A general task operation decision method and system based on dynamic multi-parameter template

Abstract

The application discloses a kind of general task operation decision method and system based on dynamic multi-parameter template, the method of the application includes respectively collecting the measured value and theoretical value corresponding to m parameters P1-Pm when being tested equipment executes task, and according to the determined order, corresponding arrangement generates dynamic multi-parameter template;Error index between the measured value and theoretical value of m parameters in dynamic multi-parameter template is calculated;Error index and preset error index threshold are compared to determine the test state of the tested equipment.The application aims to provide evaluation basis and discrimination criterion for intelligent decision of intelligent test field, can help new equipment intelligent test field task to reduce burden, can be suitable for different types of equipment intelligent test field task implementation, and can be used as equipment intelligent test field network, digitization, intelligent task operation decision method design and system development paradigm.

Description

Technical Field

[0001] This invention relates to the field of equipment testing technology, specifically to a general task operation decision-making method and system based on dynamic multi-parameter templates. Background Technology

[0002] With the rapid development of new technologies such as the Internet of Things, big data, and artificial intelligence, the level of equipment testing and evaluation worldwide has reached a new stage.

[0003] With the intelligent transformation and development of equipment testing grounds, they are moving towards a stage of intelligent and smart development based on digitalization. At this critical juncture, intelligent equipment testing grounds, as a crucial link in the equipment testing system, are not only at the forefront of supporting equipment testing and evaluation and promoting equipment improvement and upgrading, but also the most fundamental organization and force for the comprehensive digital and intelligent transformation of the equipment testing system. Therefore, the construction of intelligent equipment testing grounds is urgently needed. The basic requirements for the intelligent construction of equipment testing grounds are to effectively integrate existing resources, utilize intelligent technologies to improve management efficiency, support the intelligent and efficient completion of equipment testing tasks, ensure the high reliability and security of intelligent equipment testing, and enhance the intelligent service support capabilities of equipment testing grounds.

[0004] Currently, there is no intelligent task operation decision-making method design or related intelligent system based on general discrimination criteria at the equipment test site level to solve the mismatch between the test system control and the on-site task execution capability. The problems of multiple tasks and heavy burden at the equipment test site have not been fundamentally solved. Summary of the Invention

[0005] The technical problem to be solved by this invention is to provide a general task operation decision-making method and system based on dynamic multi-parameter templates, addressing the aforementioned problems of the prior art. This invention aims to provide evaluation criteria and judgment standards for intelligent decision-making in smart test sites, helping to reduce the task burden of newly built equipment smart test sites, and is applicable to the implementation of smart test site tasks for different types of equipment. It can serve as a paradigm for the design and system development of networked, digitalized, and intelligent task operation decision-making methods for equipment smart test sites.

[0006] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows:

[0007] A general task execution decision-making method based on dynamic multi-parameter templates includes:

[0008] S101, collect the measured and theoretical values ​​of m parameters P1 to Pm corresponding to the tested equipment when performing the task, and arrange them in a determined order to generate a dynamic multi-parameter template;

[0009] S102, calculate the error index between the measured and theoretical values ​​of m parameters in the dynamic multi-parameter template;

[0010] S103, compare the error index with the preset error index threshold to determine the test status of the equipment under test.

[0011] Optionally, the functional expression for calculating the error index between the measured and theoretical values ​​of m parameters in step S102 is as follows:

[0012] Dsm = [(PS1-PL1)] 2 +(PS2-PL2) 2 +…+(Psi-PLi) 2 +…+(PSm-PLm) 2 ] 0.5 ,

[0013] In the above formula, Dsm is the error index between the measured and theoretical values ​​of m parameters, PS1~PSm are the measured values ​​of m parameters respectively, and PL1~PLm are the theoretical values ​​of m parameters respectively.

[0014] Optionally, in step S101, the task performed by the tested equipment refers to an outdoor flight combat test mission, including an A-type carrier aircraft launching a B-type air-to-air missile at airspace point S1 to fire at a C-type target drone, and setting a time interval after which the B-type air-to-air missile and the C-type target drone encounter each other. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include, but are not limited to, some or all of time, X-coordinate, Y-coordinate, Z-coordinate, and velocity. In step S103, when determining the test status of the tested equipment, it includes determining whether the waypoint planning of the tested equipment is reasonable: if the error index of the tested equipment is less than or equal to the preset error index threshold of the tested equipment, then the waypoint planning of the tested equipment is determined to be reasonable; otherwise, the waypoint planning of the tested equipment is determined to be unreasonable, and the waypoints of the tested equipment need to be replanned.

[0015] Optionally, in step S101, the task performed by the tested equipment refers to an outdoor flight combat test mission, including an A-type carrier aircraft launching a B-type air-to-air missile to fire at a C-type target drone at airspace point S1, and assuming that the B-type air-to-air missile and the C-type target drone encounter each other at time Tg. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include, but are not limited to, some or all of time, X-coordinate, Y-coordinate, Z-coordinate, and velocity, and the theoretical values ​​are obtained from simulation. In step S103, when determining the test state of the tested equipment, it includes determining whether the simulation results of the tested equipment are reasonable: if the error index of the tested equipment is less than or equal to the preset error index threshold of the tested equipment, the simulation results of the tested equipment are determined to be reasonable; otherwise, the simulation results of the tested equipment are determined to be unreasonable.

[0016] Optionally, in step S101, the task performed by the tested equipment refers to an outdoor flight combat test mission, including an A-type carrier aircraft launching a B-type air-to-air missile to fire at a C-type target drone at airspace point S1, and assuming that the B-type air-to-air missile and the C-type target drone encounter each other at time Tg. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include, but are not limited to, some or all of time, X-coordinate, Y-coordinate, Z-coordinate, and velocity. In step S103, when determining the test status of the tested equipment, it includes determining whether the tested equipment is normally executing command and control commands: if the error index of the tested equipment is less than or equal to the preset error index threshold DJsm of the tested equipment, then the tested equipment is determined to be... The system is capable of executing command and control commands normally and can output command and control commands normally. If the error index of the tested equipment is greater than the preset error index threshold DJsm but less than or equal to 1.5 DJsm, it is determined that the tested equipment has encountered a minor problem in performing the task, and the command and control commands need to be modified to slightly correct the parameters of the tested equipment. If the error index of the tested equipment is greater than 1.5 DJsm but less than or equal to 2 DJsm, it is determined that the tested equipment has encountered a major problem in performing the task, and the command and control commands need to be modified to significantly correct the parameters of the tested equipment. If the error index of the tested equipment is greater than 2 DJsm, it is determined that the tested equipment has encountered a serious problem in performing the task, and the command and control commands cannot continue and the test needs to be terminated.

[0017] Optionally, in step S101, the task performed by the tested equipment refers to an outdoor flight combat test mission, including an A-type carrier aircraft launching a B-type air-to-air missile at airspace point S1 to fire at a C-type target drone, and assuming that the B-type air-to-air missile and the C-type target drone encounter each other at time Tg. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include, but are not limited to, some or all of time, X-coordinate, Y-coordinate, Z-coordinate, and velocity, and the theoretical values ​​are obtained from simulation. Step S103 includes: if the error index of the tested equipment is less than or equal to the preset error index threshold DJsm of the tested equipment, then it is determined that the process of the tested equipment performing the task is stable and can be performed normally. The test equipment is routinely subjected to test tasks. If the error index of the tested equipment is greater than the preset error index threshold DJsm but less than or equal to 1.5 DJsm, it is determined that a minor problem has occurred in the process of the tested equipment performing the task, and the parameters of the tested equipment need to be slightly adjusted to restore it to the normal range. If the error index of the tested equipment is greater than 1.5 DJsm but less than or equal to 2 DJsm, it is determined that a major problem has occurred in the process of the tested equipment performing the task, and the parameters of the tested equipment need to be significantly adjusted to restore it to the normal range. If the error index of the tested equipment is greater than 2 DJsm, it is determined that a serious problem has occurred in the process of the tested equipment performing the task, and the test task needs to be stopped.

