Guided missile simulation key and important information automatic statistics and discrimination method

Abstract

The invention discloses a missile simulation key and important information automatic statistics and discrimination method. The method comprises the steps of 1, simulation planning design, 2, simulation preparation, 3, simulation control, 4, real-time simulation and 5, data analysis. Wherein in the step 5, parameters in the simulation test process are recorded and analyzed in real time, parameters which do not conform to expectation are recorded, and possible influence factors are analyzed. And taking the execution condition of the simulation period obtained by executing the step 1 to the step 5 once, the corresponding characteristics in the battle situation setting and the simulation parameters after the influence factors are adjusted as input conditions of next simulation, repeating the step 1 to the step 5 to start a new simulation period, and stopping simulation until a simulation termination condition is met. According to the method, the possible influence factors are automatically analyzed when the important information does not conform to the expected target, so that the simulation efficiency is greatly improved, and the influence caused by subjective factors of people during analysis is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of missiles, and in particular relates to a method for automatically counting and distinguishing important information of missile simulation. Background Art

[0002] Semi-physical simulation is also called physical-mathematical simulation or semi-physical simulation. Semi-physical simulation refers to the introduction of a part of the simulated object system into the simulation loop in the form of a physical object (or physical model) for the simulation research content; the rest of the simulated object system is described by a mathematical model and converted into a simulation calculation model. With the help of the physical effect model, real-time mathematical simulation and physical simulation are combined.

[0003] When the existing technology uses semi-physical simulation technology to simulate the missile launch and flight process, it is often necessary to manually record and analyze the key information in the simulation, such as the drop speed, drop angle, target dragging amount, maximum trajectory height, etc., after a simulation cycle is completed, and adjust the simulation parameters according to the results of the recording and analysis to re-simulate. The existing technology seriously affects the efficiency of the simulation, and the analysis process is greatly interfered by human subjective factors, which is not conducive to the simulation optimization. Summary of the invention

[0004] In order to overcome the shortcomings of the prior art, the present invention provides a method for automatic statistics and discrimination of missile simulation critical information, including step 1 simulation planning and design, step 2 simulation preparation, step 3 simulation control, step 4 real-time simulation, and step 5 data analysis. Among them, step 5 records and analyzes the parameters in the simulation test process in real time, and records and analyzes the possible influencing factors for the parameters that do not meet expectations. The execution status of the simulation cycle obtained by executing steps 1 to 5 once, the corresponding characteristics in the battle situation setting, and the simulation parameters after adjusting the influencing factors are used as the input conditions for the next simulation, and steps 1 to 5 are repeated to start a new simulation cycle, and the simulation is stopped after the simulation termination conditions are met. The present invention automatically analyzes the possible influencing factors when the critical information does not meet the expected goals, thereby greatly improving the simulation efficiency and reducing the influence of human subjective factors during analysis.

[0005] The technical solution adopted by the present invention to solve the technical problem is as follows:

[0006] Step 1: Simulation planning and design;

[0007] Overall planning of simulation and preparation of relevant data before simulation, formulation of simulation test samples according to actual test requirements, calibration of simulator parameters and seeker related parameters;

[0008] Step 2: Simulation preparation;

[0009] After the equipment is turned on and the software is started, the test personnel select or generate the assumption data through the command and control computer, and the software automatically completes the data release through the optical fiber network. Then the test personnel can issue simulation preparation instructions through the command and control computer at any time according to the test requirements;

[0010] After receiving the simulation preparation instruction, each participating computer obtains the assumption data related to the computer from the optical fiber network and completes parameter initialization based on the obtained data, including:

[0011] The real-time simulator obtains trajectory assumption data for initialization of flight trajectory parameters;

[0012] The seeker measurement, control and communication computer obtains launch control assumption data for initialization of flight mission data during weapon launch;

[0013] The control computer of the injection infrared target simulator obtains the infrared target assumption data and completes the infrared scene simulation configuration and initialization;

[0014] Step 3: Simulation control;

[0015] The test personnel issue start-up control instructions through the simulation control computer according to the test requirements;

[0016] The seeker measurement and control communication computer responds to the start-up control command, completes the control process according to the working sequence of the seeker under test, and reports the command response status and operation status; if the seeker under test works in the pre-launch interception mode, the real-time simulation computer sends initialization instructions and data after the seeker under test intercepts the target, and the turntable system queries the drive control instructions and data sent by the real-time simulation computer in real time to complete the motion initialization. The real-time simulation computer reports the command response status according to the turntable initialization completion status, and other participating nodes dynamically report the operation status;

[0017] After the relevant test computers and simulation equipment have executed the start-up control command, they report the start-up control status to the simulation control computer through the real-time communication network. After the control computer receives the command response status and operation status fed back by the relevant test computers, it performs the following judgment and control:

[0018] If the command response status fed back by the relevant test computers is normal, wait for the test personnel to launch the weapon to start the real-time simulation phase;

[0019] If the command response fed back by the relevant participating computers indicates that the node status is abnormal, a simulation abort command is issued to stop the simulation process, and then each participating computer completes status recovery and waits for the next simulation preparation;

[0020] Step 4: Real-time simulation;

[0021] After the launch control phase is completed, the test personnel can issue weapon launch commands through the simulation control computer according to the test requirements and enter the real-time simulation phase;

[0022] In the real-time simulation stage, each participating computer takes the next synchronization interrupt corresponding to the synchronization interrupt of the weapon launch command as the simulation zero time, and starts the simulation test after synchronization according to their respective working cycles. At this time:

[0023] The real-time simulation computer advances the simulation process according to the preset simulation cycle;

[0024] The seeker measurement and control communication computer completes the measurement and control of the seeker under test and forwards the guidance signal;

