CN208459789U - A kind of amphibious aircraft landing gear folding and unfolding ancillary test device of large size - Google Patents
A kind of amphibious aircraft landing gear folding and unfolding ancillary test device of large size Download PDFInfo
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- CN208459789U CN208459789U CN201721463076.3U CN201721463076U CN208459789U CN 208459789 U CN208459789 U CN 208459789U CN 201721463076 U CN201721463076 U CN 201721463076U CN 208459789 U CN208459789 U CN 208459789U
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- unfolding
- folding
- landing gear
- aircraft landing
- large size
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Abstract
The utility model discloses a kind of amphibious aircraft landing gear folding and unfolding ancillary test devices of large size, including folding and unfolding control system and folding and unfolding display system, the device passes through transit cable, aviation special connector is connect with Aircraft landing gear system, the folding and unfolding control system is controlled by hydraulic buttery valve, and hydraulic buttery valve working signal is simulated using light emitting diode, button switch simulates upper and lower lock signal, and with safe and efficient guarantee undercarriage control debugging efforts and abort situation can be accurately positioned.
Description
Technical field
The utility model relates to Aviation ElctroMechanical testing field, in particular to a kind of amphibious aircraft landing gear of large size is received
Put ancillary test device.
Background technique
Existing marine aircraft does not have undercarriage control function generally, and experimental rig of the present invention is for certain class land and water
The special test equipment of amphibious aircraft development.
Undercarriage control is related to the professions such as hydraulic, electrical, structure.More, control logic complexity is crosslinked between profession, therefore,
The folding and unfolding test of undercarriage belongs to general assembly stage critical process.
Aircraft is supported first and is adjusted horizontal using total system machine debugging by existing undercarriage control experimental technique
State, is undercarriage control stroke reserved space, and ground supplies hydraulic, power supply, passes through the corresponding extension and retraction system electromagnetism of folding and unfolding switch control
Valve work, reaches folding and unfolding test objective.
Since the prior art is long there are the preparatory period, collaborative work amount is big, relationship is complicated, each subsystem is being confirmed whether
Normal condition, i.e. development combined test work, risk is high, and failure should not be checked.It is therefore desirable to develop a kind of auxiliary
Experimental rig, it is independent that each subsystem is tested, each electromagnetic valve work state is simulated, position sensor output signal etc. makes
It can safely and conveniently carry out when carrying out undercarriage control test, improve working efficiency, and abort situation can be accurately positioned.
Utility model content
The technical problem to be solved by the utility model is to provide a kind of amphibious aircraft landing gear folding and unfolding of large size is auxiliary
Experimental rig is helped, with safe and efficient guarantee undercarriage control debugging efforts and abort situation can be accurately positioned, it is existing to solve
Caused above-mentioned defects in technology.
To achieve the above objectives, the present invention provides the following technical solutions:, and a kind of amphibious aircraft of large size rises
Frame folding and unfolding ancillary test device, including folding and unfolding control system and folding and unfolding display system are fallen, for the device by transit cable, aviation is special
It is connect with connector with Aircraft landing gear system, which is controlled by hydraulic buttery valve, and utilizes luminous two
Pole pipe simulates hydraulic buttery valve working signal, and button switch simulates upper and lower lock signal.
Preferably, the control unit of the folding and unfolding control system exports 28V positive electricity, receives solenoid valve, preceding receipts by having led
Solenoid valve, hatch door early period receive solenoid valve, solenoid valve is received in undercarriage delay, drive corresponding LED light to ignite, it was demonstrated that undercarriage on machine
It is normal normally to pack up work-based logic.
Preferably, the folding and unfolding control system control unit export 28V positive electricity, by lead discharge magnet valve, preceding put
Solenoid valve, hatch door early period electric discharge magnet valve, undercarriage delay electric discharge magnet valve, drive corresponding LED light to ignite, it was demonstrated that undercarriage on machine
It is normal normally to put down work-based logic.
Preferably, the folding and unfolding control system further include it is spare put control system, which is exporting 28V just respectively
Electricity drives corresponding LED light by having led spare electric discharge magnet valve, preceding spare electric discharge magnet valve, the spare electric discharge magnet valve of hatch door early period
It ignites, it was demonstrated that spare to put down work-based logic normal for undercarriage on machine.
Preferably, in the control unit of the folding and unfolding display system every two groups of 1-12 to detect signal all the way, press respectively
S1-S6 push switch respectively represents each gear up or down state, at the same in check machine EICAS show in should correspond to
Show every road undercarriage control situation.
It is using the beneficial effect of above technical scheme: the ancillary test device of the utility model structure, by undercarriage system
System decomposes multiple subsystems, proposes debugging solution for each subsystem, improves the work effect of Landing Gear System folding and unfolding test
Rate avoids accessing brought influence between each subsystem, makes systems inspection work more visualization, easy to operateization.
Detailed description of the invention
Fig. 1 is the control figure of the normal folding and unfolding of the utility model；
Fig. 2 is the spare control figure put of the utility model；
Fig. 3 is the control figure of the utility model display system.
Specific embodiment
The preferred embodiment that according to the present invention will be described in detail below with reference to the accompanying drawings.
Fig. 1-Fig. 3 shows specific embodiment of the present utility model: a kind of amphibious aircraft landing gear folding and unfolding of large size
Ancillary test device, including folding and unfolding control system and folding and unfolding display system, the device pass through transit cable, aviation special connector
It is connect with Aircraft landing gear system, which is controlled by hydraulic buttery valve, and is simulated using light emitting diode
Hydraulic buttery valve working signal, button switch simulate upper and lower lock signal.
Normal to receive control: folding and unfolding control switch is placed in receipts on machine, and number 10,8,6,4 of control unit 1 export respectively
28V positive electricity receives solenoid valve (D1), preceding receipts solenoid valve (D3), hatch door early period receipts solenoid valve (D5), undercarriage delay by having led
It receives solenoid valve (D7), drives corresponding LED light to ignite, it was demonstrated that it is normal normally to receive work-based logic for undercarriage on machine.
Normally put control: folding and unfolding control switch, which is placed in, on machine puts down, and number 9,7,5,3 of control unit 1 export respectively
28V positive electricity, by having led electric discharge magnet valve (D2), preceding electric discharge magnet valve (D4), hatch door early period electric discharge magnet valve (D6), undercarriage delay
It discharges magnet valve (D8), drives corresponding LED light to ignite, it was demonstrated that it is normal normally to put down work-based logic for undercarriage on machine.
Spare to put control: spare relieving pass is placed in extended position on machine, and number 5,4,3 of control unit 2 export respectively
28V positive electricity, by having led spare electric discharge magnet valve (D9), preceding spare electric discharge magnet valve (D10), the spare electric discharge magnet valve of hatch door early period
(D11), corresponding LED light is driven to ignite, it was demonstrated that spare to put down work-based logic normal for undercarriage on machine.
Display control: in control unit 3 1~12 every two groups to detect signal all the way, press S1~S6 push type respectively and open
Close, respectively represent each gear up or down state, at the same in check machine EICAS show in should correspond to and show every road undercarriage
Folding and unfolding situation.
The present invention uses aviation special connector, quick-release type interface, Portable machine box, Portable movable suitcase, turns
Connect cable, light emitting diode, push-button switch, 28V power module, fuse (5A).
Interaction: the present invention simulates hydraulic buttery valve working signal using light emitting diode, and button switch simulation is upper and lower
Position lock signal replaces powering on machine using 28V power module, by transit cable, aviation dedicated even machine and undercarriage
System connection.
Above-described is only preferred embodiments of the present invention, it is noted that for the ordinary skill of this field
For personnel, without departing from the concept of the present invention, various modifications and improvements can be made, these all belong to
In the protection scope of the utility model.
Claims (5)
1. a kind of amphibious aircraft landing gear folding and unfolding ancillary test device of large size, which is characterized in that control system including folding and unfolding
System and folding and unfolding display system, the device are connect by transit cable, aviation special connector with Aircraft landing gear system, the folding and unfolding
Control system is controlled by hydraulic buttery valve, and simulates hydraulic buttery valve working signal, button switch using light emitting diode
Simulate upper and lower lock signal.
2. the amphibious aircraft landing gear folding and unfolding ancillary test device of large size according to claim 1, which is characterized in that
The control unit of the folding and unfolding control system exports 28V positive electricity, receives solenoid valve, preceding receipts solenoid valve, hatch door early period by having led
Solenoid valve, undercarriage delay receipts solenoid valve are received, drives corresponding LED light to ignite, it was demonstrated that undercarriage is normally packed up work and patrolled on machine
It collects normal.
3. the amphibious aircraft landing gear folding and unfolding ancillary test device of large size according to claim 1, which is characterized in that
The control unit of the folding and unfolding control system exports 28V positive electricity, by having led electric discharge magnet valve, preceding electric discharge magnet valve, hatch door early period
Discharge magnet valve, undercarriage delay electric discharge magnet valve, drives corresponding LED light to ignite, it was demonstrated that undercarriage normally puts down work and patrols on machine
It collects normal.
4. the amphibious aircraft landing gear folding and unfolding ancillary test device of large size according to claim 1, which is characterized in that
The folding and unfolding control system further include it is spare put control system, which exports 28V positive electricity respectively, by having led spare put
Solenoid valve, preceding spare electric discharge magnet valve, the spare electric discharge magnet valve of hatch door early period, drive corresponding LED light to ignite, it was demonstrated that rise and fall on machine
Frame is spare, and to put down work-based logic normal.
5. the amphibious aircraft landing gear folding and unfolding ancillary test device of large size according to claim 1, which is characterized in that
Every two groups of 1-12 are to detect signal all the way in the control unit of the folding and unfolding display system, press S1-S6 push switch respectively,
Each gear up or down state are respectively represented, while EICAS shows that the every road of display should be corresponded in picture rises and falls in check machine
Frame folding and unfolding situation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721463076.3U CN208459789U (en) | 2017-11-06 | 2017-11-06 | A kind of amphibious aircraft landing gear folding and unfolding ancillary test device of large size |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721463076.3U CN208459789U (en) | 2017-11-06 | 2017-11-06 | A kind of amphibious aircraft landing gear folding and unfolding ancillary test device of large size |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208459789U true CN208459789U (en) | 2019-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201721463076.3U Active CN208459789U (en) | 2017-11-06 | 2017-11-06 | A kind of amphibious aircraft landing gear folding and unfolding ancillary test device of large size |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110626493A (en) * | 2019-10-30 | 2019-12-31 | 中航通飞华南飞机工业有限公司 | Electric retraction control system based on large aircraft landing gear |
| 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 |
| 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 |
-
2017
- 2017-11-06 CN CN201721463076.3U patent/CN208459789U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110626493A (en) * | 2019-10-30 | 2019-12-31 | 中航通飞华南飞机工业有限公司 | Electric retraction control system based on large aircraft landing gear |
| 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 |
| CN110963074B (en) * | 2019-12-25 | 2022-12-09 | 中航贵州飞机有限责任公司 | Unmanned aerial vehicle undercarriage signal simulation system |
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