every side on the other hand, so failure-free aircraft cabin pressure control system is to finish the necessary condition of aerial mission.
The cockpit pressure regulating system of the existing large aircraft of China is still continued to use air operated control and the diaphragm valve of former Soviet Union's the middle of last century, and promptly first generation pneumatic type cockpit pressure regulating system is as control system and actuating unit.It is based on the passenger cabin occupant and was subjected to the aviator that screws up discipline for prerequisite, that is: occupant's fitness is high, can tolerate the comparatively pressure environment of harshness.But updating and improve along with the various airborne equipments of aircraft, the particularly appearance of various transport planes, passenger cabin occupant structure has expanded the expert of various technical personnels and different industries to from the high aviator of mono-fitness, at these transport planes in-flight, the control accuracy of pneumatic type cockpit pressure regulating system can not satisfy the various requirement of present generation aircraft, its static deviation and dynamic response often depart from the requirement of technical index, and system architecture complexity, reliability is low, maintainability is poor, the incompatible needs of safeguarding are seriously restricting the performance of aircraft technology level.
Summary of the invention
The objective of the invention is to overcome the deficiency of above-mentioned background technology, a kind of electric and electrically operated aircraft cabin pressure control system is provided.Its reliability and accuracy rate height, interchangeability and maintainability are good.For achieving the above object, the present invention adopts following technical scheme:
Electric and electrically operated cockpit pressure regulating system, comprise cockpit pressure control finder, the mouth of cockpit pressure control finder is connected with the cockpit pressure controller, the mouth of cockpit pressure controller is connected with the passenger cabin exhaust valve, and the feedback signal terminal of passenger cabin exhaust valve connects passenger cabin pressure control finder; Described cockpit pressure control finder comprises control input device and finder, and the mouth of control input device is electrically connected finder; Described cockpit pressure controller comprises 2 or above pressure sensor, and the automatic control module, ground selftest module, the manual control module that are electrically connected with the mouth of cockpit pressure control finder and pressure sensor respectively; Described passenger cabin exhaust valve comprises the exhaust valve execution module and exchanges actuator and direct current actuator with two input ends of exhaust valve execution module link to each other respectively.
Further, described aircraft cabin pressure controller comprises AC power supply module, atmospheric-pressure sensor, cockpit pressure sensor, master control module, first interface, second interface and the 3rd interface, described AC power supply module is connected with the master control module, atmospheric-pressure sensor is connected with the master control module respectively with the cockpit pressure sensor, described first interface is connected with cockpit pressure control finder, second interface be conditioned object aircraft main frame and be connected, the 3rd interface is connected with the cockpit pressure exhaust valve.
Further, described control input device is provided with the input port that is used for input instruction, and described finder is provided with the read-out that is used to show the pressure control input.
Further, described passenger cabin exhaust valve execution module comprises valve base and valve plate, described valve base is a block form, valve base is provided with one and revolves axle, revolve axle and be provided with A-frame, this A-frame flexibly connects with the valve plate that is positioned at valve base, and valve base in-to-in one end is provided with the sealing inclined-plane that matches with valve plate, and the other end and valve plate contact position in the valve base are provided with sealing band.
Above-mentioned interchange actuator comprises alternating current dynamo and power-transfer clutch I, and the output shaft of alternating current dynamo connects the center shaft of power-transfer clutch I, and axle is revolved in the center shaft connection of this power-transfer clutch I.
Above-mentioned direct current actuator comprises alternating current dynamo and power-transfer clutch I, and the output shaft of DC machine connects the center shaft of power-transfer clutch I, and axle is revolved in the center shaft connection of this power-transfer clutch I.
Above-mentioned exhaust valve execution module is connected with feedback potentiometer, and the mouth of feedback potentiometer is connected with manual control module with finder, automatic control module, ground selftest module respectively.
The present invention has following advantage:
1, control accuracy height, cockpit pressure control finder selects signal to send to control module pressure, the aperture of electric signal control passenger cabin pressure control valve, the cockpit pressure governor valve arrives pressure control finder, the variation of accuracy control cockpit pressure by feedback potentiometer with its aperture signal feedback.
