CN104656632A - Integrated interface test system and detection method for aircraft semi-physical simulation tests - Google Patents

Integrated interface test system and detection method for aircraft semi-physical simulation tests Download PDF

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CN104656632A
CN104656632A CN201410637947.3A CN201410637947A CN104656632A CN 104656632 A CN104656632 A CN 104656632A CN 201410637947 A CN201410637947 A CN 201410637947A CN 104656632 A CN104656632 A CN 104656632A
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bus
integrated interface
signal
rcs
aircraft
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CN104656632B (en
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王炀
张振兴
张广春
李杰奇
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China Academy of Launch Vehicle Technology CALT
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    • GPHYSICS
    • G05CONTROLLING; REGULATING
    • G05BCONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B23/00Testing or monitoring of control systems or parts thereof
    • G05B23/02Electric testing or monitoring
    • G05B23/0205Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
    • G05B23/0208Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
    • G05B23/0216Human interface functionality, e.g. monitoring system providing help to the user in the selection of tests or in its configuration

Abstract

The invention provides an integrated interface test system and detection method for aircraft semi-physical simulation tests. A concentrated test and management method is adopted for various bus interface types in an aircraft semi-physical simulation system, and signal stimulation, acquisition and analysis are carried out by one set of hardware middleware and one set of test software in a unified manner. All communication links between external simulation equipment and tested objects such as a flight control computer, a steering engine and a RCS electromagnetic valve are verified through few test times, concentrated control and distributed processing on different bus interface types are realized, the coupling degree between each equipment in the test system and a test piece can be reduced, system-level comprehensive communication failures can be rapidly positioned, and the development and detection efficiency of the semi-physical simulation test system can be obviously improved.

Description

The integrated interface test macro of aircraft semi-physical simulation and detection method
Technical field
The present invention relates to integrated interface test macro and the detection method of aircraft semi-physical simulation, belong to aerospace flight vehicle semi-physical simulation field.
Background technology
Aircraft semi-physical system integrated, needs emulator various in system and subjects organically to connect into an entirety, exchanges information, collaborative work.Therefore, the problem of communication connection and information interaction between equipment and test specimen must be solved.
Along with contemporary aircraft function is powerful all the more, the number of devices of corresponding semi-physical system is more various, communication type is more complicated, there is marked difference in electrical specification and the communications protocol of different communication interface, point-to-point, a large amount of communication tests is carried out between equipment according to classic method, intricate operation, consuming time, once occur that comprehensive, system-level communication failure is difficult to carry out multianalysis and quick position.
Summary of the invention
The technical matters that the present invention solves is: overcome prior art deficiency, integrated interface test macro and the detection method of aircraft semi-physical simulation are provided, for the multiple bus interface type in aircraft semi-physical system, adopt the method for integrated test and management, a set of Hardware Middleware and the unification of a set of testing software is utilized to carry out signal excitation, gather and analyze, by less test number (TN) to flying control machine, steering wheel, all communication links between subjects and outside emulator such as RCS solenoid valve are verified, achieve the centralized control to different bus interface type and distribution process, the degree of coupling between each equipment and test specimen in pilot system can be reduced, quick positioning system level, comprehensive communication failure, exploitation and the detection efficiency of semi-physical simulation test system can be significantly improved.
