CN103744419B - Combined target missile is imitative flies test macro - Google Patents
Combined target missile is imitative flies test macro Download PDFInfo
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- CN103744419B CN103744419B CN201310737818.7A CN201310737818A CN103744419B CN 103744419 B CN103744419 B CN 103744419B CN 201310737818 A CN201310737818 A CN 201310737818A CN 103744419 B CN103744419 B CN 103744419B
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Abstract
The present invention discloses that a kind of combined target missile is imitative flies test macro, comprising: simulating developer machine, for setting up combined target missile flight controlling model, is translated into and can perform code; Off-line simulation runs Controlling model, record rudder control signal; Receive the rudder control signal from emulation Test Host, itself and rudder control signal during emulation moving model are compared, to judge exactness or the steering wheel running condition of Flight Control Software in Controlling System on bullet; Emulation Test Host, can perform code for performing, send the flight path relevant information performing to export to interface box, send the rudder control signal of Controlling System on the bullet of interface box transfer to simulating developer machine; Interface box, for the signal transfer emulated on Test Host and bullet between Controlling System. The flight controlling system of multimode, complicated logic can be carried out simulation test and l-G simulation test by the present invention, simulates one-time-reach-place from amendment model to matter emulation, has the advantages that framework is simple, cost is low, efficiency is high.
Description
Technical field
The invention belongs to flight controlling and simulation technical field, it is specifically related to that a kind of combined target missile is imitative flies test macro, for the target missile flight controlling system of multimode, complicated logic is carried out simulation test and l-G simulation test.
Background technology
Along with the development of technology and the application of functional diversities need, target missile Control System Design trend combinationization, the seriation of simulation high-speed mobile target, the Controlling System of combined target missile has the feature of multimode, combinationization, complicated logic. And traditional semi-matter simulating system is mainly used in gesture stability, function is relatively single, and cost is high, running cost is higher, therefore combined target missile Controlling System it is not suitable for, therefore, urgently needing to be developed by combined target missile and a kind of imitative fly test macro, it not only achieves the specific aim to Control System Imitation simulation, and easy to operate, development mode flexibly, operational efficiency height.
Summary of the invention
For the deficiency of existing semi-matter simulating system, the present invention proposes that a kind of combined target missile is imitative flies test macro, the flight controlling system of multimode, complicated logic can be carried out simulation test and l-G simulation test, simulate one-time-reach-place from amendment model to matter emulation, have the advantages that framework is simple, cost is low, efficiency is high.
A kind of combined target missile is imitative flies test macro, comprising:
Simulating developer machine, connects the first end of emulation Test Host by Ethernet, for setting up based on the combined target missile flight controlling model of true rudder and simulation rudder two type; By target missile flight controlling model conversation for code can be performed and send emulation Test Host to; Off-line simulation runs target missile flight controlling model, rudder control signal in real time record operational process; Receive the rudder control signal from emulation Test Host, then the rudder control signal of record when itself and off-line simulation operation target missile flight controlling model is compared, if the corresponding Controlling model based on simulation rudder of rudder control signal, then its comparative result is in order to judge the exactness of Flight Control Software in Controlling System on bullet, if the corresponding Controlling model based on true rudder of rudder control signal, then its comparative result is in order to the running condition of the Live Flying situation and steering wheel that judge combined target missile;
Emulation Test Host, its first end connects real-time simulation exploitation machine by Ethernet, 2nd end connects Controlling System on the bullet of combined target missile by interface box, for using the true rudder drift angle information of Controlling System on bullet or simulating rudder drift angle information as the described input performing code according to Code Selection can be performed, execution can perform code, exports body flight path relevant information in real time in the process of implementation and sends Controlling System on bullet to by interface box; Receive the Control signal of the rudder from Controlling System on bullet by interface box and send simulating developer machine to;
Interface box, it is connected on the bullet of emulation Test Host and combined target missile between Controlling System, for to passing on to emulation Test Host after the true rudder drift angle information and Control signal of the rudder conditioning of Controlling System on bullet, sending Controlling System on bullet to after the body flight path relevant information from emulation Test Host being nursed one's health.