2, the speed of response of system is fast, and total system is controlled by electric signal, and motor rotates the aperture of control valve, and system is instantaneous corresponding.
3, interchangeability is good, maintenance easily, total system is divided into cockpit pressure control finder, cockpit pressure controller and three parts of cockpit pressure governor valve, each part is taken apart and is worked independently and be independent of each other, but when one of them part breaks down, only need maintenance or change fault partly device or parts.
4, high conformity, the aperture size of cockpit pressure exhaust valve is existing relation with the cockpit pressure size, can accurately regulate.
Description of drawings
Fig. 1 is a system principle diagram of the present invention;
Fig. 2 is a structured flowchart of the present invention;
Fig. 3 is cockpit pressure controller architecture scheme drawing in the invention;
Passenger cabin exhaust valve structural representation among Fig. 4 the present invention.
Among the figure: 1, cockpit pressure control finder; 2, cockpit pressure controller; 3, passenger cabin exhaust valve; 1.1, control input device, 1.2, finder; 2.1, pressure sensor, 2.2, automatic control module, 2.3, the ground selftest module, 2.4 manual control module; 3, passenger cabin exhaust valve, 3.1, brake, 3.2, alternating current dynamo, 3.3, power-transfer clutch I, 3.4, the exhaust valve execution module (3.4.1, valve base, 3.4.2, valve plate, 3.4.3, revolve the axle), 3.5, DC machine, 3.6, power-transfer clutch II, 3.7, feedback potentiometer.
The specific embodiment
The present invention is described in further detail below in conjunction with the drawings and specific embodiments:
As depicted in figs. 1 and 2, electric and electrically operated cockpit pressure regulating system, comprise cockpit pressure control finder 1, the mouth of cockpit pressure control finder 1 is connected with cockpit pressure controller 2, the mouth of cockpit pressure controller 2 is connected with passenger cabin exhaust valve 3, and the feedback signal terminal of passenger cabin exhaust valve 3 connects passenger cabin pressure control finder 1; Described cockpit pressure control finder 1 comprises control input device 1.1 and finder 1.2, and the mouth of control input device 1.1 is electrically connected finder 1.2; Described cockpit pressure controller 2 comprises 2 or above pressure sensor 2.1, and the automatic control module 2.2, ground selftest module 2.3, the manual control module 2.4 that are electrically connected with the mouth of cockpit pressure control finder 1 and pressure sensor 2.1 respectively; Passenger cabin exhaust valve 3 comprises exhaust valve execution module 3.4 and exchanges actuator and direct current actuator with two input ends of exhaust valve execution module 3.4 link to each other respectively.The aircraft cabin pressure controller, comprise AC power supply module, atmospheric-pressure sensor, cockpit pressure sensor, master control module, first interface, second interface and the 3rd interface, described AC power supply module is connected with the master control module, atmospheric-pressure sensor is connected with the master control module respectively with the cockpit pressure sensor, described first interface is connected with cockpit pressure control finder, second interface be conditioned object aircraft main frame and be connected, the 3rd interface is connected with the cockpit pressure exhaust valve.
