CN208156508U - A kind of airplane ground test interconnection of signals case - Google Patents
A kind of airplane ground test interconnection of signals case Download PDFInfo
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- CN208156508U CN208156508U CN201820539407.5U CN201820539407U CN208156508U CN 208156508 U CN208156508 U CN 208156508U CN 201820539407 U CN201820539407 U CN 201820539407U CN 208156508 U CN208156508 U CN 208156508U
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- interconnection
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- signals case
- automatic pilot
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Abstract
A kind of airplane ground test interconnection of signals case,Multiple disconnection terminals are distributed on the front panel of interconnection of signals case,Each disconnection terminal corresponds to a signal of flying instruments or automatic pilot,Ground power supply input interface is equipped on the rear panel of interconnection of signals case,The signaling interface of flying instruments and automatic pilot,Peripheral airborne equipment signaling interface,Above-mentioned disconnection terminal is the connector of a threeway,Disconnection terminal front end interface can be connect with external bus monitoring/emulator,There are two interfaces for disconnection terminal rear end,One of interface is connected with corresponding flying instruments on the rear panel of interconnection of signals case and automatic pilot signaling interface,The peripheral airborne equipment signaling interface connection corresponding on the rear panel of interconnection of signals case of another interface of disconnection terminal rear end,Multiple two-position switch are additionally provided on the front panel of interconnection of signals case,The two-position switch be used to control flying instruments and automatic pilot power on and the input of discrete magnitude.
Description
Technical field
It is specifically a kind of to be directed to airplane ground test this application involves the integration testing and control technology of a kind of multiclass signal
Middle flying instruments and automatic pilot have the interconnection of signals case of the test of OFF signal.
Background technique
In airplane synthetic fire control system, flying instruments is integrated comprehensive display system, is received by display processor
Airborne 60 multiple signals of finished product in periphery, after comprehensive calculation process on flight displays Overlapping display.Automatic pilot is to assist
The stable important system with operating aircraft of driver, the flight control computer of the system receives peripheral 30 multiple signals, through a series of
Output control signal driving steering engine rotation after resolving.
In order to verify the flying instruments of aircraft, the airborne finished product crosslinking interface relationship of automatic pilot and periphery it is whether correct,
Rationally whether logic control relation, whether performance indicator meets installation requires, and is completed at the same time the failure finished product of above-mentioned two system
Reappeared on ground, the work such as troubleshooting positioning, needs to carry out the integrated fire control system comprising above-mentioned two subsystem before installation
Ground surface crosslinking of uniting is tested.
Data interaction is more between flying instruments, each airborne finished product of automatic pilot and periphery, is crosslinked relationship complexity, existing examination
The test method for testing platform is：The cable ends of display processor, flight control computer are provided with hanging plug, all need in periphery
It accesses on hanging plug, completes in ground experiment according to core wire definition after accessing the interim fishing line welding contact pin of computer-internal
Crosslinking between each finished product signal.This method brings certain drawbacks and inconvenience, specifically has：
(1) monitoring of key signal and injection mode are unfriendly.Existing test platform is not provided with monitoring port, if desired
When carrying out failure monitoring or key signal and injecting, can only the existing connecting cable of artificial destruction, access temporary track in parallel and realize letter
Number monitoring and injection.This method safety is poor, serious to restrict test troubleshooting progress, changes the integrated planning of test platform,
It is bad that long-time service will lead to cable contact, influences test effect.
(2) reliability, poor compatibility of existing test platform, does not support the test of different types of machines, can only remake new
The testing requirement of multi-model can just be met by increasing test cable and changing the mode of connection of existing test platform, caused and be produced into
The waste of increase originally and resource.
(3) cable of test platform moves towards disorderly and unsystematic, and the anti-leakage function of interim fishing line junction is poor, improper use
It is also easy to produce the short circuit of signal, there are security risks.And the Operation switch for controlling signal arranges dispersion, is not easy to staff behaviour
Make, causes test troubleshooting working efficiency low.
Summary of the invention
Aiming at the problems existing in the prior art, the signal that the application is designed to provide a kind of airplane ground test is handed over
Join TT&C system and investigating method.
A kind of airplane ground test interconnection of signals case, which is characterized in that be distributed on the front panel of interconnection of signals case
Multiple disconnection terminals, each disconnection terminal corresponds to a signal of flying instruments or automatic pilot, after interconnection of signals case
Panel is equipped with ground power supply input interface, the signaling interface of flying instruments and automatic pilot, peripheral airborne equipment signal and connects
Mouthful, above-mentioned disconnection terminal is the connector of a threeway, and disconnection terminal front end interface can be with external bus monitoring/emulator
Connection, disconnection terminal rear end is there are two interface, one of interface and corresponding flying instruments on the rear panel of interconnection of signals case
It is connected with automatic pilot signaling interface, another interface of disconnection terminal rear end is corresponding on the rear panel of interconnection of signals case
Peripheral airborne equipment signaling interface connects, and is additionally provided with multiple two-position switch on the front panel of interconnection of signals case, which uses
In control flying instruments and automatic pilot power on and the input of discrete magnitude.
In use, the power input interface of interconnection of signals case rear panel is connected with ground power supply, behind interconnection of signals case
The peripheral airborne equipment signaling interface of plate is connected with the signal of multiple external airborne finished products, the flight instrument of interconnection of signals case rear panel
Table and the winged control with the display processor of flying instruments, system change-over panel, automatic pilot respectively of automatic pilot signaling interface
Computer signal is connected, using test cable by the disconnection terminal front end interface of monitoring bus/emulator and interconnection of signals case
It is connected, the observing and controlling of airplane ground test interconnection of signals can be realized.
The beneficial effects of the present application are as follows：A kind of airplane ground test interconnection of signals case that this patent proposes, will fly
The discrete magnitude and bus signals of instrument and automatic pilot periphery crosslinking relationship complexity are integrated in interconnection of signals box house
And adaptation, will need monitor, injection and control signal converting to panel on, and according to type with function carry out taxonomic revision,
In final output to flying instruments finished product plug related to automatic pilot.
Existing test platform is solved because cabling layout caused by interconnection of signals relationship is complicated is unreasonable, improves flight instrument
The experimental condition of table and automatic pilot, is additionally arranged signal monitoring and injection port, realize to discrete signal, bus signals,
The test and control of hundred road signal of power supply Deng Jin, integration degree is high, effectively increases working efficiency, reduces production cost, tool
There are good scalability and compatibility.
The application is described in further detail with reference to embodiments.
Detailed description of the invention
Fig. 1 is interconnection of signals cabinet front panel figure.
Fig. 2 is interconnection of signals cabinet rear panel figure.
Fig. 3 is interconnection of signals cabinet wiring relationship block diagram.
Explanation is numbered in figure：1 flying instruments monitoring with injection unit, 2 disconnection terminals, 3 flying instruments control units,
4DPU1 28V switch, 5DPU2 28V switch, 6 wheel load switch, 7 self-test switch, 8 picture change-over switches, 9DCP change-over switch,
10 specified INS1 switches, 11 specified INS2 switches, 12 specified ADC1 switches, 13 specified ADC2 switches, the monitoring of 14 automatic pilots
It is opened with injection unit, 15 automatic pilot control units, 16AP28V switch, 17AP115V switch, 18AP26V switch, 19 quick-breaks
Pass, 20AP self-test switch, 21AP wheel load switch, 22 power input interfaces, 23 peripheral airborne equipment signaling interfaces, 24 aviations are inserted
Seat, 25 automatic pilot signaling interfaces, 26 flying instruments signaling interfaces, 27 interconnection of signals cabinets.
Specific embodiment
As shown, the left side of the front panel of the airplane ground test interconnection of signals cabinet 27 of the application is multiple disconnections
Flying instruments monitoring and the injection unit 1 that terminal 2 forms, the letter of the corresponding flying instruments of each disconnection terminal of the unit
Number, the flying instruments control unit 3 of multiple two-position switch compositions, the right side of the front panel of interconnection of signals cabinet 27 is multiple disconnections
Automatic pilot monitoring and the injection unit 14 that terminal 2 forms, the corresponding automatic pilot of each disconnection terminal of the unit
Signal, the automatic pilot control unit 15 of multiple two-position switch composition is equipped on the rear panel of interconnection of signals cabinet 27
Ground power supply input interface 22, automatic pilot signaling interface 25, flying instruments signaling interface 26, peripheral airborne equipment signal connect
Mouth 23, above-mentioned disconnection terminal 2 are the connector of a threeway, and disconnection terminal front end interface can be with external bus monitoring/emulation
Equipment connection, disconnection terminal rear end is there are two interface, one of interface and corresponding flight on the rear panel of interconnection of signals case
Instrument signal interface 26 or automatic pilot signaling interface 25 connect, another interface and interconnection of signals case of disconnection terminal rear end
Rear panel on corresponding peripheral airborne equipment signaling interface 23 connect, behind the upper end of above-mentioned two-position switch and interconnection of signals case
Corresponding power input interface 22 connects on plate, the lower end of two-position switch and corresponding flying instruments on interconnection of signals case rear panel
Signaling interface 26 or automatic pilot signaling interface 25 connect.By the disconnection terminal and two-position switch of interconnection of signals case front panel
Side has the silk-screen of corresponding function to identify, and the disconnection terminal with identical silk-screen mark is to be shorted in body interior.
After 27 internal core of interconnection of signals cabinet defines the assembly for completing rear panel and front panel according to core wire, by ground electricity
The power cables such as the direct current+28V in source, direct current GND, exchange+115V, exchange GND, exchange+26V are connected to power input interface 22
Place, by 429 buses, 422 buses, discrete magnitude signal boundling of the airborne finished product in the periphery such as air data computer, inertial navigation, MLS at
Cable is followed by peripheral airborne equipment signaling interface 23.The cable of automatic pilot signaling interface 25 is connected to automatic pilot
Flight control computer at, the cable of flying instruments signaling interface 26 is connected to the display processor and system change-over panel of flying instruments
Place.
Four kinds of operating modes of device are described as follows below with reference to Fig. 1.
Operating mode one：Control model.
In the test of aircraft fire control system ground surface crosslinking, need to provide external supply to flying instruments and automatic pilot first
Electricity verifies installation finished product to the control logic of flying instruments and each working method of automatic pilot, below in fact again after normally powering on
It applies example and describes the operating method of flying instruments and automatic pilot power supply, working method.
When DPU1 28V switch 4, DPU2 28V switch 5 are allocated to "ON" in flying instruments control unit 3,28V is effective,
The power on operation of flying instruments is completed, on the contrary it is electrically operated under completing.
When wheel load switch 6 is allocated to "ON", ground is effective, indicates that aircraft is in the state of ground.Conversely, indicating that aircraft is in aerial
State.
When self-test switch 7 is allocated to "ON", ground is effective, the achievable self-test operations of flying instruments.
When picture change-over switch 8 is allocated to "ON", ground is effective, and MFD, PFD picture for completing flying instruments switch mutually.
When DCP change-over switch 9 is allocated to "ON", ground is effective, the left PFD of No. 2 DCP controls, left MFD, the right PFD of No. 1 DCP control,
Right MFD.Conversely, No. 1 DCP controls left PFD, left MFD, No. 2 DCP control right PFD, right MFD.
Specified INS1 switch 10 or specified INS2 switch 11 is any when being allocated to "ON", ground is effective, and flying instruments or so is shown
Device uses No. 1 or No. 2 sources INS.If specified INS1 switch 10 and specified INS2 switch 11 are allocated to "Off", flying instruments is left
Right display uses No. 1 and No. 2 sources INS respectively.
Specified ADC1 switch 12 or specified ADC2 switch 13 is any when being allocated to "ON", ground is effective, and flying instruments or so is shown
Device uses No. 1 or No. 2 sources ADC.If specified ADC1 switch 12 and specified ADC2 switch 13 are allocated to "Off", flying instruments is left
Right display uses No. 1 and No. 2 sources ADC respectively.
AP28V switch 16, AP115V switch 17, the AP26V switch 18 of automatic pilot control unit 15 are allocated to "ON"
When, automatic pilot power on operation is completed, on the contrary it is electrically operated under completing.
When quick-break switch 19 is allocated to "Off" by "ON", quick-break signal open circuit, for disconnecting automatic pilot.
When AP self-test switch 20 is allocated to "ON", ground is effective, completes automatic pilot self-test operations.
When AP wheel load switch 21 is allocated to "ON", ground is effective, indicates that aircraft is in the state of ground.Conversely, indicating that aircraft is in
Airborne status.
Operating mode two：Monitoring mode.
In order to whether normal in airborne finished product function, performance of laboratory's verifying in addition to flying instruments, automatic pilot,
Reliable basis is provided for troubleshooting, the external cross-linking signal of flying instruments, automatic pilot need to be monitored, be implemented below
Example describes the operating method of signal monitoring.
The monitoring of one end access flying instruments and injection unit 1, automatic pilot monitoring and the injection unit of core wire will be tested
At the front end interface of 14 corresponding disconnection terminals 2, the test core wire other end accesses monitoring bus/emulator, from monitoring bus/imitative
True device-readable takes the state of peripheral airborne equipment and flying instruments, automatic pilot crosslinking signal.
Operating mode three：Compatibility mode.
In order to save production cost, the compatibility of TT&C system is improved, on the basis of existing interconnection of signals case hardware resource
Adaptability change is carried out, the testing requirement of different type of machines can be met, following examples set forth the compatible different machines of TT&C system
The test method of type.
Finished product cable of the original machine type in addition to flying instruments, automatic pilot is disconnected, new architecture is related to the letter of change
Number fishing line access flying instruments monitoring with before injection unit 1 or automatic pilot monitoring disconnection terminal corresponding with injection unit 14
At end interface, that is, complete the replacement of different type of machines test cable, the ground surface crosslinking test of compatible different type of machines.
Operating mode four：Signal injection way.
In fire control system ground experiment, in order to verify the function of flying instruments, automatic pilot the two ready system products
And whether performance is normal, need to inject each class testing signal that monitoring bus/emulator generates to above-mentioned two systems, it is real below
It applies example and describes signal method for implanting.
The flying instruments monitoring that one end access device front panel of core wire will be tested is supervised with injection unit 1 or automatic pilot
It surveys at the front end interface of disconnection terminal corresponding to injection unit 14, the test core wire other end connects monitoring bus/emulator, leads to
Monitoring bus/emulator is crossed to flying instruments or automatic pilot injection test signal, verifies the related function of the two systems
Energy.
Claims (2)
1. a kind of airplane ground test interconnection of signals case, which is characterized in that be distributed on the front panel of interconnection of signals case more
A disconnection terminal, each disconnection terminal corresponds to a signal of flying instruments or automatic pilot, behind interconnection of signals case
Plate is equipped with ground power supply input interface, the signaling interface of flying instruments and automatic pilot, peripheral airborne equipment signaling interface,
Above-mentioned disconnection terminal is the connector of a threeway, and disconnection terminal front end interface can connect with external bus monitoring/emulator
Connect, disconnection terminal rear end there are two interface, one of interface and corresponding flying instruments on the rear panel of interconnection of signals case and
The connection of automatic pilot signaling interface, another interface of disconnection terminal rear end are corresponding on the rear panel of interconnection of signals case outer
Enclose the connection of airborne equipment signaling interface, be additionally provided with multiple two-position switch on the front panel of interconnection of signals case, the two-position switch it is upper
End is connected with power input interface corresponding on interconnection of signals case rear panel, the lower end of two-position switch and interconnection of signals case rear panel
Upper corresponding flying instruments or the connection of automatic pilot signaling interface.
2. airplane ground test as described in claim 1 interconnection of signals case, which is characterized in that in interconnection of signals case front panel
Disconnection terminal and two-position switch beside have corresponding function silk-screen identify, and with identical silk-screen mark disconnection terminal exist
Body interior is to be shorted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820539407.5U CN208156508U (en) | 2018-04-16 | 2018-04-16 | A kind of airplane ground test interconnection of signals case |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820539407.5U CN208156508U (en) | 2018-04-16 | 2018-04-16 | A kind of airplane ground test interconnection of signals case |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208156508U true CN208156508U (en) | 2018-11-27 |
Family
ID=64378156
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820539407.5U Active CN208156508U (en) | 2018-04-16 | 2018-04-16 | A kind of airplane ground test interconnection of signals case |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208156508U (en) |
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2018
- 2018-04-16 CN CN201820539407.5U patent/CN208156508U/en active Active
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