CN204044310U - Helicopter electronic circuit automatic detection device - Google Patents
Helicopter electronic circuit automatic detection device Download PDFInfo
- Publication number
- CN204044310U CN204044310U CN201420459689.XU CN201420459689U CN204044310U CN 204044310 U CN204044310 U CN 204044310U CN 201420459689 U CN201420459689 U CN 201420459689U CN 204044310 U CN204044310 U CN 204044310U
- Authority
- CN
- China
- Prior art keywords
- module
- signal
- circuit
- matrix switch
- output
- 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 discloses that a kind of efficiency is high, false failure rate is low and can to the helicopter electronic circuit automatic detection device detected fast up to 192 circuits.It comprises ARM11 Embedded System, detection signal and feedback signal amplification circuit module, 4 × 4 matrix switch relays export and load module, the output of matrix switch transmission line and load module and the output that can be connected with helicopter electronic circuit socket and input converting member module and form, and the input end of detection signal amplification circuit module connects with the output terminal of the many waveform modellings signal source in described microprocessor; The output terminal of feedback signal amplification circuit module connects with the input end in the detection signal process authentication data storehouse in described microprocessor.When adopting the utility model device to detect helicopter electronic circuit, test speed is fast, test accuracy rate is high.What it broke traditions differentiates by manual test the situation whether circuit is intact in overhaul and in daily servicing.
Description
Technical field
The utility model relates to a kind of pick-up unit for helicopter, particularly a kind of device of energy fast automatic detecting helicopter electronic circuit.
Background technology
At types such as straight nine type armed helicopters " Z9 type and Z9A (N1) type " and SA365N helicopters after overhaul or in daily servicing, whether intact testing to be carried out to the electronic circuit be arranged on helicopter.
This device characteristic be can by special attachment plug with cable to the flight interphone system, the autopilot system that are arranged on helicopter, communicate, navigation aid systems and course, pitching, control of sideward roll steering wheel, pedal and joystick, whether the operation circuit be connected on helicopter than general switch etc. intact carries out fast automatic test.
Detection method used in prior art adopts to confirm that whether circuit is normal by using universal electric meter measuring circuit loop resistance or audio signal generator to measure audio signal path between the plug of the terminal strip end be arranged on helicopter and installing electronic equipment end, this method of testing, automaticity is low, whether most cases is intact by artificial cognition circuit by manual test, therefore, its detection speed is slow, often produce wiring error in test process, thus cause that test job efficiency is low, the high deficiency of false pass rate.
Summary of the invention
The technical problems to be solved in the utility model is to provide the helicopter electronic circuit automatic detection device that a kind of efficiency is high, false failure rate is low and can detect fast 168 or 192 circuits.
In order to solve the problems of the technologies described above, the technical solution adopted in the utility model is:
Helicopter electronic circuit automatic detection device of the present utility model, comprise casing, be placed in the detection signal generator in casing, this detection signal transferred to the signal circuit of helicopter electronic circuit and helicopter electronic circuit feedback signal reception is transferred to the signal receiving circuit of detector, it is characterized in that: wherein
Described detection signal generator and detector are ARM11 Embedded System;
Described signal circuit is made up of with the output converting member module that can be connected with helicopter electronic circuit socket the detection signal amplification circuit module be connected successively, 4 × 4 matrix switch relay output modules, matrix switch transmission line output module, wherein, the input end of described detection signal amplification circuit module connects with the output terminal of the many waveform modellings signal source in described microprocessor;
Described signal receiving circuit is made up of the input converting member module that can be connected with helicopter electronic circuit socket, matrix switch transmission line load module, 4 × 4 matrix switch relay input modules and the feedback signal amplification circuit module be connected successively, wherein, the output terminal of described feedback signal amplification circuit module connects with the input end in the detection signal process authentication data storehouse in described microprocessor;
The magnification ratio control end of described detection signal amplification circuit module and feedback signal amplification circuit module connects with the Data Control processor in described microprocessor respectively;
The matrix switch control end of described 4 × 4 matrix switch relay output modules and 4 × 4 matrix switch relay input modules connects with the Data Control processor in described microprocessor respectively;
The line strobe control end of described matrix switch transmission line output module and matrix switch transmission line load module connects with the Data Control processor in described microprocessor respectively.
The output terminal of described many waveform modellings signal source is four, is respectively the analog DC voltage output terminal that can control potential change, the sine wave signal output terminal that can control frequency conversion, can controls the triangular signal output terminal of frequency conversion and can control the square-wave signal output terminal of frequency conversion.
Described detection signal amplification circuit module module is identical with the structure of feedback signal amplification circuit module module, and it is made up of rejection gate control circuit, the first code translator, enlargement factor gating circuit and signal amplification circuit, wherein,
Rejection gate control circuit is made up of two OR-NOT circuit arranged side by side, and its input end can be obtained binary coded signal from described Data Control processor and by its output terminal, this binary coded signal is configured to the input end of described first code translator;
First code translator is according to its input end binary coded signal, and selectivity connects branch road corresponding to different amplification in described enlargement factor gating circuit, and the build-out resistor in this branch road is loaded on the enlargement factor control end of described signal amplification circuit;
The instrument amplifier that described signal amplification circuit is INA128 primarily of model is formed, and its signal input part is connected to the output terminal of described many waveform modellings signal source or is connected to the described input converting member module be connected with helicopter electronic circuit socket; Its signal output part is connected to the input end of described 4 × 4 matrix switch relay output modules or is connected to the input end in described detection signal process authentication data storehouse;
The enlargement factor of described signal amplification circuit is 1 times, 2 times, 5 times and 10 times.
Described 4 × 4 matrix switch relay output modules are identical with 4 × 4 matrix switch relay input module structures, and it has four input ends and four output terminals, and each input end is connected with described four output terminals respectively by four different relays.
Described matrix switch transmission line output module is identical with the structure of matrix switch transmission line load module and all have four groups of transmission units, and often organizing transmission unit is 1 select 42 or 1 and select 48 matrix form signal transmssion lines.
Described output converting member module is identical with the structure of input converting member module and all have four bridgewares, and each bridgeware is 50 line standard connector sockets.
The utility model adopts ARM11 Embedded System produce the many waveform modellings signal source needed for detection helicopter electronic circuit and the Data Control processor of the detection signal process authentication data storehouse of being undertaken contrasting by helicopter electronic circuit feedback signal and canonical parameter and the conducting of control signal transmission channel selectivity (if test result is normal, is proceeded next step; If after test and abnormally send alarm signal, and automatically record test failure wire size, afterwards, proceed next step test), when this test makes to adopt the utility model device to detect helicopter electronic circuit, test speed is fast, test accuracy rate is high.It is special after described signal transmission passage adopts scaling signal amplification circuit module of the present utility model, 4 × 4 matrix switch relay module, matrix switch transmission line module, more make that its reliability is high, good stability, and as required many waveform modellings signal can promptly and accurately be switched to arbitrary electronic circuit in up to 192, otherwise, also the feedback signal from 168 or 192 electronic circuits promptly and accurately can be reached in ARM11 detection signal process authentication data storehouse and compare with canonical parameter.
What the utility model broke traditions differentiates by manual test the situation whether circuit is intact in overhaul and in daily servicing, its can to the various function operation circuits of air environment various on helicopter whether intact automatically test and carry out contrast with the normal value being stored in AM11 Embedded System standard setting differentiate, the test result and differentiate relative error value and stored record is got off, when needing printable go out test result carry out fault analysis and judgement.The utility model test process is safe and reliable, and test automation degree is high, and test job efficiency is high.
Accompanying drawing explanation
Fig. 1 is device circuit block scheme of the present utility model.
Fig. 2 is test mode process schematic of the present utility model.
Fig. 3 is signal amplification circuit module principle figure of the present utility model.
Fig. 4 is 4 × 4 matrix switch relay module circuit theory diagrams of the present utility model.
Fig. 5 is the control circuit module principle figure of module in Fig. 4.
Fig. 6 is matrix switch transmission line of the present utility model input (output) module principle figure.
Fig. 7 is profile panel schematic diagram of the present utility model.
Fig. 8 is LED display window schematic diagram in Fig. 7.
Fig. 9 is power unit schematic diagram in Fig. 7.
Figure 10 is key part schematic diagram in Fig. 7.
Figure 11 is LCDs schematic diagram in Fig. 7.
Reference numeral is as follows:
Detection signal amplification circuit module 1,4 × 4 matrix switch relay output module 2, matrix switch transmission line output module 3, export converting member module 4, feedback signal amplification circuit module 5,4 × 4 matrix switch relay input module 6, matrix switch transmission line load module 7, input converting member module 8, test isochronous controller A, signal generator B, signal discriminator C with the input and output conversion port 9 of the tested connection of helicopter, ARM11 Embedded System.
Embodiment
Helicopter electronic circuit automatic detection device of the present utility model be one relate to be applied to the types such as straight nine type armed helicopters " Z9 type and Z9A (N1) type " and SA365N helicopter after overhaul or in daily servicing to being arranged on the whether intact device carrying out detecting fast of electronic circuit on helicopter.
Its feature be can by special attachment plug with cable to the flight interphone system, the autopilot system that are arranged on helicopter, communicate, navigation aid systems and course, pitching, control of sideward roll steering wheel, pedal and joystick, whether the operation circuit be connected on helicopter than general switch etc. intact carries out fast automatic test.
As shown in Figure 1, helicopter electronic circuit automatic detection device of the present utility model is arranged in casing, is provided with ARM11 Embedded System, signal circuit, signal receiving circuit in casing.
Described signal circuit is made up of with the output converting member that can be connected with helicopter electronic circuit socket detection signal amplification circuit module 1,4 × 4 matrix switch relay output module 2 be connected successively, matrix switch transmission line output module 3.
Described signal receiving circuit is made up of the input converting member that can be connected with helicopter electronic circuit socket, matrix switch transmission line load module 7,4 × 4 matrix switch relay input module 6 and the feedback signal amplification circuit module 5 be connected successively.
One, described ARM11 Embedded System, is made up of many waveform modellings signal source, detection signal process authentication data storehouse and Data Control processor three modules.
1, many waveform modellings signal source (also known as signal generator B):
There are four output terminals, export " analog DC voltage of potential change can be controlled " (hereinafter referred to as " d. c. voltage signal ") respectively, " sine wave signal of frequency conversion can be controlled " (hereinafter referred to as " sine wave signal "), " triangular signal of frequency conversion can be controlled " (hereinafter referred to as " triangular signal ") and " can control the square-wave signal of frequency conversion " are (hereinafter referred to as " square-wave signal "), this simulating signal is first after described detection signal amplification circuit module 1 scales up, again through 4 × 4 matrix switch relay output modules 2, matrix switch transmission line output module 3 and described output converting member module 4 export to electronic circuit to be tested on helicopter.Electronic loop is formed by the connection line on helicopter and the signal receiving circuit described in the utility model and detection signal process authentication data storehouse.
2, detection signal process authentication data storehouse (also known as signal discriminator C):
Helicopter electronic circuit is stored when being in serviceable condition, the standard parameter value (also known as normal data) that detection signal should detect after each electronic circuit feedback in this database.
Described many waveform modellings signal through helicopter electronic circuit output terminal, input converting member, matrix switch transmission line load module 7,4 × 4 matrix switch relay input module 6 and feedback signal amplification circuit module 5 again in described signal receiving circuit to this detection signal process authentication data storehouse, after comparing differentiation with the standard parameter value of this database purchase, draw the error ratio detecting data and normal data, differentiate whether this electronic circuit breaks down by the size of this error ratio.
3, Data Control processor (also known as test isochronous controller A):
According to the input of the related key be located on machine shell panel, produce " 1 " or " 0 " low and high level, then produce following control signal:
1) described detection signal amplification circuit module 1 and feedback signal amplification circuit module 5 is made to select corresponding magnification ratio.
2) described 4 × 4 matrix switch relay output module 2 and 4 × 4 matrix switch relay input modules 6 are made to select corresponding signal transmission passage.
3) described matrix switch transmission line output module 3 and matrix switch transmission line load module 7 is made to select corresponding signal transmission passage.
Two, detection signal amplification circuit module 1 identical with feedback signal amplification circuit module 5 structure (" numerical control proportion operational amplifier " namely in Fig. 2), as shown in Figure 3, it is made up of rejection gate control circuit, the first code translator U2, enlargement factor gating circuit and signal amplification circuit, the instrument amplifier that signal amplification circuit is INA128 primarily of model is formed, and the signal input part of this instrument amplifier is connected to the output terminal of described many waveform modellings signal source or is connected to the described input converting member be connected with helicopter electronic circuit socket; Its signal output part is connected to the input end of described 4 × 4 matrix switch relay output modules 2 or is connected to the input end in described detection signal process authentication data storehouse.
The magnification ratio of this signal amplification circuit has four gears, is respectively 1 times, 2 times, 5 times or 10 times.
Described rejection gate control circuit is made up of two OR-NOT circuit arranged side by side, its input end can obtain " 1 " or " 0 " signal from described Data Control processor and produce " 00; 01,10,11 " four binary codings by its output terminal at the input end of described first code translator.
Described first code translator is according to the binary coded signal of its input end, selectivity connects different amplification in described enlargement factor gating circuit corresponding branch road LS1, LS2, LS3, and the build-out resistor R1 in this branch road, R2, R3 are loaded on enlargement factor control end GS1, GS2 of described signal amplification circuit.
Described detection signal amplification circuit module 1, after being amplified by detection signal, is supplied to tested electronic circuit on helicopter and detects use.Wherein, described " d. c. voltage signal " supply lines two ends are directly communicated with, circuit is not through any connection device, the loop detection that directly can form direct current resistance test is used, described " sine wave signal " supply exists in tested circuit to be used using electric capacity or coupling transformer as the line test of isolation coupling, in test, the required height of selected frequency has direct relation with the capacitance value of the inductance value of coupling transformer or coupling capacitance, when " triangular signal " and " square-wave signal " is supplied to and differentiates for the trouble spot needing to carry out circuit in some special environment, the about location of Judging fault point is come with the voltage amplitude value difference that the delay inequality between the square wave forward position of transmitting terminal and loop feedback receiving end and rear edge and triangular wave slope produce.
Described feedback signal amplification circuit module 5, transport to described detection signal process authentication data storehouse after being amplified by the signal-under-test exported by the tested electronic circuit of helicopter, because the processing signals voltage magnitude in detection signal process authentication data storehouse is all at below 3V, so, the signal that this feedback signal amplification circuit module 5 will be sent in detection signal process authentication data storehouse, scaled within the scope of 0-3V, the resistance that this level adjustment work is connected by the instrument amplifier output terminal in described signal amplification circuit is that the resistance R4 (also known as potential divider meter) in 10K Europe has come.
Three, described 4 × 4 matrix switch relay output modules 2 are identical with 4 × 4 matrix switch relay input module 6 (" 4 × 4 matrix control circuit " namely in Fig. 2) structures, as shown in Figure 4, this module has four input ends and four output terminals, and each input end is connected with described four output terminals respectively by four different relays.
Wherein have 16 different relays (i.e. JZ-K1 to JZ-K16).
Relay on-off described in control be control relay circuit, as shown in Figure 5, the input end of this control relay circuit is connected with latch module by the second decoder module, and its output terminal is connected to the control end that described 4 × 4 matrix forms exchange each relay in relay module.
Described control relay circuit is four groups of photoelectric coupling circuits, often organize photoelectric coupling circuit to be made up of four photoelectrical couplers and a driving chip, the input end of four photoelectrical couplers is connected to the output terminal of described second decoder module, its output terminal is connected to the signal input pin of described driving chip, and the output pin of this driving chip is connected to the control end of described relay.16 photoelectrical coupler (i.e. U4A to U4D are had in control relay circuit 3; U5A to U5D; U6A to U6D; U7A to U7D; ) and 4 driving chip (i.e. U8 to U11).
The model of described photoelectrical coupler is TLP621-4; The model of described driving chip is ULN2003A.
Described second decoder module is by second code translator (i.e. U2A, U2B, U3A, U3B) of four groups of two wires to four lines, and the model often organizing the second code translator is the coding chip of 74LS139.Often organize the second code translator and have two wires input end, four line output terminals, input end coding has 00,10,01,11, and it is by the relay work that control four is different respectively of Y0N, Y1N, Y2N, Y3N end.
The model of described latch module is 74HC573.It is 8 bit address latch U1, D0-D7 pin on it is data input pin, Q0-Q7 pin on it is the data output end after latching, Q0-Q7 pin, by controlling the photoelectrical coupler TLP621-4 in photoelectric coupling circuit after the second decoder for decoding, makes the work of driving chip ULN2003A output voltage control relay then.
The function of this module to make any one test point of test port all can be connected with any one analog signal waveform output port of " many waveform modellings signal source ", and any one test point of test port maybe can be made all to be connected with any one analog signal waveform input port in described detection signal process authentication data storehouse.
Four, described matrix switch transmission line output module 3 is identical with the structure of matrix switch transmission line load module 7 all has four groups of transmission units, often organize transmission unit to have 1 and select 48 (or 1 selects 42) bar matrix form signal transmssion line (" 1 × 42 matrix majorization gating circuit " namely in Fig. 2), this module work schematic diagram as indicated with 6.