As shown in Figure 3, control input device is provided with input port, is used for the input pressure regulating control command, and described finder 1.2 is provided with the read-out that is used to show the pressure control input, shows cabin pressure and air pressure in real time.Passenger cabin exhaust valve execution module 3.4 comprises valve base 3.4.1 and valve plate 3.4.2, as shown in Figure 4, valve base 3.4.1 is a block form, valve base 3.4.1 is provided with one and revolves a 3.4.3, revolve a 3.4.3 and be provided with A-frame, this A-frame flexibly connects with the valve plate 3.4.2 that is positioned at valve base 3.4.1, and valve base 3.4.1 in-to-in one end is provided with the sealing inclined-plane that matches with valve 3.4.2 plate, and the other end and valve plate 3.4.2 contact position in the valve base 3.4.1 are provided with sealing band.Described interchange actuator comprises alternating current dynamo 3.2 and power-transfer clutch I3.3, the output shaft of alternating current dynamo 3.2 connects the center shaft of power-transfer clutch I3.3, a 3.4.3 is revolved in the center shaft connection of this power-transfer clutch I3.3, direct current actuator 3. comprises DC machine 3.5 and power-transfer clutch II3.6, the output shaft of DC machine 3.5 connects the center shaft of power-transfer clutch II3.6, and axle is revolved in the center shaft connection of this power-transfer clutch II3.6.The mouth of automatic control module 2.2 and ground selftest module 2.3 is connected alternating current dynamo 3.2, power-transfer clutch I3.3 respectively and is used to control the brake 3.1 that exhaust valve execution module 3.4 stops to move, and the mouth of manual control module 2.4 connects power-transfer clutch I3.3, power-transfer clutch II3.6 and DC machine 3.5 respectively.
Exhaust valve execution module 3.4 is connected with feedback potentiometer 3.7, and the mouth of feedback potentiometer 3.7 is connected with finder 1.2, automatic control module 2.2, ground selftest module 2.3 and manual control module 2.4 respectively.
Working process of the present invention is, control input device 1.1 is used for the input pressure of aviator to electric and electrically operated cockpit pressure regulating system, finder 1.2 is used to select the mode of cockpit pressure control, promptly selects to adopt automatic guidance or manually control or self check control, and shows the control result; 2 or above pressure sensor 2.1 are gathered the pressure signal of arrogant compression ring border and cabin interior environment respectively out of my cabin, with the pressure signal input automatic control module of gathering 2.2, ground selftest module 2.3 and manual control module 2.4, by alternating current dynamo 3.2 in the finder 1.2 selected module controls passenger cabin exhaust valves 3 or DC machine 3.5 actions, the output shaft that the output shaft of alternating current dynamo 3.2 drives power-transfer clutch I3.3 or DC machine 3.5 drives power-transfer clutch II3.6 action, the aperture of control valve plate 3.4.2, pressure in the automatically regulating passenger cabin, make it satisfy predetermined cockpit pressure and cockpit pressure rate of change, simultaneously, the signal of the aperture of valve plate 3.4.2 feeds back to finder 1.2 by feedback potentiometer 3.7, automatic control module 2.2, ground selftest module 2.3 and manual control module 2.4 have improved the accuracy rate of total system control.
System of the present invention is two remaining systems, can realize pressure control under the automatic control mode and the pressure control under the manual mode.In system, cockpit pressure controller 2 is core control parts of Cabin Pressure Control System, it is by overbottom pressure in the cabin of cycle checkout passenger cabin, bar pressure out of my cabin, compare with the force value of selecting in advance, according to pressure selected change curve (predetermined cockpit pressure is regulated system), export corresponding electric signal, 3 actions of control electrodynamic type passenger cabin exhaust valve are to realize system's voltage regulation function, the while output alarm signal.Taking off preceding or automatic control unit when losing efficacy, the aviator can directly select M/C cockpit pressure control finder to realize manually control.
Claims (7)
1. electric and electrically operated cockpit pressure regulating system, it is characterized in that: comprise cockpit pressure control finder, the mouth of cockpit pressure control finder is connected with the cockpit pressure controller, the mouth of cockpit pressure controller is connected with the passenger cabin exhaust valve, and the feedback signal terminal of passenger cabin exhaust valve connects passenger cabin pressure control finder; Described cockpit pressure control finder comprises control input device and finder, and the mouth of control input device is electrically connected finder; Described cockpit pressure controller comprises 2 or above pressure sensor, and the automatic control module, ground selftest module, the manual control module that are electrically connected with the mouth of cockpit pressure control finder and pressure sensor respectively; Described passenger cabin exhaust valve comprises the exhaust valve execution module and exchanges actuator and direct current actuator with two input ends of exhaust valve execution module link to each other respectively.
2. electric and electrically operated cockpit pressure regulating system according to claim 1 is characterized in that: described control input device is provided with the input port that is used for input instruction, and described finder is provided with the read-out that is used to show the pressure control input.
3. electric and electrically operated cockpit pressure regulating system according to claim 1, it is characterized in that: described aircraft cabin pressure controller comprises AC power supply module, atmospheric-pressure sensor, the cockpit pressure sensor, the master control module, first interface, second interface and the 3rd interface, described AC power supply module is connected with the master control module, atmospheric-pressure sensor is connected with the master control module respectively with the cockpit pressure sensor, described first interface is connected with cockpit pressure control finder, second interface be conditioned object aircraft main frame and be connected, the 3rd interface is connected with the cockpit pressure exhaust valve.
4. electric and electrically operated cockpit pressure regulating system according to claim 1, it is characterized in that: described passenger cabin exhaust valve execution module comprises valve base and valve plate, described valve base is a block form, valve base is provided with one and revolves axle, revolve axle and be provided with A-frame, this A-frame flexibly connects with the valve plate that is positioned at valve base, and valve base in-to-in one end is provided with the sealing inclined-plane that matches with valve plate, and the other end and valve plate contact position in the valve base are provided with sealing band.
5. electric and electrically operated cockpit pressure regulating system according to claim 4, it is characterized in that: described interchange actuator comprises alternating current dynamo and power-transfer clutch I, the output shaft of alternating current dynamo connects the center shaft of power-transfer clutch I, and axle is revolved in the center shaft connection of this power-transfer clutch I.
6. electric and electrically operated cockpit pressure regulating system according to claim 4, it is characterized in that: described direct current actuator comprises DC machine and power-transfer clutch II, the output shaft of DC machine connects the center shaft of power-transfer clutch II, and axle is revolved in the center shaft connection of this power-transfer clutch II.
7. according to the arbitrary described electric and electrically operated cockpit pressure regulating system of claim 1-6, it is characterized in that: described exhaust valve execution module is connected with feedback potentiometer, and the mouth of feedback potentiometer is connected with manual control module with finder, automatic control module, ground selftest module respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010106177685A CN102069909A (en) | 2010-12-31 | 2010-12-31 | Electronic electrodynamic type cabinet pressure regulation system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010106177685A CN102069909A (en) | 2010-12-31 | 2010-12-31 | Electronic electrodynamic type cabinet pressure regulation system |
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| CN102069909A true CN102069909A (en) | 2011-05-25 |
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| CN2010106177685A Pending CN102069909A (en) | 2010-12-31 | 2010-12-31 | Electronic electrodynamic type cabinet pressure regulation system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103577706A (en) * | 2013-11-13 | 2014-02-12 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining control parameter of digital controller of cabin pressure control system |
| CN106094785A (en) * | 2016-06-01 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Cabin Pressure Control System ground experiment device |
| 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 |
| 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 |
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| CN101365625A (en) * | 2006-01-12 | 2009-02-11 | 空中客车德国有限公司 | Process and system for controlling the pressure in an aircraft cabin |
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2010
- 2010-12-31 CN CN2010106177685A patent/CN102069909A/en active Pending
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| CN101365625A (en) * | 2006-01-12 | 2009-02-11 | 空中客车德国有限公司 | Process and system for controlling the pressure in an aircraft cabin |
Non-Patent Citations (2)
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| 孙胜利等: "数字式座舱压力调节系统", 《中国航空学会2007年学术年会论文集》 * |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103577706A (en) * | 2013-11-13 | 2014-02-12 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining control parameter of digital controller of cabin pressure control system |
| CN103577706B (en) * | 2013-11-13 | 2016-08-24 | 中国航空工业集团公司西安飞机设计研究所 | The control parameter of digital controller of Cabin Pressure Control System determines method |
| CN106094785A (en) * | 2016-06-01 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Cabin Pressure Control System ground experiment device |
| CN106094785B (en) * | 2016-06-01 | 2018-07-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Cabin Pressure Control System ground experiment device |
| 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 |
| 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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Application publication date: 20110525 |