CN204044310U - Helicopter electronic circuit automatic detection device - Google Patents
Helicopter electronic circuit automatic detection device Download PDFInfo
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- 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
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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 detection device for helicopter, in particular to can quick automated inspection helicopter electronic circuit's device.
Background
After overhaul or in daily maintenance of the helicopter models such as the straight nine armed helicopter model Z9 and Z9A (N1) and the SA365N helicopter, the electronic circuit mounted on the helicopter needs to be detected to be in good condition.
The device is characterized in that a special connecting plug and a cable can be used for quickly and automatically testing whether a built-in communication system, an autopilot system, a communication and navigation equipment system, a course, pitching and rolling control steering engine, a pedal plate, a control handle, a Bipu switch and other control circuits connected on the helicopter are intact or not.
The detection method used in the prior art is to use a universal meter to measure the loop resistance of a line or an audio signal generator to measure an audio signal path between a terminal board end installed on a helicopter and a plug installed on an electronic equipment end to confirm whether the line is normal or not.
Disclosure of Invention
The to-be-solved technical problem of the utility model is to provide an efficient, the misdetection rate is low and can be to 168 or 192 line short-term test's helicopter electronic circuit automatic checkout device.
In order to solve the technical problem, the utility model discloses a technical scheme be:
the utility model discloses a helicopter electronic circuit automatic checkout device, including the casing, arrange the detection signal generator in the casing in, with this detection signal transmission to helicopter electronic circuit's signal transmission circuit and with helicopter electronic circuit feedback signal reception and transmit the signal reception circuit to the detector, its characterized in that: wherein,
the detection signal generator and the detector are ARM11 embedded microprocessors;
the signal transmission circuit consists of a detection signal amplifying circuit module, a 4 multiplied by 4 matrix exchange relay output module, a matrix exchange transmission line output module and an output conversion component module which can be connected with a helicopter electronic circuit socket, wherein the input end of the detection signal amplifying circuit module is connected with the output end of a multi-waveform analog signal source in the microprocessor;
the signal receiving circuit consists of an input conversion component module, a matrix exchange transmission line input module, a 4 x 4 matrix exchange relay input module and a feedback signal amplifying circuit module which are sequentially connected and can be connected with a helicopter electronic circuit socket, wherein the output end of the feedback signal amplifying circuit module is connected with the input end of a detection signal processing and identifying database in the microprocessor;
the amplification ratio control ends of the detection signal amplification circuit module and the feedback signal amplification circuit module are respectively connected with a data control processor in the microprocessor;
the matrix exchange control ends of the 4 x 4 matrix exchange relay output module and the 4 x 4 matrix exchange relay input module are respectively connected with a data control processor in the microprocessor;
and the line gating control ends of the matrix exchange transmission line output module and the matrix exchange transmission line input module are respectively connected with a data control processor in the microprocessor.
The output ends of the multi-waveform analog signal source are four, namely an analog direct-current voltage output end capable of controlling potential change, a sine wave signal output end capable of controlling frequency conversion, a triangular wave signal output end capable of controlling frequency conversion and a rectangular wave signal output end capable of controlling frequency conversion.
The detection signal amplification circuit module and the feedback signal amplification circuit module have the same structure and are composed of a NOR gate control circuit, a first decoder, an amplification factor gating circuit and a signal amplification circuit, wherein,
the NOR gate control circuit consists of two parallel NOR gate circuits, the input end of the NOR gate circuit can obtain a binary code signal from the data control processor and the binary code signal is configured to the input end of the first decoder through the output end of the NOR gate circuit;
the first decoder selectively switches on the branches corresponding to different amplification factors in the amplification factor gating circuit according to the binary coded signal at the input end of the first decoder, and loads the matching resistor in the branch to the amplification factor control end of the signal amplification circuit;
the signal amplification circuit mainly comprises an instrument amplifier with the model number of INA128, and the signal input end of the signal amplification circuit is connected with the output end of the multi-waveform analog signal source or connected with the input conversion component module connected with a helicopter electronic circuit socket; the signal output end of the detection signal processing and identifying module is connected with the input end of the 4 multiplied by 4 matrix switching relay output module or the input end of the detection signal processing and identifying database;
the amplification factor of the signal amplification circuit is 1 time, 2 times, 5 times and 10 times.
The output module of the 4 x 4 matrix switching relay and the input module of the 4 x 4 matrix switching relay have the same structure, and are provided with four input ends and four output ends, and each input end is respectively connected with the four output ends through four different relays.
The matrix exchange transmission line output module and the matrix exchange transmission line input module have the same structure and are provided with four groups of transmission units, and each group of transmission units are matrix signal transmission lines with 42 or 48 matrix signal transmission lines selected from 1.
The output conversion component module and the input conversion component module have the same structure and are respectively provided with four conversion pieces, and each conversion piece is a 50-wire standard connection socket.
The utility model discloses a ARM11 embedded microprocessor produces the required multi-waveform analog signal source of detection helicopter electronic circuit, and will carry out the data control treater that the detection signal processing who contrasts distinguishes database and control signal transmission channel selectivity and switches on by helicopter electronic circuit feedback signal and standard parameter (if the test result is normal, continue to carry on next step, if compare back test abnormal alarm signal that sends to automatic recording test fault line number, later, continue to carry out test on next step), this test makes the adoption the utility model discloses the device examines time measuring to helicopter electronic circuit, and testing speed is fast, the test rate of accuracy is high. Particularly signal transmission passageway adopts the utility model discloses a behind proportional signal amplifier circuit module, 4X 4 matrix switching relay module, the matrix switching transmission line module, more make its reliability high, stability good, can in time accurately switch many wave forms analog signal to reaching arbitrary electronic circuit in 192 as required moreover, otherwise, also can in time accurately reach ARM11 detection signal processing identification database with standard parameter comparison with the feedback signal that comes from 168 or 192 electronic circuit.
The utility model discloses break the tradition and differentiate whether intact situation of circuit through manual test in overhaul and routine maintenance, it can go up various airborne electronic equipment's on the helicopter various function control circuit whether intact automatic test and compare the judgement with the normal value of storage at the embedded microprocessor standard setting of AM11 to the storage record gets off the test result and differentiates the comparative error value, and printable test result carries out failure analysis and judgement when needing. The utility model discloses test process safe and reliable, test degree of automation is high, and test work efficiency is high.
Drawings
Fig. 1 is a circuit block diagram of the apparatus of the present invention.
Fig. 2 is a schematic view of the testing process of the present invention.
Fig. 3 is a schematic diagram of a signal amplification circuit module according to the present invention.
Fig. 4 is a schematic circuit diagram of a 4 × 4 matrix switching relay module according to the present invention.
Fig. 5 is a block diagram of a control circuit of the block of fig. 4.
Fig. 6 is a schematic diagram of the input (output) module of the matrix switching transmission line of the present invention.
Fig. 7 is a schematic view of the appearance panel of the present invention.
Fig. 8 is a schematic view of the LED lamp display window in fig. 7.
Fig. 9 is a schematic diagram of a portion of the power supply of fig. 7.
Fig. 10 is a schematic view of a key portion of fig. 7.
Fig. 11 is a schematic view of the liquid crystal display panel of fig. 7.
The reference numbers are as follows:
the test signal amplification circuit comprises a detection signal amplification circuit module 1, a 4 x 4 matrix exchange relay output module 2, a matrix exchange transmission line output module 3, an output conversion component module 4, a feedback signal amplification circuit module 5, a 4 x 4 matrix exchange relay input module 6, a matrix exchange transmission line input module 7, an input conversion component module 8, an input and output conversion port 9 connected with a tested line of the helicopter, an ARM11 embedded microprocessor test synchronization controller A, a signal generator B and a signal discriminator C.
Detailed Description
The utility model discloses a helicopter electronic circuit automatic checkout device relates to and is applied to and directly does not carry out the device of short-term test to installing electronic circuit on the helicopter in models such as nine type armed helicopters "Z9 type and Z9A (N1) type" and SA365N helicopter in the overhaul back or in daily maintenance.
The automatic test system is characterized in that whether control circuits connected with a helicopter, such as a built-in call system, an autopilot system, a communication and navigation equipment system, a course, pitching and rolling control steering engine, a pedal plate, a control handle, a Bipu switch and the like, which are arranged on the helicopter are intact can be quickly and automatically tested through a special connecting plug and a cable.
As shown in figure 1, the automatic detection device for helicopter electronic circuits of the utility model is installed in a casing, and an ARM11 embedded microprocessor, a signal transmission circuit and a signal receiving circuit are arranged in the casing.
The signal transmission circuit consists of a detection signal amplifying circuit module 1, a 4 x 4 matrix exchange relay output module 2, a matrix exchange transmission line output module 3 and an output conversion component which are connected in sequence and can be connected with a helicopter electronic circuit socket.
The signal receiving circuit consists of an input conversion component, a matrix exchange transmission line input module 7, a 4 x 4 matrix exchange relay input module 6 and a feedback signal amplifying circuit module 5 which are connected in sequence and can be connected with a helicopter electronic circuit socket.
The ARM11 embedded microprocessor consists of three modules, namely a multi-waveform analog signal source, a detection signal processing and identifying database and a data control processor.
1. Multi-waveform analog signal source (also called signal generator B):
the analog signal is firstly amplified in proportion by the detection signal amplifying circuit module 1 and then output to an electronic circuit to be tested on the helicopter through the 4 x 4 matrix exchange relay output module 2, the matrix exchange transmission line output module 3 and the output conversion component module 4. Through interconnecting link on the helicopter with the utility model discloses in signal reception circuit and detection signal process distinguish the database and constitute electronic circuit.
2. Detection signal processing discrimination database (also called signal discriminator C):
the database stores standard parameter values (also called standard data) which should be detected after the detection signals are fed back by each electronic circuit when the helicopter electronic circuits are in a perfect state.
The multi-waveform analog signal is transmitted to the detection signal processing and identifying database through the output end of a helicopter electronic circuit, an input conversion component in the signal receiving circuit, a matrix exchange transmission line input module 7, a 4 x 4 matrix exchange relay input module 6 and a feedback signal amplifying circuit module 5, and is compared and judged with standard parameter values stored in the database to obtain the error ratio of the detection data to the standard data, and whether the electronic circuit has a fault is judged according to the error ratio.
3. Data control processor (also called test synchronization controller a):
according to the input of the relevant key arranged on the panel of the shell, the high and low levels of '1' or '0' are generated, and then the following control signals are generated:
1) and enabling the detection signal amplification circuit module 1 and the feedback signal amplification circuit module 5 to select corresponding amplification ratios.
2) And enabling the 4 x 4 matrix switching relay output module 2 and the 4 x 4 matrix switching relay input module 6 to select corresponding signal transmission channels.
3) The matrix exchange transmission line output module 3 and the matrix exchange transmission line input module 7 are enabled to select corresponding signal transmission channels.
The detection signal amplification circuit module 1 and the feedback signal amplification circuit module 5 have the same structure (i.e. the "numerical control proportional operational amplifier" in fig. 2), and as shown in fig. 3, the detection signal amplification circuit module is composed of a nor gate control circuit, a first decoder U2, an amplification factor gating circuit and a signal amplification circuit, the signal amplification circuit is mainly composed of an instrumentation amplifier with the model number INA128, and the signal input end of the instrumentation amplifier is connected to the output end of the multi-waveform analog signal source or to the input conversion component connected to the helicopter electronic circuit socket; the signal output end is connected with the input end of the 4 multiplied by 4 matrix exchange relay output module 2 or the input end of the detection signal processing and identifying database.
The amplification ratio of the signal amplification circuit has four gears which are respectively 1 time, 2 times, 5 times or 10 times.
The nor gate control circuit consists of two parallel nor gates, the input end of which can obtain a '1' or '0' signal from the data control processor and generate four binary codes of '00, 01, 10, 11' at the input end of the first decoder through the output end of the nor gate control circuit.
The first decoder selectively switches on branches LS1, LS2 and LS3 corresponding to different amplification factors in the amplification factor gating circuit according to binary coded signals at the input end of the first decoder, and loads matching resistors R1, R2 and R3 in the branches to amplification factor control ends GS1 and GS2 of the signal amplification circuit.
And the detection signal amplifying circuit module 1 amplifies the detection signal and provides the amplified detection signal for detection of a tested electronic circuit on the helicopter. The 'direct current voltage signal' supply circuit is directly communicated with two ends, the circuit is not provided with any connecting equipment, the circuit can be directly used for loop detection of direct current resistance test, the 'sine wave signal' is supplied for circuit test with a capacitor or a coupling transformer as isolation coupling in a tested circuit, the height of the selected frequency required in the test has a direct relation with the inductance value of the coupling transformer or the capacitance value of the coupling capacitor, and the 'triangular wave signal' and the 'rectangular wave signal' are provided for judging the approximate position of a fault point by using the delay difference between the leading edge and the trailing edge of a rectangular wave of a transmitting end and a loop feedback receiving end and the voltage amplitude difference generated by the slope of the triangular wave when the fault point of the circuit needs to be judged in some special environments.
The feedback signal amplifying circuit module 5 amplifies the tested signals output by the tested electronic circuit of the helicopter and then outputs the amplified signals to the detection signal processing and identifying database, and because the processing signal voltage amplitudes of the detection signal processing and identifying database are all below 3V, the feedback signal amplifying circuit module 5 proportionally reduces the signals sent to the detection signal processing and identifying database to be within the range of 0-3V, and the level adjustment work is completed by a resistor R4 (also called a potential divider) with the resistance value of 10K ohm, which is connected with the output end of an instrument amplifier in the signal amplifying circuit.
And the 4 × 4 matrix switching relay output module 2 and the 4 × 4 matrix switching relay input module 6 (i.e. the "4 × 4 matrix control circuit" in fig. 2) have the same structure, and as shown in fig. 4, the module has four input terminals and four output terminals, and each input terminal is connected to the four output terminals through four different relays.
There are 16 different relays (i.e., JZ-K1 through JZ-K16).
The relay is controlled to be switched on and off by a relay control circuit, as shown in fig. 5, the input end of the relay control circuit is connected with the latch module through a second decoder module, and the output end of the relay control circuit is connected with the control end of each relay in the 4 x 4 matrix type exchange relay module.
The relay control circuit is four groups of photoelectric coupling circuits, each group of photoelectric coupling circuit is composed of four photoelectric couplers and a driving chip, the input ends of the four photoelectric couplers are connected with the output end of the second decoder module, the output ends of the four photoelectric couplers are connected with the signal input pin of the driving chip, and the output pin of the driving chip is connected with the control end of the relay. The relay control circuit 3 has 16 photocouplers (i.e., U4A to U4D; U5A to U5D; U6A to U6D; U7A to U7D) and 4 driver chips (i.e., U8 to U11).
The model of the photoelectric coupler is TLP 621-4; the model of the driving chip is ULN 2003A.
The second decoder module consists of four sets of two-to-four wire second decoders (i.e., U2A, U2B, U3A, U3B), each set of second decoders having a decoding chip size of 74LS 139. Each group of second decoder has two-wire input end and four-wire output end, and the input end codes are 00, 10, 01 and 11, and can respectively control four different relays to work through Y0N, Y1N, Y2N and Y3N ends.
The latch module is of type 74HC 573. The driving circuit is an 8-bit address latch U1, pins D0-D7 on the driving circuit are data input ends, pins Q0-Q7 on the driving circuit are latched data output ends, and pins Q0-Q7 are decoded by a second decoder and then control a photoelectric coupler TLP621-4 in a photoelectric coupling circuit, so that a voltage control relay of a driving chip ULN2003A works.
The function of the module is that any test point of the test port can be connected with any analog signal waveform output port of the multi-waveform analog signal source, or any test point of the test port can be connected with any analog signal waveform input port of the detection signal processing identification database.
The matrix switching transmission line output module 3 and the matrix switching transmission line input module 7 have the same structure and are respectively provided with four groups of transmission units, each group of transmission units is provided with 1 to 48 (or 1 to 42) matrix signal transmission lines (namely, a '1 x 42 matrix control gating circuit' in fig. 2), and the working principle diagram of the module is shown as 6.
The function of the module is that under the control of the data control processor, every 1 group of 48 (or 42) test points can be selected to be connected with 1 to 1 test equipment, and 4 groups of 48 circuit switching points can be selected to be connected with 192 test points (or 4 × 42 ═ 168 test points) to be connected with the test equipment.
And fifthly, the output conversion component module 4 and the input conversion component module 8 have the same structure and are respectively provided with four conversion parts (namely, 50-wire input and output port connectors in fig. 2), and each conversion part is a 50-wire standard connection socket. It can be through connecting special plug will the utility model discloses get up with the on-plane tested circuit connection.
And sixthly, the functions of other components (shown in figure 2).
1) The test input socket on the helicopter (i.e., "electronic equipment connecting plug on helicopter" in fig. 2) selects the plug of the TKR123 vhf transceiver.
2) A wiring patch terminal block (i.e., "helicopter upper relay terminal block" in the figure) to which the electronic devices on the helicopter are connected.
3) A terminal box is arranged on the helicopter: the circuit is used for matching the impedance and the level of various audio signals on the helicopter, and because a matching transformer is isolated in a coupling circuit, a signal source of the circuit needs to adopt a sine wave signal during testing, and a detection end judges the quality of the circuit by the amplitude of a signal measured by an oscilloscope formed by an AM11 microprocessor.
4) Intercom system jack of helicopter (i.e. "pilot on helicopter headset jack" in fig. 2): the audio frequency alternating current testing device is an earphone and microphone jack connected with a communication system in a helicopter and needs an audio frequency alternating current signal for testing.
5) The test is with connecting earphone plug: the plug is used for connecting an earphone and a microphone plug of a communication system in a helicopter, and is used for connecting a 50-wire detection plug end of the conversion piece with a tested line on the helicopter.
6) Test output socket on the helicopter: the test input socket structure of the helicopter in the '5)' is the same as that of the test input socket structure of the helicopter, and the plug of the control box of the TKR123 VHF station is selected.
The names and functions of the operation components on the panel of the casing of the present invention are as follows (as shown in fig. 7):
as shown in fig. 8, the test function selects the LED lamp display window:
when a certain LED lamp display window in the test function option is lighted, the following conditions are indicated: the corresponding test function is the currently selected option to be tested.
The test function options are 10:
1) "aircraft instrument control line" option: within this option, the interface end of the type of aircraft instrument installed on the aircraft to be tested can be selected in a sub-item on the screen of a "data control central processor" ARM11 embedded microprocessor:
an atmospheric data component (503 HX).
LZ-4A course system:
a wireless electromagnetic indicator (607HX), an EK-14 control box (603HX), a QH-1 course coupler (601HX), a TH-14 course gyro (602HX), and a GHC-7 magnetic sensor (604 HX).
A gyrodipine:
a gyroscope horizon (20F) for the driver H140 and a horizon (21F) for the co-driver.
CG130 gyromagnetic compass:
a control box (54F) and a No. 2 gyro magnetic compass (50F).
A driver IVA557 wireless electromagnetic indicator (16F); a secondary driver IVA557 wireless electromagnetic indicator (17F); a driver ZEH-2L horizontal position indicator (23F).
Radio altimeter system:
a driver altimeter indicator (103L2), a co-driver altimeter indicator (103L1), and an altimeter transceiver (101L).
Rotor maximum minimum speed warning:
the rotary wing maximum and minimum rotating speed warning alarm device (20E), the rotary wing maximum and minimum rotating speed detection box (11E), a forward-driving rotary wing tachometer indicator (12E), a copilot rotary wing tachometer indicator (26E) and a tachometer sensor (31E).
2) "VHF station control line" option: within this option, the interface of the category of the VHF station control line installed on the aircraft to be tested can be selected in a sub-item on the screen of the "data control central processor" ARM11 embedded microprocessor:
TKR123 ultrashort wave radio: a control box (122W) and a transceiver (121W).
TKR123B ultrashort wave radio station I: a control box (132W), a transceiver (131W), a 30128 security machine (401W) and (101W).
TR800 ultrashort wave radio station: a control box (98R), a transceiver (97R).
VHF-20 ultrashort wave radio station: control box, transceiver.
VHF-22 ultrashort wave radio station: control box, transceiver.
3) Short-wave communication control line: in the option, the interface terminal of the short wave communication station control line category which needs to be tested and is installed on the airplane can be selected in a sub-item on a screen of a data control central processing unit ARM11 embedded microprocessor:
STR-170F short-wave communication station: a control box (201W), a receiver/exciter (202W), a power amplifier (203W), a weather regulator (204W), a crypto main unit (207W) and a crypto main unit (207W).
HF-220 short wave single sideband communication station: control box, receiver/exciter, power amplifier and antenna.
HF-230 short-wave single-sideband communication station: a control box (55R), a receiver/exciter (56R), a power amplifier (57R) and a sky tone (58R).
4) "navigation reception control line": within this option, the interface terminal of the type of the navigation reception control line installed on the airplane to be tested can be selected in a sub-item on the screen of a 'data control central processor' ARM11 embedded microprocessor:
WL-9 radio compass: a control box (903W) and a receiver (901W).
JQD-1 orientation apparatus: the device comprises an orientator (701W), an SRT651C radio station (101W) and an orientation control box (703W).
EAS AD851 ADF system: a console (63R), a receiver (107R), and a loop antenna (61R).
5) "call control line inside" includes: within this option, the interface of the type of control line of the airplane-mounted intercom system to be tested can be selected in a sub-item on the screen of the "data control central processor" ARM11 embedded microprocessor:
JT-9W built-in communication system: the vehicle-mounted front passenger control system comprises a junction box (22R), a driver main control switch (24R), a secondary driver main control switch (23R), a driver jack (30R), a secondary driver jack (29R) and a left front passenger main control switch (25R).
TEAM TB31 built-in call system: the vehicle-mounted front passenger control system comprises a junction box (22R), a driver main control switch (24R), a secondary driver main control switch (23R), a driver jack (30R), a secondary driver jack (29R) and a left front passenger main control switch (25R).
6) "self-driving computer control": within this option, the interface of the type of control line of the self-driving computer installed on the airplane to be tested can be selected in a sub-item on the screen of a 'data control central processor' ARM11 embedded microprocessor:
a self-driving computer (16C) of KJ-13 series and a self-driving computer (16C) of SF1M 155D series.
7) "coupled computer control": within this option, the interface of the category of control lines of the coupled computer installed on the aircraft to be tested can be selected in a sub-item on the screen of the "data control central processor" ARM11 embedded microprocessor:
CDV85 couples computer (17C), SJ-3 couples computer (17C).
8) "AP console control line": within this option, the interface of the type of control line of the AP console installed on the aircraft to be tested can be selected in a sub-selection on the screen of the "data control central processor" ARM11 embedded microprocessor:
KJ13 series AP console (18C), SF1M 155D series AP console (18C).
9) "coupling console control": within this option, the interface of the type of control line of the coupling control console installed on the aircraft to be tested can be selected in a sub-item on the screen of a "data control central processor" ARM11 embedded microprocessor:
CDV85 coupler console (30C), SJ-3 coupler console (30C).
10) "steering engine amplifier control": in the option, the interface end of the control line category of the steering engine amplifier which needs to be tested and is installed on the airplane can be selected in a sub-item on a screen of a data control central processing unit ARM11 embedded microprocessor:
a KJ13 series steering engine amplifier (19C), a pitching balancing steering engine (21C), a pitching steering engine (23C), a rolling steering engine (24C), a rolling steering engine (25C), a rolling balancing steering engine (27C), a course steering engine (26C) and a course balancing steering engine (22C);
SF1M 155D series steering engine amplifier (19C), pitching trim steering engine (21C), pitching steering engine (23C), rolling steering engine (24C), rolling steering engine (25C), rolling trim steering engine (27C), course steering engine (26C) and course trim steering engine (22C).
Power supply section in tester panel (as shown in fig. 9):
the 'direct current power supply input' plug is used for supplying power to the tester by using a direct current 28V power supply on an airplane or a battery car under the condition of no 220V alternating current commercial power during field operation. In order to prevent the polarity of a power supply from being mistakenly connected during field operation, a bridge rectifier circuit is connected to an input circuit, and the tester cannot be damaged even if the input circuit is mistakenly connected.
The 'AC power supply input' is a socket accessed when 220V AC commercial power is used for charging the tester, and the DC voltage of the input power supply of the tester after being converted into DC voltage by a switching power supply is isolated by an isolation diode and then is combined with a 28V DC input port to be supplied to the tester for use.
The power-on switch controls the internal system circuit of the test instrument to start working or be used when the test instrument is closed.
Key part function (as shown in fig. 10):
the system is reset, the system is tested to be reset to an initial power-on self-test state by pressing the key, and the display panel displays an initial detection picture.
The 'test option' -pressing the key display panel can generate a test function selection menu, at this time, the 'up' key and the 'down' key on the right hand side are pressed to select the test function, after the selection is finished, the 'test start' key is pressed to enter a test program, and the 'test interrupt' key is pressed in the test process to interrupt the test process.
"test Start" -pressing this key after the test item is selected can initiate the test.
"test interrupt" -pressing this key during the test can interrupt the test.
"Up, Back" -this key is a multiplex key:
1) the item indicator bar on the display screen can be moved upwards by pressing the key when testing the item.
2) After the test is over or "test interrupt" is pressed, pressing this key may return to the previous level menu to check for test items.
"continue, down" - - -this key is a multiplex key:
1) after the test process is interrupted by pressing the 'test interrupt' key in the test process, the test program can be continuously tested according to the interrupt point by pressing the key.
2) The item indicator bar on the display screen can be moved downwards by pressing the key when testing the item.
"left, artificial" - - -this key is a multiplex key.
1) Pressing this key shifts the icon in the test item to the left while testing functions.
2) After the test option, pressing this key may cause the test function to go to manual testing.
"right, auto" - - -this key is a multiplex key:
1) pressing this key shifts the icons in the test item to the right while testing the function.
2) In the manual test state, pressing the key can cause the test function to be switched to the automatic test state.
Three liquid crystal display positions (as shown in fig. 11):
is the control and display window of an ARM11 embedded microprocessor.
The display screen on the left outputs and displays the multi-waveform analog signal source. The voltage generated by the D/A conversion output circuit can be controlled to output the direct current voltage signal, the sine wave signal, the triangular wave signal and the rectangular wave signal.
The display screen on the right side outputs and displays the detection signal processing and identification database. The error ratio of the detected data and the standard data is judged by comparing the detected signal with the standard data stored in the database, so that whether the line has a fault or not is judged.
The middle display screen is used for controlling and displaying the tested equipment and the test working state.
Claims (6)
1. An automatic detection device for helicopter electronic circuits, which comprises a shell, a detection signal generator arranged in the shell, a signal transmission circuit for transmitting a detection signal to the helicopter electronic circuits and a signal receiving circuit for receiving and transmitting feedback signals of the helicopter electronic circuits to a detector, and is characterized in that: wherein,
the detection signal generator and the detector are ARM11 embedded microprocessors;
the signal transmission circuit consists of a detection signal amplification circuit module (1), a 4 x 4 matrix exchange relay output module (2), a matrix exchange transmission line output module (3) and an output conversion component module (4) which can be connected with a helicopter electronic circuit socket, wherein the input end of the detection signal amplification circuit module (1) is connected with the output end of a multi-waveform analog signal source in the microprocessor;
the signal receiving circuit consists of an input conversion component module (8), a matrix exchange transmission line input module (7), a 4 x 4 matrix exchange relay input module (6) and a feedback signal amplifying circuit module (5) which are connected in sequence and can be connected with a helicopter electronic circuit socket, wherein the output end of the feedback signal amplifying circuit module (5) is connected with the input end of a detection signal processing and identifying database in the microprocessor;
the amplification ratio control ends of the detection signal amplification circuit module (1) and the feedback signal amplification circuit module (5) are respectively connected with a data control processor in the microprocessor;
the matrix exchange control ends of the 4 x 4 matrix exchange relay output module (2) and the 4 x 4 matrix exchange relay input module (6) are respectively connected with a data control processor in the microprocessor;
and the line gating control ends of the matrix exchange transmission line output module (3) and the matrix exchange transmission line input module (7) are respectively connected with a data control processor in the microprocessor.
2. An automatic helicopter electronic circuit testing device according to claim 1, characterized in that: the output ends of the multi-waveform analog signal source are four, namely an analog direct-current voltage output end capable of controlling potential change, a sine wave signal output end capable of controlling frequency conversion, a triangular wave signal output end capable of controlling frequency conversion and a rectangular wave signal output end capable of controlling frequency conversion.
3. An automatic helicopter electronic circuit testing device according to claim 2, characterized in that: the detection signal amplification circuit module (1) and the feedback signal amplification circuit module (5) have the same structure and are composed of a NOR gate control circuit, a first decoder, an amplification gating circuit and a signal amplification circuit, wherein,
the NOR gate control circuit consists of two parallel NOR gate circuits, the input end of the NOR gate circuit can obtain a binary code signal from the data control processor and the binary code signal is configured to the input end of the first decoder through the output end of the NOR gate circuit;
the first decoder selectively switches on the branches corresponding to different amplification factors in the amplification factor gating circuit according to the binary coded signal at the input end of the first decoder, and loads the matching resistor in the branch to the amplification factor control end of the signal amplification circuit;
the signal amplification circuit mainly comprises an instrument amplifier with the model number of INA128, and the signal input end of the signal amplification circuit is connected with the output end of the multi-waveform analog signal source or connected with the input conversion component module (8) connected with a helicopter electronic circuit socket; the signal output end of the detection signal processing and identifying module is connected with the input end of the 4 multiplied by 4 matrix switching relay output module (2) or the input end of the detection signal processing and identifying database;
the amplification factor of the signal amplification circuit is 1 time, 2 times, 5 times and 10 times.
4. An automatic helicopter electronic circuit testing device according to claim 1, characterized in that: the 4 x 4 matrix switching relay output module (2) and the 4 x 4 matrix switching relay input module (6) have the same structure, and are provided with four input ends and four output ends, and each input end is respectively connected with the four output ends through four different relays.
5. An automatic helicopter electronic circuit testing device according to claim 1, characterized in that: the matrix exchange transmission line output module (3) and the matrix exchange transmission line input module (7) are identical in structure and are provided with four groups of transmission units, and each group of transmission units are matrix signal transmission lines with 42 or 48 matrix signal transmission lines in 1-to-one selection.
6. An automatic helicopter electronic circuit detection device according to any of claims 1 to 5, characterized in that: the output conversion component module (4) and the input conversion component module (8) are identical in structure and are provided with four conversion pieces, and each conversion piece is a 50-wire standard connection socket.
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 |
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| CN204044310U true CN204044310U (en) | 2014-12-24 |
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| CN201420459689.XU Expired - Lifetime CN204044310U (en) | 2014-08-14 | 2014-08-14 | Helicopter electronic circuit automatic detection device |
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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 not_active Expired - Lifetime
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 |
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