The function of this module is under the control of described Data Control processor, select every 1 group all can select to be connected 1 with testing apparatus 1 to 48 (or 42) individual test point, namely 4 group of 48 road exchange spot can select 192 test points (or 4 × 42=168 test point) to be connected with testing apparatus.
Five, described output converting member module 4 is identical with the structure of input converting member module 8 all four bridgewares (" 50 line inputs, output port connector " namely in Fig. 2), and each bridgeware is 50 line standard connector sockets.Tested connection on the utility model and aircraft can get up by connecting plug special by it.
Six, the effect (as shown in Figure 2) of other parts.
1) test input socket (" on helicopter electronic equipment attachment plug " namely in Fig. 2) on helicopter, selects the plug of TKR123 very high frequency(VHF) transceiver.
2) the wiring patchcord terminal block (" the upper patchcord terminal strip of helicopter " namely in figure that on helicopter, electronic equipment connects.
3) terminal box on helicopter: for the impedance of sound signal various on helicopter and level match, isolate because there being matching transformer in coupled circuit, so this loop in testing signal source to adopt " sine wave signal ", oscillograph that test side is made up of AM11 microprocessor surveys signal wave amplitude to judge the quality of circuit.
4) the flight interphone system socket (" on helicopter pilot's earphone jack " namely in Fig. 2) of helicopter: be the earphone and microphone socket that on helicopter, flight interphone system connects, need audible communication signal to test.
5) test frames connecting with headphone plug: be the earphone for connecting flight interphone system on helicopter and phono connector, for the tested connection on 50 line test plug ends of described bridgeware and helicopter is got up.
6) output socket tested by helicopter: identical with test input outlet structure on the helicopter in aforementioned " 5) ", selected the plug of the control enclosure of TKR123 VHF radio.
Be below title and the effect (as shown in Figure 7) of each functional unit on the utility model machine shell panel:
As shown in Figure 8, test function selects LED display window:
When certain the LED display window in test function option ignites, namely represent: the test function corresponding with it is the option to be tested of current selected.
Test function option is 10:
1) " instrument control line " option: can itemize again on " Data Control central processing unit " ARM11 Embedded System screen in this option and select to need the installation instrument classification plug receptacle end aboard of test:
Atmosphere data assembly (503HX).
LZ-4A heading system:
Radio magnetic indicator (607HX), EK-14 control enclosure (603HX), QH-1 course coupling mechanism (601HX), TH-14 directional gyro (602HX), GHC-7 Magnetic Sensor (604HX).
Gyro horizon:
Driver H140 gyro horizon (20F), copilot's horizon instrument (21F).
CG130 gyro mag:
Control enclosure (54F), No. 2 gyro mags (50F).
Driver IVA557 radio magnetic indicator (16F); Copilot IVA557 radio magnetic indicator (17F); Driver ZEH-2L horizontal situation indicator (23F).
Radio altimeter system:
High driver shows indicator (103L2), copilot's height indicator indicator (103L1), height indicator transceiver (101L).
Rotor minimax rotating speed is warned:
Rotor minimax rotating speed Warning alarm device (20E), rotor minimax rotating speed detection box (11E), skipper's Revolving-wing Rotation Speed Meter indicator (12E), copilot Revolving-wing Rotation Speed Meter indicator (26E), tachogenerator (31E).
2) " VHF radio station control line " option: can itemize again on " Data Control central processing unit " ARM11 Embedded System screen in this option and select to need the installation VHF radio station control line classification plug receptacle end aboard of test:
TKR123 ultrashort wave radio set: control enclosure (122W), transceiver (121W).
TKR123B ultrashort wave radio set I: control enclosure (132W), transceiver (131W), 30128 cryptos (401W), (101W).
TR800 ultrashort wave radio set: control enclosure (98R), transceiver (97R).
VHF-20 ultrashort wave radio set: control enclosure, transceiver.
VHF-22 ultrashort wave radio set: control enclosure, transceiver.
3) short wave communication control line: can itemize again on " Data Control central processing unit " ARM11 Embedded System screen in this option and select to need the installation short wave communication radio station control line classification plug receptacle end aboard of test:
STR-170F short wave communication radio station: (204W), crypto main frame (207W), crypto main frame (207W) are adjusted in control enclosure (201W), receiver/driver (202W), power amplifier (203W), sky.
HF-220 short-wave single-sideband communication radio station: control enclosure, receiver/driver, power amplifier, sky are adjusted.
HF-230 short-wave single-sideband communication radio station: (58R) is adjusted in control enclosure (55R), receiver/driver (56R), power amplifier (57R), sky.
4), " navigation receives control line ": can itemize again on " Data Control central processing unit " ARM11 Embedded System screen in this option and select to need the installation of test navigation aboard to receive control line classification plug receptacle end:
WL-9 wireless compass: control enclosure (903W), receiver (901W).
JQD-1 direction finder: orientor (701W), SRT651C radio station (101W), oriented control box (703W).
EAS AD851 ADF system: control stand (63R), receiver (107R), tours antenna (61R).
5) " flight interphone control line ": can itemize again on " Data Control central processing unit " ARM11 Embedded System screen in this option and select to need the installation flight interphone Systematical control line classification plug receptacle end aboard of test:
JT-9W flight interphone system: terminal box (22R), driver's main switching control (24R), copilot main switching control (23R), driver's jack (30R), copilot's jack (29R), left front passenger's main switching control (25R).
TEAM TB31 flight interphone system: terminal box (22R), driver's main switching control (24R), copilot main switching control (23R), driver's jack (30R), copilot's jack (29R), left front passenger's main switching control (25R).
6) " control of self-driving computing machine ": can itemize again on " Data Control central processing unit " ARM11 Embedded System screen in this option and select to need the installation self-driving computing machine control line classification plug receptacle end aboard of test:
KJ-13 series self-driving computing machine (16C), SF1M 155D series self-driving computing machine (16C).
7) " coupled computers control ": can itemize again on " Data Control central processing unit " ARM11 Embedded System screen in this option and select to need the installation coupled computers control line classification plug receptacle end aboard of test:
CDV85 coupled computers (17C), SJ-3 coupled computers (17C).
8) " AP control stand control line ": can itemize again on " Data Control central processing unit " ARM11 Embedded System screen in this option and select to need the installation AP control stand control line classification plug receptacle end aboard of test:
KJ13 series A P control stand (18C), SF1M 155D series A P control stand (18C).
9) " coupling control stand controls ": can itemize again on " Data Control central processing unit " ARM11 Embedded System screen in this option and select to need the installation coupling control stand control line classification plug receptacle end aboard of test:
CDV85 coupling mechanism control stand (30C), SJ-3 coupling mechanism control stand (30C).
10) " control of steering wheel amplifier ": can itemize again on " Data Control central processing unit " ARM11 Embedded System screen in this option and select to need the installation steering wheel amplifier control line classification plug receptacle end aboard of test:
KJ13 series steering wheel amplifier (19C), pitching trim steering wheel (21C), pitch control steering wheel (23C), roll handle steering wheel (24C), steering wheel (25C), roll trim steering wheel (27C), directional control steering wheel (26C), course trim steering wheel (22C) are handled in roll;
SF1M 155D series steering wheel amplifier (19C), pitching trim steering wheel (21C), pitch control steering wheel (23C), roll handle steering wheel (24C), steering wheel (25C), roll trim steering wheel (27C), directional control steering wheel (26C), course trim steering wheel (22C) are handled in roll.
Power unit (as shown in Figure 9) in tester panel:
" direct supply input " plug uses when not having 220V electric main during the direct current 28V Power supply on aircraft or in battery truck when being to provide tester operation in the wild and uses.In order to when preventing operation in the wild due to carelessness wrong look the polarity as power supply, input circuit has accessed a bridge rectifier circuit, even if wrong also can not damage tester.
" AC power input " is the socket of access when charge to tester with 220V electric main, and its input power becomes the DC voltage after direct current through Switching Power Supply isolates to merge with 28V direct current input port through isolating diode again and be supplied to tester and use.
" switch on power " when switch control rule testing tool built-in system circuit is started working or closes use and use.
Key part function (as shown in Figure 10):
" system reset "-press this key test macro to reset into initial startup self-detection state, display panel display initial detecting picture.
" test option "-press this key display panel there will be a test function choice menus, at this moment press dexter multiplexing button " upwards ", " downwards " key selects test function, choose rear pressing " test starting " and enter test procedure, in test process, pressing " test is interrupted ", key can interrupt test process.
" test starting "-press after selected test event this key can start test.
Pressing this key in " test is interrupted "-test process can interrupt test.
" upwards, return "-this key is multiplexing key:
1) option bar on display screen can be moved up by this key of pressing when testing option.
2) terminate in test or after pressing " test is interrupted ", press this key and can return previous menu checkout item.
" continue, downwards "--this key is multiplexing key:
1), after pressing in test process " test is interrupted " key has interrupted test process, press this key and make to make test procedure continue to start to test according to the point of interruption.
2) option bar on display screen can be moved down by this key of pressing when testing option.
" left, manually "--this key is multiplexing key.
1) when test function, press this key and icon in test event is offset left.
2) after test option, press this key and test function can be made to proceed to manual detection.
" to the right, automatically "--this key is multiplexing key:
1) when test function, press this key and icon in test event is offset to the right.
2) in manual testing's state, press this key and test function can be made to proceed to automatic detected state.
Three LCDs positions (as shown in figure 11):
Control and the display window of ARM11 Embedded System.
The display screen on the left side is " many waveform modellings signal source " output display.Control D/A changes the voltage exportable described " d. c. voltage signal ", " sine wave signal ", " triangular signal " and " square-wave signal " that output circuit produces.
The display screen on the right is " detection signal process authentication data storehouse " output display.Normal data for detected signal and database purchase compares the error ratio differentiating and detect data and normal data, thus differentiates whether circuit breaks down.
Middle display screen controls and show the equipment and test job state tested.
Claims (6)
1. a helicopter electronic circuit automatic detection device, comprise casing, be placed in the detection signal generator in casing, this detection signal transferred to the signal circuit of helicopter electronic circuit and helicopter electronic circuit feedback signal reception is transferred to the signal receiving circuit of detector, it is characterized in that: wherein
Described detection signal generator and detector are ARM11 Embedded System;
Described signal circuit is made up of with the output converting member module (4) that can be connected with helicopter electronic circuit socket the detection signal amplification circuit module (1) be connected successively, 4 × 4 matrix switch relay output modules (2), matrix switch transmission line output module (3), wherein, the described input end of detection signal amplification circuit module (1) connects with the output terminal of the many waveform modellings signal source in described microprocessor;
Described signal receiving circuit is made up of the input converting member module (8) that can be connected with helicopter electronic circuit socket be connected successively, matrix switch transmission line load module (7), 4 × 4 matrix switch relay input modules (6) and feedback signal amplification circuit module (5), wherein, the output terminal of described feedback signal amplification circuit module (5) connects with the input end in the detection signal process authentication data storehouse in described microprocessor;
The magnification ratio control end of described detection signal amplification circuit module (1) and feedback signal amplification circuit module (5) connects with the Data Control processor in described microprocessor respectively;
The matrix switch control end of described 4 × 4 matrix switch relay output modules (2) and 4 × 4 matrix switch relay input modules (6) connects with the Data Control processor in described microprocessor respectively;
The line strobe control end of described matrix switch transmission line output module (3) and matrix switch transmission line load module (7) connects with the Data Control processor in described microprocessor respectively.
2. helicopter electronic circuit automatic detection device according to claim 1, it is characterized in that: the output terminal of described many waveform modellings signal source is four, be respectively the analog DC voltage output terminal that can control potential change, the sine wave signal output terminal that can control frequency conversion, the triangular signal output terminal of frequency conversion can be controlled and the square-wave signal output terminal of frequency conversion can be controlled.
3. helicopter electronic circuit automatic detection device according to claim 2, it is characterized in that: described detection signal amplification circuit module (1) module is identical with the structure of feedback signal amplification circuit module (5) module, it is made up of rejection gate control circuit, the first code translator, enlargement factor gating circuit and signal amplification circuit, wherein
Rejection gate control circuit is made up of two OR-NOT circuit arranged side by side, and its input end can be obtained binary coded signal from described Data Control processor and by its output terminal, this binary coded signal is configured to the input end of described first code translator;
First code translator is according to its input end binary coded signal, and selectivity connects branch road corresponding to different amplification in described enlargement factor gating circuit, and the build-out resistor in this branch road is loaded on the enlargement factor control end of described signal amplification circuit;
The instrument amplifier that described signal amplification circuit is INA128 primarily of model is formed, and its signal input part is connected to the output terminal of described many waveform modellings signal source or is connected to the described input converting member module (8) be connected with helicopter electronic circuit socket; Its signal output part is connected to the input end of described 4 × 4 matrix switch relay output modules (2) or is connected to the input end in described detection signal process authentication data storehouse;
The enlargement factor of described signal amplification circuit is 1 times, 2 times, 5 times and 10 times.
4. helicopter electronic circuit automatic detection device according to claim 1, it is characterized in that: described 4 × 4 matrix switch relay output modules (2) are identical with 4 × 4 matrix switch relay input module (6) structures, it has four input ends and four output terminals, and each input end is connected with described four output terminals respectively by four different relays.
5. helicopter electronic circuit automatic detection device according to claim 1, it is characterized in that: described matrix switch transmission line output module (3) is identical with the structure of matrix switch transmission line load module (7) and all have four groups of transmission units, often organizing transmission unit is 1 select 42 or 1 and select 48 matrix form signal transmssion lines.
6. the helicopter electronic circuit automatic detection device according to any one of claim 1-5, it is characterized in that: described output converting member module (4) is identical and all have four bridgewares with the structure of input converting member module (8), and each bridgeware is 50 line standard connector sockets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420459689.XU CN204044310U (en) | 2014-08-14 | 2014-08-14 | Helicopter electronic circuit automatic detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420459689.XU CN204044310U (en) | 2014-08-14 | 2014-08-14 | Helicopter electronic circuit automatic detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204044310U true CN204044310U (en) | 2014-12-24 |
Family
ID=52244960
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420459689.XU Active CN204044310U (en) | 2014-08-14 | 2014-08-14 | Helicopter electronic circuit automatic detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204044310U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108398601A (en) * | 2018-05-07 | 2018-08-14 | 上海海鹰机械厂 | Control stick grip comprehensive tester |
| CN108872749A (en) * | 2018-07-02 | 2018-11-23 | 中国民航大学 | A kind of automatic test platform based on the more electric aircraft wirings of simulation |
-
2014
- 2014-08-14 CN CN201420459689.XU patent/CN204044310U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108398601A (en) * | 2018-05-07 | 2018-08-14 | 上海海鹰机械厂 | Control stick grip comprehensive tester |
| CN108398601B (en) * | 2018-05-07 | 2024-04-16 | 上海海鹰机械厂 | Comprehensive tester for steering column handle |
| CN108872749A (en) * | 2018-07-02 | 2018-11-23 | 中国民航大学 | A kind of automatic test platform based on the more electric aircraft wirings of simulation |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104122498B (en) | Photoelectric approach switch motion distance detection system | |
| CN204044310U (en) | Helicopter electronic circuit automatic detection device | |
| CN112034388A (en) | Automatic wire harness detection system and detection method | |
| CN113340323B (en) | Rapid fault positioning method and detection device for inertial sensor | |
| CN108205093B (en) | Cable connection proofreading instrument for engineering construction | |
| CN210212410U (en) | Locomotive signal vehicle-mounted equipment on-board testing device | |
| CN108107346B (en) | STP vehicle-mounted motherboard card detector and motherboard card detection method | |
| CN209813763U (en) | Detection system of battery management system | |
| CN107170187A (en) | High-tension electricity equipment availability vehicle location early warning system and method | |
| CN111204475A (en) | Ground off-position detection device and method for airplane ground proximity warning system | |
| CN203489970U (en) | Electrical test system able to do color detection | |
| CN203714184U (en) | Testing system of navigation device | |
| CN207623467U (en) | STP on-vehicle host board detectors | |
| CN211452697U (en) | Wireless torque detection module | |
| CN106657990A (en) | Mainboard testing equipment and method | |
| CN207741842U (en) | A kind of road administration inspection display system | |
| CN110672264A (en) | Detection system and detection method for pressure sensor of micro-electro-mechanical system | |
| CN111641462A (en) | Interphone, interphone battery and power abnormity detection method | |
| CN107894545B (en) | Intelligent detection method for portable equipment wiring and locomotive signal sensor | |
| JP4416395B2 (en) | Wiring test equipment | |
| CN219957751U (en) | Contact arrangement detection device for electric connector of tractor and trailer | |
| CN104569723A (en) | Multi-station multi-type hybrid wire harness testing method for intelligent wire harness tester | |
| KR20050068376A (en) | Signal measurement system for interfacing current collection apparature in a train | |
| KR0179577B1 (en) | Multi-function current loop to rs232c converter | |
| CN104407263A (en) | Wire harness and temperature sensor detector |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |