CN2788075Y - Intelligent measurement and control device for aeroplane environment control system - Google Patents
Intelligent measurement and control device for aeroplane environment control system Download PDFInfo
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- CN2788075Y CN2788075Y CNU2004200099432U CN200420009943U CN2788075Y CN 2788075 Y CN2788075 Y CN 2788075Y CN U2004200099432 U CNU2004200099432 U CN U2004200099432U CN 200420009943 U CN200420009943 U CN 200420009943U CN 2788075 Y CN2788075 Y CN 2788075Y
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Abstract
The utility model relates to an intelligent measurement and control device for an environment control system of an aeroplane. The utility model comprises an airflow temperature sensor of an entrance of an aeroplane cockpit, a temperature selector and a flow adjusting valve in the aeroplane cockpit, an airflow temperature sensor of an entrance of an electronic compartment cockpit, a pressure sensor and a flow adjusting valve in the electronic compartment cockpit, a data acquisition SCM, a motor control SCM, a main control algorism SCM and an upper supervisory control computer. The utility model shares the information of every subsystems in a public control system by an airborne data bus line. Commands are transmitted by the comprehensive dispatch of the upper supervisory control computer. The main control algorism SCM executes the optimized control decision. The data acquisition SCM and the motor control SCM directly integrate and measure the raw information and control the terminal. The utility model combines modern high technologies such as artificial intelligence technology as fuzzy inference and expert system, communication and computer technology, motor speed regulation, sensor technology, etc. into a whole. Thereby, the utility model can become the main stream direction of the development in measurement and control technology of the environment control system of the aeroplane.
Description
Technical field
The utility model patent relates to a kind of air conditioning control system of plane environmental control system, especially at a kind of intelligent measure and the control device of passenger cabin and electronics bay temperature.It is mainly used in temperature survey, record, control and the analysis of plane environmental control system running.
Background technology
What at present, the air conditioning control system generally adopted in the domestic and international plane environmental control system is analog control technique or analog/digital mixed control technology.Through the checking of engineering practice for many years, the experts and scholars and the engineers and technicians of domestic this research field generally believe: the intelligent monitoring technology that integrated digital control technology and artificial intelligence technology combine is one of main direction of studying that comprehensively improves the plane environmental control system performance.At present, this technology has become the problem of advanced plane environmental control system primary study in China " 15 " military pre-research project.The utility model patent is being summed up on our the achievement in research basis in the past few years the novel integrated digital intelligent observing and controlling system and the corresponding apparatus device of exploitation just.
Summary of the invention
The purpose of this utility model is to solve the deficiency that prior art exists, and proposes a kind of device that is used for plane environmental control system passenger cabin and electronics bay temperature survey record, data analysis, Based Intelligent Control.The inlet air flow temperature of passenger cabin and electronics bay can be measured, shows and be write down to this device in real time, the pressure in the electronics bay.According to plane environmental control system thermal force and system requirements under different flight state, adopt the artificial intelligence control technology that corresponding flow control valve is controlled in real time, in the hope of the course of work of acquisition system the best.
Technical solution adopted in the utility model is: a kind of plane environmental control system intelligent measuring and control device, it comprises temperature selector and passenger cabin flow control valve in aircraft cockpit inlet air flow temperature sensor, the cabin, electronics bay inlet air flow temperature sensor, cabin pressure sensor and electronics bay flow control valve, the data acquisition single-chip microcomputer, the Electric Machine Control single-chip microcomputer, master control algorithm single-chip microcomputer, the upper monitoring computer.Passenger cabin inlet air flow temperature sensor, electronics bay inlet air flow temperature sensor and electronics bay cabin pressure sensor connect the analog signal that collects respectively through binding post goes up the data acquisition single-chip microcomputer, the data acquisition single-chip microcomputer carries out the laggard line data analysis of mould/number conversion to each road sense channel, comprises digital filtering and signal reliability analysis.The instruction that temperature selector is accepted the driver in the passenger cabin cabin is converted into data signal to analog signal and sends to the upper monitoring computer and accept integrated dispatch.After the data signal of upper monitoring computer acceptance from the data acquisition single-chip microcomputer, carry out information fusion and comprehensive allotment, and send real time control command to master control algorithm single-chip microcomputer.After master control algorithm single-chip microcomputer is accepted required real time information from data/address bus, carry out process optimization control and simple fault detect, final execution decision-making is sent to the Electric Machine Control single-chip microcomputer.The Electric Machine Control single-chip microcomputer directly links to each other with the electronics bay flow control valve with passenger cabin, and it finishes final end control work by the intelligent speed-regulating algorithm.The 1553B data/address bus is adopted in digital communication in the process.
