Onboard suspension object parallel test system and method with exclusive front end and multiplexing resource fusion

Abstract

The invention relates to an exclusive front end and reuse resource fused airborne suspension object parallel test system and method, and the system comprises a test control unit which is used for operating parallel test software; the switch is used for expanding an LAN interface for the test control unit; the program-controlled direct-current power supply can receive an instruction through the program-controlled interface, complete output power supply parameter configuration and simultaneously supply power to at least four tested pieces; the satellite signal transponder is used for distributing satellite signals to multiple paths of tested pieces through a power divider; the comprehensive test box is connected with the test control unit through an LAN (Local Area Network) interface via the switch; and a tested piece is connected through a cable. According to the test method, a multi-process framework and a naming shared memory mechanism are adopted, a host process and a plurality of client processes exchange data through a shared memory, it is ensured that the test processes of all tested pieces are completely parallel, and the total test time does not exceed the test duration of a single tested piece. The invention relates to the technical field of airborne suspension object ground parallel testing.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of airborne suspension ground parallel test, and particularly relates to a parallel test system and method for airborne suspension with exclusive front end and multiplexed resource fusion. BACKGROUND

[0002] Parallel test technology is relative to the traditional sequential test technology. The traditional sequential test can only test one parameter of one unit under test (UUT) at a time. Parallel test technology increases the number of devices under test in a unit of time to improve the throughput of the test system, reduces the idle time of instruments and processors to improve the utilization of test equipment, and saves test costs through sharing of valuable equipment. Parallel test technology will be more and more widely used in the field of automatic test. At present, parallel test technology has been introduced into the fields of weapon equipment test, satellite test, vehicle-mounted electronic product test, etc., and various dedicated parallel automatic test systems have been developed. The present application belongs to the field of airborne suspension test and relates to the field of ground test of electrical parameters of airborne suspension, and particularly relates to the development of a parallel test system for electrical parameters of airborne suspension.

[0003] Ten years ago, parallel test technology was in its infancy. Most domestic experts in the same field stayed in conceptual analysis and method research, and did not systematically study the actual development and organization of parallel test systems, that is, there was no engineering practice. In recent years, practical engineering of parallel test systems for various types of weapon equipment has gradually appeared in this field. Through investigation, these parallel test systems mostly use two types of technical solutions as shown in the following. Figure 1

[0004] The first scheme is composed of a test control unit 1, a test resource unit 2 and a switch module 3. The test control unit 1 controls each functional test resource unit 2 through software, and realizes the switching of the electrical circuit test channel through the control of the switch module 3. Each component of the test system is based on the PXI / CPCI bus, and the test system is connected with the device under test through a test cable. The first scheme only uses a set of hardware test resources based on the PXI / CPCI bus, has high standardization, realizes time-sharing multiplexing of all hardware resources through the switch module 3, reduces the demand for expensive test resource units of multiple UUTs, and significantly reduces the cost.

[0005] ​The system composition of the second scheme is similar to the first scheme, and in the design of the test resource unit 2, the resource redundancy configuration is adopted for the important signals with a long test period, so that the one-to-one full parallel test of the test resource and the DUT can be realized during the test of the important signals, and for other signals with a short test period or low importance, the time division multiplexing technology of the first scheme is used. The components of the test system are the same as those of the first scheme and are based on the PXI / CPCI bus, and the standardization degree is high. Compared with the first scheme, the full parallel processing of the key test process is realized by increasing the test resource configuration, and the test efficiency is significantly improved.

[0006] The two schemes above are standard parallel test methods for the ground test of the electrical parameters of the airborne suspension, and the test resources are based on the PXI / CPCI bus technology architecture, the system hardware is composed of a standard case, a high-performance embedded controller and a multifunctional modular card, and the hardware procurement and deployment cost is high. On the other hand, the system design is based on the hardware time division multiplexing architecture, and it should be pointed out that there is a competition conflict in the allocation of test resources in the two schemes. If the resource competition intensity is to be reduced to improve the test efficiency, the test cost will increase. This essentially reflects the trade-off between test efficiency and economic benefit. The hardware time division multiplexing architecture itself will bring a phenomenon of macro-parallel but micro-serial execution, so the total test time of the multi-UUT will exceed the test time of the single UUT to different degrees.

[0007] In summary, for the ground parallel test of the electrical parameters of the airborne suspension, if the multi-UUT parallel test time is required to be no more than the single UUT test time, and the relationship between the test efficiency and the test cost can be effectively considered, there is no good design scheme at present. SUMMARY The present application is directed to the ground parallel test of the electrical parameters of the airborne suspension, solves the problem that the prior art cannot simultaneously solve the test efficiency and economic cost, and further proposes a parallel test system and method of the airborne suspension with the fusion of exclusive front-end and multiplexing resources.

[0008] The technical scheme adopted by the present application to solve the above problem is: The present application proposes a parallel test system of the airborne suspension with the fusion of exclusive front-end and multiplexing resources, comprising: A test control unit is used for running parallel test software and controlling and interacting data with a program-controlled direct current power supply, a satellite signal transponder and a comprehensive test box; A switch is used for expanding a LAN interface for the test control unit; A program-controlled direct current power supply can receive instructions through a program-controlled interface to complete the output power parameter configuration and simultaneously supply power for at least four DUTs; Satellite signal transponder, receiving outdoor satellite signal, purifying satellite signal, distributing satellite signal to multiple measured objects through power divider; The comprehensive test box is connected through a LAN interface, a switch 7 and a test control unit, and is connected with the measured object through a cable.

[0009] Further, the comprehensive test box comprises a ZYNQ-based comprehensive test board for collecting analog and on-off quantities of the measured object, monitoring the power supply voltage and current of the measured object, outputting on-off and switching quantity control signals, and completing UART communication and 1553B communication.

[0010] Further, the parallel test software is used for completing the test instruction issuing, data interaction and test result evaluation of the multiple airborne suspensions, and focuses on realizing that the total test time length is not more than the single UUT test time length.

[0011] Further, the parallel test software comprises one main process and multiple client processes, the number of the client processes is the same as that of the measured objects, the main process is used for creating a named shared memory and managing a test interface, and the client process is used for reading a start flag signal in the shared memory to synchronously execute a test task and writing a result into the shared memory.

[0012] Further, the test control unit comprises a KVM switcher and a server, the KVM switcher is used for providing a display, a keyboard and a mouse for the server, the server is used for running the parallel test software and controlling and interacting data of the programmable direct-current power supply, the satellite signal transponder and the comprehensive test box through the switch, and is also used for storing data such as logs and test reports.

[0013] Further, the number of the comprehensive test boxes is four, the height of each comprehensive test box is 2U, and the width is only half of the normal cabinet slot width.

[0014] The application further provides an airborne suspension parallel test method of exclusive front end and multiplex resource fusion, comprising the following steps: Step 1, extending and deploying the comprehensive test box 5 to each measured object position; Step 2, running the parallel test software, and the main process creates a shared memory and listens to user instructions; Step 3, after the user triggers the test, the main process stores a start flag signal into the shared memory; Step 4, the client process reads the start flag signal and starts a test flow; Step 5, each client program stores a test state into the shared memory, the main process reads the test state in the shared memory to update the interface test result, and ensures that the total test time length is not greater than the single measured object test time length.

[0015] The beneficial effects of the present application are: 1、The present application proposes a parallel test system of airborne suspension object with exclusive front end and multiplexed resource fusion at the hardware level. The multiplexed resource can simultaneously meet the test requirements of four DUTs, and there is no resource competition compared with the common time-sharing multiplexing technology. At the software level, the named shared memory mechanism and multi-process architecture are adopted, and each DUT corresponds to a test process, and there is no waiting phenomenon due to resource scheduling. Therefore, the present application can realize constant time parallel test with the total parallel test time not exceeding the single UUT test time.

[0016] 2、The present application provides a low-cost, miniaturized and distributed-based exclusive front end, namely a comprehensive test box. Compared with the common test resources based on PXI, CPCI and the like interfaces, all the functional modules are integrated in a comprehensive test board in the present application, and no additional chassis is needed. The comprehensive test box has only 2U height, and the width is only half of the normal cabinet slot width. The present application supports customizable working temperature range while realizing low cost through highly customized and integrated design.

[0017] 3、The present application customizes the core test resources of the test system into an exclusive miniaturized test front end, and adopts LAN interface, so that as long as the test control unit, the program-controlled direct current power supply, the satellite signal transponder and the like multiplexed resources meet the requirements, the expansion of the number of DUTs can be easily realized at the hardware and software levels. BRIEF DESCRIPTION OF DRAWINGS

[0018] Fig. 1 is a diagram of two schemes of the prior art; Fig. 2 is a front / rear schematic view of a test system cabinet according to the present application; Fig. 3 is a schematic view of hardware connection of a test system according to the present application; Fig. 4 is a multi-process software architecture diagram according to the present application.

[0019] Reference numerals in the drawings are: 1-test control unit, 2-test resource unit, 3-switching module, 4-DUT, 5-comprehensive test box, 6-KVM switch, 7-switch, 8-server, 9-satellite signal transponder, 10-program-controlled direct current power supply, 11-power distribution unit, 12-power divider, 13-receiving antenna, 14-transmitting antenna, 15-interface converter, 16-parallel test software. DETAILED DESCRIPTION

[0020] Specific embodiment one: the present embodiment proposes a parallel test system of airborne suspension object with exclusive front end and multiplexed resource fusion, comprising: Test control unit: belongs to multiplexed resources, used to run parallel test software 16 and control and interact data with programmable direct current power supply 10, satellite signal repeater 9 and integrated test box 5. Parallel test software 16 is used to complete test instruction issuing, data interaction and test result evaluation for multiple airborne suspensions, and focuses on realizing that the total test time does not exceed the test time of a single UUT; Switch 7: expands LAN interface for test control unit 1; Programmable direct current power supply 10: belongs to multiplexed resources, which can receive instructions through a programmable interface to complete output power parameter configuration and provide working power for four DUTs; Satellite signal repeater 9: belongs to multiplexed resources, used to receive outdoor satellite signals and purify and forward the satellite signals; Power divider 12: used to divide or distribute the single-channel signal output by the satellite signal repeater; Integrated test box 5: a distributed dedicated front end, which integrates traditional test resource units 2 on a ZYNQ-based integrated test board, used to collect analog and on-off quantities from DUTs, monitor DUT power supply voltage and current, output on-off and switching quantities, complete UART communication and 1553B communication. Four integrated test boxes are connected through LAN interface, switch 7 and test control unit 1. The integrated test box 5 is connected with the DUT through a customized cable. The dedicated front end adopts highly customized and integrated design, which does not need standardized PXI / CPCI chassis and controller, significantly reducing the economic cost of the system.

[0021] Specific implementation method two: this implementation method proposes a parallel test method for airborne suspensions with the fusion of dedicated front end and multiplexed resources, which is divided into hardware and software two levels. At the hardware level, when there is no test task or the equipment needs to be moved, the integrated test box 5 can be stored in the cabinet. When executing the test task, since the DUTs are placed in different explosion-proof rooms in the actual scene, the test equipment in the test room needs to complete the parallel test of four airborne suspensions in different explosion-proof rooms. Therefore, a dedicated distributed hardware front end, i.e. integrated test box 5, is needed, which is extended to each DUT through LAN interface. In this way, the integrated test box 5 serves as a dedicated front end, and the test control unit 1, programmable direct current power supply 10, satellite signal repeater 9 and other resources serve as multiplexed resources, forming a parallel test system for airborne suspensions with the fusion of dedicated front end and multiplexed resources. Since the multiplexed resources are sufficient to meet the test requirements of four DUTs at the same time, there is no resource competition at the hardware level. The overall scheme of the system is shown in Figure 3 .

[0022] At the software level, the naming shared memory mechanism and the multi-process software architecture are adopted to divide the software into the main process and the client process. The naming shared memory is realized through file mapping, and one tested item corresponds to one client process. Since the address spaces of the processes are different, when an exception occurs in a process, the operating system will limit the exception in the single process, thereby avoiding affecting other processes, well playing an isolation role and effectively improving the software reliability. The main process and the client process interact through the shared memory for data and commands, and there is no resource competition at the software level. The overall scheme of the parallel test software is as shown in Figure 4

[0023] The test method specifically includes the following steps: Step 1. The extension of the comprehensive test box 5 is deployed to the position of each tested item. Step 2. The parallel test software 16 is run, and the main process creates the shared memory and listens to the user instructions. Step 3. After the user triggers the test, the main process stores the start flag signal into the shared memory. Step 4. The client process reads the start flag signal and starts the test flow. Step 5. Each client program stores the test state into the shared memory, and the main process polls and reads the test state in the shared memory to update the interface test result, ensuring that the total test time length is not greater than the test time length of a single tested item.

[0024] Embodiment: Referring to FIG. 2, four comprehensive test boxes 5, a KVM switch 6, a switch 7, a server 8, a satellite signal transponder 9, a programmable direct current power supply 10 and a power distribution unit 11 are assembled into a 15U cabinet to form an airborne suspension parallel test system with exclusive front-end and multiplexed resource fusion, wherein the KVM switch 6 and the server 8 jointly form a test control unit 1.

[0025] Referring to FIG. 3, the process and the use method of the application are further described in detail: 1. The model of the tested item is selected. 2. The test items, signal characteristics and technical indicators are listed according to the test requirements. 3. The selection of the KVM switch 6, the switch 7, the server 8, the satellite signal transponder 9, the power divider 12 and the programmable direct current power supply 10 is completed: 1) The KVM switch 6 provides a display, a keyboard and a mouse for the server 8. 2) The switch 7 expands the multi-path LAN interface for the server 8. ​3) Server 8: used to run the parallel test software 16 and control and interact data with the programmable DC power supply 10, the satellite signal repeater 9 and the integrated test box 5 through the switch 7. The server 8 is also used to store data such as logs and test reports; 4) Satellite signal repeater 9: the satellite positioning test and integrated navigation test are included in the electrical parameter test items, and the satellite signal repeater 9 is needed to receive the outdoor satellite signal through the receiving antenna 13, purify the satellite signal, and then retransmit the purified signal to the measured piece through the transmitting antenna 14. At the same time, the satellite signal repeater 9 uploads the star condition and positioning state to the server 8 through the interface converter 15; 5) Power divider 12: used to divide or distribute the single-channel signal output by the satellite signal repeater 9; 6) Programmable DC power supply 10: the server 8 sends programmable commands through the interface converter 15 to complete the output power parameter configuration, and at the same time provides working power for the four measured pieces; 4. Develop four integrated test boxes 5: The integrated test box 5 is a distributed hardware front end, which is used to collect analog and on-off quantities from the measured piece, monitor the power supply voltage and current of the measured piece, output on-off and switching quantities, complete UART communication and 1553B communication. The integrated test box 5 is connected through the LAN interface through the switch 7 and the server 8, and is connected through the custom cable and the measured piece. Its size is only 2U high, and the width is only half of the normal cabinet slot width.

[0026] 1) Develop an integrated test board based on ZYNQ; 2) Assemble the integrated test board, 1553B coupler, switching power supply, solid-state relay, etc. into an integrated test box 5; 5. Custom test cable, connect the measured piece and the integrated test box 5; 6. Develop parallel test software 16: Referring to FIG. 4, the parallel test software 16 is divided into one main process and four client processes. After the software is run, the main process creates a shared memory. After the user clicks the start test button, the start flag signal is stored in the shared memory, and the client process reads the start flag signal to start the test program. Each client program stores the test state in the shared memory, and the main process polls the test state in the shared memory to update the interface test result, thereby completing the electrical parameter test of the four measured pieces at the same time, and the total test time is not greater than the single UUT test time. The specific development process of the parallel test software 16 is as follows: 1) First, develop the test flow of a single UUT as one of the four client processes; 2) The software is divided into main process and client process by using the mechanism of naming shared memory and multi-process software architecture. The main process is responsible for loading the test interface, sorting and distinguishing the test data from the four client processes, and updating the interface test results. The client process is responsible for completing the detailed test process. The main process and the client process interact through shared memory for data and commands, and each client process is isolated from each other; 7. Build a distributed parallel test system and deploy parallel test software 16; 8. Place the test system cabinet in the test room, extend the four integrated test boxes to the vicinity of the corresponding DUTs through the LAN interface, and connect the integrated test box 5 and the DUT through the test cable; 9. Turn on the program-controlled DC power supply 10 and the satellite signal transponder 9, start the parallel test software 16, complete the parallel test of the electrical parameters of the four DUTs, and save the test report.

[0027] The above is only the preferred embodiment of the present application, and is not intended to limit the present application in any form. Although the present application has been disclosed as above with the preferred embodiment, it is not intended to limit the present application. Any person skilled in the art can make some changes or modifications to the above disclosed technical content without departing from the scope of the technical solution of the present application, and any simple modification, equivalent replacement and improvement of the above embodiment within the scope of the technical solution of the present application, the technical essence of the present application, and the spirit and principles of the present application are all within the protection scope of the present application.

Claims

1. An airborne pylon parallel test system with exclusive front end and multiplexed resource consolidation, characterized in that, The application relates to a parallel test system for multiple pieces of satellite equipment, which comprises the following parts: a test control unit for running parallel test software (16) and controlling and interacting data with a programmable direct current power supply (10), a satellite signal repeater (9) and a comprehensive test box (5); a switch (7) for expanding a LAN interface for the test control unit; the programmable direct current power supply (10) can receive instructions through a programmable interface, complete output power parameter configuration and simultaneously supply power for at least four pieces of measured equipment; the satellite signal repeater (9) receives outdoor satellite signals, purifies the satellite signals and distributes the satellite signals to multiple pieces of measured equipment through a power divider (12); the comprehensive test box (5) is connected with the test control unit through the switch (7) and the LAN interface and is connected with the measured equipment through a cable.

2. The exclusive front end and multiplexed resource converged airborne pod parallel test system of claim 1, wherein, The comprehensive test box (5) comprises a comprehensive test board based on ZYNQ, which is used for collecting analog and on-off quantities of the measured equipment, monitoring power supply voltage and current of the measured equipment, outputting on-off and switching control signals and completing UART communication and 1553B communication.

3. The exclusive front end and multiplexed resource consolidated airborne pod parallel test system of claim 1, wherein, The parallel test software (16) is used for completing test instruction issuing, data interaction and test result evaluation of multiple pieces of airborne suspension and mainly realizes that the total test time length is not longer than the test time length of single measured equipment.

4. The exclusive front end and multiplexed resource consolidated airborne pod parallel test system of claim 1, wherein, The parallel test software (16) comprises one main process and multiple client processes, the number of the client processes is the same as that of the measured equipment, the main process is used for creating a named shared memory and managing a test interface, and the client process is used for reading a start flag signal in the shared memory, synchronously executing a test task and writing a result into the shared memory.

5. The exclusive front end and multiplexed resource consolidated airborne pod parallel test system of claim 1, wherein, The test control unit comprises a KVM switch (6) and a server (8), the KVM switch (6) is used for providing a display, a keyboard and a mouse for the server (8); the server (8) is used for running the parallel test software (16), controlling and interacting data with the programmable direct current power supply (10), the satellite signal repeater (9) and the comprehensive test box (5) through the switch (7) and storing log and test report data.

6. The dedicated front end and multiplexed resource consolidated airborne pod parallel test system of claim 1, wherein, The number of the comprehensive test boxes (5) is four, and the height of each comprehensive test box (5) is 2U.

7. A method for parallel testing of airborne pendants with exclusive front-ends and multiplexed resources, characterized by, The application further discloses a parallel test method for multiple pieces of satellite equipment, which comprises the following steps: Step 1: extending and deploying the comprehensive test box (5) to the positions of the measured equipment; Step 2: running the parallel test software (16), creating a shared memory by the main process and listening to user instructions; Step 3: after the user triggers the test, the main process stores a start flag signal into the shared memory; Step 4: the client process reads the start flag signal and starts a test flow; Step 5: each client program stores a test state into the shared memory, the main process reads the test state in the shared memory and updates a test result on an interface, and the total test time length is not longer than the test time length of single measured equipment.

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