[0025] The injection-type infrared target simulator controls the infrared scene digital image generated by the computer to complete the drive output control of the infrared target simulator;

[0026] The turntable system completes the processing of drive control instructions and data;

[0027] Step 5: Data analysis;

[0028] The parameters in the simulation test are recorded and analyzed in real time to determine whether the key information of the missile corresponding to the tested seeker meets expectations. If there is any non-compliance, the time point of non-compliance is recorded and possible influencing factors are analyzed, including:

[0029] Step 5-1: Establish a knowledge graph of target trajectory key information and influencing factors, and obtain a deep learning analysis model that covers the most key information and influencing factors as the analysis model for this simulation cycle;

[0030] Step 5-2: Establish a set of important information U1 of the missile to be tested, and establish a set of target range of important information U2 of the missile to be tested; during the simulation test, obtain parameter information belonging to U1, and determine whether the obtained parameter information belongs to the target range of the corresponding parameter in U2, and take the parameters that belong to U1 but not to the corresponding target range of U2 as the target parameters, and proceed to step 5-3;

[0031] Step 5-3: Record the time period information when the target parameter does not belong to U2: T0, Tz, Q, where T0 is the time point when the target parameter does not belong to U2 for the first time in the time period; Tz is the time point when the target parameter returns to U2 in the time period, and the absence of Tz means that the target parameter has not returned to U2 in this simulation cycle; Q is the length of the time period; and determine whether Q is greater than W. If Q is greater than W, go to step 5-4, W is the upper limit of the time period that the target parameter can accept to exceed the error, W≥0, when W=0, the target parameter does not accept the error;

[0032] Step 5-4: Use the analysis model selected in step 5-1, combined with the key information-influencing factor knowledge graph obtained in step 5-1, to analyze the influencing factors of the target parameters, obtain the possible influencing factors that lead to the appearance of the target parameters, and form the corresponding influencing weights;

[0033] Step 6: After the simulation is performed for a preset time or the missile flies a preset distance, a simulation cycle is completed;

[0034] Step 7: Use the execution status of this simulation cycle obtained by executing steps 1 to 5 once, the corresponding characteristics in the battle situation setting, and the simulation parameters after adjusting the influencing factors as the input conditions for the next simulation, and repeat steps 1 to 5 to start a new simulation cycle, and stop the simulation when the simulation termination conditions are met.

[0035] Furthermore, the preparation of simulation test samples in step 1 specifically includes: performing specific sample condition planning according to the test task, missile performance, and semi-physical simulation performance; the sample condition planning includes:

[0036] Launch condition planning: Determine the missile entry angle, launch distance, initial speed, and elevation difference parameters based on the missile attack area and target movement capability;

[0037] Target characteristic parameter determination, including: determining the target type, maneuvering mode, and radiation energy parameters based on the target motion and radiation characteristics;

[0038] Determination of interference condition parameters, including: determining the number of interference missiles, missile interval, release angle, initial velocity, and release time parameters according to the interference type and release strategy;

[0039] Determine the background environment parameters, including: determine the background type and lighting condition parameters;

[0040] The deviation condition parameters are determined, including: determining the target, the deviation range of interference and the condition parameters.

[0041] Furthermore, in step 2, the test personnel select or generate the assumption data through the command and control computer, the software automatically completes the data release through the optical fiber network, and then the test personnel issue the simulation preparation instruction through the command and control computer at any time according to the test requirements, including:

[0042] Step 2-1: The real-time simulation computer sends initialization instructions and data according to the assumed turntable pre-bias value, and the turntable system queries the drive control instructions and data sent by the real-time simulation computer in real time to complete the motion initialization; other participating computers complete the initialization of local software;

[0043] Step 2-2: After executing the simulation preparation instruction, each relevant test computer and simulation device reports the simulation preparation status and operation status to the command control computer through the optical fiber reflection memory network;

[0044] Step 2-3: After the control computer inquires and waits for the feedback status of each participating computer, it executes the following judgment control:

[0045] If the feedback status of each participating computer is normal, wait for the test personnel to start the control operation to enter the start control simulation stage;

[0046] If there are nodes with abnormal status in the feedback from each participating computer, a simulation termination instruction is issued to stop the simulation process, and then each participating computer completes status recovery and waits for the next simulation preparation;

[0047] If the simulation control computer fails to query the feedback status of all participating computers within the specified time, it will prompt that the preparation has timed out and send a simulation abort instruction to stop the simulation process. Each participating computer will complete the status recovery according to the simulation abort instruction, and the software and hardware of each node will be restored to the state of waiting for the next simulation preparation.

[0048] Furthermore, during the simulation experiment in step 4, the specific workflow of the real-time simulation computer includes:

[0049] Step 4-1-1: Complete the sending of clock synchronization interrupt, receiving of guidance data, calculation of ballistic model and calculation of driving model, and send the data to be published to the optical fiber reflection memory network after associating the timestamp, and complete the target encounter condition judgment according to the ballistic parameters and the maximum flight time, and give the simulation end instruction when the target encounter condition is met or the maximum flight time is reached;

[0050] Step 4-1-2: Complete the record cache of local data;

[0051] Step 4-1-3: Dynamically respond to the random control instructions issued by the simulation control computer throughout the whole process, and complete the dynamic update of the response and operation status;

[0052] Step 4-1-4: When the working state given by the seeker under test does not meet the guidance closed loop requirements or enters the blind range, the real-time combat situation solving computer freezes the device drive data update and switches to the recursive mode, and continues to simulate and solve the flight trajectory until the pre-target conditions are met or the maximum flight time is reached;

[0053] Step 4-1-5: After the simulation end condition is met or the simulation termination instruction is received, the key data of the simulation process is first stored in the file, and then the status is restored and the recovery status is reported;

[0054] Step 4-1-6: Enter the simulation waiting state and wait for the next simulation preparation instruction.

[0055] Furthermore, in step 4, the specific workflow of the seeker measurement and control communication computer during the simulation experiment includes:

[0056] Step 4-2-1: collect the guidance data output by the measured guidance head in each working cycle, and send the guidance data to the optical fiber reflection memory network;

[0057] Step 4-2-2: Dynamically respond to the simulation control instruction and complete the update of the response and operation status;

[0058] Step 4-2-3: Complete the record cache of local data;

[0059] Step 4-2-4: After receiving the simulation end or simulation termination instruction, first complete the file storage of the key data of the simulation process, then complete the status recovery and report the recovery status;

[0060] Step 4-2-5: Enter the simulation waiting state and wait for the next simulation preparation instruction.

[0061] Furthermore, in step 4, the specific workflow of the injection-type infrared target simulator during the simulation experiment includes:

[0062] Step 4-3-1: Acquire target-missile driving data and generate infrared scene digital image;

[0063] Step 4-3-2: Cache data from video memory to internal memory;

[0064] Step 4-3-3: Cache on the injection transmission card through the PCI-E bus;

[0065] Step 4-3-4: Responding to the trigger of the synchronization signal, the data is transmitted to the front-end conversion module via the optical fiber;

[0066] Step 4-3-5: The front-end conversion module uses the CML bus to send the signal to the seeker signal processor for simulation;

[0067] Step 4-3-6: After receiving the simulation end or simulation termination instruction, first complete the file storage of the key data of the simulation process, then complete the status recovery and report the recovery status;

[0068] Step 4-3-7: Enter the simulation waiting state and wait for the next simulation preparation instruction.

[0069] Further, the turntable system includes a multi-axis turntable system and a desktop simulation system;

[0070] The multi-axis turntable system is: a three-axis turntable system or a five-axis turntable system;

[0071] The desktop simulation system is: a desktop injection-type simulation system based on sight angle compensation or a seeker injection-type simulation system based on a stable platform model.

[0072] Furthermore, in step 4, the specific workflow of the multi-axis turntable system during the simulation experiment includes:

[0073] Step 4-4-1: Query the turntable drive control instructions and data to complete the positioning, servo and zero return motion control of the turntable frame;

[0074] Step 4-4-2: Dynamically respond to the turntable emergency trigger, and activate the safety protection mechanism when the trigger is valid;

[0075] Step 4-4-3: Real-time dynamic update of feedback data and operation status;

[0076] Step 4-4-4: Complete the record cache of local data;

[0077] Step 4-4-5: When receiving the zeroing drive control instruction, first complete the file storage of the key data of the simulation process, then complete the state recovery and report the recovery state;

[0078] Step 4-4-6: Enter the simulation waiting state and wait for the next simulation preparation instruction.

[0079] Furthermore, when the turntable system is a desktop injection-type simulation system based on line of sight angle compensation, the seeker, flight control cabin, inertial group simulator, and injection-type infrared target simulator are all placed on the desktop;

[0080] The main simulation unit receives the flight control command from the flight control cabin based on the line of sight angular velocity information and the inertial navigation information generated by the inertial navigation simulator, and solves the missile body attitude motion data. The data is sent to the line of sight angular velocity compensation module for line of sight angular velocity compensation in combination with the seeker frame angle data; combined with the missile acceleration information, it is sent to the inertial navigation simulator to generate new inertial navigation information; at the same time, the target-missile position and attitude data are sent to the high-performance graphics workstation in the injection infrared target simulator as the data source for real-time generation of infrared scenes; the data is transmitted and stored through the reflective memory network;

[0081] The injection-type infrared target simulator receives the seeker frame angle signal and target-missile position and attitude data transmitted by the test product - signal collector, generates infrared scenes in real time, and converts them into 16-bit image data injected into the seeker; the image is sent and injected to the board card and transmitted to the signal conversion module through optical fiber. The module converts the signal into CML signal and directly injects it into the signal processor of the seeker to realize signal injection simulation.

[0082] Furthermore, when the turntable system is a seeker injection simulation system based on a stable platform model, the seeker, the flight control cabin, the inertial group simulator, and the injection infrared target simulator are all placed on the desktop;

[0083] The main simulation unit receives the flight control command formed by the flight control cabin based on the line of sight angular velocity information and the inertial navigation information generated by the inertial navigation simulator, and solves the missile body attitude motion data, which is sent to the seeker stable platform model, and the model generates the servo frame angle information and the seeker line of sight angular velocity information in real time, wherein the seeker line of sight angular velocity information is transmitted to the flight control cabin, and the servo frame angle information is transmitted to the injection infrared target simulator; the missile acceleration information generated by the main simulation unit is sent to the inertial navigation simulator to generate new inertial navigation information, and at the same time, the target-missile position and attitude data are sent to the high-performance graphics workstation in the injection infrared target simulator as the data source for real-time generation of infrared scenes; the data is transmitted and stored through the reflective memory network;

[0084] The injection-type infrared target simulator receives the seeker frame angle signal generated by the seeker stabilization platform and the target-missile position and attitude data calculated by the main simulator, generates an infrared scene in real time, and converts it into 16-bit image data that is injected into the seeker. The image is sent and injected to the board and transmitted to the signal conversion module through optical fiber. The module converts the signal into a CML signal and directly injects it into the seeker signal processing unit to realize signal injection simulation.

[0085] The beneficial effects of the present invention are as follows:

[0086] The present invention provides a method for automatic statistics and discrimination of missile simulation critical information. Based on the existing semi-physical simulation technology, the method combines knowledge graphs and deep learning analysis models to analyze whether the critical information meets the expected goals during the simulation process, and automatically analyzes possible influencing factors when the critical information does not meet the expected goals, thereby greatly improving the simulation efficiency and reducing the influence of human subjective factors during analysis. DETAILED DESCRIPTION

[0087] The present invention is further described below in conjunction with embodiments.

[0088] The embodiment of the present invention exemplarily provides a method for automatically counting and distinguishing important information of missile simulation, including the following steps:

[0089] Step 1: Simulation planning and design;

[0090] Overall planning of simulation and preparation of relevant data before simulation, formulation of simulation test samples according to actual test requirements, calibration of simulator parameters and seeker related parameters;

[0091] Step 2: Simulation preparation:

[0092] After the equipment is turned on and the software is started, the test personnel select or generate the assumption data through the command and control computer, and the software automatically completes the data release through the optical fiber network. Then the test personnel can issue simulation preparation instructions through the command and control computer at any time according to the test requirements;

[0093] After receiving the simulation preparation instruction, each participating computer obtains the assumption data related to the computer from the optical fiber network and completes parameter initialization based on the obtained data, including:

[0094] The real-time simulator obtains trajectory assumption data for initialization of flight trajectory parameters;

[0095] The seeker measurement, control and communication computer obtains launch control assumption data for initialization of flight mission data during weapon launch;

[0096] The control computer of the injection infrared target simulator obtains the infrared target assumption data and completes the infrared scene simulation configuration and initialization;

[0097] Step 3: Simulation control;

[0098] The test personnel issue start-up control instructions through the simulation control computer according to the test requirements;

[0099] The seeker measurement and control communication computer responds to the start-up control command, completes the control process according to the working sequence of the seeker under test, and reports the command response status and operation status; if the seeker under test works in the pre-launch interception mode, the real-time simulation computer sends initialization instructions and data after the seeker under test intercepts the target, and the turntable system queries the drive control instructions and data sent by the real-time simulation computer in real time to complete the motion initialization. The real-time simulation computer reports the command response status according to the turntable initialization completion status, and other participating nodes dynamically report the operation status;

[0100] After the relevant test computers and simulation equipment have executed the start-up control command, they report the start-up control status to the simulation control computer through the real-time communication network. After the control computer receives the command response status and operation status fed back by the relevant test computers, it performs the following judgment and control:

[0101] If the command response status fed back by the relevant test computers is normal, wait for the test personnel to launch the weapon to start the real-time simulation phase;

[0102] If the command response fed back by the relevant participating computers indicates that the node status is abnormal, a simulation abort command is issued to stop the simulation process, and then each participating computer completes status recovery and waits for the next simulation preparation;

[0103] Step 4: Real-time simulation;

[0104] After the launch control phase is completed, the test personnel can issue weapon launch commands through the simulation control computer according to the test requirements and enter the real-time simulation phase;

[0105] In the real-time simulation stage, each participating computer takes the next synchronization interrupt corresponding to the synchronization interrupt of the weapon launch command as the simulation zero time, and starts the simulation test after synchronization according to their respective working cycles. At this time:

[0106] The real-time simulation computer advances the simulation process according to the preset simulation cycle;

[0107] The seeker measurement and control communication computer completes the measurement and control of the seeker under test and forwards the guidance signal;

[0108] The injection-type infrared target simulator controls the infrared scene digital image generated by the computer to complete the drive output control of the infrared target simulator;

[0109] The turntable system completes the processing of drive control instructions and data;

[0110] Step 5: Data analysis;

[0111] The parameters in the simulation test are recorded and analyzed in real time to determine whether the key information of the missile corresponding to the tested seeker meets expectations. If there is any non-compliance, the time point of non-compliance is recorded and possible influencing factors are analyzed, including:

[0112] Step 5.1: Establish a knowledge graph of target trajectory key information and influencing factors, and obtain a deep learning analysis model that covers the most key information and influencing factors as the analysis model for this simulation cycle;

[0113] Step 5.2 establishes a set of important information of the missile to be tested, U1, and establishes a set of target range of important information of the missile to be tested, U2; during the simulation test, obtains parameter information belonging to U1, and determines whether the obtained parameter information belongs to the target range of the corresponding parameter in U2, and takes the parameters that belong to U1 but not to the corresponding target range of U2 as the target parameters, and proceeds to step 5.3;

[0114] Step 5.3 records the time period information when the target parameter does not belong to U2: T0, Tz, Q, where T0 is the time point when the target parameter does not belong to U2 for the first time in the time period, Tz is the time point when the target parameter returns to U2 in the time period, and the absence of Tz means that the target parameter has not returned to U2 in this simulation cycle, and Q is the length of the time period; and judge whether Q is greater than W. If Q is greater than W, go to step 5.4, W is the upper limit of the time period that the target parameter can accept to exceed the error, W≥0, when W=0, the target parameter does not accept the excess error;

[0115] Step 5.4: Utilize the analysis model selected in step 5.1 and combine it with the key information-influencing factor knowledge graph obtained in step 5.1 to analyze the influencing factors of the target parameters, obtain the possible influencing factors that lead to the appearance of the target parameters, and form the corresponding influencing weights;

[0116] Step 6: After the simulation is performed for a preset time or the missile flies a preset distance, a simulation cycle is completed;

[0117] Step 7: Use the execution status of this simulation cycle obtained by executing steps 1 to 5 once, the corresponding characteristics in the battle situation setting, and the simulation parameters after adjusting the influencing factors as the input conditions for the next simulation, and repeat steps 1 to 5 to start a new simulation cycle, and stop the simulation when the simulation termination conditions are met.

[0118] Based on the existing semi-physical simulation technology, the present invention combines knowledge graphs and deep learning analysis models to analyze whether the key information meets the expected goals during the simulation process, and automatically analyzes possible influencing factors when the key information does not meet the expected goals, thereby greatly improving the simulation efficiency and reducing the impact of human subjective factors during analysis.