The utility model has the advantages that: sufficient information is shared and advanced artificial intelligence technology makes the optimum control of big system become possibility.Digital communication replaces traditional analog signal, improved the precision and the reliability of signal transmission, has avoided signal attenuation, precise decreasing in the analog signal transmission and has been subject to the problem of external disturbance.On-the-spot completely decentralised control replaces traditional centralized Control, and function modoularization is beneficial to be selected for use flexibly and replace, and layout succinctly is beneficial to regular maintenance and dismounting.
Description of drawings
Fig. 1 is a general assembly connection diagram of the present utility model.
The specific embodiment
Describe the working condition of this device in detail below in conjunction with accompanying drawing 1.
The high temperature and high pressure gas of drawing from aircraft engine compressor (1) is divided into two-way through the bleed pipeline.One the tunnel is used for passenger cabin (5) adjustment, and another road is used for electronics bay (6) adjustment.Be used for the thermoregulator engine bleed of passenger cabin (5) and be divided into two-way again, wherein one road primary heat sink (2) of flowing through parallel connection becomes " the cold road of cabin air supply "; Flowing through in another road becomes " the hot road of cabin air supply " behind the passenger cabin flow control valve (11)." the cold road of cabin air supply " is after primary heat sink (2) cooling for the first time, pass through secondary radiator (3) again, the punching press cold air of launched machine air intake duct is lowered the temperature for the second time, and the engine bleed of HTHP is through becoming the air-flow of temperature in the high pressure behind the double temperature drop like this.This strand air-flow is cooling turbine unit (4) the expansion acting of fan through overload again, and temperature reduces once more, becomes one low-temperature airflow and is used for and high temperature gas flow mixing temperature adjustment.The exit flow on " the cold road of cabin air supply " is divided into two-way, leads up to and the high temperature gas flow on " the hot road of cabin air supply " mixes and flows into aircraft cockpit (5); Another road realizes becoming " the cold road of electronics bay air feed " after flow proportional distributes by current-limiting apparatus (18), is mixed into air electronics cabin (6) with " the hot road of the electronics bay air feed " high temperature gas flow that passes through electronics bay flow control valve (10).
During work, the data that passenger cabin inlet air flow temperature sensor (7), electronics bay inlet air flow temperature sensor (8) and electronics bay cabin pressure sensor (9) are gathered are accepted and analyzed to data acquisition single-chip microcomputer (13) in real time, data packed send to upper monitoring computer (16) then.Temperature selector in the passenger cabin cabin (12) is by data/address bus (17) temperature requirements in upper supervisory control comuter (16) sends the passenger cabin cabin; Upper monitoring computer (16) goes out temperature requirement in the electronics bay cabin by analyzing the data from electronics bay cabin pressure sensor (9) through function calculation.By comprehensive thermal force analysis, upper monitoring computer (16) provides temperature requirement instruction in the cabin of passenger cabin and electronics bay respectively, and together sends to master control algorithm single-chip microcomputer (15) in conjunction with real-time temperature information.Master control algorithm single-chip microcomputer (15) adopts the system optimizing control with artificial intelligence technology, as having selected FUZZY ALGORITHMS FOR CONTROL in this device for use.By the critical data that large number of ground simulated test and simulation study are obtained, FUZZY ALGORITHMS FOR CONTROL is optimized, and the final control instruction that obtains after the complicated calculations sends to Electric Machine Control single-chip microcomputer (14).Passenger cabin flow control valve (11) and electronics bay flow control valve (10) all are the butterfly type valve that is driven by direct current generator.Electric Machine Control single-chip microcomputer (14) is by intelligent speed-regulating and the control of functional operation realization to direct current generator, and then realization finally obtains temperature in the required cabin of system to the control of passenger cabin and electronics bay flow.
Claims (5)
1, a kind of plane environmental control system intelligent measuring and control device, comprise aircraft cockpit inlet air flow temperature sensor, temperature selector and passenger cabin flow control valve in the cabin, electronics bay inlet air flow temperature sensor, cabin pressure sensor and electronics bay flow control valve, the data acquisition single-chip microcomputer, the Electric Machine Control single-chip microcomputer, master control algorithm single-chip microcomputer, the upper monitoring computer, it is characterized in that: the upper monitoring computer, the data acquisition single-chip microcomputer, temperature selector in the passenger cabin cabin, master control algorithm single-chip microcomputer and Electric Machine Control single-chip microcomputer all are parallel on the data/address bus, all the sensors all is parallel on the data acquisition single-chip microcomputer, and all control valves all are parallel on the Electric Machine Control single-chip microcomputer.
