CN109933046B - Unmanned aerial vehicle undercarriage retraction controller test system - Google Patents
Unmanned aerial vehicle undercarriage retraction controller test system Download PDFInfo
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- CN109933046B CN109933046B CN201910218991.3A CN201910218991A CN109933046B CN 109933046 B CN109933046 B CN 109933046B CN 201910218991 A CN201910218991 A CN 201910218991A CN 109933046 B CN109933046 B CN 109933046B
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- 238000012360 testing method Methods 0.000 title claims abstract description 116
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- 238000001514 detection method Methods 0.000 claims description 5
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Abstract
The application discloses a test system for an unmanned aerial vehicle landing gear retraction controller, and aims to provide a test system which is compact in structure, high in reusability, powerful in test function and high in intelligent degree. The method is realized by the following technical scheme: the testing system comprises a motor testing system, a high-power programmable power supply, an embedded industrial personal computer module, a three-in-one control platform, an adapter, shaft end loading equipment and a testing cable which are integrated in a cabinet. The adapter is connected to the embedded industrial personal computer module, the high-power programmable power supply and the shaft end loading equipment through internal cables, power supply and motor shaft end loading are achieved, the adapter is connected to the falling frame retraction controller through the test cables, communication and transmission and driving of tested signals are completed, the embedded industrial personal computer module receives state data of the front lifting, the left lifting and the right lifting output by the landing gear retraction controller through a multifunctional data card and a bus communication card inserted into an embedded CPCI bus interface, and all test functions are achieved through running test software.
Description
Technical Field
The application belongs to the technical field of test instruments, and particularly relates to a test device for complete machine test, motor shaft end loading and fault diagnosis of a landing gear retraction controller.
Background
The landing gear retraction controller is used as an important core component, and the reliability of the landing gear retraction controller directly influences the normal retraction of the landing gear. The situation of the unmanned aerial vehicle is complicated due to the need to bear a violent impact when the unmanned aerial vehicle lands. The great difficulty in measuring the drop test results on a drop stand therefore requires the use of specialized measurement methods and test techniques. In order to overcome the defects of the traditional control mode of retraction of the landing gear of the unmanned aerial vehicle, particularly the defects of control condition change or difficult injection, the retraction controller of the landing gear of the unmanned aerial vehicle to be tested needs to perform performance test, motor shaft end loading and fault diagnosis on the whole unmanned aerial vehicle in the production process. At present, the device comprises a brake test, a retraction path test and an automatic retraction test device for an unmanned aerial vehicle landing gear, wherein the device is mainly special test equipment, and the main products of the device comprise a digital storage oscilloscope series, an arbitrary waveform generator and a frequency meter series, a multichannel high-capacity waveform recorder series, a special data acquisition system, a data acquisition system special for an unmanned aerial vehicle drop test, a data acquisition system for an unmanned aerial vehicle drop table, and the like. Because the test function is simple and single, the operation is complicated, the intelligent degree is low, and the test requirement of the undercarriage retraction controller cannot be met. For example, in the shock impact test, various parameters of the unmanned aerial vehicle need to be measured to determine the conditions of the unmanned aerial vehicle, such as displacement, load, acceleration, force and strain, and the like, the measured parameters are more, the shock test result is very difficult to measure in the shock test stand, a special measuring method and a testing technology need to be adopted to infer whether the airborne equipment in the unmanned aerial vehicle is damaged, and in the test, in addition to the acceleration and the duration, the influence of factors such as impact waveform, impact response and the like need to be considered, so that the environmental factors are high, the control method is complex, and the actual operation is difficult or even impossible, so that the method is difficult to meet various actual requirements.
Disclosure of Invention
The application aims to provide a test system which has the advantages of compact structure, simple connection, high reusability, powerful test function and high intelligent degree, aiming at the defects existing in the prior art.
The technical scheme adopted for solving the technical problems is as follows: an unmanned aerial vehicle undercarriage retraction controller test system comprising: the embedded industrial personal computer module and shaft end loading equipment are integrated in the cabinet, the motor testing system for monitoring 1-12 paths of motor current output by the landing gear retraction controller, the high-power programmable power supply, the embedded industrial personal computer module and shaft end loading equipment which are connected with the three-in-one control platform through a USB interface and a VGA, and the embedded industrial personal computer module is internally provided with testing software, and the embedded industrial personal computer module is characterized in that: the motor testing system, the high-power programmable power supply, the embedded industrial personal computer module and the shaft end loading equipment are connected together through buses, the output ends of the motor testing system, the high-power programmable power supply, the embedded industrial personal computer module and the shaft end loading equipment are connected with an adapter, the adapter is connected with a landing gear retraction controller through a testing cable, wherein the high-power programmable power supply, the embedded industrial personal computer module and the shaft end loading equipment receive state data of a front lifter, a left lifter and a right lifter output by the landing gear retraction controller, and the transmission and driving of tested signals; the embedded industrial personal computer module is internally provided with an RS422 bus card and a multifunctional acquisition card which are connected with an adapter, the multifunctional acquisition card and a bus communication card are connected through an embedded CPCI bus interface, 1-8 paths of discrete quantity signals are automatically controlled through a relay switch in the multifunctional acquisition card, the discrete quantity signals, 1-11 paths of control switch signals and 2 paths of RS422 bus signals generated by a program control switch are sent to the adapter, and 1-3 paths of loading signals generated by shaft end loading equipment are also input to a landing gear retraction controller through the adapter; the multifunctional acquisition card automatically acquires three discrete quantity input signals output by the landing gear retraction controller; the test software is used for simulating and controlling three groups of motor signals of the undercarriage retraction controller and 1-3 paths of motors of the shaft end loading device by means of software and hardware resources, running the test software with self-detection, full-automatic test and fault diagnosis functions to carry out full-automatic fault diagnosis, and testing all functions of the undercarriage retraction controller.
Compared with the prior art, the application has the following beneficial effects.
Compact structure, simple connection and high reusability. According to the application, the motor test system, the high-power programmable power supply, the embedded industrial personal computer module, the three-in-one control platform, the adapter and the shaft end loading equipment are integrated in the cabinet, so that the structure is compact, the circuit connection is simple, and the integration level of ground test of the landing gear system is improved. The landing gear winding and unwinding controller is connected with the adapter through the test cable, and is connected to the RS422 bus card and the multifunctional acquisition card which are arranged in the embedded industrial personal computer module through the adapter, so that the connection is firm and convenient, the signal transmission is reliable, the test period is shorter, and the cost is lower. All modules in the cabinet can adopt a structure with guide rails on two sides and pin holes for connecting and inserting ends, so that the maintenance and the expansion of corresponding instrument systems are more convenient, the modules cannot be impacted or rocked due to external vibration, the cabinet is small in size, the cabinet has a plurality of electrical characteristics specially designed for testing, the I/O expansibility is good, a plurality of modules can be integrated, a bus type trigger line and a star type trigger line which can realize the triggering or asynchronous triggering of the modules are provided on a backboard of the cabinet, and electromagnetic interference accords with EMC and CE standards.
The test function is powerful, and the intelligent degree is high. The application adopts the embedded industrial personal computer module to receive the state data of the front lifting, the left main lifting and the right main lifting output by the landing gear retraction controller through the multifunctional acquisition card and the bus communication card inserted into the embedded CPCI bus interface, realizes all the test functions through the running test software with the functions of self-detection, full-automatic test and fault diagnosis, has high measurement speed and high accuracy, and achieves unattended operation. The system can meet the functions of brake test, retraction path test, retraction fatigue test, tire inflation and the like of an unmanned aerial vehicle landing gear system.
And 4, good humanized design. The signal testing column is arranged on the front panel of the adapter, so that on-line detection, fault diagnosis, positioning and isolation of signals are facilitated. The user software divides the functional blocks, the man-machine communication interface is friendly, and the user can finish the test function by one key.
Drawings
Fig. 1 is an isometric view of a cabinet device of the unmanned aerial vehicle landing gear retraction controller test system of the present application.
Fig. 2 is an isometric view of the adapter of fig. 1.
Fig. 3 is a rear view of the adapter of fig. 2.
Fig. 4 is a partial view of a test device with a landing gear retraction controller for an unmanned aerial vehicle placed on a test table.
Fig. 5 is a schematic diagram of the circuit principle of fig. 1.
Fig. 6 is a schematic circuit diagram of the relevant module of fig. 1.
In the figure: the device comprises a cabinet 1, a motor test system 2, a high-power programmable power supply 3, an embedded industrial personal computer module 4, a three-in-one control platform 5, an adapter 6, a drawer 7, an 8-shaft end loading device, an adapter front panel 9, a cabinet 10, a test socket 11, an adapter rear panel 12, a signal socket 13, a landing gear retraction controller 14 and a test cable 15.
For the purpose of further explanation and not limitation of the above-described implementation of the application, the application is further explained below with reference to the drawings and examples, but the application is not limited to the described implementation scope, and all these concepts should be regarded as the disclosure of the present technology and the protection scope of the patent of the present application.
Detailed Description
See fig. 1-5. In the embodiments described below, an unmanned aerial vehicle landing gear retraction controller test system includes: the system is integrated in a cabinet 1, a motor test system 2 for monitoring 1-12 paths of motor current output by a landing gear retraction controller 14, a high-power programmable power supply 3, an embedded industrial personal computer module 4 and shaft end loading equipment 8 which are connected with a three-in-one control platform 5 through a USB interface and a VGA, and test software installed in the embedded industrial personal computer module 4. The motor testing system 2, the high-power programmable power supply 3, the embedded industrial personal computer module 4 and the shaft end loading equipment 8 are connected together through buses, the output ends of the motor testing system, the embedded industrial personal computer module 4 and the shaft end loading equipment 8 are connected with the adapter 6, the adapter 6 is connected with the landing gear retraction controller 14 through a testing cable, wherein the high-power programmable power supply 3, the embedded industrial personal computer module 4 and the shaft end loading equipment 8 receive state data of the front lifting, the left lifting and the right lifting output by the landing gear retraction controller 14, and the transmission and the driving of tested signals; the embedded industrial personal computer module 4 is internally provided with an RS422 bus card and a multifunctional acquisition card which are connected with the adapter 6, the multifunctional acquisition card and the bus communication card are connected through an embedded CPCI bus interface, 1-8 paths of discrete quantity signals are automatically controlled through a relay switch in the multifunctional acquisition card, the discrete quantity signals, 1-11 paths of control switch signals and 2 paths of RS422 bus signals generated by a program control switch are sent to the adapter 6, and 1-3 paths of loading signals generated by the shaft end loading equipment 8 are also input to the landing gear retraction controller 14 through the adapter 6; the multifunctional acquisition card automatically acquires three discrete quantity input signals output by the landing gear retraction controller 14; the test software is used for simulating and controlling three groups of motor signals of the landing gear retraction controller 14 and 1-3 paths of motors of the shaft end loading device 8 by means of software and hardware resources, running the test software with self-detection, full-automatic test and fault diagnosis functions to carry out full-automatic fault diagnosis, and testing all functions of the landing gear retraction controller 14.
The adapter 6 comprises an adapter front panel 9, a case 10 and an adapter rear panel 12, wherein the adapter front panel 9 is provided with a test socket 11, a signal indicator light and a signal monitoring port, and the adapter rear panel 12 is provided with a signal socket 13, a high-power programmable power bus monitoring port and a safety seat. The test socket 11 on the front panel 9 of the adapter is connected with the landing gear retraction controller 14 through a test cable, and the signal of the test socket 11 is connected to the signal socket 13 of the rear panel of the adapter through the internal connection wire of the adapter 6 to complete the signal transmission. The landing gear retraction controller 14 is connected to the test socket 11 on the front panel 9 of the adapter through a test cable, and the signal of the test socket 11 is connected to the signal socket 13 of the rear panel of the adapter through the internal connection wire of the adapter 6 to complete the signal transmission.
The embedded industrial personal computer module 4 is internally provided with a multifunctional acquisition card in the form of CPCI bus interface and an RS422 bus communication card. The landing gear retraction controller 14 is connected to the test socket 11 on the adapter front panel 9 by a test cable 15. The high-power programmable power supply 3 provides working power required by the working of the landing gear retraction controller 14 through the power socket XS5 of the signal socket 13 of the rear panel 12 of the adapter and the test socket 11 of the front panel 9 of the adapter.
