CN206243509U - A kind of analogue means of aircraft test signal - Google Patents
A kind of analogue means of aircraft test signal Download PDFInfo
- Publication number
- CN206243509U CN206243509U CN201621234579.9U CN201621234579U CN206243509U CN 206243509 U CN206243509 U CN 206243509U CN 201621234579 U CN201621234579 U CN 201621234579U CN 206243509 U CN206243509 U CN 206243509U
- Authority
- CN
- China
- Prior art keywords
- switch
- interface
- power supply
- cable
- test
- 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.)
- Active
Links
Landscapes
- Testing Electric Properties And Detecting Electric Faults (AREA)
Abstract
The utility model is related to a kind of analogue means of aircraft test signal, device power supply (DPS) interface and multiple test cable interfaces are set on the debugging panel, multiple switch two and switch one are additionally provided with the debugging panel, the device power supply (DPS) interface is cascaded with switch one by cable, the switch one is connected in parallel with multiple switch two by cable, the switch two is cascaded with test cable interface by cable, the device power supply (DPS) interface is connected with ground power supply equipment, one end of electric connector is connected with the test cable interface, the other end of the electric connector is connected with corresponding airborne equipment.The utility model provides corresponding analog signal to multiple airborne equipments by device power supply (DPS) interface, only need to pull analogue means respective switch on ground, and alleviates the work load of tester, improves aircraft floor and is powered the efficiency of test.
Description
Technical field
The utility model belongs to aviation special equipment testing field, more particularly to a kind of simulation of aircraft test signal is filled
Put.
Background technology
Aircraft is in general assembly, ground energization test process of taking a flight test, it is necessary to be aircraft power system, Mechatronic Systems, avionics system
System, flight control system etc. provide the signals such as various wheel loads, hatchcover, hatch door, undercarriage, hydraulic unloading, so as to ensure that each system is led to
What electricity was debugged is normally carried out.
Patent No. CN203601583U, the applying date is 2013-11-29, discloses a kind of aircraft windows assembly property
Test system.Including industrial computer, for being connected with programmable logic controller (PLC) and control aircraft windows components examination is transmitted
The pulse signal of experiment device, and receive the electric current letter of the aircraft windows assembly test device after being processed through programmable logic controller (PLC)
Number；Including programmable logic controller (PLC), the pulse signal of aircraft windows assembly test device is controlled for receiving industrial computer,
And the current signal of reception processing aircraft windows assembly test device；Including aircraft windows assembly test device and for being aircraft
Porthole assembly test device provides the source of the gas of air.
Above-mentioned patent is by temperature, the pressure parameter under effectively simulation aircraft flight operating mode, true reflection aircraft windows glass
The influence that physical property and assembling assembly in glass real work are produced to its performance, to the test data during performance test
Can automatically intercept and be saved in industrial computer, expansible test function.But it is airborne that above-mentioned patent is only capable of test one
Equipment, as present generation aircraft needs the signal of monitoring more and more, the particularly use of built-in type magazine, traditional simulator is only
The method that aircraft wheel information carrying number can be simulated can not be applicable, if individually tested each product airborne equipment, work
Efficiency is low, the work load weight of tester.
Utility model content
The purpose of this utility model is to overcome the above-mentioned problems in the prior art, there is provided a kind of aircraft test signal
Analogue means, this device can provide corresponding analog signal to multiple airborne equipments, it is not necessary to the multiple airborne of aircraft
Equipment carries out individually operated, alleviates the work load of tester, improves aircraft floor and is powered the efficiency of test.
To achieve the above object, the technical solution adopted in the utility model is as follows：
A kind of analogue means of aircraft test signal, including test cable interface, device power supply (DPS) interface and debugging panel, institute
State and device power supply (DPS) interface and multiple test cable interfaces are set on debugging panel, multiple switch is additionally provided with the debugging panel
Two are cascaded with switch one with switch one, the device power supply (DPS) interface by cable, the switch one and multiple switch
Two are connected in parallel by cable, and the switch two is cascaded with test cable interface by cable, the equipment
Power interface is connected with ground power supply equipment, and one end of electric connector, the electrical connection are connected with the test cable interface
The other end of device is connected with corresponding airborne equipment.
The switch two is toggle switch, and the upper-lower position of the toggle switch is provided with indicator lamp, one button
Switch two indicator lamps of correspondence, the indicator lamp is arranged on debugging panel.
The airborne equipment includes wheel load, hatchcover, hatch door, undercarriage and hydraulic system.
The switch one is button switch.
The debugging panel is cube structure.
Using the utility model has the advantage of：
1st, provide corresponding analog signal to multiple airborne equipments by a device power supply (DPS) interface, aircraft general assembly,
Take a flight test in ground energization test process, it is not necessary to multiple airborne equipments of aircraft are carried out individually operated, need to only be pulled on ground
Analogue means respective switch, you can the analog signal of multiple corresponding systems is provided for aircraft, and alleviate the work of tester
Burden, improves the efficiency of aircraft floor energization test.
2nd, simple, convenient by toggle switch and indicator lamp setting up and down, operating personnel are more intuitive when working
The state in which of switch is observed, both whether analog signal was in feed status, prevented operational error.
3rd, analog signal is sent by wheel load, hatchcover, hatch door, undercarriage and hydraulic system, so as to ensure that each system is led to
What electricity was debugged is normally carried out.
4th, it is simple by operation of push-button switch.
5th, by the debugging panel of cube structure, at work, it is easily placed, appearance looks elegant.
Brief description of the drawings
Fig. 1 is the utility model structural representation.
Fig. 2 is the utility model circuit structure block diagram.
Marked in figure：1st, test cable interface, 2, device power supply (DPS) interface, 3, debugging panel, 4, switch one, 5, indicator lamp,
6th, two are switched.
Specific embodiment
The utility model is described further below in conjunction with the accompanying drawings.
Embodiment 1
As shown in Figure 1 to Figure 2, a kind of analogue means of aircraft test signal, including test cable interface 1, device power supply (DPS)
Interface 2 and debugging panel 3, set device power supply (DPS) interface 2 and multiple test cable interfaces 1, the debugging on the debugging panel 3
Multiple switch 24 and switch 1 are additionally provided with panel 3, the device power supply (DPS) interface 2 is connected with switch 1 by cable
Together, the switch 1 is connected in parallel with multiple switch 24 by cable, described to switch 24 with test cable interface
1 is cascaded by cable, and the device power supply (DPS) interface 2 is connected with ground power supply equipment, on the test cable interface 1
One end of electric connector is connected with, the other end of the electric connector is connected with corresponding airborne equipment.
Work operation when, open switch 26, ground power supply equipment start conveying analog signal and electric power, when need test
During one or several airborne equipments, corresponding switch 1 is opened, ground power supply equipment is by debugging the setting on panel 3
Each part is connected with airborne equipment, and analog signal is also transported in surveyed airborne equipment accordingly, and multiple switch 1 is connected in parallel on
Together, each how corresponding airborne equipment of the control of switch 1, provides to multiple airborne equipments by a device power supply (DPS) interface 2
Corresponding analog signal, in aircraft in general assembly, ground energization test process of taking a flight test, it is not necessary to multiple airborne equipments of aircraft
Carry out it is individually operated, only need to pull analogue means respective switch on ground, you can for aircraft provides multiple corresponding systems simulation
Signal, and the work load of tester is alleviated, improve the efficiency of aircraft floor energization test.
Embodiment 2
As shown in Figure 1 to Figure 2, a kind of analogue means of aircraft test signal, including test cable interface 1, device power supply (DPS)
Interface 2 and debugging panel 3, set device power supply (DPS) interface 2 and multiple test cable interfaces 1, the debugging on the debugging panel 3
Multiple switch 24 and switch 1 are additionally provided with panel 3, the device power supply (DPS) interface 2 is connected with switch 1 by cable
Together, the switch 1 is connected in parallel with multiple switch 24 by cable, described to switch 24 with test cable interface
1 is cascaded by cable, and the device power supply (DPS) interface 2 is connected with ground power supply equipment, on the test cable interface 1
One end of electric connector is connected with, the other end of the electric connector is connected with corresponding airborne equipment.
The switch 24 is toggle switch, and the upper-lower position of the toggle switch is provided with indicator lamp 5, one button
Sub switch two indicator lamps 5 of correspondence, the indicator lamp 5 is arranged on debugging panel 3.
Work operation when, open switch 26, ground power supply equipment start conveying analog signal and electric power, when need test
During one or several airborne equipments, corresponding switch 1 is opened, ground power supply equipment is by debugging the setting on panel 3
Each part is connected with airborne equipment, and analog signal is also transported in surveyed airborne equipment accordingly, and multiple switch 1 is connected in parallel on
Together, each how corresponding airborne equipment of the control of switch 1, provides to multiple airborne equipments by a device power supply (DPS) interface 2
Corresponding analog signal, in aircraft in general assembly, ground energization test process of taking a flight test, it is not necessary to multiple airborne equipments of aircraft
Carry out it is individually operated, only need to pull analogue means respective switch on ground, you can for aircraft provides multiple corresponding systems simulation
Signal, and the work load of tester is alleviated, improve the efficiency of aircraft floor energization test.
24 are switched for toggle switch, can be adjusted up and down, and the upper-lower position of toggle switch is respectively provided with an indicator lamp 5, on
One, face is opened for green is represented, below one close for red expression, by toggle switch and indicator lamp setting up and down, behaviour
Make simple, convenient, the state in which of more intuitive observation switch when operating personnel work, both whether analog signal is in conveying
State, prevents operational error.
Embodiment 3
As shown in Figure 1 to Figure 2, a kind of analogue means of aircraft test signal, including test cable interface 1, device power supply (DPS)
Interface 2 and debugging panel 3, set device power supply (DPS) interface 2 and multiple test cable interfaces 1, the debugging on the debugging panel 3
Multiple switch 24 and switch 1 are additionally provided with panel 3, the device power supply (DPS) interface 2 is connected with switch 1 by cable
Together, the switch 1 is connected in parallel with multiple switch 24 by cable, described to switch 24 with test cable interface
1 is cascaded by cable, and the device power supply (DPS) interface 2 is connected with ground power supply equipment, on the test cable interface 1
One end of electric connector is connected with, the other end of the electric connector is connected with corresponding airborne equipment.
The switch 24 is toggle switch, and the upper-lower position of the toggle switch is provided with indicator lamp 5, one button
Sub switch two indicator lamps 5 of correspondence, the indicator lamp 5 is arranged on debugging panel 3.
The airborne equipment includes wheel load, hatchcover, hatch door, undercarriage and hydraulic system.
The switch 1 is button switch.
The debugging panel 3 is cube structure.
Work operation when, open switch 26, ground power supply equipment start conveying analog signal and electric power, when need test
During one or several airborne equipments, corresponding switch 1 is opened, ground power supply equipment is by debugging the setting on panel 3
Each part is connected with airborne equipment, and analog signal is also transported in surveyed airborne equipment accordingly, and multiple switch 1 is connected in parallel on
Together, each how corresponding airborne equipment of the control of switch 1, provides to multiple airborne equipments by a device power supply (DPS) interface 2
Corresponding analog signal, in aircraft in general assembly, ground energization test process of taking a flight test, it is not necessary to multiple airborne equipments of aircraft
Carry out it is individually operated, only need to pull analogue means respective switch on ground, you can for aircraft provides multiple corresponding systems simulation
Signal, and the work load of tester is alleviated, improve the efficiency of aircraft floor energization test.
24 are switched for toggle switch, can be adjusted up and down, and the upper-lower position of toggle switch is respectively provided with an indicator lamp 5, on
One, face is opened for green is represented, below one close for red expression, by toggle switch and indicator lamp setting up and down, behaviour
Make simple, convenient, the state in which of more intuitive observation switch when operating personnel work, both whether analog signal is in conveying
State, prevents operational error.
Analog signal is sent to wheel load, hatchcover, hatch door, undercarriage and hydraulic system respectively, so as to ensure each system energization
That debugs is normally carried out.
1 are switched for button switch, operation of push-button switch is simple.
The debugging panel of cube structure, at work, is easily placed, appearance looks elegant.
Embodiment described above only expresses the specific embodiment of the application, and its description is more specific and detailed, but simultaneously
Therefore the limitation to the application protection domain can not be interpreted as.It should be pointed out that for one of ordinary skill in the art
For, on the premise of technical scheme design is not departed from, various modifications and improvements can be made, these belong to this
The protection domain of application.
Claims (5)
1. a kind of analogue means of aircraft test signal, including test cable interface（1）, device power supply (DPS) interface（2）With debugging face
Plate（3）, it is characterised in that：The debugging panel（3）Upper setting device power supply (DPS) interface（2）With multiple test cable interfaces（1）, institute
State debugging panel（3）On be additionally provided with multiple switch two（4）With switch one（6）, the device power supply (DPS) interface（2）With switch one
（6）It is cascaded by cable, the switch one（6）With multiple switch two（4）It is connected in parallel by cable, it is described
Switch two（4）With test cable interface（1）It is cascaded by cable, the device power supply (DPS) interface（2）With ground power supply
Equipment is connected, the test cable interface（1）On be connected with one end of electric connector, the other end of the electric connector with it is corresponding
Airborne equipment be connected.
2. a kind of analogue means of aircraft test signal as claimed in claim 1, it is characterised in that：The switch two（4）For
Toggle switch, the upper-lower position of the toggle switch is provided with indicator lamp（5）, two indicator lamps of one toggle switch correspondence
（5）, the indicator lamp（5）It is arranged on debugging panel（3）On.
3. a kind of analogue means of aircraft test signal as claimed in claim 1, it is characterised in that：The airborne equipment includes
Wheel load, hatchcover, hatch door, undercarriage and hydraulic system.
4. a kind of analogue means of aircraft test signal as claimed in claim 1, it is characterised in that：The switch one（6）For
Button switch.
5. a kind of analogue means of aircraft test signal as claimed in claim 1 or 2, it is characterised in that：The debugging panel
（3）It is cube structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621234579.9U CN206243509U (en) | 2016-11-17 | 2016-11-17 | A kind of analogue means of aircraft test signal |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621234579.9U CN206243509U (en) | 2016-11-17 | 2016-11-17 | A kind of analogue means of aircraft test signal |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206243509U true CN206243509U (en) | 2017-06-13 |
Family
ID=59001101
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621234579.9U Active CN206243509U (en) | 2016-11-17 | 2016-11-17 | A kind of analogue means of aircraft test signal |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206243509U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108646705A (en) * | 2018-04-16 | 2018-10-12 | 西安飞机工业（集团）有限责任公司 | A kind of airplane ground test interconnection of signals TT＆C system |
| CN109189046A (en) * | 2018-09-03 | 2019-01-11 | 西安飞机工业（集团）有限责任公司 | A kind of large aircraft Mechatronic Systems all-around test stand |
| WO2019036857A1 (en) * | 2017-08-21 | 2019-02-28 | 庄铁铮 | Electronic device, system and method for facilitating debugging |
| CN110018370A (en) * | 2019-03-20 | 2019-07-16 | 成都飞机工业（集团）有限责任公司 | A kind of program-controlled oil mass oil temperature simulator |
| CN110963074A (en) * | 2019-12-25 | 2020-04-07 | 中航贵州飞机有限责任公司 | Unmanned aerial vehicle undercarriage signal simulation system |
| CN111722098A (en) * | 2019-03-18 | 2020-09-29 | 成都飞机工业（集团）有限责任公司 | Portable wheel-mounted switch inspection device |
| CN112009720A (en) * | 2019-05-30 | 2020-12-01 | 中国商用飞机有限责任公司 | Control system of aircraft landing gear and cabin door |
-
2016
- 2016-11-17 CN CN201621234579.9U patent/CN206243509U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019036857A1 (en) * | 2017-08-21 | 2019-02-28 | 庄铁铮 | Electronic device, system and method for facilitating debugging |
| US11531055B2 (en) | 2017-08-21 | 2022-12-20 | Tit Tsang CHONG | Facilitating debugging electronic device, system and method thereof |
| CN108646705A (en) * | 2018-04-16 | 2018-10-12 | 西安飞机工业（集团）有限责任公司 | A kind of airplane ground test interconnection of signals TT＆C system |
| CN109189046A (en) * | 2018-09-03 | 2019-01-11 | 西安飞机工业（集团）有限责任公司 | A kind of large aircraft Mechatronic Systems all-around test stand |
| CN111722098A (en) * | 2019-03-18 | 2020-09-29 | 成都飞机工业（集团）有限责任公司 | Portable wheel-mounted switch inspection device |
| CN110018370A (en) * | 2019-03-20 | 2019-07-16 | 成都飞机工业（集团）有限责任公司 | A kind of program-controlled oil mass oil temperature simulator |
| CN112009720A (en) * | 2019-05-30 | 2020-12-01 | 中国商用飞机有限责任公司 | Control system of aircraft landing gear and cabin door |
| CN110963074A (en) * | 2019-12-25 | 2020-04-07 | 中航贵州飞机有限责任公司 | Unmanned aerial vehicle undercarriage signal simulation system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206243509U (en) | A kind of analogue means of aircraft test signal | |
| CN103925853B (en) | A kind of carrier rocket ground testing system device | |
| CN104297623B (en) | Automatic test system for onboard cable integrity | |
| CN203759532U (en) | Aeroengine general emulator | |
| CN204086955U (en) | Portable multi-protocols dual bus multistage integratedization electromechanical coupling system measure and control device | |
| CN207258013U (en) | A kind of Mini Tele-Copter flight control system in situ detection equipment | |
| CN103048581A (en) | Cable testing device | |
| CN105752359B (en) | A kind of airborne photoelectric gondola detection means | |
| CN106802644A (en) | Vehicle-mounted controller testing system | |
| CN203812422U (en) | Simulated training system for airplane communication equipment | |
| CN205484781U (en) | General open transmitter debugging test system | |
| CN104503259A (en) | Universal programmable aircraft simulator system for launch control system | |
| CN105261254B (en) | A kind of virtual detection teaching platform in kind of long-distance opening aircraft electronic circuit half | |
| CN204856200U (en) | Flexible automatic test system of servo controller | |
| CN204731634U (en) | A kind of aviation landing system performance detection apparatus | |
| CN105913754B (en) | A kind of airborne electronic device circuitry grade Virtual Maintenance teaching platform | |
| CN207148559U (en) | A kind of dynamic simulation experiment of electric power system stage apparatus | |
| CN203720647U (en) | Air data computer testing system | |
| CN106249733A (en) | The method of testing of a kind of airplane antiskid braking control box and system | |
| CN207182084U (en) | A kind of device for being used to test flight control computer | |
| CN106091810B (en) | A kind of four-way MISSILE LAUNCHING time-series rules module | |
| CN203422664U (en) | Undercarriage control and interface assembly testboard | |
| CN108363376A (en) | A kind of Multifunctional battery packet simulating bench and its analogy method suitable for BMS system testings | |
| CN110844114B (en) | Portable aerostat test system | |
| CN107247418A (en) | A kind of dynamic simulation experiment of electric power system stage apparatus |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |