CN205375123U - Aircraft skin assists monitored control system - Google Patents
Aircraft skin assists monitored control system Download PDFInfo
- Publication number
- CN205375123U CN205375123U CN201620014600.8U CN201620014600U CN205375123U CN 205375123 U CN205375123 U CN 205375123U CN 201620014600 U CN201620014600 U CN 201620014600U CN 205375123 U CN205375123 U CN 205375123U
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- central controller
- monitoring
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- memorizer
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- Expired - Fee Related
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- Testing And Monitoring For Control Systems (AREA)
- Testing Or Calibration Of Command Recording Devices (AREA)
Abstract
The utility model discloses an aircraft skin assists monitored control system, this system can monitor humiture, atmospheric pressure, wind speed and illumiinance isoparametric, and through the various equipment of central controller control, the system has environmental monitoring, personnel's monitoring, the suggestion of reporting to the police, crack monitoring and automatic adjustment function to improving the security of aircraft, still having remote control function, the system is reliable and stable, and the maintenance management is convenient.
Description
Technical field
This utility model relates to a kind of control system, particularly to a kind of aircraft skin auxiliary monitoring system.
Background technology
Major part aircraft skin monitoring device does not possess environmental monitoring, monitored by personnel, alarm, Crack Monitoring and automatic regulating function at present, increasingly can not meet the demand of modernized society.Therefore need a kind of aircraft skin auxiliary monitoring reliably badly and control system.
Summary of the invention
The purpose of this utility model is in that to provide reasonable in design, and intelligentized control method uses safe a kind of aircraft skin auxiliary monitoring system.
To achieve these goals, the technical solution adopted in the utility model is: a kind of aircraft skin auxiliary monitoring system of the present utility model, including data acquisition and monitoring unit, data pre-processing and memorizer, central controller, mobile device, clamp device, welder, lubricating maintenance device, alarm, cloud server；Data acquisition and monitoring unit includes Temperature Humidity Sensor, barometer, air velocity transducer, light sensor, environmental monitor, three-axis gyroscope, high-definition camera, sound transducer, monitored by personnel's device, stress strain gauge, ultrasonic sensor, Crack Monitoring device；Data acquisition and monitoring unit is connected with data pre-processing and memorizer, data pre-processing and memorizer are connected with central controller input, and central controller outfan is connected with mobile device, clamp device, welder, lubricating maintenance device, alarm, cloud server respectively；Temperature Humidity Sensor, barometer, air velocity transducer, light sensor are connected with environmental monitor input；Three-axis gyroscope, high-definition camera, sound transducer are connected with monitored by personnel's device input, and stress strain gauge, ultrasonic sensor are connected with Crack Monitoring device input.
As preferably, described data pre-processing and memorizer and central controller all have 50 input ports, and 50 output ports, to realize centralized Control.
Compared with prior art, the utility model has the advantage of: the parameters such as humiture, atmospheric pressure, wind speed and illuminance can be monitored by this system, by the various equipment of central controller controls, system has environmental monitoring, monitored by personnel, alarm, Crack Monitoring and automatic regulating function, thus improving the safety of aircraft, also having remote control function, system stability is reliable, and maintenance management is convenient.
Accompanying drawing explanation
Fig. 1 is structured flowchart of the present utility model.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Referring to Fig. 1, a kind of aircraft skin auxiliary monitoring system of the present utility model, including data acquisition and monitoring unit, data pre-processing and memorizer, central controller, mobile device, clamp device, welder, lubricating maintenance device, alarm, cloud server；Data acquisition and monitoring unit includes Temperature Humidity Sensor, barometer, air velocity transducer, light sensor, environmental monitor, three-axis gyroscope, high-definition camera, sound transducer, monitored by personnel's device, stress strain gauge, ultrasonic sensor, Crack Monitoring device；Data acquisition and monitoring unit is connected with data pre-processing and memorizer, data pre-processing and memorizer are connected with central controller input, and central controller outfan is connected with mobile device, clamp device, welder, lubricating maintenance device, alarm, cloud server respectively；Temperature Humidity Sensor, barometer, air velocity transducer, light sensor are connected with environmental monitor input；Three-axis gyroscope, high-definition camera, sound transducer are connected with monitored by personnel's device input, and stress strain gauge, ultrasonic sensor are connected with Crack Monitoring device input.Described data pre-processing and memorizer and central controller all have 50 input ports, and 50 output ports, to realize centralized Control.