The landing gear retraction controller 14 is connected to the test socket 11 on the front panel 9 of the adapter through a test cable, and the signal of the test socket 11 is connected to the signal socket 13 of the rear panel of the adapter through the internal connection wire of the adapter 6 to complete the signal transmission.
The embedded industrial personal computer module 4 is internally provided with a multifunctional acquisition card in the form of CPCI bus interface and an RS422 bus communication card.
The landing gear retraction controller 14 is connected to the test socket 11 on the adapter front panel 9 by a test cable 15.
The high-power programmable power supply 3 provides working power required by the landing gear retraction controller 14 through the power socket XS5 of the signal socket 13 on the rear panel 12 of the adapter and the test socket 11 on the front panel 9 of the adapter.
The landing gear receive and release controller 14 utilizes the RS422 bus card in the embedded industrial personal computer module 4 to realize the output of 2 paths of high-power programmable power supplies to the landing gear receive and release controller 14 in a program-controlled mode by means of software and hardware resources, the output of 8 paths of discrete quantity signals is automatically controlled to the landing gear receive and release controller 14 through a relay switch in a multifunctional acquisition card in the embedded industrial personal computer module 4, the output of 11 paths of switching signals is controlled to the landing gear receive and release controller 14 through the program-controlled switch in the embedded industrial personal computer module 4, the RS422 bus card in the embedded industrial personal computer module 4 is used for simulating and controlling 3 sets of motor signals of the landing gear receive and release controller 14, the RS422 bus card in the embedded industrial personal computer module 4 is used for controlling the 3 paths of motor shaft ends on the shaft end loading device 8, the 3 paths of discrete quantity input signals output by the landing gear receive and release controller 14 are automatically acquired through the multifunctional acquisition card in the embedded industrial personal computer module 4, and the 12 paths of motor current output by the landing gear receive and release controller 14 are monitored through the motor test system 2.
The adapter 6 is connected to the embedded industrial personal computer module 4, the high-power programmable power supply 3 and the shaft end loading device 8 through internal cables, so that power supply and motor shaft end loading are realized. The embedded industrial personal computer module 4 outputs a control instruction through the RS422 bus card, transmits the control instruction to the linear array signal socket 13 and the bus socket XS8 which are arranged on the rear panel 12 of the adapter, simultaneously provides a digital quantity instruction sent by the multifunctional acquisition card to the undercarriage retractable controller 14 through the test socket 11 on the front panel 9 of the adapter, and the undercarriage retractable controller 14 outputs a driving signal according to the instruction to drive the built-in motor of the shaft end loading device 8 to operate. The multifunctional acquisition card automatically acquires 3 paths of discrete quantity input signals output by the landing gear retraction controller 14. The adapter 6 is connected to the embedded industrial personal computer module 4, the high-power programmable power supply 3 and the shaft end loading device 8 through internal cables, so that power supply and motor shaft end loading are realized.
The embedded industrial personal computer module 4 outputs a control instruction through an RS422 bus card, transmits the control instruction to a linear array signal socket 13 and a bus socket XS8 thereof which are arranged on the rear panel 12 of the adapter, simultaneously provides a digital quantity instruction sent by the multifunctional acquisition card to the undercarriage retractable controller 14 through a test socket 11 on the front panel 9 of the adapter, and the undercarriage retractable controller 14 outputs a driving signal according to the instruction to drive a built-in motor of the shaft end loading device 8 to operate; the embedded industrial personal computer module 4 changes an operation rate control word, controls the motor operation rate of the shaft end loading device 8 to correspondingly change, outputs an instruction to the motor test system 2 through the RS422 bus card, and the motor test system 2 tests and monitors U, V, W phase sequences and bus currents marked on the motor binding posts; the landing gear retraction controller test system controls a brake in the shaft end loading equipment 8 according to the instruction, effectively loads a motor in the shaft end loading equipment 8, monitors the shaft end loading, and receives the state conditions of front lifting, left main lifting and right main lifting output by the landing gear retraction controller 14 by a multifunctional acquisition card.
The embedded industrial personal computer module 4 changes an operation rate control word, controls the motor operation rate of the shaft end loading device 8 to correspondingly change, outputs an instruction to the motor test system 2 through the RS422 bus card, and tests and monitors the motor winding U phase, the motor winding V phase, the motor winding W phase and the bus current of the motor; the landing gear retraction controller test system controls a brake in the shaft end loading equipment 8 according to the instruction, effectively loads a motor in the shaft end loading equipment 8, monitors the shaft end loading, and receives the state conditions of front lifting, left main lifting and right main lifting output by the landing gear retraction controller 14 by a multifunctional acquisition card.
See fig. 6. In an alternative embodiment, the embedded industrial personal computer module 4 is internally provided with an RS422 bus card and a multifunctional acquisition card, the RS422 bus card is connected with the motor test system 2, the shaft end loading device 8 and the high-power programmable power supply 3 through buses, three groups of motor signals and the shaft end loading device 8 connected through buses send three paths of loading signals to the landing gear retraction controller 14, and the high-power programmable power supply 3 also sends 2 paths of working power supplies to the landing gear retraction controller 14; the landing gear retraction controller 14 sends 12 paths of motor current to the motor test system 2 and sends three paths of discrete magnitude signals to the multifunctional acquisition card. The multifunctional acquisition cartoon process control switch and the relay switch respectively send 8 paths of discrete quantity signals and 11 paths of switching quantity signals into the undercarriage retraction controller 14.
It will be apparent to those skilled in the art that the present application may be embodied in other specific forms than those herein set forth without departing from the spirit or essential characteristics of the application. The above description is thus to be regarded in all aspects as illustrative instead of limiting. The scope of the application should be determined by reasonable interpretation of the appended claims and all change which comes within the equivalent scope of the application are intended to be included in the scope of the application. In addition, claims that do not explicitly depend from each other may be combined to provide embodiments or new claims can be added by modification after submitting the application.
Claims (9)
1. An unmanned aerial vehicle undercarriage retraction controller test system comprising: the intelligent landing gear testing system is integrated in a cabinet (1), monitors motor testing systems (2) of 1-12 paths of motor currents output by a landing gear retraction controller (14), high-power programmable power supplies (3), embedded industrial personal computer modules (4) and shaft end loading equipment (8) which are connected with a three-in-one control platform (5) through USB interfaces and VGAs, and installs testing software in the embedded industrial personal computer modules (4), and is characterized in that: the motor testing system (2), the high-power programmable power supply (3), the embedded industrial personal computer module (4) and the shaft end loading device (8) are connected together through buses, the output ends of the motor testing system, the embedded industrial personal computer module and the shaft end loading device are connected with the adapter (6), the adapter (6) is connected with the landing gear retraction controller (14) through a testing cable, wherein the high-power programmable power supply (3), the embedded industrial personal computer module (4) and the shaft end loading device (8) receive state data of a front lifter, a left lifter and a right lifter, which are output by the landing gear retraction controller (14), and the transmission and driving of tested signals; an RS422 bus card and a multifunctional acquisition card of an adapter (6) are connected in the embedded industrial personal computer module (4), the multifunctional acquisition card and the bus communication card are connected through an embedded CPCI bus interface, 1-8 paths of discrete quantity signals are automatically controlled through a relay switch in the multifunctional acquisition card, the discrete quantity signals, 1-11 paths of distance control switch signals generated by a program control switch and two paths of RS422 bus signals are sent to the adapter (6), and 1-3 paths of loading signals generated by shaft end loading equipment (8) are also input to a landing gear retraction controller (14) through the adapter (6); the multifunctional acquisition card automatically acquires three discrete quantity input signals output by the landing gear retraction controller (14); the test software is used for simulating and controlling three groups of motor signals of the landing gear retraction controller (14) and 1-3 paths of motors of the shaft end loading device (8) by means of software and hardware resources, running the test software with self-detection, full-automatic test and fault diagnosis functions to carry out full-automatic fault diagnosis, and testing all functions of the landing gear retraction controller (14);
the landing gear retraction controller test system controls a brake in the shaft end loading equipment (8) according to the instruction, effectively loads a motor in the shaft end loading equipment (8), monitors the shaft end loading, and receives the state conditions of the front lifting, the left main lifting and the right main lifting output by the landing gear retraction controller (14).
2. The unmanned aerial vehicle landing gear retraction controller test system of claim 1 wherein: the landing gear retraction controller (14) is connected to the test socket (11) on the front panel (9) of the adapter through a test cable, and signals of the test socket (11) are connected to the signal socket (13) of the rear panel of the adapter through internal connection wires of the adapter (6) so as to complete signal transmission.
3. The unmanned aerial vehicle landing gear retraction controller test system of claim 1 wherein: the embedded industrial personal computer module (4) is internally provided with a multifunctional acquisition card in the form of CPCI bus interface and an RS422 bus communication card.
4. The unmanned aerial vehicle landing gear retraction controller test system of claim 1 wherein: the landing gear retraction controller (14) is connected to a test socket (11) on the adapter front panel (9) by a test cable (15).
5. The unmanned aerial vehicle landing gear retraction controller test system of claim 1 wherein: the high-power programmable power supply (3) provides working power required by the work of the landing gear retraction controller (14) through the power socket XS5 of the signal socket (13) on the rear panel (12) of the adapter and the test socket (11) on the front panel (9) of the adapter.
6. The unmanned aerial vehicle landing gear retraction controller test system of claim 1 wherein: the landing gear receiving and releasing controller (14) uses RS422 bus cards in the embedded industrial personal computer module (4) to realize the output of 2 paths of high-power programmable power sources to the landing gear receiving and releasing controller (14) in a program-controlled mode, automatically controls the output of 8 paths of discrete quantity signals to the landing gear receiving and releasing controller (14) through a relay switch in a multifunctional acquisition card in the embedded industrial personal computer module (4), controls the output of 11 paths of switching signals to the landing gear receiving and releasing controller (14) through a program-controlled switch in the embedded industrial personal computer module (4), controls 3 sets of motor signals of the landing gear receiving and releasing controller (14) through the RS422 bus cards in the embedded industrial personal computer module (4), controls the shaft ends of a 3 paths of motors on the shaft end loading device (8), automatically acquires the discrete quantity input signals of the 3 paths of the landing gear output by the receiving and releasing controller (14) through the multifunctional acquisition card in the embedded industrial personal computer module (4), and monitors the current output of the landing gear receiving and releasing controller (14) through the motor testing system (2).
7. The unmanned aerial vehicle landing gear retraction controller test system of claim 1 wherein: the adapter (6) is connected to the embedded industrial personal computer module (4), the high-power programmable power supply (3) and the shaft end loading device (8) through an internal cable, so that power supply and motor shaft end loading are realized.
8. The unmanned aerial vehicle landing gear retraction controller test system of claim 1 wherein: the embedded industrial personal computer module (4) outputs a control instruction through the RS422 bus card, transmits the control instruction to the linear array signal socket (13) and the bus socket XS8 thereof which are arranged on the adapter rear panel (12), and simultaneously provides a digital quantity instruction sent by the multifunctional acquisition card to the undercarriage retractable controller (14) through the test socket (11) on the adapter front panel (9), and the undercarriage retractable controller (14) outputs a driving signal according to the instruction to drive a built-in motor of the shaft end loading equipment (8) to operate.
9. The unmanned aerial vehicle landing gear retraction controller test system of claim 1 wherein: the embedded industrial personal computer module (4) changes the operation rate control word, controls the motor operation rate of the shaft end loading device (8) to correspondingly change, outputs instructions to the motor test system (2) through the RS422 bus card, and the motor test system (2) tests and monitors the motor winding U, the motor winding V, the motor winding W and the bus current of the motor.
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| CN201910218991.3A CN109933046B (en) | 2019-03-21 | 2019-03-21 | Unmanned aerial vehicle undercarriage retraction controller test system |
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| CN201910218991.3A CN109933046B (en) | 2019-03-21 | 2019-03-21 | Unmanned aerial vehicle undercarriage retraction controller test system |
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| CN101532903A (en) * | 2009-04-08 | 2009-09-16 | 南京航空航天大学 | Drop test device for movable impact platform |
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