[0018] Optionally, in step S101, the task performed by the tested equipment refers to an outdoor flight combat test mission, including an A-type carrier aircraft launching a B-type air-to-air missile at airspace point S1 to fire at a C-type target drone, and assuming that the B-type air-to-air missile and the C-type target drone encounter each other at time Tg. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include, but are not limited to, some or all of time, X-coordinate, Y-coordinate, Z-coordinate, and velocity, and the theoretical values ​​are obtained from simulation. Step S103 includes: calculating the minimum distance Dgbc between the B-type missile and the C-type target drone at the moment of encounter Dgbc = [(XCGci – XBGci). 2 +(YCGci–YBGci) 2 +(ZCGci–ZBGci)2] 0.5 Where XBGci, YBGci, and ZBGci are the spatial coordinates of the B-type missile at the moment of encounter, and XCGci, YCGci, and ZCGci are the spatial coordinates of the C-type target drone at the moment of encounter. If the minimum distance Dgbc is less than or equal to the preset miss distance index DbcJ, the test result of the B-type missile intercepting the C-type target drone is deemed to meet the requirements; otherwise, the test result of the B-type missile intercepting the C-type target drone is deemed to have failed to meet the expected requirements.

[0019] Optionally, the calculation function expression for the preset error index threshold is:

[0020] DJsm = σ1 + σ2 + ... + σ i +…+σ m +k

[0021] In the above formula, DJsm represents the preset error index threshold, σ1~σ m Let P1 be the theoretical error of each of the m parameters P1 to Pm, and k be an empirical value.

[0022] Furthermore, the present invention also provides a general task execution decision system based on dynamic multi-parameter templates, including a microprocessor and a memory interconnected thereto, wherein the microprocessor is programmed or configured to execute the general task execution decision method based on dynamic multi-parameter templates.

[0023] Furthermore, the present invention also provides a computer-readable storage medium storing a computer program for being programmed or configured by a microprocessor to execute the general task execution decision method based on dynamic multi-parameter templates.

[0024] Compared with existing technologies, the present invention has the following main advantages: The method of the present invention includes collecting the measured values ​​and theoretical values ​​of m parameters P1 to Pm corresponding to the tested equipment when performing a task, and arranging them in a determined order to generate a dynamic multi-parameter template; calculating the error index between the measured values ​​and theoretical values ​​of the m parameters in the dynamic multi-parameter template; and comparing the error index with a preset error index threshold to determine the test state of the tested equipment. The present invention aims to provide evaluation criteria and judgment standards for intelligent decision-making in smart test sites, helping to reduce the workload of newly built smart test sites for equipment, and is applicable to the implementation of smart test site tasks for different types of equipment. It can serve as a paradigm for the design and system development of networked, digitalized, and intelligent task operation decision-making methods for smart test sites for equipment. This invention proposes a general mission operation decision-making method based on dynamic multi-parameter templates, based on the combat and technical indicators, simulation data, and test measurement data of equipment or systems at the test range. This provides evaluation criteria and judgment standards for intelligent decision-making in equipment or system test missions. Furthermore, this invention designs an intelligent test mission operation decision-making method for smart test ranges to meet the full-process test mission requirements of different types of equipment. It proposes a general mission operation decision-making criterion based on dynamic multi-parameter templates and develops a mission operation management system platform. This addresses the problems of cumbersome and complex mission planning for test-participating equipment, test and measurement equipment, command and control equipment, and data information processing equipment; low efficiency in the entire process of test simulation, implementation, testing and measurement, and evaluation; and insufficient test capabilities. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the basic process of the method in an embodiment of the present invention.

[0026] Figure 2 This is a schematic diagram of the general judgment process based on the preset error index threshold DJsm in an embodiment of the present invention. Detailed Implementation

[0027] like Figure 1 As shown, the general task execution decision-making method based on dynamic multi-parameter templates in this embodiment includes:

[0028] S101 collects the measured and theoretical values ​​of m parameters P1 to Pm corresponding to the tested equipment during the task, and arranges them in a predetermined order to generate a dynamic multi-parameter template. The order of parameters and the correspondence between measured and theoretical values ​​in the dynamic multi-parameter template are fixed and cannot be arbitrarily changed. This avoids increased errors due to differences in units and meanings, which could lead to decision-making errors. The value of m can be selected according to the different equipment or systems.

[0029] S102, calculate the error index between the measured and theoretical values ​​of m parameters in the dynamic multi-parameter template;

[0030] S103, compare the error index with the preset error index threshold to determine the test status of the equipment under test.

[0031] In step S102 of this embodiment, the functional expression for calculating the error index between the measured and theoretical values ​​of m parameters is as follows:

[0032] Dsm = [(PS1-PL1)] 2 +(PS2-PL2) 2 +…+(Psi-PLi) 2 +…+(PSm-PLm) 2 ] 0.5 ,

[0033] In the above formula, Dsm is the error index between the measured and theoretical values ​​of m parameters, PS1 to PSm are the measured values ​​of m parameters respectively, and PL1 to PLm are the theoretical values ​​of m parameters respectively. The theoretical and measured values ​​of the above m parameters are arranged in a corresponding order to generate a dynamic multi-parameter template. For example, the dynamic multi-parameter template generated in this embodiment is shown in Table 1:

[0034] Table 1: A typical dynamic multi-parameter template.

[0035] Parameter name P1 P2 P3 P4 … Pi … Pm Theoretical values PL1 PL2 PL3 PL4 … PLi … PLm Measured values PS1 PS2 PS3 PS4 … PSi … PSm

[0036] It should be noted that the m parameters are quantifiable parameters. If important qualitative indicators are to be selected, they must first be quantified. In specific experiments, the total number m of the same parameter is fixed; the value of m can be dynamically adjusted for different equipment or systems, but the order of the m parameters should remain unchanged; if a parameter does not exist, it needs to be set to "0" to facilitate software programming; unless otherwise specified, the units of the parameters shall be in the standard International System of Units (SI).

[0037] This embodiment of the method includes proposing a general mission operation decision-making method based on dynamic multi-parameter templates, according to the tactical and technical indicators, simulation data, and test measurement data of equipment or systems. This provides an evaluation basis and judgment criteria for intelligent decision-making of equipment or systems in a smart test range. Based on the analysis and judgment of test range mission requirements, and according to the intelligent decision-making basis and judgment criteria determined by the general mission operation decision-making method based on dynamic multi-parameter templates, a mission operation management system platform is developed. This platform includes at least a smart planning system, a smart simulation and deduction system, a smart implementation and execution system, a smart test and measurement system, a smart command and control system, and a smart evaluation and appraisal system. Specific mission operation status judgment method templates are also generated. The tactical and technical indicators of the equipment or system refer to the tactical and technical indicators of the equipment or system participating in the test range. Tactical indicators are quantitative or qualitative indicators that directly measure the combat capability of equipment, such as weapon range, payload, and fire accuracy, and the speed, combat radius, and range of various combat platforms. Technical indicators refer to indicators that ensure the realization of tactical performance, such as the geometric dimensions, weight, reliability, and standardization requirements of equipment. Among them, equipment or system simulation data refers to various types of data generated by running the simulation model of equipment or system on a simulation platform according to set rules; equipment or system test and measurement data refers to various types of data obtained by the test and measurement equipment at the test site to test and measure the external and internal states of the tested equipment or system. In this embodiment, the general task operation decision-making method based on dynamic multi-parameter templates can be programmed, calculated, and stored using a connected microprocessor and memory. By running the computer program in the computer-readable storage medium, the basic data calculation and decision-making functions of the general task operation decision-making method based on dynamic multi-parameter templates can be realized.

[0038] In this embodiment, the task content and processing flow within the scope of the intelligent equipment test range are examined, including task type, main task content, key task flow, and task interface relationship. Among them, task type refers to the types of test tasks carried out by the test range, mainly including equipment performance test and effectiveness test. Equipment performance test mainly refers to test with the main purpose of evaluating and identifying equipment performance indicators, such as radar power identification test; equipment effectiveness test mainly refers to test with the purpose of evaluating and identifying the ability of equipment to complete specified tasks under certain conditions, such as reconnaissance aircraft reconnaissance test against terrorist forces in a certain area. The main task content includes three parts: task preparation, task implementation, and task result evaluation. The key task flow mainly includes: (1) task planning and simulation in the task preparation stage; (2) command and control, implementation and testing in the task implementation stage; (3) data processing and result evaluation in the task result evaluation stage. Task interface relationships refer to the data information transmission protocols and network infrastructure interface standards between various task systems. They mainly include the interface relationships between the task planning system and the simulation system, the simulation system and the implementation system, the implementation system and the test and measurement system, the command and control system and the implementation and test and measurement systems, and the test, measurement and evaluation system.

[0039] The equipment intelligent test site mission operation management system platform includes at least an intelligent planning system, an intelligent simulation and deduction system, an intelligent command and control system, an intelligent testing and measurement system, and an intelligent evaluation and appraisal system.

[0040] Specifically, the intelligent planning and design system is an intelligent system that intelligently conducts test planning and analysis based on test mission requirements, formulates test schedules, plans test resource allocation, and performs intelligent route planning for equipment according to a general mission operation decision-making method based on dynamic multi-parameter templates. Its inputs include documents such as mission notifications and annual work arrangements from superiors, and its outputs include specific equipment test tasks and execution schedules, planned routes, or executable files.

[0041] In this embodiment, the task performed by the tested equipment in step S101 refers to the field flight combat test of the aircraft, including the launch of a type B air-to-air missile by a type A carrier aircraft at airspace point S1 to shoot at a type C target drone, and setting that the type B air-to-air missile and the type C target drone encounter each other at time Tg. The tested equipment refers to one of the type A carrier aircraft, the type B air-to-air missile, and the type C target drone. The m parameters P1 to Pm include, but are not limited to, time, X coordinate, Y coordinate, Z coordinate, and some or all of velocity. When determining the test state of the tested equipment in step S103, it includes determining whether the waypoint planning of the tested equipment is reasonable: if the parameter error index of the tested equipment is less than or equal to the preset parameter error index threshold of the tested equipment, the waypoint planning of the tested equipment is determined to be reasonable; otherwise, the waypoint planning of the tested equipment is determined to be unreasonable, and the waypoints of the tested equipment need to be replanned. The m parameters P1 to Pm of the type A carrier aircraft, the type B air-to-air missile, and the type C target drone can be represented as the general dynamic multi-parameter template shown in Table 2.

[0042] Table 2: Universal dynamic multi-parameter template for Type A carrier aircraft, Type B air-to-air missile, and Type C target drone.

[0043]

[0044] The aircraft field combat test mission includes an A-type carrier aircraft launching a B-type air-to-air missile from airspace point S1 to fire at a C-type target drone. At time Tg, the B-type air-to-air missile and the C-type target drone encounter each other. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The A-type carrier aircraft platform: arrives at airspace point S1 at the planned time t1, with its theoretical position three-dimensional coordinates (xA11, yA11, zA11) and theoretical velocity (vA11). The B-type air-to-air missile: is launched from the A-type carrier aircraft platform at the planned time t1, with its theoretical position three-dimensional coordinates (xA11, yA11, zA11) and theoretical velocity (vA11). 11, yA11, zA11), theoretical velocity (vA11); after launch, at time t2, the B-type air-to-air missile reaches airspace point S2, with its theoretical position three-dimensional coordinates (xB22, yB22, zB22) and theoretical velocity (vB22); C-type target drone: at planned time t1, the target drone reaches airspace point S3, with its theoretical position three-dimensional coordinates (xC13, yC13, zC13) and theoretical velocity (vC13); at time t2, it reaches airspace point S4, with its theoretical position three-dimensional coordinates (xC24, yC24, zC24) and theoretical velocity (vC24).

[0045] Taking the Type A carrier aircraft as an example, its state criterion at airspace point S1 is as follows: If DAsmi ≤ DAJsm (0.9, empirical value), then the planned values ​​of the Type A carrier aircraft match the combat performance indicators, and the waypoint planning of the Type A carrier aircraft is deemed reasonable; otherwise, the planning of the Type A carrier aircraft is deemed unreasonable, and the parameter values ​​need to be adjusted and replanned. The calculation function expression for the error index DAsmi between the measured and theoretical values ​​of the m parameters of the Type A carrier aircraft is:

[0046] DAsmi=[(t1-TAi) 2 +(xA11-XAi) 2 +(yA11-YAi) 2 +(zA11-ZAi) 2 +(vA11-VAi) 2 ] 0.5 ,

[0047] In the above formula, the dynamic multi-parameter template of the Type A carrier aircraft is shown in Table 3.

[0048] Table 3: Dynamic multi-parameter template for Type A carrier aircraft.

[0049]

[0050] Taking the Type B air-to-air missile as an example, its state criterion at airspace point S2 is as follows: If DBsmi ≤ DBJsm (=0.9, empirical value), then the planned values ​​of the Type B missile match the combat performance indicators, and the waypoint planning of the Type B missile is deemed reasonable; otherwise, it is determined that the planning of the Type B missile is unreasonable, and the parameter values ​​need to be adjusted and replanned. The calculation function expression for the error index DBsmi between the measured and theoretical values ​​of the m parameters of the Type B air-to-air missile is:

[0051] DBsmi = [(t2-TBi)] 2 +(xB22-XBi) 2 +(yB22-YBi) 2 +(zB22-ZBi) 2 +(vB22-VBi) 2 ] 0.5 ,

[0052] In the above formula, the dynamic multi-parameter template of the B-type air-to-air missile is shown in Table 4.

[0053] Table 4: Dynamic multi-parameter template for Type B air-to-air missile.

[0054]

[0055] Taking the C-type target drone as an example, its state criterion at airspace point S4 is as follows: If DCsmi ≤ DCJsm (=0.9, empirical value), then the planned values ​​of the C-type target drone match the combat performance indicators, and the C-type target drone waypoint planning is deemed reasonable; otherwise, the C-type target drone planning is deemed unreasonable, and the parameter values ​​need to be adjusted and replanned. The calculation function expression for the error index DCsmi between the measured and theoretical values ​​of the m parameters of the C-type target drone is:

[0056] DCsmi=[(t2-TCi) 2 +(xC24-XCi) 2 +(yC24-YCi) 2 +(zC24-ZCi) 2 +(vC24-VCi) 2 ] 0.5 ,

[0057] In the above formula, the dynamic multi-parameter template of the C-type target machine is shown in Table 5.

[0058] Table 5: Dynamic multi-parameter template for C-type target drone.

[0059]

[0060] The intelligent simulation and deduction system is an intelligent system that intelligently conducts mission process simulation and deduction based on the information output by the intelligent planning system, as well as the pre-installed test equipment and test situation models, and in accordance with simulation and deduction criteria. Its inputs include specific tasks and execution schedules or executable files such as units, personnel, and equipment, as well as equipment models and test situation models. Its outputs are a mission simulation and deduction scheme and a digital report of the deduction evaluation results. In step S103 of this embodiment, determining the test state of the tested equipment includes determining whether the simulation and deduction results of the tested equipment are reasonable: if the error index of the tested equipment's state parameters is less than or equal to the preset error index threshold of the tested equipment's state parameters, then the simulation and deduction results of the tested equipment are determined to be reasonable; otherwise, the simulation and deduction results of the tested equipment are determined to be unreasonable. When determining whether the simulation and deduction results of the tested equipment are reasonable, the common dynamic multi-parameter templates for the A-type carrier aircraft, B-type air-to-air missile, and C-type target drone are shown in Table 6.

[0061] Table 6: Universal dynamic multi-parameter template for Type A carrier aircraft, Type B air-to-air missile, and Type C target drone.

[0062] Planning values Tsi (time) Xsi (coordinate X) Ysi (coordinate Y) Zsi (coordinate Z) Vsi (speed) Simulation numerical Tssi (Time) Xssi (coordinate X) Yssi (coordinate Y) Zssi (coordinate Z) Vssi (Speed)

[0063] According to Table 6, the following can be calculated:

[0064] Dsmi=[(Tssi-Tsi)2+(Xssi-Xsi)2+(Yssi-Ysi)2+(Zssi-Zsi)2+(Vssi-Vsi)2]0.5,

[0065] If Dsmi≤DJsm (=0.5, empirical value), then the simulation value matches the planned value, and the simulation result is deemed reasonable; otherwise, the simulation result is deemed unreasonable, and the parameter values ​​need to be adjusted and the simulation re-performed.

[0066] Taking the Type B air-to-air missile as an example, the simulation and deduction criteria for its airspace point S2 are as follows:

[0067] If DB2smi ≤ DB2Jsm (=0.5, empirical value), then the simulation values ​​of the Type B missile match the planned values, and the simulation results of the Type B missile are deemed reasonable; otherwise, the simulation results of the Type B missile are deemed unreasonable, and the parameter values ​​need to be adjusted and the simulation re-performed. Wherein:

[0068] DB2smi=[(Tssi–t2) 2 +(Xssi-xB22) 2 +(Yssi-yB22) 2 +(Zssi-zB22) 2 +(Vssi-vB22) 2 ] 0.5

[0069] In the above formula, the dynamic multi-parameter template of the B-type air-to-air missile in the simulation inference criterion is shown in Table 7.

[0070] Table 7: Dynamic multi-parameter template for Type B air-to-air missile.

[0071]

[0072] In this embodiment, the intelligent command and control system is an intelligent system that, based on the information output by the intelligent planning system and instructions from higher authorities, intelligently generates command and control commands according to command and control principles to control the operation of the intelligent implementation system and the intelligent test and measurement system. Its inputs are the information output by the intelligent planning system and instructions from higher authorities, and its outputs are instructions or programs for controlling the operation of the intelligent implementation system and the intelligent test and measurement system. For example... Figure 2As shown, in step S103 of this embodiment, determining the test status of the tested equipment includes determining whether the tested equipment is normally executing command and control commands: if the error index of the tested equipment is less than or equal to the preset error index threshold DJsm, it is determined that the tested equipment is normally executing command and control commands and can output command and control commands normally; if the error index of the tested equipment is greater than the preset error index threshold DJsm but less than or equal to 1.5 DJsm, it is determined that the tested equipment has encountered a minor problem in executing the task and needs to modify the command and control commands to slightly correct the parameters of the tested equipment; if the error index of the tested equipment is greater than 1.5 DJsm but less than or equal to 2 DJsm, it is determined that the tested equipment has encountered a major problem in executing the task and needs to modify the command and control commands to significantly correct the parameters of the tested equipment; if the error index of the tested equipment is greater than 2 DJsm, it is determined that the tested equipment has encountered a serious problem in executing the task, cannot continue to execute command and control commands, and needs to terminate the test. As an optional implementation, this embodiment also incorporates the CP parameter (representing instructions directly issued by the superior). The CP parameter represents instructions directly issued by the superior and has the highest priority. If CP = 0, it indicates that an emergency has occurred and the experiment needs to be terminated completely; if CP = 1, there is no emergency and the experiment proceeds normally.

[0073] If an instruction CP=0 is received from the superior, it indicates an emergency situation and the experiment must be stopped; otherwise, calculate Dcsi:

[0074] Dcsi=[(Tci-Tsi) 2 +(Xci-Xsi) 2 +(Yci-Ysi) 2 +(Zci-Zsi) 2 +(Vci-Vsi) 2 ] 0.5

[0075] In the above formula, the general dynamic multi-parameter template for determining whether the tested equipment is executing command and control instructions normally is shown in Table 8.

[0076] Table 8: Universal dynamic multi-parameter template for Type A carrier aircraft, Type B air-to-air missile, and Type C target drone.

[0077] Planning values Tsi (time) Xsi (coordinate X) Ysi (coordinate Y) Zsi (coordinate Z) Vsi (speed) Simulation numerical Tci (Time) Xci (coordinate X) Yci (coordinate Y) Zci (coordinate Z) Vci (speed)

[0078] If an instruction from the superior is received that CP=0, it indicates an emergency situation and the test must be stopped; otherwise, calculate according to Table 8.

[0079] Dcsi=[(Tci-Tsi) 2 +(Xci-Xsi) 2 +(Yci-Ysi) 2+(Zci-Zsi) 2 +(Vci-Vsi) 2 ] 0.5 ,

[0080] If Dcsi ≤ DJcs (=0.9, empirical value) and CP = 1 (indicating the test is proceeding normally), the measured value matches the planned value, and command and control instructions can be output normally. Otherwise, if DJcs < Dcsi ≤ 3 / 2 * DJcs and CP = 1, a minor problem has occurred in the equipment or system status, and command and control instructions need to be modified to slightly adjust the equipment status parameters to restore them to the normal range. Otherwise, if 3 / 2 * DJcs < Dcsi ≤ 2 * DJcs and CP = 1, a major problem has occurred in the equipment or system status, and command and control instructions need to be modified to significantly adjust the equipment status parameters to restore them to the normal range. Otherwise, if Dcsi > 2 * DJcs, a serious problem has occurred in the equipment or system status, and CP should be set to 0 to stop the test.

[0081] Taking the Type B air-to-air missile as an example: if the superior command CP=0 is received, it indicates an emergency and the test must be stopped; otherwise, calculate the Type B air-to-air missile's Dcsi (denoted as DB3csi).

[0082] DB3csi=[(TBci-t2) 2 +(XBci-xB22) 2 +(YBci-yB22) 2 +(ZBci-zB22) 2 +(VBci-vB22) 2 ] 0.5 ,

[0083] The dynamic multi-parameter template of the B-type air-to-air missile parameters is shown in Table 9.

[0084] Table 9: Dynamic multi-parameter template for Type B air-to-air missile.

[0085]

[0086] If an instruction from the superior is received that CP=0, it indicates an emergency situation and the experiment must be stopped; otherwise, calculate according to Table 9:

[0087] DB3csi=[(TBci-t2) 2 +(XBci-xB22) 2 +(YBci-yB22) 2 +(ZBci-zB22) 2 +(VBci-vB22) 2 ] 0.5 ,

[0088] If DB3csi ≤ DB3Jcs (=0.9, empirical value) and CP = 1 (indicating the test is proceeding normally), then the measured value of the B-type missile at airspace point S2 matches the planned value, and it is determined that command and control commands can be output normally; otherwise, if DB3Jcs < DB3csi ≤ 3 / 2 * DB3Jcs and CP = 1, it is determined that the B-type missile or related system status has a minor problem, and the command and control commands need to be modified to slightly adjust the B-type missile or related system status parameters to restore them to the normal range; otherwise, if 3 / 2 * DB3Jcs < DB3csi ≤ 2 * DB3Jcs and CP = 1, it is determined that the B-type missile or related system status has a major problem, and the command and control commands need to be modified to significantly adjust the B-type missile or related system status parameters to restore them to the normal range; otherwise, if DB3csi > 2 * DB3Jcs, it is determined that the B-type missile or related system status has a serious problem, and CP needs to be set to 0 to stop the test.

[0089] In this embodiment, the intelligent implementation system is an intelligent system that executes the test tasks of the participating equipment at the test site based on simulation results and command and control instructions, and in accordance with the test implementation guidelines. Its inputs are the task simulation scheme and digital report of simulation evaluation results, as well as command and control instructions, and its outputs are the test site task execution program and instructions for the participating equipment. Step S103 of this embodiment includes: if the error index of the tested equipment is less than or equal to the preset error index threshold DJsm, it is determined that the process of the tested equipment performing the task is stable and the test task can be performed normally; if the error index of the tested equipment is greater than the preset error index threshold DJsm but less than or equal to 1.5 DJsm, it is determined that the process of the tested equipment performing the task has encountered a minor problem, and the parameters of the tested equipment need to be slightly adjusted to restore it to the normal range; if the error index of the tested equipment is greater than 1.5 DJsm but less than or equal to 2 DJsm, it is determined that the process of the tested equipment performing the task has encountered a major problem, and the parameters of the tested equipment need to be significantly adjusted to restore it to the normal range; if the error index of the tested equipment is greater than 2 DJsm, it is determined that the process of the tested equipment performing the task has encountered a serious problem, and the test task needs to be stopped. It should be noted that the preset error index threshold can be selected as needed. For example, as an optional implementation, the calculation function expression of the preset error index threshold in this embodiment is:

[0090] DJsm = σ1 + σ2 + ... + σ i +…+σ m +k

[0091] In the above formula, DJsm represents the preset error index threshold, σ1~σ m Let P1 be the theoretical error of each of the m parameters P1 to Pm, and k be an empirical value.

[0092] This embodiment also incorporates the CP parameter (representing instructions directly issued by the superior). The CP parameter represents instructions directly issued by the superior and has the highest priority. If CP = 0, it indicates that an emergency has occurred and the experiment needs to be terminated completely; if CP = 1, there is no emergency and the experiment proceeds normally.

[0093] Table 10: Universal dynamic multi-parameter template for Type A carrier aircraft, Type B air-to-air missile, and Type C target drone.

[0094] Simulation numerical Tssi (Time) Xssi (coordinate X) Yssi (coordinate Y) Zssi (coordinate Z) Vssi (Speed) Measured values Tci (Time) Xci (coordinate X) Yci (coordinate Y) Zci (coordinate Z) Vci (speed)

[0095] If an instruction from the superior is received that CP=0, it indicates an emergency situation and the experiment must be stopped; otherwise, calculate Dcssi=[(Tci-Tssi)] using Table 10. 2 +(Xci-Xssi) 2 +(Yci-Yssi) 2 +(Zci-Zssi) 2 +(Vci-Vssi) 2 ] 0.5 If Dcssi ≤ DJcss (=0.9, empirical value) and CP=1 (indicating the experiment is proceeding normally), then the measured value matches the simulated value, and the experiment can be carried out normally. Otherwise, if DJcss<Dcssi≤3 / 2*DJcss and CP=1, then the equipment or system status has a minor problem, and the equipment status parameters need to be adjusted slightly to restore it to the normal range. Otherwise, if 3 / 2*DJcss<Dcssi≤2*DJcss and CP=1, then the equipment or system status has a major problem, and the equipment status parameters need to be adjusted significantly to restore it to the normal range. Otherwise, if Dcssi>2*DJcss, then the equipment or system status has a serious problem, and CP needs to be set to 0 to stop the experiment.

[0096] Taking the B-type air-to-air missile as an example, if an order from higher command is received that CP=0, it indicates an emergency and the test must be stopped; otherwise, calculate DB4csi=[(TBci-Tssi)] using Table 11. 2 +(XBci-Xssi) 2 +(YBci-Yssi) 2 +(ZBci-Zssi) 2 +(VBci-Vssi) 2 ] 0.5 ,

[0097] Table 11: Dynamic multi-parameter template for Type B air-to-air missile.

[0098]

[0099]

[0100] If an instruction CP=0 is received from the superior, it indicates an emergency and the experiment must be stopped; otherwise, set DB4csi=[(TBci-Tssi)]. 2 +(XBci-Xssi) 2 +(YBci-Yssi) 2 +(ZBci-Zssi) 2 +(VBci-Vssi) 2 ] 0.5 If DB4csi ≤ DB4Jcs (=0.9, empirical value) and CP=1 (indicating the test is proceeding normally), then the measured value of the B-type missile at airspace point S2 matches the simulated value, and the test mission can be carried out normally. Otherwise, if DB4Jcs<DB4csi≤3 / 2*DB4Jcs and CP=1, it is determined that the B-type missile or related system has a minor problem, and the B-type missile or related system status parameters need to be adjusted slightly to restore them to the normal range. Otherwise, if 3 / 2*DB4Jcs<DB4csi≤2*DB4Jcs and CP=1, it is determined that the B-type missile or related system has a major problem, and the B-type missile or related system status parameters need to be adjusted significantly to restore them to the normal range. Otherwise, if DB4csi>2*DB4Jcs, it is determined that the B-type missile or related system has a serious problem, and CP needs to be set to 0 to stop the test.

[0101] The intelligent test and measurement system is an intelligent system that intelligently executes test and measurement tasks according to the test equipment's test site mission execution procedure and command and control instructions, and in accordance with test and measurement criteria. Its inputs are the test equipment's test site mission execution procedure and command and control instructions, and its output is test and measurement data. In this embodiment, five parameters are selected as indicators for the intelligent test and measurement system and the test equipment's test mission operation decision-making method. The corresponding theoretical values ​​are adjusted to planned values; the corresponding measured values ​​include Tci (time), Xci (coordinate X), Yci (coordinate Y), Zci (coordinate Z), and Vci (velocity). The generated dynamic multi-parameter template is shown in Table 12. Therefore, the judgment criterion is adjusted as follows: if an instruction CP = 0 is received from the superior authority, it indicates an emergency, and the test is stopped; otherwise, let Dcsi = [(Tci - Tsi)]. 2 +(Xci-Xsi) 2 +(Yci-Ysi) 2 +(Zci-Zsi) 2 +(Vci-Vsi) 2 ] 0.5If Dcsi ≤ DJcs (=0.9, empirical value) and CP = 1 (indicating the test is proceeding normally), the measured value matches the planned value, and the test task can be carried out normally. Otherwise, if DJcs < Dcsi ≤ 3 / 2 * DJcs and CP = 1, it indicates a minor problem with the equipment or system status, requiring slight adjustments to the equipment status parameters to restore it to the normal range. Otherwise, if 3 / 2 * DJcs < Dcsi ≤ 2 * DJcs and CP = 1, it indicates a major problem with the equipment or system status, requiring significant adjustments to the equipment status parameters to restore it to the normal range. Otherwise, if Dcsi > 2 * DJcs, it indicates a serious problem with the equipment or system status, requiring CP = 0 to stop the test.

[0102] Table 12: Universal dynamic multi-parameter template for Type A carrier aircraft, Type B air-to-air missile, and Type C target drone.

[0103] Planning values Tsi (time) Xsi (coordinate X) Ysi (coordinate Y) Zsi (coordinate Z) Vsi (speed) Measured values Tci (Time) Xci (coordinate X) Yci (coordinate Y) Zci (coordinate Z) Vci (speed)

[0104] Taking the real-time measurement of the C-type target drone status by the intelligent test and measurement system as an example, the generated dynamic parameter template of the C-type target drone is shown in Table 13.

[0105] Table 13: Dynamic multi-parameter template for C-type target drone.

[0106] Measured values TCci (Time) XCci (coordinate X) YCci (coordinate Y) ZCci (coordinate Z) VCci (speed)

[0107] If an instruction from the superior is received that CP=0, it indicates an emergency and the experiment must be stopped; otherwise, calculate DCcsi=[(TCci–t2)] using Table 13. 2 +(XCci-xC24) 2 +(YCci-yC24) 2 +(ZCci-z C24) 2 +(VCci-vC24) 2 ] 0.5If DCcsi ≤ DCJcs (=0.9, empirical value) and CP = 1 (indicating the test is proceeding normally), then the measured value matches the planned value, and the intelligent test and measurement system and the C-type target (or system) can perform the test task normally; otherwise, if DCJcs<DCcsi≤3 / 2*DCJcs and CP = 1, then the intelligent test and measurement system or the C-type target (or system) has a minor problem, and the status parameters of the intelligent test and measurement system or the C-type target (or system) need to be adjusted slightly to restore it to the normal range; otherwise, if 3 / 2*DCJcs<DCcsi≤2*DCJcs and CP = 1, then the intelligent test and measurement system or the C-type target (or system) has a major problem, and the status parameters of the intelligent test and measurement system or the C-type target (or system) need to be adjusted significantly to restore it to the normal range; otherwise, if DCcsi>2*DCJcs, then the intelligent test and measurement system or the C-type target (or system) has a serious problem, and CP needs to be set to 0 to stop the test.

[0108] The intelligent evaluation and appraisal system is an intelligent system that intelligently evaluates the test results of equipment at the test site and provides an assessment result based on simulation data, test measurement data, and the intelligent analysis and processing results of the data, in accordance with the evaluation and appraisal criteria. Its inputs are simulation data and test measurement data, and its output is the test evaluation and appraisal result (data results and evaluation report). The aforementioned evaluation and appraisal criteria are based on the general task operation decision-making method based on dynamic multi-parameter templates described in Table 1, generating specific dynamic multi-parameter templates for the evaluation and appraisal decisions of Equipment 1# and Equipment 2#, as shown in Tables 14 and 15 respectively.

[0109] Table 14: Dynamic multi-parameter template for specific evaluation and assessment decision-making of Equipment #1.

[0110] Simulation numerical T1ssi (Time) X1ssi (coordinate X) Y1ssi (coordinate Y) Z1ssi (coordinate Z) V1ssi (Speed) Measured values T1ci (time) X1ci (coordinate X) Y1ci (coordinate Y) Z1ci (coordinate Z) V1ci (speed)

[0111] In Table 14, five parameters are selected as indicators for the mission operation decision method for equipment #1. The corresponding theoretical values ​​are adjusted to simulation values, including T1ssi (time), X1ssi (X coordinate), Y1ssi (Y coordinate), Z1ssi (Z coordinate), and V1ssi (velocity); the corresponding measured values ​​include T1ci (time), X1ci (X coordinate), Y1ci (Y coordinate), Z1ci (Z coordinate), and V1ci (velocity). Therefore, the judgment criterion is adjusted as follows: If an instruction from the superior is received that CP=0, it indicates an emergency, and the experiment should be stopped; otherwise, let D1csi=[(T1ci-T1ssi)2+(X1ci-X1ssi)2+(Y1ci-Y1ssi)2+(Z1ci-Z1ssi)2+(V1ci-V1ssi)2]0.5. If D1csi≤D1Jcs (=0.9, empirical value) and CP=1 (indicating the experiment is proceeding normally), then the measured value matches the planned value, and the experiment can be judged to proceed normally. Otherwise, if D1Jcs < D1csi ≤ 3 / 2 * D1Jcs and CP = 1, it is determined that equipment #1 has a minor problem and its status parameters need to be adjusted slightly to restore it to the normal range; otherwise, if 3 / 2 * D1Jcs < D1csi ≤ 2 * D1Jcs and CP = 1, it is determined that equipment #1 has a major problem and its status parameters need to be adjusted significantly to restore it to the normal range; otherwise, if D1csi > 2 * D1Jcs, it is determined that equipment #1 has a serious problem and CP needs to be set to 0 to stop the test.

[0112] Table 15: Dynamic multi-parameter template for specific evaluation and assessment decision-making of equipment #2.

[0113] Simulation numerical T2ssi (time) X2ssi (coordinate X) Y2ssi (coordinate Y) Z2ssi (coordinate Z) V2ssi (speed) Measured values T2ci (time) X2ci (coordinate X) Y2ci (coordinate Y) Z2ci (coordinate Z) V2ci (speed)

[0114] In Table 15, five parameters are selected for Equipment #2 to form a dynamic parameter template for the mission operation decision-making method. The corresponding theoretical values ​​are adjusted to simulation values, including T2ssi (time), X2ssi (X coordinate), Y2ssi (Y coordinate), Z2ssi (Z coordinate), and V2ssi (velocity); the corresponding measured values ​​include T2ci (time), X2ci (X coordinate), Y2ci (Y coordinate), Z2ci (Z coordinate), and V2ci (velocity). Therefore, the judgment criterion is adjusted as follows: if an instruction CP = 0 is received from the superior authority, it indicates an emergency, and the experiment stops; otherwise, let D2csi = [(T2ci – T2ssi)]. 2 +(X2ci–X2ssi) 2 +(Y2ci–Y2ssi) 2 +(Z2ci–Z2ssi) 2 +(V2ci–V2ssi) 2 ] 0.5If D2csi ≤ D2Jcs (=0.9, empirical value) and CP=1 (indicating the experiment is proceeding normally), then the measured value matches the simulated value, and the experiment can be carried out normally. Otherwise, if D2Jcs<D2csi≤3 / 2*D2Jcs and CP=1, then equipment #2 has a minor problem and its parameters need to be adjusted slightly to return to the normal range. Otherwise, if 3 / 2*D2Jcs<D2csi≤2*D2Jcs and CP=1, then equipment #2 has a major problem and its parameters need to be adjusted significantly to return to the normal range. Otherwise, if D2csi>2*D2Jcs, then equipment #2 has a serious problem and CP needs to be set to 0 to stop the experiment.

[0115] Combining Tables 14 and 15, at the moment when equipment 1# and equipment 2# encounter each other, Tg12 = T2ci = T2ci. Let the minimum distance between equipment 1# and equipment 2# be Dg12 = [(X1ci – X2ci). 2 +(Y1ci–Y2ci) 2 +(Z1ci–Z2ci) 2 ] 0.5 If Dg12 ≤ D12J (minimum distance index), the test result meets the requirements; otherwise, the test result does not meet the expected requirements, and another test needs to be considered. Specifically, in step S101 of this embodiment, the task performed by the tested equipment refers to the field flight combat test task of the aircraft, including the A-type carrier aircraft launching the B-type air-to-air missile to shoot at the C-type target drone at airspace point S1, and assuming that the B-type air-to-air missile and the C-type target drone encounter each other after a certain time. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include, but are not limited to, time, X coordinate, Y coordinate, Z coordinate, and velocity, and the theoretical values ​​are obtained from simulation. Step S103 includes: calculating the minimum distance Dgbc between the B-type missile and the C-type target drone at the moment of encounter Dgbc = [(XCGci – XBGci)]. 2 +(YCGci–YBGci) 2 +(ZCGci–ZBGci)2] 0.5 XBGci, YBGci, and ZBGci are the spatial coordinates of the B-type missile at the moment of encounter, and XCGci, YCGci, and ZCGci are the spatial coordinates of the C-type target drone at the moment of encounter. If the minimum distance Dgbc is less than or equal to the preset miss distance index DbcJ, the test result of the B-type missile intercepting the C-type target drone is deemed to meet the requirements; otherwise, the test result of the B-type missile intercepting the C-type target drone is deemed to have failed to meet the expected requirements. The generated dynamic multi-parameter templates are shown in Tables 16 and 17, respectively.

[0116] Table 16: Dynamic multi-parameter template for evaluating and identifying the status of Type B missiles.

[0117]

[0118]

[0119] If an instruction from the superior is received that CP=0, it indicates an emergency situation and the experiment must be stopped; otherwise, calculate DG1csi = [(TBGci - TBGssi)] using Table 16. 2 +(XBGci-XBGssi) 2 +(YBGci-YBGssi) 2 +(ZBGci-ZBGssi) 2 +(VBGci-VBGssi) 2 ] 0.5 If DG1csi ≤ DG1Jcs (=0.9, empirical value) and CP=1 (indicating the test is proceeding normally), then the measured value matches the planned value, and it is determined that the B-type missile can carry out the test mission normally; otherwise, if DG1Jcs<DG1csi≤3 / 2*DG1Jcs and CP=1, it is determined that the B-type missile or system has a minor problem, and the B-type missile's status parameters need to be adjusted slightly to restore it to the normal range; otherwise, if 3 / 2*DG1Jcs<DG1csi≤2*DG1Jcs and CP=1, it is determined that the B-type missile or system has a major problem, and the B-type missile's status parameters need to be adjusted significantly to restore it to the normal range; otherwise, if DG1csi>2*DG1Jcs, it is determined that the B-type missile or system has a serious problem, and CP needs to be set to 0 to stop the test.

[0120] Table 17: Dynamic multi-parameter template for evaluating and identifying the status of C-type target drones.

[0121]

[0122] If an instruction from the superior is received that CP=0, it indicates an emergency and the experiment must be stopped; otherwise, calculate DGcsi=[(TCGci–TCGssi)] using Table 17. 2 +(XCGci–XCGssi) 2 +(YCGci–YCGssi) 2 +(ZCGci–ZCGssi) 2 +(VCGci–VCGssi) 2 ] 0.5If DGcsi ≤ DGJcs (=0.9, empirical value) and CP=1 (indicating the test is proceeding normally), then the measured value matches the simulated value, and the C-type target drone can perform the test task normally; otherwise, if DGJcs<DGcsi≤3 / 2*DGJcs and CP=1, then the C-type target drone or system status has a minor problem, and the C-type target drone status parameters need to be adjusted slightly to restore it to the normal range; otherwise, if 3 / 2*DGJcs<DGcsi≤2*DGJcs and CP=1, then the C-type target drone or system status has a major problem, and the C-type target drone status parameters need to be adjusted significantly to restore it to the normal range; otherwise, if DGcsi>2*DGJcs, then the C-type target drone or system status has a serious problem, and CP needs to be set to 0 to stop the test. Combining Tables 16 and 17, at the moment when the B-type missile encounters the C-type target drone, Tg = TBGci = TCGci. Let the minimum distance between the B-type missile and the C-type target drone be Dgbc = [(XCGci – XBGci). 2 +(YCGci–YBGci) 2 +(ZCGci–ZBGci)2] 0.5 If Dgbc ≤ DbcJ (miss distance index), then the test results of the air-to-air missile intercepting the target drone meet the requirements; otherwise, the test results do not meet the expected requirements, and another test needs to be considered.

[0123] In summary, this embodiment first proposes a general mission operation decision-making method based on dynamic multi-parameter templates, based on the tactical and technical indicators, simulation data, and test measurement data of the equipment or system at the test range. This provides evaluation criteria and judgment standards for intelligent decision-making in equipment or system test missions. Secondly, based on the analysis and assessment of test range mission requirements, a smart test range mission operation management system platform is designed and developed, including a smart planning system, a smart simulation system, a smart execution system, a smart test measurement system, a smart command and control system, and a smart evaluation and assessment system. It also generates specific mission operation status judgment method templates. This invention addresses the challenges of complex and cumbersome task planning for test equipment, measurement and control equipment, and data processing equipment. It proposes a general task operation decision-making criterion based on dynamic multi-parameter templates, develops a task operation management system platform, and solves problems such as low efficiency in the entire process of test simulation, implementation, measurement, and evaluation, mismatch between test system operation and on-site task control capabilities, inconsistent data processing standards, and long test evaluation cycles. This results in a significantly improved efficiency for completing equipment test tasks in a smart test site, making it applicable to different types of equipment test site tasks. It serves as a paradigm for the design of digital and intelligent task operation decision-making methods and the development of related intelligent systems for smart equipment test sites. This embodiment of the method addresses the needs of different types of equipment throughout the entire testing process by designing an intelligent test site operation decision-making method, proposing a general task operation decision-making criterion based on dynamic multi-parameter templates, and developing a task operation management system platform. This solves the problems of cumbersome and complex task planning for test equipment, test and measurement equipment, command and control equipment, and data information processing equipment, as well as the low efficiency of the entire process of test simulation, implementation, test and measurement, and evaluation, and the lack of test capabilities.

[0124] Furthermore, this embodiment also provides a general task execution decision system based on a dynamic multi-parameter template, including a microprocessor and a memory interconnected, wherein the microprocessor is programmed or configured to execute the general task execution decision method based on the dynamic multi-parameter template. Additionally, this embodiment also provides a computer-readable storage medium storing a computer program for being programmed or configured by the microprocessor to execute the general task execution decision method based on the dynamic multi-parameter template.

[0125] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product embodied on one or more computer-readable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create a machine for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to operate in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The functions specified in one or more boxes. These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable apparatus for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0126] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A general task execution decision-making method based on dynamic multi-parameter templates, characterized in that, include: S101, collect the measured and theoretical values ​​of m parameters P1 to Pm corresponding to the tested equipment when performing the task, and arrange them in a determined order to generate a dynamic multi-parameter template; S102, calculate the error index between the measured and theoretical values ​​of m parameters in the dynamic multi-parameter template; S103, compare the error index with a preset error index threshold to determine the test status of the tested equipment; the functional expression of the error index is: Dsm=[(PS1-PL1) 2 +(PS2-PL2) 2 +…+(Psi-PLi) 2 +…+(PSm-PLm) 2 ] 0.5 , In the above formula, Dsm is the error index between the measured and theoretical values ​​of m parameters, PS1~PSm are the measured values ​​of m parameters respectively, and PL1~PLm are the theoretical values ​​of m parameters respectively. The calculation function expression for the preset error index threshold is: DJsm=σ1+σ2+…+σ i +…+s m +k In the above formula, DJsm represents the preset error index threshold, σ1~σ m Let P1 be the theoretical error of each of the m parameters P1 to Pm, and k be an empirical value. In step S101, the task performed by the tested equipment refers to an outdoor flight combat test mission, including an A-type carrier aircraft launching a B-type air-to-air missile to fire at a C-type target drone at airspace point S1, and setting that the B-type air-to-air missile and the C-type target drone encounter each other at time Tg. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include some or all of time, X-coordinate, Y-coordinate, Z-coordinate, and velocity. In step S103, when determining the test status of the tested equipment, it includes determining whether the waypoint planning of the tested equipment is reasonable: if the error index of the tested equipment is less than or equal to the preset error index threshold of the tested equipment, the waypoint planning of the tested equipment is determined to be reasonable; otherwise, the waypoint planning of the tested equipment is determined to be unreasonable, and the waypoints of the tested equipment need to be replanned. Alternatively, in step S101, the mission performed by the tested equipment refers to an outdoor flight combat test mission, including an A-type carrier aircraft launching a B-type air-to-air missile to fire at a C-type target drone at airspace point S1, and assuming that the B-type air-to-air missile and the C-type target drone encounter each other at time Tg. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include some or all of time, X-coordinate, Y-coordinate, Z-coordinate, and velocity, and the theoretical values ​​are obtained through equipment combat technical indicators or simulation. In step S103, when determining the test state of the tested equipment, it includes determining whether the simulation results of the tested equipment are reasonable: if the error index of the tested equipment is less than or equal to the preset error index threshold of the tested equipment, the simulation results of the tested equipment are deemed reasonable; otherwise, the simulation results of the tested equipment are deemed unreasonable. Alternatively, in step S101, the task performed by the tested equipment refers to an outdoor flight combat test mission, including an A-type carrier aircraft launching a B-type air-to-air missile to fire at a C-type target drone at airspace point S1, and setting that the B-type air-to-air missile and the C-type target drone encounter each other at time Tg. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include some or all of time, X-coordinate, Y-coordinate, Z-coordinate, and velocity. In step S103, when determining the test status of the tested equipment, it includes determining whether the tested equipment is normally executing command and control commands: if the error index of the tested equipment is less than or equal to the preset error index threshold DJsm of the tested equipment, it is determined that the tested equipment is normally executing command and control commands and can normally output command and control commands. If the error index of the tested equipment is greater than the preset error index threshold DJsm but less than or equal to 1.5 DJsm, it is determined that the tested equipment has encountered a minor problem when performing the task, and the command and control instructions need to be modified to slightly correct the parameters of the tested equipment. If the error index of the tested equipment is greater than 1.5 DJsm and less than or equal to 2 DJsm, it is determined that the tested equipment has encountered a major problem in performing the mission, and the command and control instructions need to be modified to significantly correct the parameters of the tested equipment; if the error index of the tested equipment is greater than 2 DJsm, it is determined that the tested equipment has encountered a serious problem in performing the mission, and the command and control instructions cannot be continued and the test needs to be terminated. Alternatively, in step S101, the mission performed by the tested equipment refers to an outdoor flight combat test mission, including an A-type carrier aircraft launching a B-type air-to-air missile at airspace point S1 to fire at a C-type target drone, and assuming that the B-type air-to-air missile and the C-type target drone encounter each other at time Tg. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include some or all of time, X-coordinate, Y-coordinate, Z-coordinate, and velocity, and the theoretical values ​​are obtained through equipment combat technical indicators, while the measured values ​​are obtained through simulation. Step S103 includes: if the error index of the tested equipment is less than or equal to the preset error index threshold DJsm of the tested equipment, then it is determined that the tested equipment has performed the mission. If the process is stable and the equipment under test can perform the test tasks normally, then if the error index of the equipment under test is greater than the preset error index threshold DJsm but less than or equal to 1.5 DJsm, it is determined that there is a minor problem in the process of the equipment under test performing the task, and the parameters of the equipment under test need to be slightly adjusted to restore it to the normal range; if the error index of the equipment under test is greater than 1.5 DJsm but less than or equal to 2 DJsm, it is determined that there is a major problem in the process of the equipment under test performing the task, and the parameters of the equipment under test need to be significantly adjusted to restore it to the normal range; if the error index of the equipment under test is greater than 2 DJsm, it is determined that there is a serious problem in the process of the equipment under test performing the task, and the test task needs to be stopped. Alternatively, in step S101, the task performed by the tested equipment refers to an outdoor flight combat test mission, including an A-type carrier aircraft launching a B-type air-to-air missile at airspace point S1 to fire at a C-type target drone, and assuming that the B-type air-to-air missile and the C-type target drone encounter each other after a certain time. The tested equipment refers to one of the three: the A-type carrier aircraft, the B-type air-to-air missile, and the C-type target drone. The m parameters P1 to Pm include some or all of time, X-coordinate, Y-coordinate, Z-coordinate, and velocity, and the theoretical values ​​are obtained from simulation. Step S103 includes: calculating the minimum distance Dgbc between the B-type missile and the C-type target drone at the moment of their encounter, Dgbc = [(XCGci – XBGci). 2 + (YCGci –YBGci) 2 +(ZCGci–ZBGci) 2 ] 0.5 Where XBGci, YBGci, and ZBGci are the spatial coordinates of the B-type missile at the moment of encounter, and XCGci, YCGci, and ZCGci are the spatial coordinates of the C-type target drone at the moment of encounter. If the minimum distance Dgbc is less than or equal to the preset miss distance index DbcJ, the test result of the B-type missile intercepting the C-type target drone is deemed to meet the requirements; otherwise, the test result of the B-type missile intercepting the C-type target drone is deemed to have failed to meet the expected requirements.

2. A general task execution decision system based on dynamic multi-parameter templates, comprising interconnected microprocessors and memory, characterized in that, The microprocessor is programmed or configured to execute the general task execution decision method based on dynamic multi-parameter templates as described in claim 1.

3. A computer-readable storage medium storing a computer program, characterized in that, The computer program is used to be programmed or configured by a microprocessor to execute the general task execution decision method based on dynamic multi-parameter templates as described in claim 1.

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