The technical scheme that the present invention solves is: the integrated interface test macro of aircraft semi-physical simulation, comprises the conditioning of integrated interface adaptation case, fiber reflection memory switch, integrated interface test and management computing machine; Integrated interface adaptation conditioning case comprises RS-422 interface module, 1553B interface module, DO interface module and monitoring panel; The VMIC-5565 board of integrated interface test and management allocation of computer GE company, the CP-118-UI board of MOXA company, the PCI-1553-2 board of Alta company, the PCI-1756 board of Yan Hua company, dispose Windows+RTX real-time system environment and interface testing management software;
Under normal condition:
Integrated interface adaptation conditioning case utilizes 1553B bus to receive rudderpost stroke state signal from the steering wheel of aircraft, utilizes DO bus to receive RCS jet flow status signal from the solenoid valve of aircraft thrust reaction control system(RCS) (RCS); Integrated interface adaptation conditioning case utilizes 1553B interface module the connector of the 1553B bus of aircraft steering engine to be adapted to the standard interface of the PCI-1553-2 board that Alta company produces, utilize the 5V signal that the PCI-1756 board of the 27V signal condition Cheng Yanhua company of the DO bus of aircraft RCS solenoid valve can process by DO interface module, then respectively by 1553B bus and DO bus, the RCS jet flow status signal after the rudderpost stroke state signal after adaptation and conditioning is delivered to monitoring panel and the integrated interface test and management computing machine that integrated interface adaptation nurses one's health case;
Integrated interface test and management computing machine utilizes the rudderpost stroke state signal after the adaptation in the PCI-1553-2 board reception 1553B bus of Alta company, utilize the RCS jet flow status signal after the conditioning in the PCI-1756 board reception DO bus of Yan Hua company, under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, rudderpost stroke state signal and RCS jet flow status signal are decoded and shown, utilize the VMIC-5565 board of GE company that the decoded value of rudderpost stroke state signal and RCS jet flow status signal is sent to fiber reflection memory switch by optical fiber cable simultaneously,
The decoded value of the rudderpost stroke state signal that the integrated interface test and management computing machine on fiber reflection memory switch reception optical fiber cable sends and RCS jet flow status signal, and by optical fiber cable, the decoded value of rudderpost stroke state signal and RCS jet flow status signal is forwarded to outside emulator, calculate for navigation data;
Meanwhile, fiber reflection memory switch receives by optical fiber cable the navigation data signal that outside emulator calculates, and is forwarded to integrated interface test and management computing machine by optical fiber cable;
Integrated interface test and management computing machine utilizes the VMIC-5565 board of GE company to receive the navigation data signal that on optical fiber cable, outside emulator is sent here, show under Windows+RTX real-time system environment, simultaneously according to the communications protocol that semi-physical simulation specifies, encode to navigation data signal, navigation data encoding value is sent to integrated interface adaptation conditioning case by RS-422 bus by the CP-118-UI board of recycling MOXA company;
Integrated interface adaptation conditioning case receives the navigation data encoding value in RS-422 bus, what utilize RS-422 interface module that navigation data coding is sent to the integrated interface adaptation conditioning monitoring panel of case and aircraft by RS-422 bus simultaneously flies control machine, and the rudderpost stroke state signal for steering wheel exports and the RCS jet flow status signal output of RCS solenoid valve.
The integrated interface test macro of aircraft semi-physical simulation and detection method, comprise outside emulator detection-phase and subjects detection-phase,
Described outside emulator detection-phase is as follows:
(1) integrated interface adaptation conditioning case is connected with the 1553B bus between integrated interface test and management computing machine and DO bus disconnects;
(2) integrated interface test and management computing machine is under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, generate the rudderpost stroke state signal of steering wheel of aircraft and the decoded value of the RCS jet flow status signal of RCS solenoid valve;
(3) utilize the VMIC-5565 board of GE company that the decoded value of the rudderpost stroke state signal of step (2) and RCS jet flow status signal is sent to fiber reflection memory switch by optical fiber cable, by fiber reflection memory switch, the decoded value of rudderpost stroke state signal and RCS jet flow status signal is forwarded to emulator, calculates for navigation data;
(4) navigation data signal that calculated by optical fiber cable receiving step (3) outside emulator of fiber reflection memory switch, and be forwarded to integrated interface test and management computing machine by optical fiber cable;
(5) integrated interface test and management computing machine utilizes the VMIC-5565 board of GE company to receive the navigation data signal of the step (4) that emulator is sent here on optical fiber cable, shows under Windows+RTX real-time system environment;
(6) result shown according to step (5) judges whether navigation data signal meets the communications protocol requirement of semi-physical simulation; If do not have navigation data signal to show, illustrate that the hardware communication equipment of outside emulator breaks down; If there is navigation data signal to show, but navigation data signal numerical value does not meet the communications protocol requirement of semi-physical simulation, illustrates that mistake appears in the software programming of outside emulator;
Described subjects detection-phase is as follows:
(7) optical fiber cable between fiber reflection memory switch with integrated interface test and management computing machine is connected disconnects;
(8) integrated interface test and management computing machine is under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, generate the coding of navigation data signal, navigation data encoding value is sent to integrated interface adaptation conditioning case by RS-422 bus by the CP-118-UI board of recycling MOXA company;
(9) integrated interface adaptation conditioning case receives the navigation data encoding value in RS-422 bus, what utilize RS-422 interface module that the navigation data of step (8) coding is sent to the integrated interface adaptation conditioning monitoring panel of case and aircraft by RS-422 bus simultaneously flies control machine, and the rudderpost stroke state signal for steering wheel exports and the RCS jet flow status signal output of RCS solenoid valve;
(10) integrated interface adaptation conditioning case utilizes 1553B bus to receive rudderpost stroke state signal from the steering wheel of aircraft, utilizes DO bus to receive RCS jet flow status signal from the solenoid valve of the RCS of aircraft;
(11) integrated interface adaptation conditioning case utilizes 1553B interface module the connector of the 1553B bus of aircraft steering engine to be adapted to the standard interface of the PCI-1553-2 board that Alta company produces, utilize DO interface module by the manageable 5V signal of PCI-1756 board of the 27V signal condition Cheng Yanhua company of the DO bus of aircraft RCS solenoid valve, then respectively the RCS jet flow status signal after the rudderpost stroke state signal after adaptation and conditioning will be delivered to monitoring panel and the integrated interface test and management computing machine of integrated interface adaptation conditioning case by 1553B bus and DO bus,
(12) integrated interface test and management computing machine utilizes the PCI-1553-2 board of Alta company to receive the rudderpost stroke state signal of the step (11) in 1553B bus, the PCI-1756 board of Yan Hua company is utilized to receive the RCS jet flow status signal of the step (11) in DO bus, under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, rudderpost stroke state signal and RCS jet flow status signal are decoded and shown;
(13) judge whether data meet the communications protocol requirement of semi-physical simulation according to the result of the display of step (12); If there is no rudderpost stroke state signal or the display of RCS jet flow status signal, illustrate that the hardware communication equipment of the control machine that flies of aircraft, steering wheel or RCS solenoid valve breaks down, can standard test equipment be utilized, measure by the output of monitoring panel to 1553B bus, DO bus and RS-422 bus of integrated interface adaptation conditioning case and investigate fault; If have rudderpost stroke state signal and the display of RCS jet flow status signal, but rudderpost stroke state signal or RCS jet flow status signal numerical value do not meet the communications protocol requirement of semi-physical simulation, illustrate that mistake appears in the software programming that the control machine that flies of aircraft, steering wheel or RCS solenoid valve are relevant.
The present invention's advantage is compared with prior art:
(1) the present invention utilizes integrated interface adaptation conditioning case to achieve integrated process to three kinds of bus interface types such as 1553B, DO and RS-422 in aircraft semi-physical system, comprise interface adaptation and signal condition function, can the signal unification in above-mentioned three kinds of buses be exported to external unit and carry out integration testing, avoid and carry out point-to-pointly testing one by one to various interface type under system communication failure condition, solve the integrated process problem of different bus interface type, significantly improve the efficiency of system communications link testing.
(2) the present invention utilizes integrated interface adaptation conditioning case, under system communication failure condition, can not abort process, directly by monitoring panel, three kinds of bus signals such as 1553B, DO and RS-422 are measured, solve the quick detection and positioning problem of hardware interface and cable fault.
(3) the present invention utilizes integrated interface test and management computing machine to monitor in real time and data transmission the three kinds of bus interface signals of 1553B, DO and RS-422 etc. in aircraft semi-physical system, pumping signal can be produced in communication failure situation, with fly the subjects such as control machine, steering wheel, RCS solenoid valve or outside emulator carries out independent communication, reduce the degree of coupling of equipment room communication in semi-physical system, realize the quick detection to system communication fault, analysis and location.
(4) the present invention proposes a kind of graphical write method of communication test program, establish RS-422, 1553B, the signal of DO and fiber reflection internal memory network exports and acquisition module, data framing conciliates frame module and typical pumping signal module, can to be connected with module input/output relation by the configuration of simple module parameter and to realize writing of test case program, communication test program and communications protocol document is made to have two-way retrospective close relation, have without the need to hand-written code, fast, intuitively, the advantage such as reusable, reliability and the work efficiency of communication test can be improved.
Accompanying drawing explanation
Fig. 1 is present system Organization Chart;
Fig. 2 is integrated interface of the present invention adaptation conditioning case schematic diagram;
Fig. 3 is the basic module of interface management software of the present invention;
Fig. 4 is present system operating process.
Embodiment
Basic ideas of the present invention are: the integrated interface test macro and the detection method that provide aircraft semi-physical simulation, for the 1553B in aircraft semi-physical system, DO, three kinds of bus interface types such as RS-422, integrated interface adaptation conditioning case is adopted to carry out interface adaptation and signal condition, signal excitation is carried out by integrated interface test and management computing machine, gather and display, and then realization is to the integrated test of three kinds of bus signals and management, the degree of coupling between each equipment and test specimen in pilot system can be reduced, quick positioning system level, comprehensive communication failure, exploitation and the detection efficiency of semi-physical simulation test system can be significantly improved.
Be described in further detail the present invention below in conjunction with accompanying drawing, as shown in Figure 1, the integrated interface test macro of aircraft semi-physical simulation, comprises the conditioning of integrated interface adaptation case, fiber reflection memory switch, integrated interface test and management computing machine; Integrated interface adaptation conditioning case comprises RS-422 interface module, 1553B interface module, DO interface module and monitoring panel; The VMIC-5565 board of GE company of the integrated interface test and management allocation of computer U.S. (General Electric Company), the CP-118-UI board of MOXA company (Taiwan MOXA Science and Technology Co., Ltd.), the PCI-1553-2 board of Alta company of the U.S. (Alta Data Technologies Company), the PCI-1756 board of Yan Hua company (Yanhua Co., Ltd), dispose Windows+RTX real-time system environment and interface testing management software;
Under normal condition:
Integrated interface adaptation conditioning case utilizes 1553B bus to receive rudderpost stroke state signal from the steering wheel of aircraft, utilizes DO bus to receive RCS jet flow status signal from the solenoid valve of aircraft thrust reaction control system(RCS) (RCS); Integrated interface adaptation conditioning case utilizes 1553B interface module the connector of the 1553B bus of aircraft steering engine to be adapted to the standard interface of the PCI-1553-2 board that Alta company produces, utilize the 5V signal that the PCI-1756 board of the 27V signal condition Cheng Yanhua company of the DO bus of aircraft RCS solenoid valve can process by DO interface module, then respectively by 1553B bus and DO bus, the RCS jet flow status signal after the rudderpost stroke state signal after adaptation and conditioning is delivered to monitoring panel and the integrated interface test and management computing machine that integrated interface adaptation nurses one's health case; By integrated interface adaptation conditioning case to the integrated process of 1553B, DO bus signals, achieve and input to unified for different bus signals the function that an external unit carries out concentrated collection, display and analysis, to avoid under system fault conditions the point-to-point test that different signal types carries out one by one, the work efficiency of system communications link fault detect and location can be significantly improved;
Integrated interface test and management computing machine utilizes the rudderpost stroke state signal after the adaptation in the PCI-1553-2 board reception 1553B bus of Alta company, utilize the RCS jet flow status signal after the conditioning in the PCI-1756 board reception DO bus of Yan Hua company, under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, rudderpost stroke state signal and RCS jet flow status signal are decoded and shown, utilize the VMIC-5565 board of GE company that the decoded value of rudderpost stroke state signal and RCS jet flow status signal is sent to fiber reflection memory switch by optical fiber cable simultaneously, utilize the fiber reflection internal memory mechanics of communication of VMIC-5565, achieve the high-speed transfer of rudderpost stroke state signal and RCS jet flow status signal, greatly reduce the system communication time delay that intermediate equipment causes,
The decoded value of the rudderpost stroke state signal that the integrated interface test and management computing machine on fiber reflection memory switch reception optical fiber cable sends and RCS jet flow status signal, and by optical fiber cable, the decoded value of rudderpost stroke state signal and RCS jet flow status signal is forwarded to outside emulator, calculate for navigation data;
Meanwhile, fiber reflection memory switch receives by optical fiber cable the navigation data signal that outside emulator calculates, and is forwarded to integrated interface test and management computing machine by optical fiber cable;
Integrated interface test and management computing machine utilizes the VMIC-5565 board of GE company to receive the navigation data signal that on optical fiber cable, outside emulator is sent here, show under Windows+RTX real-time system environment, simultaneously according to the communications protocol that semi-physical simulation specifies, encode to navigation data signal, navigation data encoding value is sent to integrated interface adaptation conditioning case by RS-422 bus by the CP-118-UI board of recycling MOXA company; Thus achieve the integrative display to 1553B, DO, RS-422 tri-kinds of bus signals by integrated interface test and management computing machine simultaneously, and can under system communication failure condition, not abort process, the bus type that express-analysis is broken down;
Integrated interface adaptation conditioning case receives the navigation data encoding value in RS-422 bus, what utilize RS-422 interface module that navigation data coding is sent to the integrated interface adaptation conditioning monitoring panel of case and aircraft by RS-422 bus simultaneously flies control machine, and the rudderpost stroke state signal for steering wheel exports and the RCS jet flow status signal output of RCS solenoid valve; Consistent with the effect of integrated process 1553B and DO bus to the integrated effect of RS-422 bus interface type;
The detection method of the integrated interface test macro of aircraft semi-physical simulation, comprise outside emulator detection-phase and subjects detection-phase, this detection method can utilize integrated interface test and management computing machine to produce pumping signal in communication failure situation, with fly the subjects such as control machine, steering wheel, RCS solenoid valve or outside emulator carries out independent communication, reduce the degree of coupling of equipment room communication in semi-physical system, realize the quick detection to system communication fault, analysis and location
Described outside emulator detection-phase is as follows:
(1) integrated interface adaptation conditioning case is connected with the 1553B bus between integrated interface test and management computing machine and DO bus disconnects;
(2) integrated interface test and management computing machine is under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, generate the rudderpost stroke state signal of steering wheel of aircraft and the decoded value of the RCS jet flow status signal of RCS solenoid valve;
(3) utilize the VMIC-5565 board of GE company that the decoded value of the rudderpost stroke state signal of step (2) and RCS jet flow status signal is sent to fiber reflection memory switch by optical fiber cable, by fiber reflection memory switch, the decoded value of rudderpost stroke state signal and RCS jet flow status signal is forwarded to emulator, calculates for navigation data;
(4) navigation data signal that calculated by optical fiber cable receiving step (3) outside emulator of fiber reflection memory switch, and be forwarded to integrated interface test and management computing machine by optical fiber cable;
(5) integrated interface test and management computing machine utilizes the VMIC-5565 board of GE company to receive the navigation data signal of the step (4) that emulator is sent here on optical fiber cable, shows under Windows+RTX real-time system environment;
(6) result shown according to step (5) judges whether navigation data signal meets the communications protocol requirement of semi-physical simulation; If do not have navigation data signal to show, illustrate that the hardware communication equipment of outside emulator breaks down; If there is navigation data signal to show, but navigation data signal numerical value does not meet the communications protocol requirement of semi-physical simulation, illustrates that mistake appears in the software programming of outside emulator;
Described subjects detection-phase is as follows:
(7) optical fiber cable between fiber reflection memory switch with integrated interface test and management computing machine is connected disconnects;
(8) integrated interface test and management computing machine is under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, generate the coding of navigation data signal, navigation data encoding value is sent to integrated interface adaptation conditioning case by RS-422 bus by the CP-118-UI board of recycling MOXA company;
(9) integrated interface adaptation conditioning case receives the navigation data encoding value in RS-422 bus, what utilize RS-422 interface module that the navigation data of step (8) coding is sent to the integrated interface adaptation conditioning monitoring panel of case and aircraft by RS-422 bus simultaneously flies control machine, and the rudderpost stroke state signal for steering wheel exports and the RCS jet flow status signal output of RCS solenoid valve;
(10) integrated interface adaptation conditioning case utilizes 1553B bus to receive rudderpost stroke state signal from the steering wheel of aircraft, utilizes DO bus to receive RCS jet flow status signal from the solenoid valve of the RCS of aircraft;
(11) integrated interface adaptation conditioning case utilizes 1553B interface module the connector of the 1553B bus of aircraft steering engine to be adapted to the standard interface of the PCI-1553-2 board that Alta company produces, utilize DO interface module by the manageable 5V signal of PCI-1756 board of the 27V signal condition Cheng Yanhua company of the DO bus of aircraft RCS solenoid valve, then respectively the RCS jet flow status signal after the rudderpost stroke state signal after adaptation and conditioning will be delivered to monitoring panel and the integrated interface test and management computing machine of integrated interface adaptation conditioning case by 1553B bus and DO bus,
(12) integrated interface test and management computing machine utilizes the PCI-1553-2 board of Alta company to receive the rudderpost stroke state signal of the step (11) in 1553B bus, the PCI-1756 board of Yan Hua company is utilized to receive the RCS jet flow status signal of the step (11) in DO bus, under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, rudderpost stroke state signal and RCS jet flow status signal are decoded and shown;
(13) judge whether data meet the communications protocol requirement of semi-physical simulation according to the result of the display of step (12); If there is no rudderpost stroke state signal or the display of RCS jet flow status signal, illustrate that the hardware communication equipment of the control machine that flies of aircraft, steering wheel or RCS solenoid valve breaks down, can standard test equipment be utilized, measure by the output of monitoring panel to 1553B bus, DO bus and RS-422 bus of integrated interface adaptation conditioning case and investigate fault; If have rudderpost stroke state signal and the display of RCS jet flow status signal, but rudderpost stroke state signal or RCS jet flow status signal numerical value do not meet the communications protocol requirement of semi-physical simulation, illustrate that mistake appears in the software programming that the control machine that flies of aircraft, steering wheel or RCS solenoid valve are relevant.
As shown in Figure 2, in the present invention, the key of hardware plan is integrated interface adaptation conditioning case, and on communication line between outside subjects with integrated interface test and management computing machine, connector mates and the conditioning of communication signal voltage.It is primarily of signaling interface and detect panel two parts composition.Signaling interface comprises RS-422 interface module, 1553B interface module and DO interface module.
1553B interface module one has A, B two-way, adopts 2 ESI-310 chips to carry out one turn of two design respectively, and output signal directly sends to integrated interface test and management computing machine and monitoring panel.
RS422 interface module is directly connected with subjects and integrated interface test and management computing machine, can also be switched on control and measuring interface carry out external detection by the Signal-controlled switch of monitoring panel.
DO module drive controls high_voltage isolation optocoupler TLP627 and produces output signal, and output voltage size has been come by regulating rear panel potentiometer.DO output and electric current surpass flow monitoring circuit and form voltage comparator by LM324; detect each road and flow through 50 Ohmage DO output currents; when electric current transfinites (100mA); comparer upset exports high level; fault is locked by logical trigger; produce prompting buzzing, and cut off output supply voltage simultaneously, protection external circuit is injury-free.
The monitoring panel of integrated interface adaptation conditioning case comprises the monitoring terminal of total power switch, DO output voltage monitoring gauge outfit, DO output voltage potentiometer, DO output reset switch and 1553B, RS422, DO module.
As shown in Figure 3, in integrated interface test and management computing machine, the running environment of interface management software is Windows+RTX real-time system, Matlab/Simulink compiler is utilized to carry out communication program modeling and automatic code conversion, by the data flow state of gui interface monitor-interface in program operation process.In communication program compiling procedure, software provides three class basic model storehouses, and major function is as follows:
(1) typical pumping signal
Utilize communication interface to export typical pumping signal at program run duration, comprise five classes such as constant value signal, step signal, ramp signal, clock signal, square-wave signal.
(2) data framing conciliates frame
At program run duration, the module in data framing model bank converts the data type of specifying according to the protocol requirement of communication interface to input data, and according to the sequential arrangement of specifying, exports to the module in signal output model storehouse.Data framing comprises scale-of-two array to decimal data conversion, double precision type data to integer, the functional modules such as scale-of-two code bit is arranged, empty coding.
Module in data solution frame model bank, at program run duration, converts input data the data type of specifying to and according to the sequential arrangement of specifying, carries out interface data display according to the protocol requirement of communication interface.Data solution frame comprises decimal data to scale-of-two array, integer to functions such as double precision type, the acquisitions of scale-of-two code bit.
Data check comprise and verify, exclusive or check two kinds of methods.
(3) signal exports and gathers
Signal exports and gathers and is mainly used in driving hardware communication board to carry out data output or data acquisition according to the clock period of specifying, comprise the interface type such as RS-422, MIL-STD-1553B, DO and fiber reflection internal memory, the characteristics such as board port numbers, timing cycle and protocol code parameter can be configured by interactive interface.
Above-mentioned software adopts patterned way system for writing and compiling interface testing program, both the mistake that hand-written code causes had been avoided, improve code by operations such as interface configurations and signal relation connections again and write efficiency, final establishing between interface communication protocol document and program interface framework two-wayly reviews relation, and any problem in test and process of the test can be located efficiently.
