CN203759530U - Online circuit breaker tester of helicopter automatic drive system - Google Patents
Online circuit breaker tester of helicopter automatic drive system Download PDFInfo
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- CN203759530U CN203759530U CN201320807507.9U CN201320807507U CN203759530U CN 203759530 U CN203759530 U CN 203759530U CN 201320807507 U CN201320807507 U CN 201320807507U CN 203759530 U CN203759530 U CN 203759530U
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Abstract
An online circuit breaker tester of a helicopter automatic drive system is disclosed in the utility model, is safe and reliable in testing process, high in testing automation degree, and high in testing efficiency, and includes a helicopter shell and a control circuit which is arranged in the helicopter shell; the control circuit is composed of a control box and a cable transfer box; the control box is internally provided with a detection simulation circuit containing a micro processor; the detection simulation circuit can receive an input control signal of a helicopter automatic drive computer to a course gyro, first vertical gyro, second vertical gyro and H.S.I, can monitor a circuit installed on the helicopter, and can also generate an analog signal to control heading, pitch and roll channels of the automatic drive computer to work as required; the cable transfer box is internally provided with a signal transmission circuit for connecting the detection simulation circuit with the automatic drive computer. The online circuit breaker tester of the utility model, after the helicopter is overhauled or when the helicopter external field is in maintenance, can facilitate the overall electricity online testing or the fault analysis and judgment of the helicopter automatic drive system.
Description
Technical field
The utility model relates to a kind of exerciser for aircraft self-driving status of equipment is detected, particularly a kind of for the online open-circuit test device of helicopter automated driving system.
Background technology
Helicopter automated driving system isolating switch is to be connected to helicopter self-driving computing machine and to set firmly a micro processor controls testing apparatus between described self-driving computing machine socket aboard, after being applied to helicopter and carrying out large repairs, the automated driving system of installing on helicopter is carried out to entirety energising on-line testing, the on-line testing of switching on while also can be applicable in helicopter flight-line service, helicopter automated driving system is carried out fault analysis and judged.
" helicopter automated driving system isolating switch " of the prior art is by many patchplug interrupt test points in test process, use patchcord attachment plug, manually interrupt and connect, will cause so many artificial factors to make, in test, unnecessary accident occurs, thus, easily cause that testing reliability is poor, security is low, automaticity is not high and the shortcoming such as test job efficiency is low.
Summary of the invention
The technical problems to be solved in the utility model is to provide the online open-circuit test device of helicopter automated driving system that a kind of test process is safe and reliable, test automation degree is high, test job efficiency is high.
In order to solve the problems of the technologies described above, the technical solution adopted in the utility model is:
The online open-circuit test device of helicopter automated driving system of the present utility model, comprise casing, the display that is placed on machine shell panel and joins with the control circuit in casing, function key is being installed in line and the interface on self-driving computing machine socket on helicopter with can be used for connecting, described control circuit is made up of control enclosure and Splices cable box, in control enclosure, be provided with and comprise the receiving from helicopter self-driving computing machine directional gyro of microprocessor, the first vertical gyro, the input control signal of the second vertical gyro and H.S.I and the course of circuit being aboard installed monitoring and can produce simulating signal and go to control self-driving computing machine thereof, pitching, roll passage removes the detection mimic channel of work on request, in Splices cable box, be provided with the signal circuit that described detection mimic channel can be connected with described self-driving computing machine.
4 light-coupled isolations that described detection mimic channel comprises 12 light-coupled isolation Data Control line transport modules joining with microprocessor by 12 control buss, join with microprocessor by 4 tunnels feedback interrupt lines are returned and are interrupted controlling 2 tunnels detection voltage 5:1 isolated amplifier transport modules, 30 road optocoupler helicopter state transfer module and the LCD display modules that transport module, one end are connected with microprocessor.
Described signal circuit comprises that synchronizing signal interrupt module circuit, 2:1 sampling isolation circuit, 64 tunnel matrix switch gating circuits, No. 30 helicopter status monitoring circuit and 8 tunnels apply signal gating device circuit.
Described synchronizing signal interrupt module circuit comprises signal input part, signal output part, external synchronizing signal interface, test lead and control loop, and control loop comprises that model is 74HC573 chip, not gate, optical coupling isolator and input and output pilot relay; Test termination from microprocessor and the chip that is CD4053 by model and external synchronizing signal interface, input and output pilot relay normal-closed end touch also and can join with input end and output terminal respectively by this normal-closed end, or join by input and output pilot relay Chang Kaiduan and input end; Described input end is connected with helicopter self-driving computing machine; Output terminal is connected with the LCD display module in described control enclosure.
Described 64 tunnel matrix switch gating circuits comprise that model is that the chip serial connection that the chip of 74HC573 and at least one model are 4051 forms, and this gating circuit connects from self-driving computing machine, and its output is access to described control enclosure.
Described No. 30 helicopter status monitoring circuit connect from self-driving computing machine, and its output is access to described control enclosure Zhong 30 road optocoupler helicopter state transfer modules, and it comprises isolating diode, divider resistance and not gate.
Described 8 tunnels apply signal gating device circuit and connect 12 light-coupled isolation Data Control line transport modules in described control enclosure, and it is access to self-driving computing machine; It comprises that model is that 8 passages that the master chip of 74HC573, analog-converted chip, amplifier, model that model is TLC5615 are 4051 apply voltage gate and apply voltage gating output circuit, described in apply the isolating diode that voltage comparator that voltage gating output circuit is LM324 by model and model are IN4091 and form.
Described microprocessor is ARM11 microprocessor.
The joint that is access to self-driving computing machine by described Splices cable box is respectively the first plug 40 lines, the second plug 67 lines and the 3rd plug 67 lines; The control line that is access to control enclosure by Splices cable box is 50.
Be provided with in the transmit port of microprocessor the RS232 interface that at least one can join with computing machine on helicopter or other parts; Be provided with at least one and can talk with USB interface used in when debugging and computer man-machine.
Compared with prior art, the utility model can receive from helicopter self-driving computing machine directional gyro, the first vertical gyro, the input control signal of the second vertical gyro and H.S.I and the course of circuit being aboard installed monitoring and can produce simulating signal and go to control self-driving computing machine thereof, pitching, roll passage removes the detection mimic channel of work on request and signal circuit that this detection mimic channel is connected with self-driving computing machine is arranged in an exquisite casing, by cable transmission line, after helicopter overhaul or in helicopter flight-line service, can carry out entirety energising on-line testing or carry out fault analysis and judgement helicopter automated driving system very easily.The utility model test process is safe and reliable, and test automation degree and test job efficiency are high.
Brief description of the drawings
Fig. 1 is the connection diagram between the utility model and helicopter.
Fig. 2 is profile of the present utility model and guidance panel schematic diagram.
Fig. 3 is attaching plug and the switch schematic diagram in Fig. 2.
Fig. 4 is top, the pilot lamp viewing area function key schematic diagram in Fig. 2.
Fig. 5 is middle part, the pilot lamp viewing area function key schematic diagram in Fig. 2.
Fig. 6 is bottom, the pilot lamp viewing area function key schematic diagram in Fig. 2.
Fig. 7 is the key part function key schematic diagram in Fig. 2.
Fig. 8 is manipulation control enclosure circuit working principle calcspar of the present utility model.
Fig. 9 is Splices cable box circuit working principle calcspar of the present utility model.
Figure 10 is synchronizing signal interrupt module circuit theory diagrams of the present utility model.
Figure 11 is 64 tunnel matrix switch gating circuit schematic diagrams of the present utility model.
Figure 12 is the circuit theory diagrams of the control mode of 30 paths of LEDs of the present utility model to helicopter working state monitoring display circuit.
Figure 13 is that 8 tunnels of the present utility model apply signal gating device circuit theory diagrams.
Figure 14 is that the test detection point of interruption schematic diagram of navigation system is as follows:
Embodiment
As shown in Figure 1, 2, the utility model is to be connected to helicopter self-driving computing machine and to be installed in a micro processor controls testing apparatus between the above self-driving computing machine socket of this aircraft, after being applied to helicopter and carrying out large repairs, the automated driving system of installing on helicopter is carried out to entirety energising on-line testing, the on-line testing of switching on while also can be applicable in helicopter flight-line service, helicopter automated driving system is carried out fault analysis and judged.
The utility model is compared with traditional " helicopter automated driving system isolating switch ", and to have test process safe and reliable, and test automation degree is high, test job efficiency advantages of higher.
The utility model center is controlled by embedded system " ARM11 microprocessor " and is controlled, and steering order language adopts " ARM11 embedded Linux system " exploitation to control.
The utility model adopts the two-way interruption control mode of input signal: can test the directional gyro coming from self-driving computing machine external transmission, the first vertical gyro (claiming again left horizon instrument), the second vertical gyro (claiming again right horizon instrument), whether the control inputs signals such as H.S.I (being horizontal situation indicator) are normal, differentiate directional gyro and comprise that whether circuit is aboard installed normal with this equipment connection, differentiate the first vertical gyro and the second vertical gyro and whether circuit is aboard installed normal with these two equipment connections, differentiate " H.S.I " and whether normal with the installation of this equipment connection circuit aboard, and handle stick force and survey, than general control, signals such as side acceleration meter and whether be attached thereto the circuit connecing normal, also can simulate control signal that outside input comes and go to control the course of self-driving computing machine, pitching, roll passage goes work on request, checks self-driving computing machine, steering wheel amplifier, course pressurized strut, navigation trim pressurized strut, No. 1 inclination pressurized strut, No. 2 inclination pressurized struts, pitching pressurized strut, pitching trim pressurized strut, whether the equipment work such as inclination trim pressurized strut are normal.
Attaching plug on the utility model machine shell panel and switch are as shown in Figure 3, when wherein " direct supply input " plug is to provide exerciser operation in the wild, in the situation that there is no 220V electric main, while using the direct current 28V Power supply on aircraft or in battery truck, use; " AC power input " is the socket of access while using 220V electric main to charge to exerciser; When still closing, the switch Control experiment device built-in system work that " switches on power " uses.
As shown in Figure 4, wherein, each function key implication and distribution are shown in that A plug as following in following table-1(claims again the first plug to top, pilot lamp viewing area function key on the utility model machine shell panel; B plug claims again the second plug; C plug claims again the 3rd plug):
Table-1
Middle part, pilot lamp viewing area function key on the utility model machine shell panel as shown in Figure 5, wherein, be shown in as following table-2 by each function key implication and distribution:
Table-2
Bottom, pilot lamp viewing area function key on the utility model machine shell panel as shown in Figure 6, wherein, be shown in as following table-3 by each function key implication and distribution:
Table-3
In the time detecting test, can show that whether the circuit working of differentiation test macro part is normal according to the pilot lamp on exerciser panel.
Key part function key on the utility model machine shell panel as shown in Figure 7, wherein,
" system reset "-press this key test macro to reset into initial startup self-detection state, display panel shows 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 selection test function, after choosing, press " test starting " and enter test procedure, key can interrupt test process in test process, to press " test is interrupted ".
" test starting "-after selected test event, press this key can start test.
In " test is interrupted "-test process, pressing this key can interrupt test.
" upwards, return "-this key is multiplexing key:
1), in the time of test option, can option bar on display screen be moved up by pressing this key.
2), press this key when " pitching " function and can control aircraft and upwards come back surveying.
3), finish or press after " test interrupt " in test, press this key and can return to previous menu checkout item.
" continuation, downward "--this key is multiplexing key:
1), in test process, press " test interrupt " key and interrupted after test process, press this key and make to make test procedure to continue to start to test according to the point of interruption.
2), in the time of test option, can option bar on display screen be moved down by pressing this key.
3), press this key when " pitching " function and can control aircraft and bow downwards surveying.
" left, manually "--this key is multiplexing key:
1),, press this key aircraft is offset left when " course " function in test.
2),, press this key aircraft is tilted to the left when " inclination " function in test.
3), test option after, press this key and can make test function proceed to manual detection.
" to the right, automatically "--this key is multiplexing key:
1),, press this key aircraft is offset to the right when " course " function in test.
2),, press this key aircraft is tilted to the right when " inclination " function in test.
3), at manual testing's state, press this key and can make test function proceed to automatic detected state.
Display screen on the utility model machine shell panel is for interactive window, after start, shows the initial homepage picture of start (press " system reset " key and also can get back to this picture) through self-check program rear panel:
Control circuit of the present utility model is arranged in casing, it is made up of control enclosure and Splices cable box, in control enclosure, be provided with and comprise the receiving from helicopter self-driving computing machine directional gyro of microprocessor, the first vertical gyro, the input control signal of the second vertical gyro and H.S.I and the course of circuit being aboard installed monitoring and can produce simulating signal and go to control self-driving computing machine thereof, pitching, roll passage removes the detection mimic channel of work on request, in Splices cable box, be provided with the signal circuit that described detection mimic channel can be connected with described self-driving computing machine.
Described control circuit respectively be arranged at display on machine shell panel, each function key is joined.
As shown in Figure 8, described detection mimic channel comprises 12 light-coupled isolation Data Control line transport modules joining with microprocessor by 12 control buss, 4 light-coupled isolations of joining with microprocessor by 4 tunnels feedback interrupt lines return and interrupt controlling 2 tunnels detection voltage 5:1 isolated amplifier transport modules, 30 road optocoupler helicopter state transfer module and the LCD display modules that transport module, one end are connected with microprocessor.
As shown in Figure 9, described signal circuit comprises that synchronizing signal interrupt module circuit, 2:1 sampling isolation circuit, 64 tunnel matrix switch gating circuits, No. 30 helicopter status monitoring circuit and 8 tunnels apply signal gating device circuit.
Controlling in described control enclosure and processing core is " ARM11 Embedded System ", it by with being connected of following interface, control the carrying out of test function:
" 12 control buss " being connected with Splices cable box controlled the function of all detection tests:
1), controlling 5 groups " input signal relay interrupts gate module " interrupts as required and detects all input signal sources in pitching, inclination, course, can drive the attitude variation of controlling aircraft to rear end by outer increase control signal according to demand, also can detect front end signal, whether working properlyly differentiate front-end equipment.
2), control 2 groups " 64 bit matrix exchange signal gating device modules " gating handover measurement voltage is carried out in 64 monitoring points of monitoring of helicopter.
3), control 2 groups " D/A switch analog voltages generator modules " and produce with data line control as required the analog voltage of 0-15V.
4), controlling the synchronizing signals such as 5 groups " external sync generators " gyroscope instrument on as required can simulated aircraft changes in ground attitude by pitching (2 groups), tilt (2 groups), course (1 group) control aircraft.
5), other digital signal that need to control.
" 4 interrupt control line ":
Complete the interruption processing in control procedure.
" pressure-wire is detected on 2 tunnels ":
2 tunnels are entered to the voltage signal of " in transit cable control enclosure " interior also warp " 64 bit matrix exchange signal gating device module " State selective measurements, first select through the dividing potential drop of 2:1, then arrive in described control enclosure after 5:1 isolated amplifier transport module by transmission line, be transferred to again " ADC " interface of " ARM11 Embedded System ", thereby analog voltage signal is transformed into digital signal and demonstrates measuring voltage result by " LCD display ".Because the ADC interface acceptable analog input voltage of 10 bit resolutions of " ARM11 Embedded System " is 0-3.3V voltage, so first pass through 2:1 dividing potential drop in selecting the each point voltage of test helicopter self-driving system to be direct current 0-+28V voltage range, test voltage 0-+28V is become to 0-+14V, the object of processing is like this because " 64 bit matrix exchange signal gating device module " operating voltage is+15V that gating control channel can only be selected the variation voltage signal in 0-15V.
The variation voltage of measuring is measured from the variation range (10:1) that Splices cable box is transferred to described control enclosure, isolation makes the variation range of 0-+28V become 0 – 2.8V after amplifying through 5:1 voltage divider again.
" 30 tunnel duty LED display line ":
30 kinds of control and duty during by helicopter self-driving system works are presented on machine shell panel in real time, this circuit directly by the operating voltage+27V of various transmission corresponding helicopter self-driving system and+15V, after control line takes out the voltage signal changing, become again the voltage change signal of 0-+5V through voltage divider, pass through photoelectric coupler isolation, be transferred to control enclosure by Splices cable box, then show to LED through Sheffer stroke gate control.
Test operation personnel can be intuitively igniting and extinguishing the control lever judged on aircraft, whether have fault than operation circuits such as general control, total distances by LED lamp.
In " ARM11 Embedded System " transmit port, " RS232-1 ", " RS232-2 " and " RS232-3 " three serial ports are set, so that in Future Development, in the time that aircraft functions is carried out to comprehensive connecting test, can link up with other parts by this serial line interface and computing machine.
In " ARM11 Embedded System " transmit port, " USB-1 " and " USB-2 " interface is set, for using in the time that debug process is talked with computer man-machine.
As shown in figure 10, described synchronizing signal interrupt module circuit comprises signal input part, signal output part, external synchronizing signal interface, test lead and control loop, and control loop comprises that model is 74HC573 chip, not gate, optical coupling isolator and input and output pilot relay; Test termination from microprocessor and the chip that is CD4053 by model and external synchronizing signal interface, input and output pilot relay normal-closed end touch also and can join with input end and output terminal respectively by this normal-closed end, or join by input and output pilot relay Chang Kaiduan and input end; Described input end is connected with helicopter self-driving computing machine; Output terminal is connected with the LCD display module in described control enclosure.
This synchronizing signal interrupt module is designed for course channel input signal and interrupts 1,2 of pitch channel signal interruption (1 loop and 2 loops), and 2 of ramp way signal interruption (1 loop and 2 loops), principle of work circuit diagram is as shown above.
5 input signal interrupt module control circuit principle of work are identical, while being arranged on different passages, control 11 pin " KZTB-LE " and 1 pin " KZTB-OE " the address strobe line traffic control of gating by control integration circuit 74HC573, " KZTB-OE " signal is " 0 " state, this port address bus is high-impedance state, this partial circuit is uncontrolled, do not access test circuit, outside gyro signal X, Y, Z are directly communicated with " X, Y, Z delivery outlet " through " X, Y, Z input port " and the normally closed pin of relay K 1, are not subject to interrupt controlling.
In the time that " KZTB-OE " signal is one state, modular circuit is subject to " KZTB-LE " line traffic control, when " KZTB-LE " line states is " 1 ", integrated circuit 74HC573 electronic switch is opened, D0-D7 incoming level signal is synchronizeed with Q1-Q7 output level, when " KZTB-LE " line states is " 0 ", integrated circuit 74HC573 electronic switch cuts out, D0-D7 incoming level signal is inoperative, state when Q1-Q7 output level keeps electronic switch to open, this module logical relation coding schedule is as shown in the table:
| KZTB-OE | KZTB-LE | D state | Q state | K1 state | K2 state | U1 state |
| 0 | 1 | D1=0 | Q1=0 | 0 | 0 | X=X0 |
| 0 | 1 | D1=1 | Q1=1 | 0 | 0 | X=X1 |
| 0 | 1 | D2=0 | Q2=0 | 0 | 0 | Y=Y0 |
| 0 | 1 | D2=1 | Q2=1 | 0 | 0 | Y=Y1 |
| 0 | 1 | D3=0 | Q3=0 | 0 | 0 | Z=Z0 |
| 0 | 1 | D3=1 | Q3=1 | 0 | 0 | Z=Z1 |
| 0 | 1 | D4=0 | Q4=0 | 0 | 0 | 0 |
| 0 | 1 | D4=1 | Q4=1 | 0 | 1 | 0 |
| 0 | 1 | D5=0 | Q5=0 | 0 | 0 | 0 |
| 0 | 1 | D5=1 | Q5=1 | 1 | 0 | 0 |
| 0 | 0 | D1=0 | Q1=X | Keep | Keep | Keep |
| 1 | X | X | High resistant | Do not work | Do not work | Do not work |
As shown in figure 11, described 64 tunnel matrix switch gating circuits comprise that model is that the chip serial connection that the chip of 74HC573 and at least one model are 4051 forms, and this gating circuit connects from self-driving computing machine, and its output is access to described control enclosure.
Control the access of 64 tunnel matrix switch gating circuits or disconnect 11 pin " XTXH-LE " and 1 pin " XTXH-OE " the address strobe line traffic control by U10 control integration circuit 74HC573, " XTXH-OE " signal is " 0 " state, this port address bus is high-impedance state, this partial circuit is uncontrolled, do not access test circuit, in the time that " XTXH-OE " signal is one state, modular circuit is subject to " XTXH-LE " line traffic control, when " XTXH-LE " line states is " 1 ", integrated circuit 74HC573 electronic switch is opened, D0-D7 incoming level signal is synchronizeed with Q1-Q7 output level, when " XTXH-LE " line states is " 0 ", integrated circuit 74HC573 electronic switch cuts out, D0-D7 incoming level signal is inoperative, state when Q1-Q7 output level keeps electronic switch to open, Gai64 road matrix switch module logical relation is as described below:
Control " A by individual position, B, C " three line composition BCD coding 1-8 gating control U1-U8 electronic switches convert simultaneously in passage 1-8, ten Strobe inputs of controlling gating electronic switch U9 are all sent in each electronic switch gating output, the sheet that carries out 1-8 by U9 again selects, so just form the matrix switch gating circuit of 8X8, all be connected to the voltage divider of 2:1 with buffer circuit in the input port of the each gating circuit of U1-U8, be that 0-+14V test voltage is for gate gating by the 0-+28V voltage transition in test circuit, then deliver to the ADC voltage transitions digital signal circuit that controller of the present utility model carries out giving after 5:1 isolated amplifier dividing potential drop the 11 micro-processing of the utility model embedded-type ARM again, so just the 0-+28V voltage signal of test is converted to the accessible 0 – 2.8V voltage signal of the micro-processing of ARM11.
As shown in figure 12, described No. 30 helicopter status monitoring circuit connect from self-driving computing machine, and its output is access to described control enclosure Zhong 30 road optocoupler helicopter state transfer modules, and it comprises isolating diode, divider resistance and not gate.
Helicopter duty monitoring circuit sample circuit take from control circuit on helicopter to self-driving computer control and computing machine the signal transmission to other working equipment control, this signal transmission is useful+control of 27V power supply, useful+15V power supply control, in sample circuit design, each sampled point is all had to an IN4001 diode-isolated, avoid circuit to interact.
Sampled signal+27V voltage is given ungated integrated circuit 74LS06 after by a 2K resistance and 500 Ohmage dividing potential drops and is controlled, in order to be adapted to the anti-interference factor of Long-distance Control, photoelectric coupling buffer circuit has been installed on the utility model controller to be completed by TLP521, this circuit photoelectricity LED is powered by+15V, in signal transmission, has avoided external voltage interference.
When detecting on helicopter after state-change, + 27V(or+15V) to make 74LS06 input end be noble potential to voltage, make output terminal become " 0 " through not gate, LED display lamp is ignited, reported check point duty corresponding on helicopter to operator.
As shown in figure 13, described 8 tunnels apply signal gating device circuit and connect 12 light-coupled isolation Data Control line transport modules in described control enclosure, and it is access to self-driving computing machine; It comprises that model is that 8 passages that the master chip of 74HC573, analog-converted chip, amplifier, model that model is TLC5615 are 4051 apply voltage gate and apply voltage gating output circuit, described in apply the isolating diode that voltage comparator that voltage gating output circuit is LM324 by model and model are IN4091 and form.
Voltage signal generator is produced by data, the analog converter U1TLC5615 of serial line interface, it can first control the analog-converted voltage that produces 10 DAC by serial data control line " control data line 001 ", " controlling data line 002 ", " controlling data line 003 " three, and the pin function of TLC5615 chip is as shown below:
The variation voltage that the voltage (0-5V) producing from the data of serial line interface, analog converter U1TLC5615 becomes 0-15V after the 1:3 proportional amplifier of U2 amplifies is sent to U5(4051) 8 channel to channel adapters, the voltage after gating is applied to U3A-U3D and 8 passages of U4A-U4D voltage follower are applied to needed applying on test signal reference mark through isolating diodes.
Controlling 8 passages applies the control signal access of voltage gate or disconnects 11 pin " SJDY-LE " and 1 pin " SJDY-OE " the address strobe line traffic control by U6 control integration circuit 74HC573, " SJDY-OE " signal is " 0 " state, this port address bus is high-impedance state, this partial circuit is uncontrolled, do not apply voltage access test circuit, in the time that " SJDY-OE " signal is one state, modular circuit is subject to " SJDY-LE " line traffic control, when " SJDY-LE " line states is " 1 ", integrated circuit 74HC573 electronic switch is opened, D0-D7 incoming level signal is synchronizeed with Q1-Q7 output level, when " SJDY-LE " line states is " 0 ", integrated circuit 74HC573 electronic switch cuts out, D0-D7 incoming level signal is inoperative, state when Q1-Q7 output level keeps electronic switch to open.
The utility model interrupts the selection of test point on helicopter, and according to the testing process establishment of self-driving system self-driving computer maintenance handbook, the test of its navigation system detects point of interruption schematic diagram as shown in figure 14.
Claims (9)
1. the online open-circuit test device of helicopter automated driving system, comprise casing, the display that is placed on machine shell panel and joins with the control circuit in casing, function key is being installed in line and the interface on self-driving computing machine socket on helicopter with can be used for connecting, it is characterized in that: described control circuit is made up of control enclosure and Splices cable box, in control enclosure, be provided with and comprise the receiving from helicopter self-driving computing machine directional gyro of microprocessor, the first vertical gyro, the input control signal of the second vertical gyro and H.S.I and the course of circuit being aboard installed monitoring and can produce simulating signal and go to control self-driving computing machine thereof, pitching, roll passage removes the detection mimic channel of work on request, in Splices cable box, be provided with the signal circuit that described detection mimic channel can be connected with described self-driving computing machine, described microprocessor is ARM11 microprocessor.
2. the online open-circuit test device of helicopter automated driving system according to claim 1, is characterized in that: 4 light-coupled isolations that described detection mimic channel comprises 12 light-coupled isolation Data Control line transport modules joining with microprocessor by 12 control buss, join with microprocessor by 4 tunnels feedback interrupt lines are returned and interrupted controlling 2 tunnels detection voltage 5:1 isolated amplifier transport modules, 30 road optocoupler helicopter state transfer module and the LCD display modules that transport module, one end are connected with microprocessor.
3. the online open-circuit test device of helicopter automated driving system according to claim 2, is characterized in that: described signal circuit comprises that synchronizing signal interrupt module circuit, 2:1 sampling isolation circuit, 64 tunnel matrix switch gating circuits, No. 30 helicopter status monitoring circuit and 8 tunnels apply signal gating device circuit.
4. the online open-circuit test device of helicopter automated driving system according to claim 3, it is characterized in that: described synchronizing signal interrupt module circuit comprises signal input part, signal output part, external synchronizing signal interface, test lead and control loop, control loop comprises that model is 74HC573 chip, not gate, optical coupling isolator and input and output pilot relay; Test termination from microprocessor and the chip that is CD4053 by model and external synchronizing signal interface, input and output pilot relay normal-closed end touch also and can join with input end and output terminal respectively by this normal-closed end, or join by input and output pilot relay Chang Kaiduan and input end; Described input end is connected with helicopter self-driving computing machine; Output terminal is connected with the LCD display module in described control enclosure.
5. the online open-circuit test device of helicopter automated driving system according to claim 3, it is characterized in that: described 64 tunnel matrix switch gating circuits comprise that model is that the chip serial connection that the chip of 74HC573 and at least one model are 4051 forms, this gating circuit connects from self-driving computing machine, and its output is access to described control enclosure.
6. the online open-circuit test device of helicopter automated driving system according to claim 3, it is characterized in that: described No. 30 helicopter status monitoring circuit connect from self-driving computing machine, its output is access to described control enclosure Zhong 30 road optocoupler helicopter state transfer modules, and it comprises isolating diode, divider resistance and not gate.
7. the online open-circuit test device of helicopter automated driving system according to claim 3, is characterized in that: described 8 tunnels apply signal gating device circuit and connect 12 light-coupled isolation Data Control line transport modules in described control enclosure, and it is access to self-driving computing machine; It comprises that model is that 8 passages that the master chip of 74HC573, analog-converted chip, amplifier, model that model is TLC5615 are 4051 apply voltage gate and apply voltage gating output circuit, described in apply the isolating diode that voltage comparator that voltage gating output circuit is LM324 by model and model are IN4091 and form.
8. according to the online open-circuit test device of the helicopter automated driving system described in any one in claim 1-7, it is characterized in that: the joint that is access to self-driving computing machine by described Splices cable box is respectively the first plug 40 lines, the second plug 67 lines and the 3rd plug 67 lines; The control line that is access to control enclosure by Splices cable box is 50.
9. the online open-circuit test device of helicopter automated driving system according to claim 1, is characterized in that: be provided with in the transmit port of microprocessor the RS232 interface that at least one can join with computing machine on helicopter or other parts; Be provided with at least one and can talk with USB interface used in when debugging and computer man-machine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320807507.9U CN203759530U (en) | 2013-12-10 | 2013-12-10 | Online circuit breaker tester of helicopter automatic drive system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320807507.9U CN203759530U (en) | 2013-12-10 | 2013-12-10 | Online circuit breaker tester of helicopter automatic drive system |
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| Publication Number | Publication Date |
|---|---|
| CN203759530U true CN203759530U (en) | 2014-08-06 |
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|---|---|---|---|
| CN201320807507.9U Expired - Fee Related CN203759530U (en) | 2013-12-10 | 2013-12-10 | Online circuit breaker tester of helicopter automatic drive system |
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| Country | Link |
|---|---|
| CN (1) | CN203759530U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107817698A (en) * | 2017-12-14 | 2018-03-20 | 广东优翼航空技术有限公司 | Circuit breaker control circuit and flight simulator circuit breaker manipulation system |
| US11592486B2 (en) | 2020-06-05 | 2023-02-28 | Saudi Arabian Oil Company | Electromechanical relay tester |
| CN117110766A (en) * | 2023-10-18 | 2023-11-24 | 沈阳圣飞航空科技有限公司 | Detection system and method for detecting avionics control device |
-
2013
- 2013-12-10 CN CN201320807507.9U patent/CN203759530U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107817698A (en) * | 2017-12-14 | 2018-03-20 | 广东优翼航空技术有限公司 | Circuit breaker control circuit and flight simulator circuit breaker manipulation system |
| US11592486B2 (en) | 2020-06-05 | 2023-02-28 | Saudi Arabian Oil Company | Electromechanical relay tester |
| CN117110766A (en) * | 2023-10-18 | 2023-11-24 | 沈阳圣飞航空科技有限公司 | Detection system and method for detecting avionics control device |
| CN117110766B (en) * | 2023-10-18 | 2024-01-09 | 沈阳圣飞航空科技有限公司 | Detection system and method for detecting avionics control device |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140806 Termination date: 20171210 |