2, plane environmental control system intelligent measuring and control device according to claim 1, it is characterized in that passenger cabin import and electronics bay import install a temperature sensor respectively, pressure sensor of the inner installation of electronics bay, the data acquisition single-chip microcomputer detects three sensors respectively, and carries out digital filtering and signal reliability analysis.
3, plane environmental control system intelligent measuring and control device according to claim 1, it is characterized in that on passenger cabin and the electronics bay hot-air runner flow control valve being installed respectively, the Electric Machine Control single-chip microcomputer drives passenger cabin and electronics bay flow control valve and finishes terminal control by the intelligent speed-regulating algorithm.
4, plane environmental control system intelligent measuring and control device according to claim 1, after it is characterized in that the data signal of upper monitoring computer acceptance from the data acquisition single-chip microcomputer, carry out information fusion and comprehensive allotment, and send real time control command to master control algorithm single-chip microcomputer; After master control algorithm single-chip microcomputer is accepted required real time information from data/address bus, carry out process optimization control and simple fault detect, final execution decision-making is sent to the Electric Machine Control single-chip microcomputer.
5, plane environmental control system intelligent measuring and control device according to claim 1 is characterized in that the 1553B data/address bus is adopted in digital communication in the process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2004200099432U CN2788075Y (en) | 2004-12-13 | 2004-12-13 | Intelligent measurement and control device for aeroplane environment control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2004200099432U CN2788075Y (en) | 2004-12-13 | 2004-12-13 | Intelligent measurement and control device for aeroplane environment control system |
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| Publication Number | Publication Date |
|---|---|
| CN2788075Y true CN2788075Y (en) | 2006-06-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNU2004200099432U Expired - Fee Related CN2788075Y (en) | 2004-12-13 | 2004-12-13 | Intelligent measurement and control device for aeroplane environment control system |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103138493A (en) * | 2013-03-14 | 2013-06-05 | 苏州工业园区鑫海胜电子有限公司 | Airflow self-service start type motor |
| CN104102248A (en) * | 2014-07-02 | 2014-10-15 | 北京航空航天大学 | Unmanned aerial vehicle equipment cabin temperature control system capable of utilizing heat of engine |
| CN104808710A (en) * | 2015-04-25 | 2015-07-29 | 北京航空航天大学 | Unmanned helicopter equipment cabin temperature control system capable of utilizing external airflow |
| CN104850153A (en) * | 2015-05-06 | 2015-08-19 | 江苏科技大学 | Stratospheric airship electronic equipment cabin temperature control system and control method |
| CN104848963A (en) * | 2013-09-05 | 2015-08-19 | 罗斯蒙特航天公司 | Supercritical total air temperature sensors |
| CN112748751A (en) * | 2020-12-22 | 2021-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Digital airplane environment control system and method |
-
2004
- 2004-12-13 CN CNU2004200099432U patent/CN2788075Y/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103138493A (en) * | 2013-03-14 | 2013-06-05 | 苏州工业园区鑫海胜电子有限公司 | Airflow self-service start type motor |
| CN104848963A (en) * | 2013-09-05 | 2015-08-19 | 罗斯蒙特航天公司 | Supercritical total air temperature sensors |
| CN104848963B (en) * | 2013-09-05 | 2018-03-30 | 罗斯蒙特航天公司 | Overcritical total air temperature sensor |
| CN104102248A (en) * | 2014-07-02 | 2014-10-15 | 北京航空航天大学 | Unmanned aerial vehicle equipment cabin temperature control system capable of utilizing heat of engine |
| CN104102248B (en) * | 2014-07-02 | 2016-08-17 | 北京航空航天大学 | A kind of unmanned plane equipment compartment temperature control system of available heat of engine |
| CN104808710A (en) * | 2015-04-25 | 2015-07-29 | 北京航空航天大学 | Unmanned helicopter equipment cabin temperature control system capable of utilizing external airflow |
| CN104808710B (en) * | 2015-04-25 | 2017-02-22 | 北京航空航天大学 | Unmanned helicopter equipment cabin temperature control system capable of utilizing external airflow |
| CN104850153A (en) * | 2015-05-06 | 2015-08-19 | 江苏科技大学 | Stratospheric airship electronic equipment cabin temperature control system and control method |
| CN112748751A (en) * | 2020-12-22 | 2021-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Digital airplane environment control system and method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |