CN105867281A - Wireless monitoring system for aircraft running state - Google Patents
Wireless monitoring system for aircraft running state Download PDFInfo
- Publication number
- CN105867281A CN105867281A CN201610416422.6A CN201610416422A CN105867281A CN 105867281 A CN105867281 A CN 105867281A CN 201610416422 A CN201610416422 A CN 201610416422A CN 105867281 A CN105867281 A CN 105867281A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- module
- sensor
- main control
- node module
- 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.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/048—Monitoring; Safety
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
-
- G—PHYSICS
- G08—SIGNALLING
- G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
- G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
- G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Automation & Control Theory (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
Abstract
The invention belongs to the field of wireless monitoring of aircrafts and relates to a wireless monitoring system for an aircraft running state. The wireless monitoring system solves the problems that an existing airborne monitoring system is multiple in testing parameter, complex in wire, great in additional weight, lack of flexibility, low in expandability and low in intelligent degree. The wireless monitoring system comprises a plurality of terminal node modules, a main node module and a PC; the terminal node modules are respectively fixed to all portions of an aircraft and are used for detecting state information of all the portions of the aircraft and gathering the detected state information to the main node module in a wireless transmission mode, the main node module can send the gathered state information to the PC, and the PC is used for displaying the received state information in real time, so that the aircraft running state can be monitored. The wireless monitoring system is mainly applied to monitoring aircraft states.
Description
Technical field
The invention belongs to aircraft wireless monitor field.
Background technology
Development along with aeronautical technology, aeroplane performance improves constantly, function is the most perfect, aircraft system structure heals and becomes complicated, heavily loaded, Aircraft Flight Test subject increases day by day, therefore during airborne testing, sensor acquisition parameter kind and quantity are multiplied, and the requirement to state of flight monitoring system is also gradually improving.And, each sensor that traditional Aircraft Flight Test test system is used is both needed to be connected to specific conditioning circuit and actuator just can complete process and the transfer function of signal.When system needs the physical quantity measuring multiple factor of influence in environment, the special sensor interface being directed to a certain specific signal just cannot meet the measurement of polytype status information.Simultaneously along with test parameter amount and the increase of port number, substantial amounts of on-the-spot line and impost can be introduced, cause the trouble of system maintenance and the low of testing efficiency；Along with the integrated raising of airborne products, reserving to testing machine that to install the space of test sensor and wiring additional extremely limited, construction is restricted.
For problem above, the present invention designs a kind of module based on the airborne status monitoring being wirelessly transferred, the series of problems such as solve that the test parameter existing for existing airborne monitoring system is many, lead-in wire is complicated, impost big, to lack motility, expandability and intelligence degree low.
Summary of the invention
The present invention is that test parameter existing for existing airborne monitoring system is many, lead-in wire is complicated, impost is big, lack the problem that motility, expandability and intelligence degree are low in order to solve, and the invention provides a kind of aircraft running status wireless monitor system.
Aircraft running status wireless monitor system, it includes multiple terminal node module, host node module and PC；
Multiple terminal node modules are separately fixed at each position of aircraft, status information for each position of sense aircraft, and the status information detected is converged to host node module by the way of being wirelessly transferred, the status information converged is delivered to PC by host node module, PC is for carrying out real-time display to the status information received, thus monitors the running status of aircraft.
Described each terminal node module includes sensor-based system, signal conditioning circuit, No. 1 main control module and No. 1 wireless transport module；
Sensor-based system is for the status information of sense aircraft, and this status information delivers to No. 1 main control module after signal conditioning circuit is nursed one's health, and the status information received is sent to host node module by No. 1 main control module by No. 1 wireless transport module.
Described host node module includes No. 2 wireless transport modules and No. 2 main control modules；
No. 2 main control modules are carried out data transmission with all of No. 1 wireless transport module by No. 2 wireless transport modules simultaneously, and No. 2 main control modules are additionally operable to control all of No. 1 main control module, thus control all of signal conditioning circuit.
Described sensor-based system includes attitude transducer, foil gauge, vibrating sensor, pressure transducer and temperature sensor；
Attitude transducer is used for the attitude information of sense aircraft,
Foil gauge is used for the strain differential on sense aircraft surface,
Vibrating sensor is used for the vibration information of sense aircraft,
Pressure transducer is used for the pressure-bearing information of sense aircraft,
Temperature sensor is for the temperature information of sense aircraft.
Described signal conditioning circuit includes programmable gain amplifier and 12 analog-digital converters；
Described programmable gain amplifier is for being amplified the attitude information received, and delivers to after 12 analog-digital converters carry out analog digital conversion, deliver to No. 1 main control module.
All it is embedded with Contiki operating system in described all of terminal node module and host node module, and the workflow of described Contiki operating system task and the event of process is as follows:
Start, perform clock successively, serial ports initializes, after process initialization, start system process, then start user's self-starting process, and perform this and carry out, terminate.
No. 1 described main control module and No. 2 main control modules use MSP430F5438A cake core to realize.
UIPv6 agreement is all transplanted in described each terminal node module and host node module, during each terminal node module building network, a unique IP address can be distributed, IP address be the node of 1.0 be host node, terminal node module forms wireless network by the way of multi-hop and self-organizing, and all data collected all converge on the host node at host node module place.
Described temperature sensor uses thermoelectricity occasionally resistance temperature detector to realize.
The detailed process that in described each terminal node module, sensor-based system is driven by No. 1 main control module is:
First, signal conditioning circuit is initialized, sensor-based system perception status information, after the status information received being carried out 32 stage gain amplifications by programmable gain amplifier, analog digital conversion is carried out again by 12 analog-digital converters, data after conditioning are sent, is ultimately delivered to host node module, is shown by PC.
1, sensor is articulated on end sensor node, writes sensor driver, including data acquisition, can the functional realiey such as gain amplification, analog digital conversion；
2. complete the software and hardware configuration of hardware module, power including device, Contiki system transplantation, collecting sensor signal driver programming, on each node apparatus, transplant uIPv6 agreement etc.；
3. distribute IP address for each terminal node, it is simple to distinguish different node；
4. take a flight test environment for simulated aircraft, the module configured can be installed on the diverse location of vehicle, and work on power, build Distributed Measurement System based on wireless sensor network, the status data in vehicle operation is monitored.
5. aggregation node is connected to PC by serial ports, by PC end host computer, Monitoring Data is carried out observation analysis.
The present invention brings and provides the benefit that, present invention achieves being wirelessly transferred the collection of state parameter during Aircraft Flight Test and data.Realize different conditions monitoring modular networking and data transmission, decrease existing detecting system lead-in wire complexity, impost, the raising monitoring motility of system, expandability and intelligence degree.Motility and intelligence degree all improve more than 30%.The present invention can will be distributed over the status data of the state monitoring module of diverse location and realize converging, and is uploaded to PC and presents and subsequent treatment.
Accompanying drawing explanation
Fig. 1 is the principle schematic of the aircraft running status wireless monitor system described in detailed description of the invention one；
Fig. 2 is the inside principle schematic of the host node module described in detailed description of the invention three；
Fig. 3 is the inside principle schematic of the sensor-based system described in detailed description of the invention four；
Fig. 4 is the inside principle schematic of the signal conditioning circuit described in detailed description of the invention five；
Fig. 5 is Contiki operating system task and the workflow diagram of the event of process.
Fig. 6 is the workflow diagram that sensor-based system is driven by No. 1 main control module.
Detailed description of the invention
Detailed description of the invention one: see Fig. 1 and present embodiment is described, the aircraft running status wireless monitor system described in present embodiment, it includes multiple terminal node module 1, host node module 2 and PC 3；
Multiple terminal node modules 1 are separately fixed at each position of aircraft, status information for each position of sense aircraft, and the status information detected is converged to host node module 2 by the way of being wirelessly transferred, the status information converged is delivered to PC 3 by host node module 2, PC 3 is for carrying out real-time display to the status information received, thus monitors the running status of aircraft.
Present embodiment, multiple terminal node modules 1 are deployed in aircraft fuselage different parts, build distributed test system based on wireless sensor network, the status information (temperature, stress, pressure, vibration etc.) during aircraft flies is gathered by dissimilar sensor, the mode being wirelessly transferred realizes intermodule networking, test convergence is to the host node at host node module 2 place the most at last, and by serial ports, status data is uploaded to PC, provide reliable data for aircraft state monitoring and fault diagnosis.
The position that position is terminal node of the aircraft fuselage residing for each terminal node module 1, the position of the aircraft fuselage residing for host node module 2 is the position of host node.
The present invention realizes test parameter collection, converges and show, LabVIEW is utilized to write host computer procedure, realize host node and receive the display of the information such as the display of all data, source, data length, transmission path, thus while realizing observing all data modes on PC, it is possible to judge the position that abnormal data occurs.
Detailed description of the invention two: see Fig. 1 and present embodiment is described, present embodiment is with the difference of the aircraft running status wireless monitor system described in detailed description of the invention one, and described each terminal node module 1 includes sensor-based system 1-1, signal conditioning circuit 1-2, No. 1 main control module 1-3 and No. 1 wireless transport module 1-4；
Sensor-based system 1-1 is for the status information of sense aircraft, and this status information is delivered to No. 1 main control module 1-3, No. 1 main control module 1-3 after signal conditioning circuit 1-2 nurses one's health and is sent the status information received to host node module 2 by No. 1 wireless transport module 1-4.
Detailed description of the invention three: see Fig. 2 and present embodiment is described, present embodiment is with the difference of the aircraft running status wireless monitor system described in detailed description of the invention two, and described host node module 2 includes No. 2 wireless transport module 2-1 and No. 2 main control module 2-2；
No. 2 main control module 2-2 are carried out data transmission with all of No. 1 wireless transport module 1-4 by No. 2 wireless transport module 2-1 simultaneously, and No. 2 main control module 2-2 are additionally operable to control all of No. 1 main control module 1-3, thus control all of signal conditioning circuit 1-2.
Detailed description of the invention four: see Fig. 3 and present embodiment is described, present embodiment is with the difference of the aircraft running status wireless monitor system described in detailed description of the invention two or three, and described sensor-based system 1-1 includes attitude transducer 1-1-1, foil gauge 1-1-2, vibrating sensor 1-1-3, pressure transducer 1-1-4 and temperature sensor 1-1-5；
Attitude transducer 1-1-1 is used for the attitude information of sense aircraft,
Foil gauge 1-1-2 is used for the strain differential on sense aircraft surface,
Vibrating sensor 1-1-3 is used for the vibration information of sense aircraft,
Pressure transducer 1-1-4 is used for the pressure-bearing information of sense aircraft,
Temperature sensor 1-1-5 is for the temperature information of sense aircraft.
Present embodiment, multiple terminal node modules 1 are deployed in aircraft fuselage different parts, build distributed test system based on wireless sensor network, status information (the temperature during aircraft flight is gathered by dissimilar sensor, stress, pressure, vibration etc.), standard signal is converted a signal into through sensor signal conditioning circuit, and utilize wireless transmission unit in module to realize intermodule networking, test convergence is to the host node at host node module 2 place the most at last, and by serial ports, status data is uploaded to PC, reliable data are provided for flight state monitoring and fault diagnosis.
The vitals of aircraft is when system mode changes or breaks down, the signals such as its vibration, stress, pressure, temperature, attitude carry substantial amounts of status information, for measuring these status informations, IEPE acceleration transducer, foil gauge, pressure transducer, PT100 platinum resistance thermometer sensor, or K-type thermocouple, MPU9255 nine axle acceleration sensor can be selected respectively as information gathering end, gather the status information in aircraft running.
Aircraft monitoring running state wireless module design hardware platform is mainly formed by based on sensor-based system 1-1, signal conditioning circuit 1-2, No. 1 main control module 1-3 and No. 1 wireless transport module 1-4.
When temperature sensor 1-1-5 uses PT100 platinum resistance thermometer sensor, or K-type thermocouple to realize, signal conditioning circuit 1-2 can use special thermal resistance numeral output translator (supporting that 2 lines, 3 lines and 4 line RTD connect) MAX31865 and thermocouple numeral output translator (to support that 8 kinds of thermocouples connect, can automatic linearity correction) MAX31856, it is possible to easy, accurately measure temperature.Two kinds of chips can nurse one's health thermal resistance, thermocouple signal respectively, is allowed to direct output temperature data.Therefore, both modulate circuits are utilized to nurse one's health from thermal resistance and the data of thermocouple.
Detailed description of the invention five: see Fig. 4 and present embodiment is described, present embodiment is with the difference of the aircraft running status wireless monitor system described in detailed description of the invention two, and described signal conditioning circuit 1-2 includes programmable gain amplifier 1-2-1 and 12 analog-digital converter 1-2-2；
Described programmable gain amplifier 1-2-1 is for being amplified the attitude information received, and delivers to after 12 analog-digital converter 1-2-2 carry out analog digital conversion, deliver to No. 1 main control module 1-3.
Detailed description of the invention six: see Fig. 1 and Fig. 5 and present embodiment is described, present embodiment is with the difference of the aircraft running status wireless monitor system described in detailed description of the invention one, all it is embedded with Contiki operating system in described all of terminal node module 1 and host node module 2, and the workflow of described Contiki operating system task and the event of process is as follows:
Start, perform clock successively, serial ports initializes, after process initialization, start system process, then start user's self-starting process, and perform this and carry out, terminate.
Present embodiment, the design of this aircraft monitoring running state wireless module mainly utilizes wireless sensor network to build a kind of Distributed Measurement System, it is achieved the networking of diverse location intermodule and wireless data transmission.The Contiki operating system increased income that the present invention has selected Sweden's Computer Sciences Laboratory to be wireless sensor network node exploitation realizes platform building based on wireless sensor network.Official's routine of wismote platform TI MSP430x in Contiki official website and TI CC2520 formed is downloaded in Contiki operating system, compiles configuration accordingly according to MSP430F5438A, pin definitions, the amendment of clock configuration etc., completes to transplant.Then in Contiki operating system, realize the software design of hardware module and the exploitation of driver.
Often add a kind of new sensor, need in the hardware platform file of Contiki operating system, add corresponding driver.The present invention selects five kinds of sensors as information gathering end, therefore write 5 kinds of sensor driver, finally call driver repeatedly in Contiki process, it is achieved data acquisition.
(1) thermocouple, thermal resistance Driver Development
Resistance and thermocouple, by all being nursed one's health by single-chip, are controlled by spi bus by main control unit.
(2) foil gauge Driver Development
Foil gauge Driver Development flow process is as shown in Figure 5, first chip each in modulate circuit is initialized, sensor senses status information, MAX1454 is by single pin digital programmable, by controlling DIO pin level height, control it and carry out configurable 32 stage gains amplifications, control LTC2302 by SPI and carry out analog digital conversion, data after conditioning are sent, is ultimately delivered to host node and carries out host computer and show.
Detailed description of the invention seven: see Fig. 2 and present embodiment is described, present embodiment is with the difference of the aircraft running status wireless monitor system described in detailed description of the invention three, and No. 1 described main control module 1-3 and No. 2 main control module 2-2 uses MSP430F5438A cake core to realize.
In present embodiment, what No. 1 main control module 1-3 and No. 2 main control module 2-2 selected is powerful super low-power consumption microprocessor MSP430F5438A that TI releases, its rich interface, there are up to 87 common I/O pins.Meanwhile, it does well in terms of low-power consumption, and it has low-down supply voltage, and magnitude of voltage is between 1.8V to 3.6V, and has multiple-working mode, and under low-power consumption mode, minimum current is up to 0.1mA, uses the most with the obvious advantage.
No. 1 wireless transport module 1-4 and No. 2 wireless transport module 2-1 can use CC2520 radio frequency chip, CC2520 operating frequency is 2.4GHz, it is rf receiver and transmitter based on ZigBee/IEEE802.15.4 consensus standard, it is adaptable to industrial monitoring and the wireless sensor network controlling purposes.It is connected with controller MSP430F5438A by SPI interface and 6 signal line, completes to arrange and transceiving data process.
In the present system, the function of radio node is, in test terminal, controls Conditioning Circuits of Sensor by modes such as SPI or IIC and control sends data to host node；In host node, it is responsible for controlling receive the data transmitted by test terminal and shown to PC or host computer by serial ports transmission.
All of sensor signal conditioning chip all can be controlled by SPI, IIC or UART, controls function and is completed by MSP430F5438A radio node.
Detailed description of the invention eight: see Fig. 1 and present embodiment is described, present embodiment is with the difference of the aircraft running status wireless monitor system described in detailed description of the invention one or seven, uIPv6 agreement is all transplanted in described each terminal node module 1 and host node module 2, during each terminal node module 1 building network, a unique IP address can be distributed, IP address be the node of 1.0 be host node, terminal node module 1 forms wireless network by the way of multi-hop and self-organizing, and all data collected all converge on the host node at host node module 2 place.
The present invention have selected Contiki operating system as embedded OS, is more suitable for the resource constrained environment such as Internet of Things, more light weight, and has highly portable and versatility.Software realizes the transplanting on node of the uIPv6 agreement and application, it is achieved networking and convergence between node.After node powers on, carry out the initialization of the module such as system clock, UART, FLASH successively.Start sensor data acquisition process and procotol process after this.In Contiki operating system enters actual task processes it is, check and whether process queue has process need to process, process to be processed is needed if existing, system is according to the scheduling executive process preset, if not having task to need to process, node enters resting state, to system timer to after date, wakes up processor up.
Wireless sensor network is made up of the status monitoring node being deployed in aircraft diverse location, each node structure is identical, each node apparatus is transplanted uIPv6 agreement, IPv6 agreement has abundant address resource, safety is high, during each node apparatus building network, a unique IP address can be distributed, be one address of each node that will add network configuration.Address be the node of 1.0 be host node, by the way of multi-hop and self-organizing, form wireless network between node, all data collected all converge to host node.For wireless sensor network intercommunication, Contiki uses low-consumption wireless electric network stack Rime.Rime achieves many sensor network protocols, is flooded to multi-hop bulk data transfer, data dissemination from infallible data collection, best endeavors network.The Distributed Measurement System built hence with this module is possible not only to monitor different types of state parameter, acquisition module location can also be carried out by the IP address of each module, the status information of diverse location during Aircraft Flight Test can be understood more accurately, add the use value of the status data of module monitors.
Detailed description of the invention nine: see Fig. 1 and present embodiment is described, present embodiment is with the difference of the aircraft running status wireless monitor system described in detailed description of the invention one, and described temperature sensor 1-1-5 uses thermoelectricity occasionally resistance temperature detector to realize.
Detailed description of the invention ten: see Fig. 6 and present embodiment is described, present embodiment is with the difference of the aircraft running status wireless monitor system described in detailed description of the invention five, and the detailed process that in described each terminal node module 1, sensor-based system 1-1 is driven by No. 1 main control module 1-3 is:
First, signal conditioning circuit 1-2 is initialized, sensor-based system 1-1 perception status information, after the status information received being carried out 32 stage gain amplifications by programmable gain amplifier 1-2-1, analog digital conversion is carried out again by 12 analog-digital converter 1-2-2, data after conditioning are sent, is ultimately delivered to host node module 2, is shown by PC 3.
Claims (10)
1. aircraft running status wireless monitor system, it is characterised in that it includes multiple terminal node module (1), main joint
Point module (2) and PC (3)；
Multiple terminal node modules (1) are separately fixed at each position of aircraft, for the state at each position of sense aircraft
Information, and the status information detected is converged to by the way of being wirelessly transferred host node module (2), host node module (2)
The status information converged is delivered to PC (3), and the status information that PC (3) is used for receiving carries out real-time display,
Thus monitor the running status of aircraft.
Aircraft running status wireless monitor system the most according to claim 1, it is characterised in that described each end
End node module (1) includes sensor-based system (1-1), signal conditioning circuit (1-2), No. 1 main control module (1-3) and 1
Number wireless transport module (1-4)；
Sensor-based system (1-1) is for the status information of sense aircraft, and this status information is through signal conditioning circuit (1-2)
Delivering to No. 1 main control module (1-3) after conditioning, No. 1 main control module (1-3) will by No. 1 wireless transport module (1-4)
The status information received sends to host node module (2).
Aircraft running status wireless monitor system the most according to claim 2, it is characterised in that described host node
Module (2) includes No. 2 wireless transport modules (2-1) and No. 2 main control modules (2-2)；
No. 2 main control modules (2-2) by No. 2 wireless transport modules (2-1) simultaneously with all of No. 1 wireless transport module
(1-4) carrying out data transmission, No. 2 main control modules (2-2) are additionally operable to control all of No. 1 main control module (1-3), from
And control all of signal conditioning circuit (1-2).
4. according to the aircraft running status wireless monitor system described in Claims 2 or 3, it is characterised in that described biography
Sensing system (1-1) includes that attitude transducer (1-1-1), foil gauge (1-1-2), vibrating sensor (1-1-3), pressure pass
Sensor (1-1-4) and temperature sensor (1-1-5)；
Attitude transducer (1-1-1) is used for the attitude information of sense aircraft,
Foil gauge (1-1-2) is used for the strain differential on sense aircraft surface,
Vibrating sensor (1-1-3) is used for the vibration information of sense aircraft,
Pressure transducer (1-1-4) is used for the pressure-bearing information of sense aircraft,
Temperature sensor (1-1-5) is for the temperature information of sense aircraft.
Aircraft running status wireless monitor system the most according to claim 2, it is characterised in that described signal is adjusted
Reason circuit (1-2) includes programmable gain amplifier (1-2-1) and 12 analog-digital converters (1-2-2)；
Described programmable gain amplifier (1-2-1) is for being amplified the attitude information received, and delivers to 12 moulds
After number converter (1-2-2) carries out analog digital conversion, deliver to No. 1 main control module (1-3).
Aircraft running status wireless monitor system the most according to claim 1, it is characterised in that described is all of
Contiki operating system, and described Contiki all it is embedded with in terminal node module (1) and host node module (2)
The workflow of operating system task and the event of process is as follows:
Start, perform clock, serial ports initialization successively, after process initialization, start system process, then start user certainly
Startup process, and perform this and carry out, terminate.
Aircraft running status wireless monitor system the most according to claim 3, it is characterised in that No. 1 described master
Control module (1-3) and No. 2 main control modules (2-2) use MSP430F5438A cake core to realize.
8. according to the aircraft running status wireless monitor system described in claim 1 or 7, it is characterised in that described is every
UIPv6 agreement, each terminal node module (1) group is all transplanted on individual terminal node module (1) and host node module (2)
During establishing network, a unique IP address can be distributed, IP address be the node of 1.0 be host node, terminal node module (1)
Forming wireless network by the way of multi-hop and self-organizing, all data collected all converge to host node module (2) place
Host node on.
Aircraft running status wireless monitor system the most according to claim 1, it is characterised in that described temperature passes
Sensor (1-1-5) uses thermoelectricity occasionally resistance temperature detector to realize.
Aircraft running status wireless monitor system the most according to claim 5, it is characterised in that described is each
The detailed process that in terminal node module (1), sensor-based system (1-1) is driven by No. 1 main control module (1-3) is:
First, signal conditioning circuit (1-2) is initialized, sensor-based system (1-1) perception status information, by can
After programming gain amplifier (1-2-1) carries out 32 stage gain amplifications to the status information received, then by 12 analog digital conversion
Device (1-2-2) carries out analog digital conversion, the data after conditioning is sent, is ultimately delivered to host node module (2), passes through PC
Machine (3) shows.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610416422.6A CN105867281A (en) | 2016-06-12 | 2016-06-12 | Wireless monitoring system for aircraft running state |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610416422.6A CN105867281A (en) | 2016-06-12 | 2016-06-12 | Wireless monitoring system for aircraft running state |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105867281A true CN105867281A (en) | 2016-08-17 |
Family
ID=56650318
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610416422.6A Pending CN105867281A (en) | 2016-06-12 | 2016-06-12 | Wireless monitoring system for aircraft running state |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105867281A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106781350A (en) * | 2016-11-14 | 2017-05-31 | 北京临近空间飞行器系统工程研究所 | A kind of new connection system of aircraft inner sensor |
| CN106789463A (en) * | 2016-12-16 | 2017-05-31 | 华中科技大学 | A kind of sensing data based on unmanned plane IPv6ization accesses Transmission system and method |
| CN107255492A (en) * | 2017-07-17 | 2017-10-17 | 郑州航空工业管理学院 | A kind of aircraft health status monitoring system based on distributing optical fiber sensing |
| CN107560767A (en) * | 2017-08-30 | 2018-01-09 | 陕西千山航空电子有限责任公司 | A kind of airborne structural stress monitoring device |
| CN108629961A (en) * | 2018-05-11 | 2018-10-09 | 广州极飞科技有限公司 | Equipment inspection method, equipment check device, remote controler and unmanned plane |
| CN108931324A (en) * | 2018-09-20 | 2018-12-04 | 四川腾盾科技有限公司 | A kind of strain wheel load and real-time heavy condition measuring system |
| CN110231051A (en) * | 2019-06-21 | 2019-09-13 | 中国飞行试验研究院 | A kind of airborne wireless height velocity sensing device |
| CN110347461A (en) * | 2019-06-17 | 2019-10-18 | 南京航空航天大学 | Aircraft cockpit man-machine interface message scheduling system and method based on Migrating Workflow |
| CN111787505A (en) * | 2020-07-06 | 2020-10-16 | 北京理工大学 | Modular reconfigurable wireless network test node system and working method |
| CN113014636A (en) * | 2021-02-22 | 2021-06-22 | 珠海翔翼航空技术有限公司 | Flight simulator online monitoring system based on Internet of things |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080234893A1 (en) * | 2007-03-23 | 2008-09-25 | The Boeing Company | Window control system |
| CN101650201A (en) * | 2008-08-13 | 2010-02-17 | 中国科学院自动化研究所 | System and method for ground information acquisition |
| DE102009009189A1 (en) * | 2009-02-16 | 2010-08-19 | Airbus Deutschland Gmbh | Sensor and sensor network for an aircraft |
| CN201698228U (en) * | 2010-06-12 | 2011-01-05 | 北京国科环宇空间技术有限公司 | Equipment supervisor in aircraft and health supervisor in equipment supervisor |
| CN104517432A (en) * | 2014-12-24 | 2015-04-15 | 兰州大学 | Monitoring system based on unmanned aerial vehicle and wireless sensor network |
-
2016
- 2016-06-12 CN CN201610416422.6A patent/CN105867281A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080234893A1 (en) * | 2007-03-23 | 2008-09-25 | The Boeing Company | Window control system |
| CN101650201A (en) * | 2008-08-13 | 2010-02-17 | 中国科学院自动化研究所 | System and method for ground information acquisition |
| DE102009009189A1 (en) * | 2009-02-16 | 2010-08-19 | Airbus Deutschland Gmbh | Sensor and sensor network for an aircraft |
| CN201698228U (en) * | 2010-06-12 | 2011-01-05 | 北京国科环宇空间技术有限公司 | Equipment supervisor in aircraft and health supervisor in equipment supervisor |
| CN104517432A (en) * | 2014-12-24 | 2015-04-15 | 兰州大学 | Monitoring system based on unmanned aerial vehicle and wireless sensor network |
Non-Patent Citations (1)
| Title |
|---|
| 张莹 等: "《基于ZigBee无线传感器网络的飞机状态监测系统》", 《计算机测量与控制》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106781350A (en) * | 2016-11-14 | 2017-05-31 | 北京临近空间飞行器系统工程研究所 | A kind of new connection system of aircraft inner sensor |
| CN106789463A (en) * | 2016-12-16 | 2017-05-31 | 华中科技大学 | A kind of sensing data based on unmanned plane IPv6ization accesses Transmission system and method |
| CN107255492A (en) * | 2017-07-17 | 2017-10-17 | 郑州航空工业管理学院 | A kind of aircraft health status monitoring system based on distributing optical fiber sensing |
| CN107560767A (en) * | 2017-08-30 | 2018-01-09 | 陕西千山航空电子有限责任公司 | A kind of airborne structural stress monitoring device |
| CN108629961A (en) * | 2018-05-11 | 2018-10-09 | 广州极飞科技有限公司 | Equipment inspection method, equipment check device, remote controler and unmanned plane |
| CN108931324A (en) * | 2018-09-20 | 2018-12-04 | 四川腾盾科技有限公司 | A kind of strain wheel load and real-time heavy condition measuring system |
| CN110347461A (en) * | 2019-06-17 | 2019-10-18 | 南京航空航天大学 | Aircraft cockpit man-machine interface message scheduling system and method based on Migrating Workflow |
| CN110347461B (en) * | 2019-06-17 | 2021-05-11 | 南京航空航天大学 | Airplane cockpit human-computer interface information scheduling system and method based on migration workflow |
| CN110231051A (en) * | 2019-06-21 | 2019-09-13 | 中国飞行试验研究院 | A kind of airborne wireless height velocity sensing device |
| CN111787505A (en) * | 2020-07-06 | 2020-10-16 | 北京理工大学 | Modular reconfigurable wireless network test node system and working method |
| CN113014636A (en) * | 2021-02-22 | 2021-06-22 | 珠海翔翼航空技术有限公司 | Flight simulator online monitoring system based on Internet of things |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105867281A (en) | Wireless monitoring system for aircraft running state | |
| Cao-Hoang et al. | Environment monitoring system for agricultural application based on wireless sensor network | |
| Li et al. | Practical deployment of an in-field soil property wireless sensor network | |
| BR112017017431B1 (en) | DEVICE FOR TRANSMISSION AND CONTROL OF DATA IN A NETWORK OF MULTINODES SENSORS, METHOD OF CONTROL OF THE DEVICE FOR TRANSMISSION AND CONTROL OF DATA IN A NETWORK OF SENSORS MULTINODES AND PET DEVICE HAVING AN ELECTRONIC USER INTERFACE SYSTEM | |
| CN103645443A (en) | Storage battery measurement and control system | |
| CN104570793A (en) | Self-detection method for analog unit of flight control computer | |
| Mane-Deshmukh et al. | Microcontroller PIC 18f4550 based Wireless Sensor Node to monitor industrial environmental parameters | |
| CN202522915U (en) | Data acquisition system based on vibration wire type sensor | |
| WO2008065692A2 (en) | Integrated solution for sensor interface for monitoring the environmental parameters by means of rfid technologies | |
| Pawar et al. | Wireless sensor network to monitor spatiotemporal thermal comfort of polyhouse environment | |
| CN206670684U (en) | A kind of remote supervisory and control(ling) equipment for inspection oil country tubular good | |
| Hamza et al. | Wireless biomedical system design based on ZigBee technology for autonomous healthcare | |
| CN209784791U (en) | Sensing data acquisition and processing system | |
| Goh et al. | FPGA based wireless sensor node for distributed process monitoring | |
| CN210836534U (en) | Data acquisition monitoring system based on MOS pipe charging control circuit | |
| CN106856041A (en) | Suitable for the information acquisition device of long distance control system | |
| CN219657039U (en) | Temperature acquisition equipment and system for wind power generation control system | |
| CN104900028A (en) | Vibratory string type wireless acquisition fulcrum and control method thereof | |
| CN105404229A (en) | Greenhouse environment measurement and control system based on Zigbee technology | |
| CN214702550U (en) | Vibrating screen motor bearing temperature detection device and system | |
| CN203025589U (en) | Wireless humiture monitoring and controlling device for archives | |
| CN202600389U (en) | Wireless data collection apparatus | |
| CN203366110U (en) | Dovecote environment monitoring system | |
| Pawar et al. | A Hybrid Green House Management by Power Intelligent Device/Wireless Networking (Polyhouse Automation System) | |
| CN102981535A (en) | Wireless measuring and controlling device for temperature and humidity in archive |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160817 |
|
| RJ01 | Rejection of invention patent application after publication |