In the present embodiment, environmental monitor gathers humiture, atmospheric pressure, wind speed and illuminance parameter automatically by Temperature Humidity Sensor, barometer, air velocity transducer, light sensor, when Parameters variation is beyond set point, central controller can drive alarm equipment alarm prompting relevant information, when humidity, air pressure, wind speed parameter exceed setting value, central controller can drive clamp device to regulate fastening force；Monitored by personnel's device gathers the acceleration of aircraft safety testing staff, angular velocity, image and audio parameter automatically by three-axis gyroscope, high-definition camera, sound transducer, when Parameters variation is beyond set point, central controller can drive alarm equipment alarm prompting relevant information, when acceleration, angular velocity parameter exceed setting value, central controller can drive mobile device to regulate detection position.Crack Monitoring device gathers ess-strain and ultrasonic parameters automatically by stress strain gauge, ultrasonic sensor, when Parameters variation is beyond set point, central controller can drive alarm equipment alarm prompting relevant information, when ess-strain, ultrasonic parameters exceed setting value, central controller can drive welder fracture to weld, and central controller timing can drive lubricating maintenance device to be lubricated maintenance.System manager can also pass through the distance control mode of cloud server and adjust parameter setting, optimizes system and controls, safer convenience.
Claims (2)
1. an aircraft skin auxiliary monitoring system, it is characterised in that: include data acquisition and monitoring unit, data pre-processing and memorizer, central controller, mobile device, clamp device, welder, lubricating maintenance device, alarm, cloud server；Data acquisition and monitoring unit includes Temperature Humidity Sensor, barometer, air velocity transducer, light sensor, environmental monitor, three-axis gyroscope, high-definition camera, sound transducer, monitored by personnel's device, stress strain gauge, ultrasonic sensor, Crack Monitoring device；Data acquisition and monitoring unit is connected with data pre-processing and memorizer, data pre-processing and memorizer are connected with central controller input, and central controller outfan is connected with mobile device, clamp device, welder, lubricating maintenance device, alarm, cloud server respectively；Temperature Humidity Sensor, barometer, air velocity transducer, light sensor are connected with environmental monitor input；Three-axis gyroscope, high-definition camera, sound transducer are connected with monitored by personnel's device input, and stress strain gauge, ultrasonic sensor are connected with Crack Monitoring device input.
2. a kind of aircraft skin auxiliary monitoring system according to claim 1, it is characterised in that: described data pre-processing and memorizer and central controller all have 50 input ports, and 50 output ports, to realize centralized Control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620014600.8U CN205375123U (en) | 2016-01-08 | 2016-01-08 | Aircraft skin assists monitored control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620014600.8U CN205375123U (en) | 2016-01-08 | 2016-01-08 | Aircraft skin assists monitored control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205375123U true CN205375123U (en) | 2016-07-06 |
Family
ID=56276327
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620014600.8U Expired - Fee Related CN205375123U (en) | 2016-01-08 | 2016-01-08 | Aircraft skin assists monitored control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205375123U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106773877A (en) * | 2017-03-16 | 2017-05-31 | 天津京东智联科技发展有限公司 | A kind of manned vehicle automatic safety control system and its control method |
-
2016
- 2016-01-08 CN CN201620014600.8U patent/CN205375123U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106773877A (en) * | 2017-03-16 | 2017-05-31 | 天津京东智联科技发展有限公司 | A kind of manned vehicle automatic safety control system and its control method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160706 Termination date: 20170108 |