CN207510742U - A kind of parameter acquisition and monitoring device for big flight control system performance test - Google Patents
A kind of parameter acquisition and monitoring device for big flight control system performance test Download PDFInfo
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- CN207510742U CN207510742U CN201721464623.XU CN201721464623U CN207510742U CN 207510742 U CN207510742 U CN 207510742U CN 201721464623 U CN201721464623 U CN 201721464623U CN 207510742 U CN207510742 U CN 207510742U
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Abstract
The utility model discloses a kind of parameter acquisitions and monitoring device for big flight control system performance test, it is characterised in that it includes cockpit data collector, port wing data collector, starboard wing data collector, tail data collector, central monitoring machine and concentration power supply unit；Data collector is respectively placed in its corresponding position, and central monitoring machine is placed under aircraft or central control room；Data collector inside PLC directly acquires sensing data and is pre-processed, data are uploaded to central monitoring machine by Ethernet；Central monitoring machine realizes synchronous acquisition, processing, display, the record of data, and can realize the inquiry to historical data and patterned comparative analysis, realizes visualization human-computer interaction.
Description
Technical field
The utility model is related to aviation special test equipment fields, more particularly to a kind of to be used for big flight control system performance
The parameter acquisition and monitoring device of test.
Background technology
Flight control system is to ensure the critical system of Flight Safety, and the test to its performance is aircraft general assembly debugging
The important link in stage.
Due to the personalized difference of flight control system, tooling and data acquisition monitoring device to its performance test all belong to
In special equipment, patented product, the common apparatus that can not meet the requirements.
Debug the stage in the general assembly of the big aircraft of my company, need measure control wheel displacement and power, control stick displacement with
During correspondence between power, pedal displacement and power, the displacement of synchro measure control wheel and aileron displacement, control stick displacement and lifting
Correspondence between rudder displacement, pedal displacement and direction rudder displacement realizes the quantitative analysis of steerable system performance.
Since the distance of certain big aircraft cockpit and aileron, elevator, rudder is far, farthest reach 40 meters.By distance
It is limited, existing flight control system performance test apparatus can be only put in cockpit the big aircraft in factory, measure in real time
Correspondence in cockpit between control wheel displacement and power, control stick displacement and power, pedal displacement and power, treats control wheel, drives
The corresponding displacement of manual measurement aileron, elevator, rudder again after bar, pedal to some position or extreme position is sailed, it is this right
Aileron displacement, lifting rudder displacement, direction rudder displacement be asynchronous and the measurement method of non-total travel can be only done to flight control system
The qualitative analysis of performance, hence it is imperative that a set of can realize synchronous acquisition of the flight control system in relation to performance parameter and quantify
The equipment of analysis.
Utility model content
The technical problem to be solved by the utility model is to provide a kind of ginsengs for big flight control system performance test
Number acquisition and monitoring device, the utility model carry out control wheel displacement and power, control stick displacement and power in big aircraft cockpit,
Pedal displacement, when parameter acquisitions, has synchronously completed and the parameters such as aileron displacement, lifting rudder displacement, direction rudder displacement has been adopted with power
Collection and long distance transmission, and data are further processed, show, are recorded, realize the inquiry to historical data and figure
The comparative analysis of change solves the problems, such as the quantitative analysis of big flight control system performance, to solve on caused by the prior art
State multinomial defect.
To achieve the above object, the utility model provides following technical solution：One kind is used for big flight control system
The parameter acquisition and monitoring device that can be tested, are adopted including cockpit data collector, port wing data collector, starboard wing data
Storage, tail data collector, central monitoring machine and concentration power supply unit；Data collector inside PLC, directly acquires sensor
Data are simultaneously pre-processed, and data are uploaded to central monitoring machine by Ethernet；Cockpit data collector, port wing data
Collector, starboard wing data collector, tail data collector are performed respectively at cockpit, port wing, starboard wing, tail
The pretreatments such as acquisition, conversion, the filtering of sensing data.
Preferably, the central monitoring machine is laptop, below aircraft.
Preferably, the associated sensor data that the tail data collector is performed simultaneously on elevator and rudder is adopted
Collection.
It is using the advantageous effect of above technical scheme：The utility model can complete control wheel displacement, control wheel power, pair
Wing displacement/control stick displacement, control force, lifting rudder displacement/pedal displacement, pedal force, the synchronous acquisition of direction rudder displacement, place
Reason, display, record, realize the inquiry to historical data and patterned comparative analysis.
The utility model can realize the reliable and stable transmission of spot sensor signal long-distance, it can be achieved that distributed data
Synchronous acquisition, it can be achieved that the visualization of human-computer interaction；Realize synchronous acquisition and the quantitative analysis of steerable system performance parameter.
Description of the drawings
Fig. 1 is the modular structure schematic diagram of the utility model.
Specific embodiment
The preferred embodiment of the utility model is described in detail below in conjunction with the accompanying drawings.
Since the big aircraft cockpit of my company and the distance of aileron, elevator, rudder are far, most far 40 meters, institute
It is asked with solving the acquisition of the long range of the sensor signal of dispersed placement between cockpit and aileron, elevator, rudder and transmission
Topic is the main points of conceptual design.
Traditional spot sensor analog signals can be interfered in long distance transmission, is unstable.This patent uses
The programmable controller (PLC) and the digital communication technology based on Industrial Ethernet for having anti-interference advantage solve this and ask
Topic：PLC is placed in scene, directly acquire sensing data and is pre-processed, is then uploaded to data by Ethernet
Position machine.A plc data acquisition station is respectively configured in cockpit, aileron, elevator, rudder.
In addition, for the ease of operation and data analysis for flight control system performance test, outside aircraft (or center
Control room) it is configured with host computer i.e. central monitoring machine.Central monitoring machine uses laptop, while is done using SCADA softwares
Development platform for application software can be realized and historical data is looked into to the synchronous acquisition of data, processing, display, record
It askes and patterned comparative analysis.
The big aeroplane span that this equipment is directed to is 38.8m, captain 36.7m, a height of 12.8m of machine, 40 tons of empty weight, is driven
Sail cabin apart from about 30 meters of aileron, apart from about 40 meters of tail (elevator and rudder), data collection point be dispersed in cockpit,
Port wing, starboard wing, tail, and it is distant mutually, thus this equipment is based on DCS thoughts, concrete scheme is as follows：
As shown in Figure 1, the equipment by cockpit data collector, port wing data collector, starboard wing data collector,
Tail data collector, central monitoring machine, centrally connected power supply unit composition；Tail data collector is performed simultaneously elevator and direction
Associated sensor data acquisition on rudder；The industrial hub for performing ethernet communication is integrated in cockpit data collector
It is interior；Spot sensor is directly accessed on corresponding data collector；On-site data gathering device is using PLC as core, central monitoring machine
Using laptop and SCADA application software development platforms as core.
By cockpit data collector and power supply unit is concentrated to be placed in cockpit, by port wing data collector, starboard wing
Data collector, tail data collector are respectively placed in corresponding position, and central monitoring machine is placed under aircraft to operate
Personnel carry out test operation and data monitoring, analysis；With Industrial Ethernet connection by port wing data collector, starboard wing number
It is connected on the industrial hub collection of cockpit data collector according to collector, tail data collector and central monitoring machine.
4 data collectors perform respectively the acquisition to the sensing data at cockpit, port wing, starboard wing, tail,
The pretreatments such as conversion, filtering；Central monitoring machine controls 4 data collectors to synchronize digital independent and be further processed, show
Show, record, and realize the inquiry to historical data and patterned comparative analysis.
Cockpit data collector, port wing data collector, starboard wing data collector, tail data collector
PLC application software is completed to pretreatments such as the acquisitions, conversion, filtering of spot sensor data；The monitoring software of central monitoring machine
4 data collectors of control synchronize digital independent and are further processed, show, record, and realize and historical data is looked into
It askes and patterned comparative analysis.
Above-described is only the preferred embodiment of the utility model, it is noted that for the ordinary skill of this field
For personnel, under the premise of not departing from the utility model and creating design, various modifications and improvements can be made, these all belong to
In the scope of protection of the utility model.
Claims (5)
1. a kind of parameter acquisition and monitoring device for big flight control system performance test, which is characterized in that including by driving
Sail cabin data collector, port wing data collector, starboard wing data collector, tail data collector, central monitoring machine and
Centrally connected power supply unit forms；Data collector inside PLC directly acquires sensing data and is pre-processed, passes through Ethernet
Data are uploaded to central monitoring machine；Cockpit data collector, port wing data collector, starboard wing data collector, machine
Tail data collector performs the acquisition to the sensing data at cockpit, port wing, starboard wing, tail, conversion, filtering respectively
Deng pretreatment；Central monitoring machine is laptop, realizes synchronous acquisition, processing, display, the record of data, and can be realized pair
Visualization human-computer interaction is realized in the inquiry of historical data and patterned comparative analysis.
2. the parameter acquisition and monitoring device according to claim 1 for big flight control system performance test, special
Sign is, can complete control wheel displacement, control wheel power, aileron displacement/control stick displacement, control force, lifting rudder displacement/foot
Displacement, pedal force, the synchronous acquisition of direction rudder displacement, processing, display, record are pedaled, realizes the inquiry to historical data and figure
The comparative analysis of shape.
3. the parameter acquisition and monitoring device according to claim 1 for big flight control system performance test, special
Sign is, the cockpit data collector, port wing data collector, starboard wing data collector, tail data collector
Inside PLC, be respectively placed in cockpit, port wing, starboard wing, at tail.
4. the parameter acquisition and monitoring device according to claim 1 for big flight control system performance test, special
Sign is that the central monitoring machine is laptop, positioned at aircraft lower section or central control room.
5. the parameter acquisition and monitoring device according to claim 1 for big flight control system performance test, special
Sign is that the tail data collector is performed simultaneously the associated sensor data acquisition on elevator and rudder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721464623.XU CN207510742U (en) | 2017-11-06 | 2017-11-06 | A kind of parameter acquisition and monitoring device for big flight control system performance test |
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| CN201721464623.XU CN207510742U (en) | 2017-11-06 | 2017-11-06 | A kind of parameter acquisition and monitoring device for big flight control system performance test |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109279048A (en) * | 2018-11-20 | 2019-01-29 | 中航通飞华南飞机工业有限公司 | A kind of engine and APU revolving speed and avionics system are crosslinked closed loop detection method |
| CN110697074A (en) * | 2019-09-29 | 2020-01-17 | 蚌埠和能信息科技有限公司 | Aircraft testing device capable of realizing human-computer real-time interaction |
| CN111003206A (en) * | 2019-12-06 | 2020-04-14 | 江西洪都航空工业集团有限责任公司 | Airplane steering column starting force and operating force detection equipment and detection method |
| CN111547263A (en) * | 2020-05-09 | 2020-08-18 | 陕西飞机工业（集团）有限公司 | Method for testing ground dynamic characteristics of airplane control system |
| CN111811566A (en) * | 2020-05-26 | 2020-10-23 | 嘉兴立晟自动化设备有限公司 | Intelligent test platform and test method thereof |
-
2017
- 2017-11-06 CN CN201721464623.XU patent/CN207510742U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109279048A (en) * | 2018-11-20 | 2019-01-29 | 中航通飞华南飞机工业有限公司 | A kind of engine and APU revolving speed and avionics system are crosslinked closed loop detection method |
| CN109279048B (en) * | 2018-11-20 | 2021-09-24 | 中航通飞华南飞机工业有限公司 | Engine and APU (auxiliary Power Unit) rotating speed and avionics system cross-linking closed-loop detection method |
| CN110697074A (en) * | 2019-09-29 | 2020-01-17 | 蚌埠和能信息科技有限公司 | Aircraft testing device capable of realizing human-computer real-time interaction |
| CN111003206A (en) * | 2019-12-06 | 2020-04-14 | 江西洪都航空工业集团有限责任公司 | Airplane steering column starting force and operating force detection equipment and detection method |
| CN111547263A (en) * | 2020-05-09 | 2020-08-18 | 陕西飞机工业（集团）有限公司 | Method for testing ground dynamic characteristics of airplane control system |
| CN111547263B (en) * | 2020-05-09 | 2023-03-14 | 陕西飞机工业（集团）有限公司 | Method for testing ground dynamic characteristics of airplane control system |
| CN111811566A (en) * | 2020-05-26 | 2020-10-23 | 嘉兴立晟自动化设备有限公司 | Intelligent test platform and test method thereof |
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Inventor after: Zhang Yonghua Inventor after: Ren Lingzhi Inventor after: Kang Jian Inventor after: Jiang Naiqian Inventor after: Wang Lisong Inventor before: Zhang Yonghua Inventor before: Ren Lingzhi Inventor before: Kuang Jian Inventor before: Jiang Naiqian Inventor before: Wang Lisong |
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| CB03 | Change of inventor or designer information |