CN103744419A - Combination missile target imitation flight test system - Google Patents
Combination missile target imitation flight test system Download PDFInfo
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- CN103744419A CN103744419A CN201310737818.7A CN201310737818A CN103744419A CN 103744419 A CN103744419 A CN 103744419A CN 201310737818 A CN201310737818 A CN 201310737818A CN 103744419 A CN103744419 A CN 103744419A
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Abstract
The present invention discloses a combination missile target imitation flight test system, which includes a simulation development machine used in building a combination missile target flight control model, translating the simulation development machine into an executable code; an off-line simulation operation control model which records a rudder control signal and receives the rudder control signal from a simulation test host, comparing with the rudder control signal of the simulation operation model to judge the accuracy of a flight control software of the control system or the operation of a steering gear; the simulation test host which executes the executable code, sends the relevant track information of executing output to an interface box and sends the rudder control signal of an on-board control system transferred by the interface box to the simulation development machine; the interface box which is used for transferring the signals between the simulation test host and the on-board control system. The combination missile target imitation flight test system can perform a simulation test and a simulation experiment for the flight control system of multi-module and complex logic from model modification to physical simulation once, and is characterized by simple framework, low cost and high efficiency.
Description
Technical field
The invention belongs to flight and controlling and simulation technical field, being specifically related to that a kind of combined target missile is imitative flies test macro, for the target missile flight control system to multimode, complex logic, carrying out simulation test and l-G simulation test.
Background technology
Along with the development of technology and the application of functional diversities need, the target missile Control System Design trend modularization of simulation high-speed mobile target, seriation, the control system of combined target missile has the feature of multimode, modularization, complex logic.And traditional semi-matter simulating system is mainly used in attitude control, function is relatively single, and cost is high, operating cost is higher, therefore be not suitable for combined target missile control system, therefore, in the urgent need to combined target missile being developed to a kind of imitative test macro that flies, it has not only realized the specific aim to Control System Imitation simulation, and easy to operate, development mode is flexible, operational efficiency is high.
Summary of the invention
Deficiency for existing semi-matter simulating system, the present invention proposes the imitative test macro that flies of a kind of combined target missile, can carry out simulation test and l-G simulation test to the flight control system of multimode, complex logic, from revising model, to matter emulation, simulate one-time-reach-place, have the advantages that framework is simple, cost is low, efficiency is high.
Combined target missile is imitative flies a test macro, comprising:
Simulating developer machine, connects the first end of emulation testing main frame by Ethernet, for the combined target missile flight of setting up based on two types of true rudder and simulation rudders, control model; Target missile flight is controlled to model conversation to be executable code and to send emulation testing main frame to; Model, rudder control signal in real time record operational process are controlled in the flight of off-line simulation operation target missile; Reception is from the rudder control signal of emulation testing main frame, the rudder control signal recording while the flight of itself and off-line simulation operation target missile being controlled to model compares, if the control model of rudder control signal correspondence based on simulation rudder, its comparative result is in order to judge on bullet the correctness of Flight Control Software in control system, if the control model of rudder control signal correspondence based on true rudder, its comparative result is in order to the Live Flying situation of decision set mould assembly target missile and the ruuning situation of steering wheel;
Emulation testing main frame, its first end connects real-time simulation developing engine by Ethernet, the second end connects control system on the bullet of combined target missile by interface box, for selecting the true angle of rudder reflection information of control system on bullet according to executable code or simulating angle of rudder reflection information as the input of described executable code, carry out executable code, export in real time in the process of implementation body flight path relevant information and send control system on bullet to by interface box; By interface box, receive from the Control signal of the rudder of control system on bullet and send simulating developer machine to;
Interface box, be connected on the bullet of emulation testing main frame and combined target missile between control system, for to transferring to emulation testing main frame after the true angle of rudder reflection information from control system on bullet and Control signal of the rudder conditioning, after being nursed one's health, the body flight path relevant information from emulation testing main frame sends control system on bullet to.
Further, described simulating developer machine comprises:
Model construction module is controlled in flight, and for setting up combined target missile Elastomer kinematics and kinetic model, model is controlled in the target missile flight building on the basis of combined target missile Elastomer kinematics and kinetic model based on virtual rudder and two types of simulation rudders;
Model running module, controls model for the flight of off-line simulation operation target missile, the rudder control signal in real time record operational process, and send human-computer interaction module to;
Human-computer interaction module, be used for providing human-computer interaction interface to realize the imitative test process monitoring that flies, rudder control signal to the rudder control signal of model running module records and emulation testing main frame feedback compares, to judge on bullet the correctness of Flight Control Software or the Live Flying situation of combined target missile and the ruuning situation of steering wheel in control system;
Run time version generation module, for controlling model allocation models pin according to aircraft to emulation testing host hardware pin, deployment model and configuration file, to emulation testing main frame, finally generate flight and control model to the executable code of emulation testing main frame;
Developing engine Ethernet interface, its one end connects run time version generation module and user interactive module, the other end connects emulation testing main frame by Ethernet, for the executable code that run time version generation module is generated, send emulation testing main frame to, send the rudder control signal from emulation testing main frame to human-computer interaction module.
Further, described simulating developer machine adopts Matlab/Simulink to set up combined target missile body model and model is controlled in target missile flight, adopt LabVIEW founder's machine interactive interface, adopting Auto-Generation Tool RTW and SIT that flight is controlled to model conversation is executable code.
Further, described emulation testing main frame comprises:
Test machine Ethernet interface, its one end connects real-time simulation developing engine by Ethernet, other end connecting interface case, for the executable code from simulating developer machine being sent to executable code operation module, send the rudder control signal of control system on the bullet from signal acquisition module to simulating developer machine;
Executable code operation module, by supporting the hardware board of real-time system to form, for selecting the true angle of rudder reflection information of control system on bullet or simulating angle of rudder reflection information as the input of described executable code, operation, according to the executable code of target missile flight control model generation, sends the body flight path relevant information of exporting in real time in operational process to signal acquisition module;
Signal acquisition module, for sending the body flight path relevant information from executable code operation module on bullet control system by interface box, sends the rudder control signal of control system on the bullet from interface box to test machine Ethernet interface.
Further, described emulation testing main frame 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 board, AD board, DA board and serial ports board.
Further, at the imitative test process that flies, adopt TDMS binary file storage data.
Further, described interface box comprises:
+ 27V power supply, its power switch rated operational current 20A, dash current 60A;
Secondary power supply ± 15V, its output power 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 arriving the signal extension of emulation testing main frame output ± 10V scope ± 15V and 0～25V.
Technique effect of the present invention is embodied in:
The imitative structure that flies test macro employing " upper and lower computer " of the present invention, carries out data interaction by " Ethernet " between upper and lower computer.Combined target missile is imitative flies the emulation testing demand that test macro can meet target missile, and its execution cycle (imitative fly test macro operate the spent time to overall process of dynamic output from dynamic input, calculating and processing) is not more than 1ms.Imitative fly test macro by the body model of the exploitation of Matlab/Simulink in host computer and control algolithm rapid deployment in the real-time hardware of target, for controlling the real signal input of interface configuration, the output in model, and monitor the model parameter of real time execution in target machine by the human-computer interaction interface of host computer, realize storage and the real function of on-line monitoring, modification and the data of parameter.Interface box is for conditioning, connection, the transfer of signal, can imitate to fly control system, topworks on test macro and bullet and be connected to form closed-loop control.The present invention has realized the flight control system of multimode, complex logic has been carried out to simulation test and l-G simulation test, the reliability of soft and hardware work under the correctness of test flight control system soft and hardware work and harmony and certain condition, examination flies to control correctness, the rationality of software control parameter, the analyze and research difference of combined target missile emulation and result of mathematical simulation, improve and improve control law related design, for further improving the design of flight control system, providing test basis.
As optimization, the present invention adopts multi-purpose computer that Windows XP system is installed and Matlab, LabView etc. develop software, for foundation, debugging and the imitative storage and real-time demonstration that flies test data of system mathematic model.Employing code Auto-Generation Tool RTW(Real-Time Workshop) algoritic module and other control model conversation of Simulink being provided are executable code, to strengthen LabVIEW in the weak tendency of the aspects such as control algolithm.The algoritic module that Simulink is provided and other control model conversation are executable code, to strengthen LabVIEW in the weak tendency of the aspects such as control algolithm.Interactively checking Matlab/Simulink model, and like a cork these models are configured to real-time simulation hardware calculating.Adopt LabVIEW RT(Real Time) developing application, then download it in real-time target hardware and move, only need revise a little software program, just it can be integrated into like a cork and add on I/O interface or different LabVIEW real-time target hardware.Outward appearance and the similar control of traditional instrument and the TDMS binary file memory technology of utilizing LabVIEW to provide, realization comprises underlying parameter debugging, calls, the establishment at emulated data observation, storage interface, TDMS is a binary file, and binary file has file and takies the little and fast remarkable advantage of read or write speed of storage space.
Generally speaking, the present invention uses the mode of software modeling to carry out simulation test and l-G simulation test to flight control system, and the feature of this system is that framework is simple, cost is low, efficiency is high.The design that can be widely used in control algolithm in Flight Vehicle Design improves with perfect, for the overall design of aircraft provides test basis.
Accompanying drawing explanation
Fig. 1 is the theory diagram of realizing of the present invention;
Fig. 2 is the outside connection diagram of system;
Fig. 3 is principle and the workflow diagram realized of the present invention;
Fig. 4 is Matlab/Simulink generating code FB(flow block);
Fig. 5 is ± 15V output circuit schematic diagram;
Fig. 6 is 0-25V output circuit schematic diagram.
Embodiment
In order to make object of the present invention, technical scheme and advantage clearer, below in conjunction with drawings and Examples, the present invention is further elaborated.Should be appreciated that specific embodiment described herein, only in order to explain the present invention, is not intended to limit the present invention.In addition,, in each embodiment of described the present invention, involved technical characterictic just can not combine mutually as long as do not form each other conflict.
Referring to Fig. 1,2 and Fig. 3, the combined target missile of the present invention is imitative to fly test macro and comprises simulating developer machine, emulation testing main frame and interface box.
(1) simulating developer machine
Simulating developer machine connects the first end of emulation testing main frame by Ethernet, for the combined target missile flight of setting up based on true rudder and two types of simulation rudders, control model; Target missile flight is controlled to model conversation to be executable code and to send emulation testing main frame to; Model, rudder control signal in real time record operational process are controlled in the flight of off-line simulation operation target missile; Reception is from the rudder control signal of emulation testing main frame, the rudder control signal recording while the flight of itself and off-line simulation operation target missile being controlled to model compares, if the control model of rudder control signal correspondence based on simulation rudder type, its comparative result is in order to judge on bullet the correctness of Flight Control Software in control system, if the control model of rudder control signal correspondence based on true rudder, its comparative result is in order to the Live Flying situation of decision set mould assembly target missile and the ruuning situation of steering wheel.
According to one embodiment of the present invention, simulating developer machine specifically comprises:
Model construction module is controlled in flight, and for setting up combined target missile Elastomer kinematics and kinetic model, model is controlled in the target missile flight building on the basis of combined target missile Elastomer kinematics and kinetic model based on virtual rudder and two types of simulation rudders;
Model running module, controls model for the flight of off-line simulation operation target missile, the rudder control signal in real time record operational process, and send human-computer interaction module to;
Human-computer interaction module, be used for providing human-computer interaction interface to realize the imitative test process monitoring that flies, rudder control signal to the rudder control signal of model running module records and emulation testing main frame feedback compares, to judge on bullet the correctness of Flight Control Software or the Live Flying situation of combined target missile and the ruuning situation of steering wheel in control system;
Run time version generation module, for controlling model allocation models pin according to aircraft to emulation testing host hardware pin, deployment model and configuration file, to emulation testing main frame, finally generate flight and control model to the executable code of emulation testing main frame;
Developing engine Ethernet interface, its one end connects run time version generation module and user interactive module, the other end connects emulation testing main frame by Ethernet, for the executable code that run time version generation module is generated, send emulation testing main frame to, send the rudder control signal from emulation testing main frame to human-computer interaction module.
Body mathematic(al) mode has characterized target missile body characteristic and the rule under high-speed motion.Imitative to 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, adopt LabVIEW SIT to realize LabVIEW and Matlab/Simulink interactive programming, then using algoritic module and other control model conversation that Auto-Generation Tool RTW provides Simulink is executable code, and implementation procedure as shown in Figure 4.Concrete steps are:
(a), according to the body characteristic of combined target missile, use Matlab/Simulink and other professional module to set up the Simulink model of body.Building on the basis of model, can utilize the professional tool case that MATLAB provides to carry out the design and analysis work of flight control system.The result of design realizes in Simulink, carries out off-line mathematical simulation, and design parameter is optimized.
(b) characteristic parameter that will observe according to combined target missile, is used LabVIEW founder's machine interactive interface.Utilize the control that LabVIEW provides can complete fast human-computer interaction interface simple and practical, friendly interface.
(c) in the user interface that LabVIEW creates, use Simulink connection manager (SIT) to set up between LabVIEW user interface and Simulink model associated.When the configuration of LabVIEW user interface and operation Simulink model, model need stay open state in Matlab/Simulink.
(d) use Auto-Generation Tool RTW will control model conversation for executable code.By self-defined RTW code, generate option, Simulink is controlled to the model.dll file of model conversation for calling, offer LabVIEW and call.Under the executable code that compiling is generated, pass to the imitative real-time simulation calculating that flies to carry out in Test Host.
(2) emulation testing main frame
The first end of emulation testing main frame connects real-time simulation developing engine by Ethernet, the second end connects control system on the bullet of combined target missile by interface box, for selecting the true angle of rudder reflection information of control system on bullet according to executable code or simulating angle of rudder reflection information as the input of described executable code, carry out executable code, export in real time in the process of implementation body flight path relevant information and send control system on bullet to by interface box; By interface box, receive from the Control signal of the rudder of control system on bullet and send simulating developer machine to.
In the model of simulating developer machine exploitation, will define model to the pin configuration of emulation testing host hardware; Therefore be gather real angle of rudder reflection or determined by simulating developer model with the angle of rudder reflection of simulation, after emulation starts, the main function of emulation testing main frame is flight path information to be passed to control system on bullet carry out Flight Control Software operation, now emulation testing main frame and real-time simulation developing engine only have the mutual of information, and information interaction is also clear and definite in the model of being developed by simulating developer machine.
According to one embodiment of the present invention, emulation testing main frame specifically comprises:
Test machine Ethernet interface, its one end connects real-time simulation developing engine by Ethernet, other end connecting interface case, for the executable code from simulating developer machine being sent to executable code operation module, send the rudder control signal of control system on the bullet from signal acquisition module to simulating developer machine;
Executable code operation module, by supporting the hardware board of real-time system to form, for selecting the true angle of rudder reflection information of control system on bullet or simulating angle of rudder reflection information as the input of described executable code, operation, according to the executable code of target missile flight control model generation, sends the body flight path relevant information of exporting in real time in operational process to signal acquisition module;
Signal acquisition module, for sending the body flight path relevant information from executable code operation module on bullet control system by interface box, sends the rudder control signal of control system on the bullet from interface box to test machine Ethernet interface.
It is to realize simulation mathematical model to form and transform to actual target missile hardware that real-time simulation is calculated.By realistic model rapid deployment, in the real-time hardware of target, be the real signal I/O of interface configuration in control model.The present invention uses that slave computer is imitative flies that Test Host carries out that object code is realized the computing of aerodynamics and kinematical equation, the resolving of the calculating of target trajectory and target missile-target Relative Kinematics, and data acquisition and communication.As preferably, imitative fly Test Host and select the real-time embedded controller PXI-8109RT of NI based on PXI bus, PXI bus is except having the data throughout of 132MB/s, also has accurate Trigger Bus, synchronous clock and for the local bus of equipment room data transmission, can greatly improve the performance of system, and PXI controller can adopt Windows and real-time system dual system, complete system determinacy is required to harsh Simulation Application.This controller has Intel i7-620M dual core processor, the highest internal memory 4GB DDR3-1066MHz, 120GB hard disk, 4 high speed USB ports, 1 RS232 interface.
Imitative, fly in test process, the imitative test macro that flies need gather the input quantity that rudder feedback signal is calculated as dynamic movement model, needs in addition, according to control flow requirement collection, idsplay order signal, to carry out communication with control system on bullet.Described signal acquisition module comprises IO board, AD board, DA board and serial ports board.
Example:
The real-time embedded controller PXI-8109RT of NI, has Intel i7-620M dual core processor, the highest internal memory 4GB DDR3-1066MHz, 120GB hard disk, 4 high speed USB ports, 1 RS232 interface; Configuration USB interface, network interface and keyboard/mouse, display interface device etc., subsidiary Windows XP operating system and the LabVIEW RT real time operating system of prepackage NI, and the driver of various modules;
DA board: NI PXI-67338 road, 16,250ks/s; Analog quantity D/A output channel 8 tunnels, 16 of resolution, Gao Gengxin speed 1MS/s, output voltage amplitude 0～± 10V; Numeral I/O passage 8 tunnels; 24 2 of digit counters;
AD board: NI PXI-6251 analog signals difference acquisition channel 8 tunnels, 16 of resolution, high sampling rate 1.25 ± MS/s(is able to programme), maximum input voltage ± 10V; Analog signals output channel 2 tunnels, 16 of resolution, Gao Gengxin speed 2.8MS/s, maximum output voltage ± 10V; Numeral I/O passage 24 tunnels; 2,32 location/counters;
IO board: NI PXI-6528 ± 60V, 24 tunnels enter, and 24 tunnels go out, channel separation;
Serial ports board: PXI-8433/4 high-performance 4 road serial line interfaces;
(3) interface box
Be connected on the bullet of emulation testing main frame and combined target missile between control system, for control system on bullet provides power supply, for by transferring to emulation testing main frame after the true angle of rudder reflection information conditioning from control system on bullet, send the body flight path relevant information conditioning from emulation testing main frame on bullet control system simultaneously.Conditioning is mainly only the signal condition of emulation testing main frame output to be become to the signal that on bullet, control system can receive, the signal that simultaneously becomes emulation testing main frame to receive the signal condition of control system output on bullet.
The imitative interface box that flies test macro connects control system on bullet, for control system on bullet provides power supply, and comprise+27V(of power supply power switch rated operational current 20A, dash current 60A.), secondary power supply ± 15V(output power is 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 testing main frame simulation computer AD board input voltage range ± 10V, AD collection signal is directly inputted into AD analog input card after capacitance-resistance filter.D/A circuit design adopts amplifying circuit that the signal extension of simulation calculation machine board card output ± 10V scope is arrived ± 15V and 0～25V, controls the requirement of computing machine and the different voltage ranges of topworks to meet combined target missile.
At the system development initial stage, imitative fly test macro and can carry out off-line simulation to model.Utilize Simulink under Matlab 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 Control Algorithm, the result of design realizes and carries out off-line mathematical simulation in Simulink, and design parameter is optimized.After mathematical simulation completes, imitative fly test macro can by following approach complete flight control system fly control software verification and hardware-in-the-loop simulation is verified.(SIT be Labview exploitation with module simulink model interface)
The course of work of system of the present invention is specific as follows:
Realize Control System Software checking on bullet: only connect control system material object on bullet and do not connect steering wheel.Simulating developer machine plays in model entirely selects simulation steering wheel, and the Control signal of the rudder that model need be exported to body flight path relevant information and need to gather control system on bullet is deployed to the pin of emulation testing host hardware.Model has been disposed rear generation executable code and has been downloaded to emulation testing main frame, in emulation testing main frame, moves degree-of-freedom Simulation, will in simulation process, need the Control signal of the rudder of observation to send simulating developer machine to by Ethernet.In simulating developer machine, contrast control system on mathematical simulation and bullet and resolve the Control signal of the rudder obtaining, on scored bomb, fly to control program correctness.
Closed steering wheel operation in kind: connect control system material object and steering wheel on bullet, simulating developer machine entirely plays in model and selects steering wheel in kind, gathers the rudder feedback signal of steering wheel in kind.The input/output signal of model is deployed to the pin of emulation testing host hardware.Model has been disposed rear generation executable code and has been downloaded to emulation testing main frame, will after model generation executable code, be downloaded to emulation testing main frame, operation degree-of-freedom Simulation, the practical flight effect after examination access rudder in kind and the ruuning situation of steering wheel.
Imitative, can produce a large amount of data in flying test process, these process datas are for analytical test process and to find its improved route, debugging and localization of fault be very necessary.Outward appearance and the similar control of traditional instrument and TDMS binary file memory technology that native system is used LabVIEW to provide, realization comprises underlying parameter debugging, calls, the establishment at emulated data observation, storage interface.
TDMS binary file memory technology can realize reliably, active data storage, 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 binary file, binary file have file take the little and read or write speed of storage space fast remarkable advantage.As shown in table 1 through experimental test TDMS data event memory:
The test of table 1 data memory property
Those skilled in the art will readily understand; the foregoing is only preferred embodiment of the present invention; not in order to limit the present invention, all any modifications of doing within the spirit and principles in the present invention, be equal to and replace and improvement etc., within all should being included in 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 testing main frame by Ethernet, for the combined target missile flight of setting up based on two types of true rudder and simulation rudders, control model; Target missile flight is controlled to model conversation to be executable code and to send emulation testing main frame to; Model, rudder control signal in real time record operational process are controlled in the flight of off-line simulation operation target missile; Reception is from the rudder control signal of emulation testing main frame, the rudder control signal recording while the flight of itself and off-line simulation operation target missile being controlled to model compares, if the control model of rudder control signal correspondence based on simulation rudder type, its comparative result is in order to judge on bullet the correctness of Flight Control Software in control system, if the control model of rudder control signal correspondence based on true rudder, its comparative result is in order to the Live Flying situation of decision set mould assembly target missile and the ruuning situation of steering wheel;
Emulation testing main frame, its first end connects real-time simulation developing engine by Ethernet, the second end connects control system on the bullet of combined target missile by interface box, for selecting the true angle of rudder reflection information of control system on bullet according to executable code or simulating angle of rudder reflection information as the input of described executable code, carry out executable code, export in real time in the process of implementation body flight path relevant information and send control system on bullet to by interface box; By interface box, receive from the Control signal of the rudder of control system on bullet and send simulating developer machine to;
Interface box, be connected on the bullet of emulation testing main frame and combined target missile between control system, for to transferring to emulation testing main frame after the true angle of rudder reflection information from control system on bullet and Control signal of the rudder conditioning, after being nursed one's health, the body flight path relevant information from emulation testing main frame sends control system on bullet to.
2. combined target missile according to claim 1 is imitative flies test macro, it is characterized in that, described simulating developer machine comprises:
Model construction module is controlled in flight, and for setting up combined target missile Elastomer kinematics and kinetic model, model is controlled in the target missile flight building on the basis of combined target missile Elastomer kinematics and kinetic model based on virtual rudder and two types of simulation rudders;
Model running module, controls model for the flight of off-line simulation operation target missile, the rudder control signal in real time record operational process, and send human-computer interaction module to;
Human-computer interaction module, be used for providing human-computer interaction interface to realize the imitative test process monitoring that flies, rudder control signal to the rudder control signal of model running module records and emulation testing main frame feedback compares, to judge on bullet the correctness of Flight Control Software or the Live Flying situation of combined target missile and the ruuning situation of steering wheel in control system;
Run time version generation module, for controlling model allocation models pin according to aircraft to emulation testing host hardware pin, deployment model and configuration file, to emulation testing main frame, finally generate flight and control model to the executable code of emulation testing main frame;
Developing engine Ethernet interface, its one end connects run time version generation module and user interactive module, the other end connects emulation testing main frame by Ethernet, for the executable code that run time version generation module is generated, send emulation testing main frame to, send the rudder control signal from emulation testing main frame to human-computer interaction module.
3. combined target missile according to claim 2 is imitated and is flown test macro, it is characterized in that, described simulating developer machine adopts Matlab/Simulink to set up combined target missile body model and model is controlled in target missile flight, adopt LabVIEW founder's machine interactive interface, adopting Auto-Generation Tool RTW and SIT that flight is controlled to model conversation is executable code.
4. combined target missile according to claim 1 and 2 is imitative flies test macro, it is characterized in that, described emulation testing main frame comprises:
Test machine Ethernet interface, its one end connects real-time simulation developing engine by Ethernet, other end connecting interface case, for the executable code from simulating developer machine being sent to executable code operation module, send the rudder control signal of control system on the bullet from signal acquisition module to simulating developer machine;
Executable code operation module, by supporting the hardware board of real-time system to form, for selecting the true angle of rudder reflection information of control system on bullet or simulating angle of rudder reflection information as the input of described executable code, operation, according to the executable code of target missile flight control model generation, sends the body flight path relevant information of exporting in real time in operational process to signal acquisition module;
Signal acquisition module, for sending the body flight path relevant information from executable code operation module on bullet control system by interface box, sends the rudder control signal of control system on the bullet from interface box to test machine Ethernet interface.
5. combined target missile according to claim 4 is imitated and is flown test macro, it is characterized in that, described emulation testing main frame 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 board, AD board, DA board and serial ports board.
6. according to the combined target missile described in claim 1 or 2 or 3 or 4 is imitative, fly test macro, it is characterized in that, at the imitative test process that flies, adopt TDMS binary file storage data.
7. according to the combined target missile described in claim 1 or 2 or 3 or 4 is imitative, fly test macro, it is characterized in that, described interface box comprises:
+ 27V power supply, its power switch rated operational current 20A, dash current 60A;
Secondary power supply ± 15V, its output power 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 arriving the signal extension of emulation testing main frame output ± 10V scope ± 15V and 0～25V.
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| CN104731744A (en) * | 2015-03-13 | 2015-06-24 | 中国航天科技集团公司第九研究院第七七一研究所 | Reconfigurable embedded computer module based on SiP |
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| CN106324572A (en) * | 2016-08-24 | 2017-01-11 | 湖北三江航天红峰控制有限公司 | GPS simulator and realizing method thereof |
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