[0119] The present invention exemplarily provides a method for formulating simulation test samples in step 1, which is: performing specific sample condition planning according to the test task, missile performance, and semi-physical simulation performance; the sample condition planning includes:

[0120] Launch condition planning: Determine the missile entry angle, launch distance, initial speed, and elevation difference parameters based on the missile attack area and target movement capability;

[0121] Target characteristic parameter determination, including: determining the target type, maneuvering mode, and radiation energy parameters based on the target motion and radiation characteristics;

[0122] Determination of interference condition parameters, including: determining the number of interference missiles, missile interval, release angle, initial velocity, and release time parameters according to the interference type and release strategy;

[0123] Determine the background environment parameters, including: determine the background type and lighting condition parameters;

[0124] The deviation condition parameters are determined, including: determining the target, the deviation range of interference and the condition parameters.

[0125] The present invention exemplarily provides a method in which the test personnel in step 2 selects or generates the assumption data through the command and control computer, the software automatically completes the data release through the optical fiber network, and then the test personnel issues the simulation preparation instruction through the command and control computer at any time according to the test requirements, including:

[0126] Step 2.1: The real-time simulation computer sends initialization instructions and data according to the assumed turntable pre-bias value, and the turntable system queries the drive control instructions and data sent by the real-time simulation computer in real time to complete the motion initialization; other participating computers complete the initialization of local software;

[0127] Step 2.2: After executing the simulation preparation instruction, each relevant test computer and simulation device reports the simulation preparation status and operation status to the command control computer through the optical fiber reflection memory network;

[0128] Step 2.3: After the control computer queries and waits for the feedback status of each participating computer, it executes the following judgment control:

[0129] If the feedback status of each participating computer is normal, wait for the test personnel to start the control operation to enter the start control simulation stage;

[0130] If there are nodes with abnormal status in the feedback from each participating computer, a simulation termination instruction is issued to stop the simulation process, and then each participating computer completes status recovery and waits for the next simulation preparation;

[0131] If the simulation control computer fails to query the feedback status of all participating computers within the specified time, it will prompt that the preparation has timed out and send a simulation abort instruction to stop the simulation process. Each participating computer will complete the status recovery according to the simulation abort instruction, and the software and hardware of each node will be restored to the state of waiting for the next simulation preparation.

[0132] The present invention exemplarily provides a specific workflow of a real-time simulation computer when performing the simulation experiment described in step 4, including:

[0133] Step 4.1.1: Complete the sending of clock synchronization interrupt, receiving of guidance data, solving of ballistic model and solving of driving model, and send the data to be published to the optical fiber reflection memory network after associating the timestamp, and complete the target encounter condition judgment according to the ballistic parameters and the maximum flight time, and give the simulation end instruction when the target encounter condition is met or the maximum flight time is reached;

[0134] Step 4.1.2: Complete the record cache of local data;

[0135] Step 4.1.3: Dynamically respond to the random control instructions issued by the simulation control computer throughout the whole process, and complete the dynamic update of the response and operation status;

[0136] Step 4.1.4: When the working state given by the seeker under test does not meet the guidance closed loop requirements or enters the blind range, the real-time combat situation solving computer freezes the device drive data update and switches to the recursive mode, and continues to simulate and solve the flight trajectory until the pre-target conditions are met or the maximum flight time is reached;

[0137] Step 4.1.5: After the simulation end condition is met or the simulation termination instruction is received, the key data of the simulation process is first stored in the file, and then the status is restored and the recovery status is reported;

[0138] Step 4.1.6: Enter the simulation waiting state and wait for the next simulation preparation instruction.

[0139] The present invention exemplarily provides a specific workflow of a seeker measurement and control communication computer when performing the simulation experiment described in step S4, including:

[0140] Step 4.2.1: Collect the guidance data output by the measured guidance head in each working cycle, and send the guidance data to the optical fiber reflection memory network;

[0141] Step 4.2.2: Dynamically respond to the simulation control instruction and complete the update of the response and operation status;

[0142] Step 4.2.3: Complete the record cache of local data;

[0143] Step 4.2.4: After receiving the simulation end or simulation termination instruction, first complete the file storage of the key data of the simulation process, then complete the status recovery and report the recovery status;

[0144] Step 4.2.5: Enter the simulation waiting state and wait for the next simulation preparation instruction.

[0145] The present invention exemplarily provides a specific workflow of an injection-type infrared target simulator when performing the simulation experiment described in step S4, including:

[0146] Step 4.3.1: Acquire target-missile driving data and generate infrared scene digital image;

[0147] Step 4.3.2: Cache data from video memory to main memory;

[0148] Step 4.3.3: Cache on the injection transmission card through the PCI-E bus;

[0149] Step 4.3.4: Responding to the trigger of the synchronization signal, the data is transmitted to the front-end conversion module via the optical fiber;

[0150] Step 4.3.5: The front-end conversion module uses the CML bus to send the signal to the seeker signal processor for simulation;

[0151] Step 4.3.6: After receiving the simulation end or simulation termination instruction, first complete the file storage of the key data of the simulation process, then complete the status recovery and report the recovery status;

[0152] Step 4.3.7: Enter the simulation waiting state and wait for the next simulation preparation instruction.

[0153] The present invention exemplarily provides a turntable system, comprising: a multi-axis turntable system and a desktop simulation system;

[0154] The multi-axis turntable system is: a three-axis turntable system or a five-axis turntable system;

[0155] The desktop simulation system is: a desktop injection-type simulation system based on sight angle compensation or a seeker injection-type simulation system based on a stable platform model.

[0156] The present invention exemplarily provides a specific workflow of a multi-axis turntable system when performing the simulation experiment described in step 4, including:

[0157] Step 4.4.1: Query the turntable drive control instructions and data to complete the positioning, servo and zero return motion control of the turntable frame;

[0158] Step 4.4.2: Dynamically respond to the turntable emergency trigger and activate the safety protection mechanism when the trigger is valid;

[0159] Step 4.4.3: Dynamically update feedback data and operation status in real time;

[0160] Step 4.4.4: Complete the record cache of local data;

[0161] Step 4.4.5: When receiving the zeroing drive control instruction, first complete the file storage of the key data of the simulation process, then complete the state recovery and report the recovery state;

[0162] Step 4.4.6: Enter the simulation waiting state and wait for the next simulation preparation instruction.

[0163] The present invention exemplarily provides a specific workflow when the turntable system is a desktop injection simulation system based on line of sight angle compensation, including:

[0164] The seeker, flight control cabin, inertial group simulator, and injection infrared target simulator are all placed on the table;

[0165] The main simulation unit receives the flight control command from the flight control cabin based on the line of sight angular velocity information and the inertial navigation information generated by the inertial navigation simulator, and solves the missile body attitude motion data. The data is sent to the line of sight angular velocity compensation module for line of sight angular velocity compensation in combination with the seeker frame angle data; combined with the missile acceleration information, it is sent to the inertial navigation simulator to generate new inertial navigation information; at the same time, the target-missile position and attitude data are sent to the high-performance graphics workstation in the injection infrared target simulator as the data source for real-time generation of infrared scenes; the data is transmitted and stored through the reflective memory network;

[0166] The injection-type infrared target simulator receives the seeker frame angle signal and target-missile position and attitude data transmitted by the test product - signal collector, generates infrared scenes in real time, and converts them into 16-bit image data injected into the seeker; the image is sent and injected to the board card and transmitted to the signal conversion module through optical fiber. The module converts the signal into CML signal and directly injects it into the signal processor of the seeker to realize signal injection simulation.

[0167] The present invention exemplarily provides a specific workflow when a turntable system is a seeker injection simulation system based on a stable platform model, including:

[0168] The seeker, flight control cabin, inertial group simulator, and injection infrared target simulator are all placed on the table;

[0169] The main simulation unit receives the flight control command formed by the flight control cabin based on the line of sight angular velocity information and the inertial navigation information generated by the inertial navigation simulator, and solves the missile body attitude motion data, which is sent to the seeker stable platform model, and the model generates the servo frame angle information and the seeker line of sight angular velocity information in real time, wherein the seeker line of sight angular velocity information is transmitted to the flight control cabin, and the servo frame angle information is transmitted to the injection infrared target simulator; the missile acceleration information generated by the main simulation unit is sent to the inertial navigation simulator to generate new inertial navigation information, and at the same time, the target-missile position and attitude data are sent to the high-performance graphics workstation in the injection infrared target simulator as the data source for real-time generation of infrared scenes; the data is transmitted and stored through the reflective memory network;

[0170] The injection-type infrared target simulator receives the seeker frame angle signal generated by the seeker stabilization platform and the target-missile position and attitude data calculated by the main simulator, generates an infrared scene in real time, and converts it into 16-bit image data that is injected into the seeker. The image is sent and injected to the board and transmitted to the signal conversion module through optical fiber. The module converts the signal into a CML signal and directly injects it into the seeker signal processing unit to realize signal injection simulation.

Claims

1. A method for automatically counting and distinguishing important information of missile simulation, characterized in that: The steps include: Step 1: Simulation planning and design; Overall planning of simulation and preparation of relevant data before simulation, formulation of simulation test samples according to actual test requirements, calibration of simulator parameters and seeker related parameters; Step 2: Simulation preparation; After the equipment is turned on and the software is started, the test personnel select or generate the assumption data through the command and control computer, and the software automatically completes the data release through the optical fiber network. Then the test personnel can issue simulation preparation instructions through the command and control computer at any time according to the test requirements; After receiving the simulation preparation instruction, each participating computer obtains the assumption data related to the computer from the optical fiber network and completes parameter initialization based on the obtained data, including: The real-time simulator obtains trajectory assumption data for initialization of flight trajectory parameters; The seeker measurement, control and communication computer obtains launch control assumption data for initialization of flight mission data during weapon launch; The control computer of the injection infrared target simulator obtains the infrared target assumption data and completes the infrared scene simulation configuration and initialization; Step 3: Simulation control; The test personnel issue start-up control instructions through the simulation control computer according to the test requirements; The seeker measurement and control communication computer responds to the start-up control command, completes the control process according to the working sequence of the seeker under test, and reports the command response status and operation status; if the seeker under test works in the pre-launch interception mode, the real-time simulation computer sends initialization instructions and data after the seeker under test intercepts the target, and the turntable system queries the drive control instructions and data sent by the real-time simulation computer in real time to complete the motion initialization. The real-time simulation computer reports the command response status according to the turntable initialization completion status, and other participating nodes dynamically report the operation status; After the relevant test computers and simulation equipment have executed the start-up control command, they report the start-up control status to the simulation control computer through the real-time communication network. After the control computer receives the command response status and operation status fed back by the relevant test computers, it performs the following judgment and control: If the command response status fed back by the relevant test computers is normal, wait for the test personnel to launch the weapon to start the real-time simulation phase; If the command response fed back by the relevant participating computers indicates that the node status is abnormal, a simulation abort command is issued to stop the simulation process, and then each participating computer completes status recovery and waits for the next simulation preparation; Step 4: Real-time simulation; After the launch control phase is completed, the test personnel can issue weapon launch commands through the simulation control computer according to the test requirements and enter the real-time simulation phase; In the real-time simulation stage, each participating computer takes the next synchronization interrupt corresponding to the synchronization interrupt of the weapon launch command as the simulation zero time, and starts the simulation test after synchronization according to their respective working cycles. At this time: The real-time simulation computer advances the simulation process according to the preset simulation cycle; The seeker measurement and control communication computer completes the measurement and control of the seeker under test and forwards the guidance signal; The injection-type infrared target simulator controls the infrared scene digital image generated by the computer to complete the drive output control of the infrared target simulator; The turntable system completes the processing of drive control instructions and data; Step 5: Data analysis; The parameters in the simulation test are recorded and analyzed in real time to determine whether the key information of the missile corresponding to the tested seeker meets expectations. If there is any non-compliance, the time point of non-compliance is recorded and possible influencing factors are analyzed, including: Step 5-1: Establish a knowledge graph of target trajectory key information and influencing factors, and obtain a deep learning analysis model that covers the most key information and influencing factors as the analysis model for this simulation cycle; Step 5-2: Establish a set of important information U1 of the missile to be tested, and establish a set of target range of important information U2 of the missile to be tested; during the simulation test, obtain parameter information belonging to U1, and determine whether the obtained parameter information belongs to the target range of the corresponding parameter in U2, and take the parameters that belong to U1 but not to the corresponding target range of U2 as the target parameters, and proceed to step 5-3; Step 5-3: Record the time period information when the target parameter does not belong to U2: T0, Tz, Q, where T0 is the time point when the target parameter does not belong to U2 for the first time in the time period; Tz is the time point when the target parameter returns to U2 in the time period, and the absence of Tz means that the target parameter has not returned to U2 in this simulation cycle; Q is the length of the time period; and determine whether Q is greater than W. If Q is greater than W, go to step 5-4, W is the upper limit of the time period that the target parameter can accept to exceed the error, W≥0, when W=0, the target parameter does not accept the error; Step 5-4: Use the analysis model selected in step 5-1, combined with the key information-influencing factor knowledge graph obtained in step 5-1, to analyze the influencing factors of the target parameters, obtain the possible influencing factors that lead to the appearance of the target parameters, and form the corresponding influencing weights; Step 6: After the simulation is performed for a preset time or the missile flies a preset distance, a simulation cycle is completed; Step 7: Use the execution status of this simulation cycle obtained by executing steps 1 to 5 once, the corresponding characteristics in the battle situation setting, and the simulation parameters after adjusting the influencing factors as the input conditions for the next simulation, and repeat steps 1 to 5 to start a new simulation cycle, and stop the simulation when the simulation termination conditions are met.

2. The method for automatically counting and distinguishing important information of missile simulation according to claim 1, characterized in that: The specific steps of formulating simulation test samples in step 1 are: specific sample condition planning is performed according to the test task, missile performance, and semi-physical simulation performance; the sample condition planning includes: Launch condition planning: Determine the missile entry angle, launch distance, initial speed, and elevation difference parameters based on the missile attack area and target movement capability; Target characteristic parameter determination, including: determining the target type, maneuvering mode, and radiation energy parameters based on the target motion and radiation characteristics; Determination of interference condition parameters, including: determining the number of interference missiles, missile interval, release angle, initial velocity, and release time parameters according to the interference type and release strategy; Determine the background environment parameters, including: determine the background type and lighting condition parameters; The deviation condition parameters are determined, including: determining the target, the deviation range of interference and the condition parameters.

3. The method for automatically counting and distinguishing important information of missile simulation according to claim 2, characterized in that: In step 2, the test personnel select or generate the assumption data through the command and control computer, and the software automatically completes the data release through the optical fiber network. Then, the test personnel issue the simulation preparation instruction through the command and control computer at any time according to the test requirements. The method includes: Step 2-1: The real-time simulation computer sends initialization instructions and data according to the assumed turntable pre-bias value, and the turntable system queries the drive control instructions and data sent by the real-time simulation computer in real time to complete the motion initialization; other participating computers complete the initialization of local software; Step 2-2: After executing the simulation preparation instruction, each relevant test computer and simulation device reports the simulation preparation status and operation status to the command control computer through the optical fiber reflection memory network; Step 2-3: After the control computer inquires and waits for the feedback status of each participating computer, it executes the following judgment control: If the feedback status of each participating computer is normal, wait for the test personnel to start the control operation to enter the start control simulation stage; If there are nodes with abnormal status in the feedback from each participating computer, a simulation termination instruction is issued to stop the simulation process, and then each participating computer completes status recovery and waits for the next simulation preparation; If the simulation control computer fails to query the feedback status of all participating computers within the specified time, it will prompt that the preparation has timed out and send a simulation abort instruction to stop the simulation process. Each participating computer will complete the status recovery according to the simulation abort instruction, and the software and hardware of each node will be restored to the state of waiting for the next simulation preparation.

4. The method for automatically counting and distinguishing important information of missile simulation according to claim 3 is characterized in that: During the simulation experiment in step 4, the specific workflow of the real-time simulation computer includes: Step 4-1-1: Complete the sending of clock synchronization interrupt, receiving of guidance data, calculation of ballistic model and calculation of driving model, and send the data to be published to the optical fiber reflection memory network after associating the timestamp, and complete the target encounter condition judgment according to the ballistic parameters and the maximum flight time, and give the simulation end instruction when the target encounter condition is met or the maximum flight time is reached; Step 4-1-2: Complete the record cache of local data; Step 4-1-3: Dynamically respond to the random control instructions issued by the simulation control computer throughout the whole process, and complete the dynamic update of the response and operation status; Step 4-1-4: When the working state given by the seeker under test does not meet the guidance closed loop requirements or enters the blind range, the real-time combat situation solving computer freezes the device drive data update and switches to the recursive mode, and continues to simulate and solve the flight trajectory until the pre-target conditions are met or the maximum flight time is reached; Step 4-1-5: After the simulation end condition is met or the simulation termination instruction is received, the key data of the simulation process is first stored in the file, and then the status is restored and the recovery status is reported; Step 4-1-6: Enter the simulation waiting state and wait for the next simulation preparation instruction.

5. The method for automatically counting and distinguishing important information of missile simulation according to claim 4, characterized in that: In step 4, the specific workflow of the seeker control and communication computer during the simulation experiment includes: Step 4-2-1: Collect the guidance data output by the seeker under test in each working cycle, and send the guidance data to the optical fiber reflection memory network; Step 4-2-2: Dynamically respond to the simulation control instruction and complete the update of the response and operation status; Step 4-2-3: Complete the record cache of local data; Step 4-2-4: After receiving the simulation end or simulation termination instruction, first complete the file storage of the key data of the simulation process, then complete the status recovery and report the recovery status; Step 4-2-5: Enter the simulation waiting state and wait for the next simulation preparation instruction.

6. A method for automatically counting and distinguishing important information of missile simulation according to claim 5, characterized in that: In step 4, the specific workflow of the injection-type infrared target simulator during the simulation experiment includes: Step 4-3-1: Acquire target-missile driving data and generate infrared scene digital image; Step 4-3-2: Cache data from video memory to internal memory; Step 4-3-3: Cache on the injection transmission card through the PCI-E bus; Step 4-3-4: Responding to the trigger of the synchronization signal, the data is transmitted to the front-end conversion module via the optical fiber; Step 4-3-5: The front-end conversion module uses the CML bus to send the signal to the seeker signal processor for simulation; Step 4-3-6: After receiving the simulation end or simulation termination instruction, first complete the file storage of the key data of the simulation process, then complete the status recovery and report the recovery status; Step 4-3-7: Enter the simulation waiting state and wait for the next simulation preparation instruction.

7. The method for automatically counting and distinguishing important information of missile simulation according to claim 6, characterized in that: The turntable system includes a multi-axis turntable system and a desktop simulation system; The multi-axis turntable system is: a three-axis turntable system or a five-axis turntable system; The desktop simulation system is: a desktop injection-type simulation system based on sight angle compensation or a seeker injection-type simulation system based on a stable platform model.

8. The method for automatically counting and distinguishing the important information of missile simulation according to claim 7 is characterized in that: In step 4, the specific workflow of the multi-axis turntable system during the simulation experiment includes: Step 4-4-1: Query the turntable drive control instructions and data to complete the positioning, servo and zero return motion control of the turntable frame; Step 4-4-2: Dynamically respond to the turntable emergency trigger, and activate the safety protection mechanism when the trigger is valid; Step 4-4-3: Real-time dynamic update of feedback data and operation status; Step 4-4-4: Complete the record cache of local data; Step 4-4-5: When receiving the zeroing drive control instruction, first complete the file storage of the key data of the simulation process, then complete the state recovery and report the recovery state; Step 4-4-6: Enter the simulation waiting state and wait for the next simulation preparation instruction.

9. The method for automatically counting and distinguishing important information of missile simulation according to claim 8, characterized in that: When the turntable system is a desktop injection-type simulation system based on line of sight angle compensation, the seeker, flight control cabin, inertial group simulator, and injection-type infrared target simulator are all placed on the desktop; The main simulation unit receives the flight control command from the flight control cabin based on the line of sight angular velocity information and the inertial navigation information generated by the inertial navigation simulator, and solves the missile body attitude motion data. The data is sent to the line of sight angular velocity compensation module for line of sight angular velocity compensation in combination with the seeker frame angle data; combined with the missile acceleration information, it is sent to the inertial navigation simulator to generate new inertial navigation information; at the same time, the target-missile position and attitude data are sent to the high-performance graphics workstation in the injection infrared target simulator as the data source for real-time generation of infrared scenes; the data is transmitted and stored through the reflective memory network; The injection-type infrared target simulator receives the seeker frame angle signal and target-missile position and attitude data transmitted by the test product - signal collector, generates infrared scenes in real time, and converts them into 16-bit image data injected into the seeker; the image is sent and injected to the board card and transmitted to the signal conversion module through optical fiber. The module converts the signal into CML signal and directly injects it into the signal processor of the seeker to realize signal injection simulation.

10. The method for automatically counting and distinguishing the important information of missile simulation according to claim 8, characterized in that: When the turntable system is a seeker injection simulation system based on a stable platform model, the seeker, flight control cabin, inertial group simulator, and injection infrared target simulator are all placed on the desktop; The main simulation unit receives the flight control command formed by the flight control cabin based on the line of sight angular velocity information and the inertial navigation information generated by the inertial navigation simulator, and solves the missile body attitude motion data, and sends the data to the seeker stable platform model, which generates the servo frame angle information and the seeker line of sight angular velocity information in real time, wherein the seeker line of sight angular velocity information is transmitted to the flight control cabin, and the servo frame angle information is transmitted to the injection type infrared target simulator; the missile acceleration information generated by the main simulation unit is sent to the inertial navigation simulator to generate new inertial navigation information, and at the same time, the target-missile position and attitude data are sent to the high-performance graphics workstation in the injection type infrared target simulator as the data source for real-time generation of infrared scenes; Data is transmitted and stored via a reflective memory network; The injection-type infrared target simulator receives the seeker frame angle signal generated by the seeker stabilization platform and the target-missile position and attitude data calculated by the main simulator, generates an infrared scene in real time, and converts it into 16-bit image data that is injected into the seeker. The image is sent and injected to the board and transmitted to the signal conversion module through optical fiber. The module converts the signal into a CML signal and directly injects it into the seeker signal processing unit to realize signal injection simulation.