Further, described simulating developer machine comprises:
Flight controlling model construction module, for setting up combined target missile Elastomer kinematics and kinetic model, builds based on the target missile flight controlling model of virtual rudder and simulation rudder two type on the basis of combined target missile Elastomer kinematics and kinetic model;
Model running module, runs target missile flight controlling model for off-line simulation, the rudder control signal in real time record operational process, and sends human-computer interaction module to;
Human-computer interaction module, for providing, man-machine interaction interface is imitative to realize flies test process monitoring, the rudder control signal of the rudder control signal of model running module record and emulation Test Host feedback is compared, with the Live Flying situation of exactness or combined target missile that judges Flight Control Software in Controlling System on bullet and the running condition of steering wheel;
Performing code building module, for configuring model pin to emulation Test Host hardware pin according to aircraft Controlling model, deployment model and configuration file, to emulating Test Host, finally generate the performed code of flight controlling model to emulation Test Host;
Exploitation machine Ethernet interface, its one end connects execution code building module and user interactive module, the other end connects emulation Test Host by Ethernet, for sending the performed code performing code building CMOS macro cell to emulation Test Host, send the rudder control signal from emulation Test Host to human-computer interaction module.
Further, described simulating developer machine adopts Matlab/Simulink to set up combined target missile body model and target missile flight controlling model, adopt LabVIEW founder's machine interactive interface, adopt automatic generation instrument RTW and SIT by flight controlling model conversation for code can be performed.
Further, described emulation Test Host comprises:
Test machine Ethernet interface, its one end connects real-time simulation exploitation machine by Ethernet, the other end connects interface box, code operation module can be performed for being sent to by the performed code from simulating developer machine, send simulating developer machine to by from the rudder control signal of Controlling System on the bullet of signal acquisition module;
Code can be performed and run module, it is made up of the hardware board supporting real-time system, for selecting the true rudder drift angle information of Controlling System on bullet or simulate rudder drift angle information as the described input performing code, run the performed code according to target missile flight controlling model generation, send the body flight path relevant information exported in real time in operational process to signal acquisition module;
Signal acquisition module, for sending Controlling System on bullet by from the body flight path relevant information that can perform code operation module to by interface box, sends test machine Ethernet interface to by from the rudder control signal of Controlling System on the bullet of interface box.
Further, described emulation Test Host adopts the real-time embedded controller of the NI based on PXI bus to realize, and adopts Windows and real-time system dual system, and described signal acquisition module comprises IO plate card, AD plate card, DA plate card and serial ports plate card.
Further, TDMS scale-of-two file storage data is adopted at the imitative test process that flies.
Further, described interface box comprises:
+ 27V power supply, its power switch nominal operation electric current 20A, rush current 60A;
Two secondary sources �� 15V, its output rating is 50W, each 25W of generating positive and negative voltage;
A/D circuit, for gathering 8 road analog signalses, scope �� 10V;
D/A circuit, for will emulate Test Host output �� 10V scope signal extension to �� 15V and 0��25V.
The technique effect of the present invention is embodied in:
The present invention is imitative flies the structure that test macro adopts " upper and lower computer ", carries out data interaction by " Ethernet " between upper and lower computer. Combined target missile is imitated and is flown the emulation test demand that test macro can meet target missile, and its computing cycle (the imitative test macro that flies is from dynamically input, calculating and process to the time spent by a dynamical output whole process operation) is not more than 1ms. Imitative fly body model that Matlab/Simulink in upper computer develop by test macro and control algorithm to be deployed in target Real-time hardware fast, for the real signal input of the interface configuration in Controlling model, export, and by the model parameter of the man-machine interaction interface of upper computer monitoring real time execution in target machine, it is achieved the storage of the on-line monitoring of parameter, amendment and data and real function. Interface box is used for the conditioning of signal, connection, transfer, can fly Controlling System, topworks on test macro and bullet be connected to form closed-loop control by imitative. Present invention achieves and the flight controlling system of multimode, complicated logic is carried out simulation test and l-G simulation test, the reliability of soft and hardware work under the exactness of examination flight controlling system soft and hardware work and Harmony and certain condition, the exactness of examination flying-controlled box controling parameters, reasonableness, analyze the difference of research combined target missile emulation with mathematics emulation result, improve design relevant to improving control law, provide test basis for improving the design of flight controlling system further.
As optimization, the present invention adopts multi-purpose computer to install WindowsXP system and Matlab, LabView etc. and develops software, for the foundation of systematic mathematical model, debugging and imitative fly the storage of test data and display in real time. Adopting Code automatic build instrument RTW(Real-TimeWorkshop) the algorithm module that provided by Simulink and other Controlling model be converted into and can perform code, to strengthen the weak tendency of LabVIEW in control algorithm etc. Algorithm module and other Controlling model of there is provided Simulink are converted into and can perform code, to strengthen the weak tendency of LabVIEW in control algorithm etc. Interactively checking Matlab/Simulink model, and easily these models are configured to Real-time hardware simulation calculation. Adopt LabVIEWRT(RealTime) developing application, then download it in real-time target hardware and run, only software program need to be revised a little, so that it may it easily is integrated on additional I/O interface or different LabVIEW real-time target hardware. Utilize outward appearance that LabVIEW provides and the similar control of traditional instrument and TDMS scale-of-two file storage technology, realization comprises underlying parameter debugging, calls, emulation data observation, the establishment storing interface, TDMS is a scale-of-two file, and scale-of-two file has file and takies the remarkable advantage that storage space is little and read or write speed is fast.
Generally speaking, the present invention uses the mode of software modeling that flight controlling system carries out simulation test and l-G simulation test, and the feature of this system is that framework is simple, cost is low, efficiency height. The design that can be widely used in controlling in Flight Vehicle Design algorithm improves with perfect, for the overall design of aircraft provides test basis.
Accompanying drawing explanation
Fig. 1 be the present invention realize functional block diagram;
Fig. 2 is its exterior connection diagram;
Fig. 3 be the present invention realize principle and workflow diagram;
Fig. 4 is that Matlab/Simulink generates code flow block diagram;
Fig. 5 is �� 15V output circuit schematic diagram;
Fig. 6 is 0-25V output circuit schematic diagram.
Embodiment
In order to make the object of the present invention, technical scheme and advantage clearly understand, below in conjunction with drawings and Examples, the present invention is further elaborated. It is to be understood that specific embodiment described herein is only in order to explain the present invention, it is not intended to limit the present invention. In addition, if below in described each enforcement mode of the present invention involved technology feature do not form conflict each other and just can mutually combine.
See Fig. 1,2 and Fig. 3, the imitative test macro that flies of the combined target missile of the present invention comprises simulating developer machine, emulation Test Host and interface box.
(1) simulating developer machine
Simulating developer machine connects the first end of emulation Test Host by Ethernet, for setting up based on the combined target missile flight controlling model of true rudder and simulation rudder two type; By target missile flight controlling model conversation for code can be performed and send emulation Test Host to; Off-line simulation runs target missile flight controlling model, rudder control signal in real time record operational process; Receive the rudder control signal from emulation Test Host, then the rudder control signal of record when itself and off-line simulation operation target missile flight controlling model is compared, if the corresponding Controlling model based on simulation rudder type of rudder control signal, then its comparative result is in order to judge the exactness of Flight Control Software in Controlling System on bullet, if the corresponding Controlling model based on true rudder of rudder control signal, then its comparative result is in order to the running condition of the Live Flying situation and steering wheel that judge combined target missile.
According to one embodiment of the present invention, simulating developer machine specifically comprises:
Flight controlling model construction module, for setting up combined target missile Elastomer kinematics and kinetic model, builds based on the target missile flight controlling model of virtual rudder and simulation rudder two type on the basis of combined target missile Elastomer kinematics and kinetic model;
Model running module, runs target missile flight controlling model for off-line simulation, the rudder control signal in real time record operational process, and sends human-computer interaction module to;
Human-computer interaction module, for providing, man-machine interaction interface is imitative to realize flies test process monitoring, the rudder control signal of the rudder control signal of model running module record and emulation Test Host feedback is compared, with the Live Flying situation of exactness or combined target missile that judges Flight Control Software in Controlling System on bullet and the running condition of steering wheel;
Performing code building module, for configuring model pin to emulation Test Host hardware pin according to aircraft Controlling model, deployment model and configuration file, to emulating Test Host, finally generate the performed code of flight controlling model to emulation Test Host;
Exploitation machine Ethernet interface, its one end connects execution code building module and user interactive module, the other end connects emulation Test Host by Ethernet, for sending the performed code performing code building CMOS macro cell to emulation Test Host, send the rudder control signal from emulation Test Host to human-computer interaction module.
Body mathematic(al) mode characterizes target missile body characteristic and the rule under high-speed motion. Imitative fly test macro be analyzing, calculate, on the basis of simulation target missile motion, set up relate to gravity, aerodynamic force, controlling party to target missile mathematical model. Simulating developer machine uses Simulink modeling, LabVIEWSIT is adopted to realize LabVIEW and Matlab/Simulink interactive mode programming, then the algorithm module using automatic generation instrument RTW to be provided by Simulink is converted into other Controlling model and can perform code, it is achieved process is as shown in Figure 4. Concrete steps are:
A () is according to the body characteristic of combined target missile, it may also be useful to Matlab/Simulink and other professional module set up the Simulink model of body. On the basis building model, it is possible to use the design and analysis work of flight controlling system is carried out in the professional work box that MATLAB provides. The result of design realizes in Simulink, carries out off-line mathematics emulation, and is optimized by design variable.
B characteristic parameter that () to be observed according to combined target missile, it may also be useful to LabVIEW founder's machine interactive interface. The control utilizing LabVIEW to provide can complete man-machine interaction interface simple and practical, friendly interface fast.
C user interface that () creates at LabVIEW uses Simulink connect management device (SIT) to set up and associate between LabVIEW user interface with Simulink model. When the configuration of LabVIEW user interface and operation Simulink model, model need to stay open state in Matlab/Simulink.
D () uses automatic generation instrument RTW to be converted into by Controlling model can perform code. By self-defined RTW code building option, Simulink Controlling model is converted into the model.dll file that can call, it is provided that call to LabVIEW. Passed to imitate under performed code compiling generated and fly Test Host carries out real-time simulated animation.
(2) Test Host is emulated
The first end of emulation Test Host connects real-time simulation exploitation machine by Ethernet, 2nd end connects Controlling System on the bullet of combined target missile by interface box, for using the true rudder drift angle information of Controlling System on bullet or simulating rudder drift angle information as the described input performing code according to Code Selection can be performed, execution can perform code, exports body flight path relevant information in real time in the process of implementation and sends Controlling System on bullet to by interface box; Receive the Control signal of the rudder from Controlling System on bullet by interface box and send simulating developer machine to.
The model of simulating developer machine exploitation will define model to emulation Test Host hardware pin configuration; Therefore it is gather real rudder drift angle or the rudder drift angle with simulation to determine by simulating developer model, after emulation starts, the function emulating Test Host main flight path information is passed to Controlling System on bullet carry out Flight Control Software operation, now emulation Test Host and real-time simulation exploitation machine only have the mutual of information, and information interaction is also clear and definite in the model developed by simulating developer machine.
According to one embodiment of the present invention, emulation Test Host specifically comprises:
Test machine Ethernet interface, its one end connects real-time simulation exploitation machine by Ethernet, the other end connects interface box, code operation module can be performed for being sent to by the performed code from simulating developer machine, send simulating developer machine to by from the rudder control signal of Controlling System on the bullet of signal acquisition module;
Code can be performed and run module, it is made up of the hardware board supporting real-time system, for selecting the true rudder drift angle information of Controlling System on bullet or simulate rudder drift angle information as the described input performing code, run the performed code according to target missile flight controlling model generation, send the body flight path relevant information exported in real time in operational process to signal acquisition module;
Signal acquisition module, for sending Controlling System on bullet by from the body flight path relevant information that can perform code operation module to by interface box, sends test machine Ethernet interface to by from the rudder control signal of Controlling System on the bullet of interface box.
Real-time simulated animation realizes simulation mathematical model to transform to actual target missile hardware composition. Realistic model is deployed to fast in target Real-time hardware, it is the real signal I/O of the interface configuration in Controlling model. The present invention uses the lower computer i.e. imitative Test Host that flies to carry out object code and realize the computing of aerodynamics and kinematics equation, the calculating of target trajectory and target missile-target relative movement non trivial solution calculation, and data acquisition and communication. As preferably, imitative fly Test Host and select the real-time embedded controller PXI-8109RT of the NI based on PXI bus, PXI bus is except the data throughput amount with 132MB/s, also has accurate Trigger Bus, synchronous clock and the local bus for equipment room transfer, can greatly improve the performance of system, and PXI controller can adopt Windows and real-time system dual system, complete system determinacy is required harsh Simulation Application. This controller has Inteli7-620M double-core treater, the highest internal memory 4GBDDR3-1066MHz, 120GB hard disk, 4 high speed USB ports, 1 RS232 interface.
Fly in test process imitative, the imitative input flying test macro and need to gathering rudder feedback signal and calculate as dynamic movement model, need in addition to gather according to control flow check range request, show instruction signal, carry out communication with Controlling System on bullet. Described signal acquisition module comprises IO plate card, AD plate card, DA plate card and serial ports plate card.
Example:
The real-time embedded controller PXI-8109RT of NI, has Inteli7-620M double-core treater, the highest internal memory 4GBDDR3-1066MHz, 120GB hard disk, 4 high speed USB ports, 1 RS232 interface; Configuration USB interface, net mouth and keyboard/mouse, display interface device etc., the WindowsXP operating system that prepackage NI is subsidiary and LabVIEWRT real time operating system (RTOS), and the driving program of various module;
DA plate card: NIPXI-67338 road, 16,250ks/s; Analog quantity D/A output channel 8 tunnel, resolving power 16, most Gao Gengxin speed 1MS/s, output voltage amplitude 0���� 10V; Numeral I/O passage 8 tunnel; 2,24 counters;
AD plate card: NIPXI-6251 analog signals difference acquisition channel 8 tunnel, resolving power 16, most high sampling rate 1.25 �� MS/s(is able to programme), maximum input voltage �� 10V; Analog signals output channel 2 tunnel, resolving power 16, most Gao Gengxin speed 2.8MS/s, maximum output voltage �� 10V; Numeral I/O passage 24 tunnel; 2,32 location/counters;
IO plate card: NIPXI-6528 �� 60V, 24 tunnels enter, and 24 tunnels go out, channel separation;
Serial ports plate card: PXI-8433/4 high-performance 4 road serial line interface;
(3) interface box
It is connected on the bullet of emulation Test Host and combined target missile between Controlling System, for Controlling System on bullet provides power supply, pass on after the true rudder drift angle information from Controlling System on bullet is nursed one's health to emulation Test Host simultaneously, send the body flight path relevant information conditioning from emulation Test Host on bullet Controlling System. The signal that emulation Test Host exports mainly only is nursed one's health into the signal that on bullet, Controlling System can receive by conditioning, and the signal that Controlling System on bullet exports is nursed one's health into the signal that emulation Test Host can receive simultaneously.
The imitative interface box flying test macro connects Controlling System on bullet, is that on bullet, Controlling System provides power supply, and power supply comprises+27V(and powers switch nominal operation electric current 20A, rush current 60A. ), two secondary sources �� 15V(output rating be 50W, each 25W of generating positive and negative voltage), Power supply designing circuitry is as shown in Figure 5 and Figure 6. A/D circuit can gather 8 road analog signalses, scope �� 10V, and emulation Test Host simulation calculation machine AD plate card input voltage range �� 10V, AD acquired signal is directly inputted into AD analog input card after capacitance-resistance filtering. D/A circuit layout adopts amplifies circuit by the signal extension of simulation calculation machine plate card output �� 10V scope to �� 15V and 0��25V, to meet the requirement of combined target missile control computer voltage range different from topworks.
At the system development initial stage, imitative fly test macro and model can be carried out off-line simulation. The Simulink under Matlab is utilized to set up the model of target missile each several part. Building on model basis, utilizing Matlab to carry out the design and analysis of flight controlling algorithm, the result of design realizes in Simulink and carries out off-line mathematics emulation, is optimized by design variable. After mathematics has emulated, imitate and fly flying-controlled box checking and the HWIL simulation checking that test macro completes flight controlling system by following approach. (SIT is the module with simulink model interface that Labview develops)
The working process of system of the present invention is specific as follows:
Realize Control System Software checking on bullet: only connect Controlling System material object on bullet and do not connect steering wheel. Simulating developer machine plays entirely selects simulation steering wheel in model, model need to export body flight path relevant information and need to gather the pin that the Control signal of the rudder of Controlling System on bullet is deployed to emulation Test Host hardware. Model generates after having disposed and can perform code and be downloaded to emulation Test Host, runs full Ballistic Simulation of Underwater, send, by Ethernet, the Control signal of the rudder needing observation in simulation process to simulating developer machine in emulation Test Host. Simulating developer machine contrasts Controlling System on mathematics emulation and bullet and resolves the Control signal of the rudder obtained, examination bullet flies the exactness of control program.
Closed steering wheel in kind runs: connect Controlling System material object and steering wheel on bullet, and simulating developer machine plays entirely selects steering wheel in kind in model, namely gather the rudder feedback signal of steering wheel in kind. The input and output signal section of model is deployed to the pin of emulation Test Host hardware. Model generates after having disposed and can perform code and be downloaded to emulation Test Host, is downloaded to emulation Test Host, runs full Ballistic Simulation of Underwater after model generation can be performed code, practical flight effect after examination access rudder in kind and the running condition of steering wheel.
Flying produce in test process a large amount of data imitative, these process datas are for analytical test process and to find its improved route, debugging and localization of fault be very necessary. The control that outward appearance and the traditional instrument that native system uses LabVIEW to provide is similar and TDMS scale-of-two file storage technology, it is achieved comprise underlying parameter debugging, call, the establishment at emulation data observation, storage interface.
TDMS scale-of-two file storage technology can realize reliably, effective data store, and real time data and historical data are watched, the function of configuration and record warning and event. TDMS formatted file can be called in LabVIEW, Excel and Matlab. TDMS is a scale-of-two file, and scale-of-two file has the remarkable advantage that file takies that storage space is little and read or write speed is fast. As shown in table 1 through experimental test TDMS data event memory:
Table 1 data memory property is tested
Those skilled in the art will readily understand; the foregoing is only the better embodiment of the present invention; not in order to limit the present invention, all any amendment, equivalent replacement and improvement etc. done within the spirit and principles in the present invention, all should be included within protection scope of the present invention.
Claims (7)
1. combined target missile is imitative flies a test macro, comprising:
Simulating developer machine, connects the first end of emulation Test Host by Ethernet, for setting up based on the combined target missile flight controlling model of true rudder and simulation rudder two type; By target missile flight controlling model conversation for code can be performed and send emulation Test Host to; Off-line simulation runs target missile flight controlling model, rudder control signal in real time record operational process; Receive the rudder control signal from emulation Test Host, then the rudder control signal of record when itself and off-line simulation operation target missile flight controlling model is compared, if the corresponding Controlling model based on simulation rudder type of rudder control signal, then its comparative result is in order to judge the exactness of Flight Control Software in Controlling System on bullet, if the corresponding Controlling model based on true rudder of rudder control signal, then its comparative result is in order to the running condition of the Live Flying situation and steering wheel that judge combined target missile;
Emulation Test Host, its first end connects simulating developer machine by Ethernet, 2nd end connects Controlling System on the bullet of combined target missile by interface box, for using the true rudder drift angle information of Controlling System on bullet or simulating rudder drift angle information as the described input performing code according to Code Selection can be performed, execution can perform code, exports body flight path relevant information in real time in the process of implementation and sends Controlling System on bullet to by interface box; Receive the Control signal of the rudder from Controlling System on bullet by interface box and send simulating developer machine to;
Interface box, it is connected on the bullet of emulation Test Host and combined target missile between Controlling System, for to passing on to emulation Test Host after the true rudder drift angle information and Control signal of the rudder conditioning of Controlling System on bullet, sending Controlling System on bullet to after the body flight path relevant information from emulation Test Host being nursed one's health.
2. combined target missile according to claim 1 is imitative flies test macro, it is characterised in that, described simulating developer machine comprises:
Flight controlling model construction module, for setting up combined target missile Elastomer kinematics and kinetic model, builds based on the target missile flight controlling model of virtual rudder and simulation rudder two type on the basis of combined target missile Elastomer kinematics and kinetic model;
Model running module, runs target missile flight controlling model for off-line simulation, the rudder control signal in real time record operational process, and sends human-computer interaction module to;
Human-computer interaction module, for providing, man-machine interaction interface is imitative to realize flies test process monitoring, the rudder control signal of the rudder control signal of model running module record and emulation Test Host feedback is compared, with the Live Flying situation of exactness or combined target missile that judges Flight Control Software in Controlling System on bullet and the running condition of steering wheel;
Performing code building module, for configuring model pin to emulation Test Host hardware pin according to aircraft Controlling model, deployment model and configuration file, to emulating Test Host, finally generate the performed code of flight controlling model to emulation Test Host;
Exploitation machine Ethernet interface, its one end connects execution code building module and user interactive module, the other end connects emulation Test Host by Ethernet, for sending the performed code performing code building CMOS macro cell to emulation Test Host, send the rudder control signal from emulation Test Host to human-computer interaction module.
3. combined target missile according to claim 2 is imitative flies test macro, it is characterized in that, described simulating developer machine adopts Matlab/Simulink to set up combined target missile body model and target missile flight controlling model, adopt LabVIEW founder's machine interactive interface, adopt automatic generation instrument RTW and SIT by flight controlling model conversation for code can be performed.
4. combined target missile according to claim 1 and 2 is imitative flies test macro, it is characterised in that, described emulation Test Host comprises:
Test machine Ethernet interface, its one end connects simulating developer machine by Ethernet, the other end connects interface box, code operation module can be performed for being sent to by the performed code from simulating developer machine, send simulating developer machine to by from the rudder control signal of Controlling System on the bullet of signal acquisition module;
Code can be performed and run module, it is made up of the hardware board supporting real-time system, for selecting the true rudder drift angle information of Controlling System on bullet or simulate rudder drift angle information as the described input performing code, run the performed code according to target missile flight controlling model generation, send the body flight path relevant information exported in real time in operational process to signal acquisition module;
Signal acquisition module, for sending Controlling System on bullet by from the body flight path relevant information that can perform code operation module to by interface box, sends test machine Ethernet interface to by from the rudder control signal of Controlling System on the bullet of interface box.
5. combined target missile according to claim 4 is imitative flies test macro, it is characterized in that, described emulation Test Host adopts the real-time embedded controller of the NI based on PXI bus to realize, and adopting Windows and real-time system dual system, described signal acquisition module comprises IO plate card, AD plate card, DA plate card and serial ports plate card.
6. combined target missile according to claim 1 or 2 or 3 is imitative flies test macro, it is characterised in that, adopt TDMS scale-of-two file storage data at the imitative test process that flies.
7. combined target missile according to claim 1 or 2 or 3 is imitative flies test macro, it is characterised in that, described interface box comprises:
+ 27V power supply, its power switch nominal operation electric current 20A, rush current 60A;
Two secondary sources �� 15V, its output rating is 50W, each 25W of generating positive and negative voltage;
A/D circuit, for gathering 8 road analog signalses, scope �� 10V;
D/A circuit, for will emulate Test Host output �� 10V scope signal extension to �� 15V and 0��25V.
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| CN104731744B (en) * | 2015-03-13 | 2017-07-04 | 中国航天科技集团公司第九研究院第七七一研究所 | A kind of restructural Embedded Computer On Modules based on SiP |
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