CN207833324U - Aircraft floor flight control system in situ detection equipment - Google Patents
Aircraft floor flight control system in situ detection equipment Download PDFInfo
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- CN207833324U CN207833324U CN201721538510.XU CN201721538510U CN207833324U CN 207833324 U CN207833324 U CN 207833324U CN 201721538510 U CN201721538510 U CN 201721538510U CN 207833324 U CN207833324 U CN 207833324U
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 14
- 238000001514 detection method Methods 0.000 title claims abstract description 12
- 238000011065 in-situ storage Methods 0.000 title claims abstract description 9
- 238000004891 communication Methods 0.000 claims abstract description 29
- 238000006243 chemical reaction Methods 0.000 claims description 9
- 238000003745 diagnosis Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 abstract description 2
- 230000007257 malfunction Effects 0.000 abstract description 2
- 238000002360 preparation method Methods 0.000 abstract description 2
- 230000032258 transport Effects 0.000 abstract description 2
- 238000013024 troubleshooting Methods 0.000 abstract description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 7
- 239000013307 optical fiber Substances 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 4
- 230000000630 rising effect Effects 0.000 description 4
- 230000002159 abnormal effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000000835 fiber Substances 0.000 description 3
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 3
- 241000195493 Cryptophyta Species 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 2
- 238000000605 extraction Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000002955 isolation Methods 0.000 description 2
- 229910052744 lithium Inorganic materials 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000003760 magnetic stirring Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
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Abstract
The utility model discloses aircraft floor flight control system in situ detection equipment, including：Power supply system, signal converting module, switch module, multi-functional acquisition module, communication system, handheld terminal.The utility model advantage is：1. originally onsite application personnel equipment early period connection preparation needs 20 minutes, can be reduced to now 7 minutes；2. can be placed in a Portable draw-bar box, transports, is easy to carry；3. realizing fault diagnosis functions, directly by malfunction coefficient in interface after the completion of test, the troubleshooting efficiency of Field Force is substantially increased；4. using wireless+wired communication modes of Industrial Ethernet standard, user of service can be carried out at the same time operation and test result inquiry on aircraft.Device structure described in the utility model is simple, installation operability is good, applied widely, disclosure satisfy that the ground safeguard of all kinds of aircrafts, can extend in various aircraft floor test systems and use.
Description
Technical field
The utility model is related to aircraft floor flight control system in situ detection equipment, belong to technical field of aerospace.
Background technology
Currently, the wireless in situ detection equipment of traditional aircraft floor flight control system is in the way of threeway that equipment is in parallel
Whether each function signal of acquisition system is normal in Airplane Flight Control System ', then by the logical relation between signal Analysis, by event
Barrier navigates on some component or certain specific circuit.
The patent of Publication No. CN107314966A discloses a kind of algae on-line detecting system and method, the system packet
Water inlet pipe is included, one end of the water inlet pipe is stretched into acquisition water sample, and the other end of the water inlet pipe is connected with pond, is located at acquisition
It is connected with solenoid valve and the water pump for sampling on water inlet pipe between water sample and the pond in turn, the bottom in the pond is set
It is equipped with magnetic stirring apparatus, the side in the pond is provided with ultrasonic cell disintegration instrument, and the ultrasonic cell disintegration instrument passes through cable
It is connected with one end of amplitude transformer, the other end of the amplitude transformer stretches into the pond, and level sensor is provided in the pond
Device, the pond are connected by sample feeding pipe with the CytoSense flow cytometers detected for algae, the side wall in the pond
Bottom is connected with drainpipe, and the side wall upper part in the pond is connected with overflow pipe.
The patent of Publication No. CN206609789U discloses a kind of DGT devices with optical fiber chelating fluorescent detector,
Including collecting room pedestal (1), sealing cover (2), LED light (13), fiber optic collimator mirror (14), optical fiber (15) and fluorescence detector
(16)；The deep gouge (11) being recessed inwardly is equipped in the middle part of the upper surface of collecting room pedestal (1)；There are one being set on the side wall of deep gouge (11)
To the LED light (13) being irradiated in deep gouge (11)；The bottom centre of deep gouge (11) sets there are one optical fiber mounting hole；Fiber optic collimator
Mirror (14) is fixed in the optical fiber mounting hole, and front end is directed toward in deep gouge (11), and its rear end is examined by optical fiber (15) and fluorescence
Device (16) is surveyed to connect；Fluorescence detector (16) is detected glimmering in the deep gouge (11) by optical fiber (14) and fiber optic collimator mirror (13)
Luminous intensity.It can realize that field condition directly carries out in situ detection to acquisition sample.
In conclusion Airplane Flight Control System ' original position somascope haves the shortcomings that bulky, mobility is poor at present, due to for
Farther out due to test point distance, the cable length matched is longer, and connection is more complex for integrated equipment.
Utility model content
The purpose of this utility model is to provide a kind of aircraft floor flight control system that can overcome above-mentioned technical problem is former
Level detection apparatus, the utility model aim to solve the problem that poor flight control system in situ detection portable devices, equipment and test system connect
Complexity cannot carry out the problem of fault diagnosis and make device miniaturization, modularization, portability.
Equipment described in the utility model includes：Power supply system, signal converting module, switch module, multi-functional acquisition module,
Communication system, handheld terminal.Signal converting module, switch module, multi-functional acquisition module are sequentially connected, communication system respectively with
Switch module, multi-functional acquisition module, handheld terminal connection, power supply system connect with switch module, multi-functional acquisition module respectively
It connects.
Power supply system is made of power conversion module and accumulator, and wherein power conversion module is using golden rising Yang
URB2405LD DC-DC module power sources, golden rising Yang URB2405LD DC-DC module power sources are inputted with super wide voltage, and isolation is steady
The characteristics of pressure single channel exports and efficiency is up to 90%.Accumulator uses the lithium battery group of 18650 battery core of LG company.Power supply system packet
Include two kinds of power supply modes：Mode one is power supply power supply on aircraft, and 28V is converted to 5V for equipment by power conversion module on aircraft
It uses；Mode two is storage battery power supply, and accumulator 12V is converted to 5V by power conversion module and is used for equipment.
Signal converting module cooperation switch module plays the role of threeway test, and signal converting module is public using multiple ERNI
114809 connectors of department, connecting path is provided for measured signal and switch module.Equipment described in the utility model will be detected to exist
Under conditions of not influencing system under test (SUT) or component normal work, it is parallel in system under test (SUT), monitors the defeated of system under test (SUT) or component
Enter output signal, simulates various sensor standard signals or fault-signal, failure is accurately positioned accordingly.
For switch module using the STM32 chips core in order to control of STMicw Electronics, it is to switch to use IM03 relays.Switch
There are two types of functions for module, and function one is to be switched to be measured to set by measured signal by closing relay to reach test in resource
Purpose；Function is second is that for realizing the self-test inside equipment described in the utility model.
Multi-functional acquisition module realizes the acquisition to signal with different type on aircraft and collected data is passed through bus
Mode and device talk described in the utility model.Multi-functional acquisition module is general utility functions board, using the general science and technology of Olympic
OLP-9233 data collecting plate cards comprising 64 road single ended input voltage acquisition channels and 32 road differential input voltage acquisitions are logical
Road.
Communication system uses someone's science and technology USR-WIFI232 communication modules, for realizing in equipment described in the utility model
Communication between switch module, multi-functional acquisition module and handheld terminal, equipment described in the utility model pass through control command
WiFi or Ethernet are issued to communication system, and control command is forwarded to out by RS485 buses or Ethernet by communication system again
Close module or multi-functional acquisition module, multi-functional acquisition module collects and sends data to communication system by Ethernet after data
Data are uploaded to equipment described in the utility model by system, communication system by WiFi or Ethernet.Handheld terminal is tablet computer
Or laptop, it will be shown, led in the collected data transmission to handheld terminal of multi-functional acquisition module by bus marco
The mode for crossing fault tree analyzes abnormal signal, will be on fault location to component or circuit.
Equipment described in the utility model is with Airplane Flight Control System ' connection relation：Cable on machine, cable on machine, cable on machine
Function one for the connecting pin of cut cable on aircraft and test adapter, test adapter is to introduce signals into test adapter
Interior test resource is tested, and the other function of test adapter is that signal is guided to the connection of test adapter other end
Signal is drawn on device, the signal of extraction is connected by an elongated segment cable with the unit under test on aircraft, and the side of threeway is utilized
Equipment described in the utility model is parallel in system under test (SUT) by formula, to achieve the purpose that test.Test adapter is by the number of test
It is shown according to being transferred on handheld terminal by wired or wireless mode, if having abnormal by fault location to component or circuit
On.Test adapter forms test system, can be evaded more than cable using single adapter structure and the long connection brought it is complicated,
Cumbersome disadvantage.Using wireless and wired communication modes facilitate ground energization inspection personnel be carried out at the same time the operation on aircraft and
Check test mode.
The utility model has the following advantages：
1. originally onsite application personnel equipment early period connection preparation needs 20 minutes, can be reduced to now 7 minutes；
2. can be placed in a Portable draw-bar box, transports, is easy to carry；
3. realizing fault diagnosis functions, directly by malfunction coefficient in interface after the completion of test, scene is substantially increased
The troubleshooting efficiency of personnel；
4. using wireless+wired communication modes of Industrial Ethernet standard, user of service can be carried out at the same time on aircraft
Operation and test result inquiry.
Device structure described in the utility model is simple, installation operability is good, applied widely, disclosure satisfy that all kinds of aircrafts
Ground safeguard, can extend in various aircraft floor test systems and use.
Description of the drawings
Fig. 1 is equipment described in the utility model and Airplane Flight Control System ' connection diagram；
Fig. 2 is the structural schematic diagram of equipment described in the utility model.
Specific implementation mode
The embodiment of the utility model is described in detail below in conjunction with the accompanying drawings.As shown in Fig. 2, the utility model institute
Stating equipment includes：Power supply system 11, signal converting module 12, switch module 13, multi-functional acquisition module 14, communication system 15,
Handheld terminal 16.Signal converting module 12, switch module 13, multi-functional acquisition module 14 are sequentially connected, and communication system 15 is distinguished
Connect with switch module 13, multi-functional acquisition module 14, handheld terminal 16, power supply system 11 respectively with switch module 13, more work(
It can the connection of acquisition module 14.
Power supply system 11 is made of power conversion module and accumulator, and wherein power conversion module is using golden rising Yang
URB2405LD DC-DC module power sources, golden rising Yang URB2405LD DC-DC module power sources are inputted with super wide voltage, and isolation is steady
The characteristics of pressure single channel exports and efficiency is up to 90%.Accumulator uses the lithium battery group of 18650 battery core of LG company.Power supply system 11
Including two kinds of power supply modes：Mode one is power supply power supply on aircraft, and 28V is converted to 5V for setting by power conversion module on aircraft
It is standby to use；Mode two is storage battery power supply, and accumulator 12V is converted to 5V by power conversion module and is used for equipment.
Signal converting module 12 coordinates switch module 13 to play the role of threeway test, and signal converting module 12 is using multiple
114809 connectors of ERNI companies provide connecting path for measured signal and switch module 13.It will detection the utility model institute
Equipment is stated under conditions of not influencing system under test (SUT) or component and working normally, is parallel in system under test (SUT), monitor system under test (SUT) or
The input/output signal of component simulates various sensor standard signals or fault-signal, failure is accurately positioned accordingly.
For switch module 13 using the STM32 chips core in order to control of STMicw Electronics, it is to switch to use IM03 relays.It opens
Closing module 13, there are two types of functions, and function one is to be switched to measured signal by closing relay to be measured to set to reach survey in resource
The purpose of examination；Function is second is that for realizing the self-test inside equipment described in the utility model.
Multi-functional acquisition module 14 is realized the acquisition to signal with different type on aircraft and is passed through collected data total
The mode of line and device talk described in the utility model.Multi-functional acquisition module 14 is general utility functions board, using the general section of Olympic
Skill OLP-9233 data collecting plate cards comprising 64 road single ended input voltage acquisition channels and 32 road differential input voltage acquisitions are logical
Road.
Communication system 15 uses someone's science and technology USR-WIFI232 communication modules, for realizing equipment described in the utility model
Communication between middle switch module 13, multi-functional acquisition module 14 and handheld terminal 16, equipment described in the utility model will control
Order is issued to communication system 15 by WiFi or Ethernet, and communication system 15 will be controlled by RS485 buses or Ethernet again
Order is forwarded to switch module 13 or multi-functional acquisition module 14, and function acquisition module 14 will by Ethernet after collecting data
Data are sent to communication system 15, and data are uploaded to described in the utility model set by communication system 15 by WiFi or Ethernet
It is standby.Handheld terminal 16 is tablet computer or laptop, by bus marco by 14 collected number of multi-functional acquisition module
It is shown according to being transferred on handheld terminal 16, abnormal signal is analyzed by way of fault tree, fault location is arrived
On component or circuit.
It is equipment described in the utility model and Airplane Flight Control System ' connection diagram as shown in Figure 1, cable 1 on machine, on machine
Cable 3 is the connecting pin of cut cable and test adapter 4, test adapter 5, test adapter 6 on aircraft on cable 2, machine, is surveyed
The function one of trying adapter is that the test resource introduced signals into test adapter is tested, and test adapter is in addition
Function be to guide to signal on test adapter other end connector to draw signal, the signal of extraction passes through an elongated segment
Cable is connected with unit under test 7, unit under test 8, the unit under test 9 on aircraft, by the utility model institute in the way of threeway
It states equipment to be parallel in system under test (SUT), to achieve the purpose that test.Test adapter 4, test adapter 5, test adapter 6 will
The data of test are transferred on handheld terminal 16 by wired or wireless mode and are shown, if there is exception to arrive fault location
On component or circuit.
Test adapter 4, test adapter 5, test adapter 6 form test system, using single adapter structure energy
Enough evade more than cable and grows connection complexity, the cumbersome disadvantage brought.Facilitate ground logical using wireless and wired communication modes
The operation and check test mode that electrical inspection personnel are carried out at the same time on aircraft.
As shown in Figure 1, 2, adapter power supply is carried out with the power supply mode two in the power supply system 11 in Fig. 2 first, opened
Handheld terminal 16 starts self-check program and carries out self-test to equipment described in the utility model.When equipment described in the utility model from
When detection passes through, device powers down described in the utility model is connected in the way of Fig. 1 with aircraft, after the completion of connection, by logical
News system 15 is communicated with handheld terminal 16.Opening test software is tested after realizing communication.On-the-spot test personnel pass through
Software prompt in handheld terminal 16 carries out aircraft energization, carries out signal acquisition by multi-functional acquisition module 14, will collect
Signal transferred data in a wireless or wired way in handheld terminal 16 by communication system 15, host computer is to collecting
Signal analysis is compared with standard value, finally provide fault message.
Above description is only a specific implementation of the present invention, but the scope of protection of the utility model is not limited to
In this, any one skilled in the art is in range disclosed by the utility model, the variation that can readily occur in
Or replace, it should all cover in the protection domain of the utility model claims.
Claims (2)
1. aircraft floor flight control system in situ detection equipment, which is characterized in that including：Power supply system, signal converting module, switch
Module, multi-functional acquisition module, communication system, handheld terminal, signal converting module, switch module, multi-functional acquisition module according to
Secondary connection, communication system are connect with switch module, multi-functional acquisition module, handheld terminal respectively, power supply system respectively with switch
Module, the connection of multi-functional acquisition module；The signal converting module connection measured signal and switch module；The switch module is adopted
It is switch with IM03 relays；The communication system is using the universal wireless communication module for being integrated with ICP/IP protocol.
2. aircraft floor flight control system in situ detection equipment according to claim 1, which is characterized in that the power supply system
Including：Power conversion module and accumulator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721538510.XU CN207833324U (en) | 2017-11-17 | 2017-11-17 | Aircraft floor flight control system in situ detection equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721538510.XU CN207833324U (en) | 2017-11-17 | 2017-11-17 | Aircraft floor flight control system in situ detection equipment |
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| Publication Number | Publication Date |
|---|---|
| CN207833324U true CN207833324U (en) | 2018-09-07 |
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ID=63386284
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721538510.XU Active CN207833324U (en) | 2017-11-17 | 2017-11-17 | Aircraft floor flight control system in situ detection equipment |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112558582A (en) * | 2020-10-30 | 2021-03-26 | 哈尔滨哈飞航空工业有限责任公司 | Helicopter avionics-based distributed in-situ troubleshooting device and method |
-
2017
- 2017-11-17 CN CN201721538510.XU patent/CN207833324U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112558582A (en) * | 2020-10-30 | 2021-03-26 | 哈尔滨哈飞航空工业有限责任公司 | Helicopter avionics-based distributed in-situ troubleshooting device and method |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 101300, Beijing, Shunyi District Renhe Town Du Yang North Street, No. 1, 19, 4 Patentee after: Beijing andaville Intelligent Technology Co.,Ltd. Address before: 101300, Beijing, Shunyi District Renhe Town Du Yang North Street, No. 1, 19, 4 Patentee before: BEIJING ANDAWELL MEASUREMENT & CONTROL TECHNOLOGY Co.,Ltd. |
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| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 101300 4th floor, building 1, No. 19, duyang North Street, Renhe Town, Shunyi District, Beijing Patentee after: Beijing Tianpu Situo Intelligent Technology Co.,Ltd. Address before: 101300 4th floor, building 1, No. 19, duyang North Street, Renhe Town, Shunyi District, Beijing Patentee before: Beijing andaville Intelligent Technology Co.,Ltd. |