As shown in Figure 4, Dynamic System flow process is as follows:
(1) hardware device connects
According to the signal wiring relation that Fig. 1 describes, connect the subjects of semi-physical system and outside emulator;
(2) communication program is write
Select according to the input/output relation of interface various between emulator and subjects and the communications protocol of interface, connect and configuration basic module, the communication program of construction system, utilizes Simulink Coder that patterned program frame is compiled into the executable program file of program codes;
(3) communication program is run
In Windows+RTX environment, run communication program, utilize gui interface to observe the data flow state of interface.In data transfer, the present invention serves two Main Functions: first is connect the communication link also between Matching Experiment object and outside emulator, second is produce pumping signal on communication link, gathers and records all communication datas, carry out interpretation for testing crew.
(4) test terminates
If the output signal of gui interface display total interface is all correct, can confirm that system interface state is normal, experimental test terminates.
(5) hardware device detects
If gui interface show certain interface do not export data display time, need to utilize oscilloscope apparatus to test at the monitoring panel of integrated interface adaptation conditioning case further, if still do not have signal to export, hardware link generation hardware fault between outside emulator or subjects is described, pending fault restarts step (3) after solving;
(6) software program detects
If gui interface show certain interface to signal data show, but data result is not right, illustrates that the program code of outside emulator or subjects and configuration are broken down, and pending fault restarts step (3) after solving;
Non-elaborated part of the present invention belongs to techniques well known.

Claims (2)

1. the integrated interface test macro of aircraft semi-physical simulation, is characterized in that: comprise the conditioning of integrated interface adaptation case, fiber reflection memory switch, integrated interface test and management computing machine; Integrated interface adaptation conditioning case comprises RS-422 interface module, 1553B interface module, DO interface module and monitoring panel; Integrated interface test and management allocation of computer VMIC-5565 board, CP-118-UI board, PCI-1553-2 board, PCI-1756 board, dispose Windows+RTX real-time system environment and interface testing management software;
Under normal condition:
Integrated interface adaptation conditioning case utilizes 1553B bus to receive rudderpost stroke state signal from the steering wheel of aircraft, utilizes DO bus to receive RCS jet flow status signal from the solenoid valve of aircraft thrust reaction control system(RCS) RCS; Integrated interface adaptation conditioning case utilizes 1553B interface module the connector of the 1553B bus of aircraft steering engine to be adapted to the standard interface of the PCI-1553-2 board that Al ta company produces, utilize the 5V signal that the 27V signal condition of the DO bus of aircraft RCS solenoid valve becomes PCI-1756 board to process by DO interface module, then respectively by 1553B bus and DO bus, the RCS jet flow status signal after the rudderpost stroke state signal after adaptation and conditioning is delivered to monitoring panel and the integrated interface test and management computing machine that integrated interface adaptation nurses one's health case;
Integrated interface test and management computing machine utilizes the rudderpost stroke state signal after the adaptation in PCI-1553-2 board reception 1553B bus, utilize the RCS jet flow status signal after the conditioning in PCI-1756 board reception DO bus, under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, rudderpost stroke state signal and RCS jet flow status signal are decoded and shown, utilize VMIC-5565 board that the decoded value of rudderpost stroke state signal and RCS jet flow status signal is sent to fiber reflection memory switch by optical fiber cable simultaneously,
The decoded value of the rudderpost stroke state signal that the integrated interface test and management computing machine on fiber reflection memory switch reception optical fiber cable sends and RCS jet flow status signal, and by optical fiber cable, the decoded value of rudderpost stroke state signal and RCS jet flow status signal is forwarded to outside emulator, calculate for navigation data;
Meanwhile, fiber reflection memory switch receives by optical fiber cable the navigation data signal that outside emulator calculates, and is forwarded to integrated interface test and management computing machine by optical fiber cable;
Integrated interface test and management computing machine utilizes VMIC-5565 board to receive the navigation data signal that on optical fiber cable, outside emulator is sent here, show under Windows+RTX real-time system environment, simultaneously according to the communications protocol that semi-physical simulation specifies, encode to navigation data signal, navigation data encoding value is sent to integrated interface adaptation conditioning case by RS-422 bus by recycling CP-118-UI board;
Integrated interface adaptation conditioning case receives the navigation data encoding value in RS-422 bus, what utilize RS-422 interface module that navigation data coding is sent to the integrated interface adaptation conditioning monitoring panel of case and aircraft by RS-422 bus simultaneously flies control machine, and the rudderpost stroke state signal for steering wheel exports and the RCS jet flow status signal output of RCS solenoid valve.
2. the detection method of the integrated interface test macro of aircraft semi-physical simulation, is characterized in that comprising outside emulator detection-phase and subjects detection-phase,
Described outside emulator detection-phase is as follows:
(1) integrated interface adaptation conditioning case is connected with the 1553B bus between integrated interface test and management computing machine and DO bus disconnects;
(2) integrated interface test and management computing machine is under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, generate the rudderpost stroke state signal of steering wheel of aircraft and the decoded value of the RCS jet flow status signal of RCS solenoid valve;
(3) utilize VMIC-5565 board that the decoded value of the rudderpost stroke state signal of step (2) and RCS jet flow status signal is sent to fiber reflection memory switch by optical fiber cable, by fiber reflection memory switch, the decoded value of rudderpost stroke state signal and RCS jet flow status signal is forwarded to emulator, calculates for navigation data;
(4) navigation data signal that calculated by optical fiber cable receiving step (3) outside emulator of fiber reflection memory switch, and be forwarded to integrated interface test and management computing machine by optical fiber cable;
(5) integrated interface test and management computing machine utilizes VMIC-5565 board to receive the navigation data signal of the step (4) that emulator is sent here on optical fiber cable, shows under Windows+RTX real-time system environment;
(6) result shown according to step (5) judges whether navigation data signal meets the communications protocol requirement of semi-physical simulation; If do not have navigation data signal to show, illustrate that the hardware communication equipment of outside emulator breaks down; If there is navigation data signal to show, but navigation data signal numerical value does not meet the communications protocol requirement of semi-physical simulation, illustrates that mistake appears in the software programming of outside emulator;
Described subjects detection-phase is as follows:
(7) optical fiber cable between fiber reflection memory switch with integrated interface test and management computing machine is connected disconnects;
(8) integrated interface test and management computing machine is under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, generate the coding of navigation data signal, navigation data encoding value is sent to integrated interface adaptation conditioning case by RS-422 bus by recycling CP-118-UI board;
(9) integrated interface adaptation conditioning case receives the navigation data encoding value in RS-422 bus, what utilize RS-422 interface module that the navigation data of step (8) coding is sent to the integrated interface adaptation conditioning monitoring panel of case and aircraft by RS-422 bus simultaneously flies control machine, and the rudderpost stroke state signal for steering wheel exports and the RCS jet flow status signal output of RCS solenoid valve;
(10) integrated interface adaptation conditioning case utilizes 1553B bus to receive rudderpost stroke state signal from the steering wheel of aircraft, utilizes DO bus to receive RCS jet flow status signal from the solenoid valve of the RCS of aircraft;
(11) integrated interface adaptation conditioning case utilizes 1553B interface module the connector of the 1553B bus of aircraft steering engine to be adapted to the standard interface of the PCI-1553-2 board that Al ta company produces, utilize DO interface module that the 27V signal condition of the DO bus of aircraft RCS solenoid valve is become the manageable 5V signal of PCI-1756 board, then respectively the RCS jet flow status signal after the rudderpost stroke state signal after adaptation and conditioning will be delivered to monitoring panel and the integrated interface test and management computing machine of integrated interface adaptation conditioning case by 1553B bus and DO bus;
(12) integrated interface test and management computing machine utilizes PCI-1553-2 board to receive the rudderpost stroke state signal of the step (11) in 1553B bus, PCI-1756 board is utilized to receive the RCS jet flow status signal of the step (11) in DO bus, under Windows+RTX real-time system environment, according to the communications protocol that semi-physical simulation specifies, rudderpost stroke state signal and RCS jet flow status signal are decoded and shown;
(13) judge whether data meet the communications protocol requirement of semi-physical simulation according to the result of the display of step (12); If there is no rudderpost stroke state signal or the display of RCS jet flow status signal, illustrate that the hardware communication equipment of the control machine that flies of aircraft, steering wheel or RCS solenoid valve breaks down, can standard test equipment be utilized, measure by the output of monitoring panel to 1553B bus, DO bus and RS-422 bus of integrated interface adaptation conditioning case and investigate fault; If have rudderpost stroke state signal and the display of RCS jet flow status signal, but rudderpost stroke state signal or RCS jet flow status signal numerical value do not meet the communications protocol requirement of semi-physical simulation, illustrate that mistake appears in the software programming that the control machine that flies of aircraft, steering wheel or RCS solenoid valve are relevant.
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