Method and system for determining attack area of adversarial air-to-air missile and electronic equipment

Abstract

The invention relates to a confrontation type air-to-air missile attack area determination method and system and electronic equipment, and the method comprises the steps: building a confrontation target maneuvering model, building an air-to-air missile model, and obtaining a trajectory simulation model used for simulating the attack process of an air-to-air missile on a maneuvering target, setting the initial value of the entry angle, the initial value of the altitude and the initial value of the speed of the air-to-air missile in the air-to-air missile model, setting the initial value of the altitude, the initial value of the speed and the initial position of a maneuvering target in the target maneuvering model, and simulating the maneuvering target in the air-to-air missile model by utilizing the trajectory simulation model and based on a binary method. Calculating the longest distance of the air-to-air missile hitting the maneuvering target corresponding to the initial value of the entry angle, changing the initial value of the entry angle to obtain the longest distances corresponding to the specific values of different entry angles, and obtaining the attack area corresponding to the air-to-air missile at the initial value of the altitude and the initial value of the speed according to all the longest distances, the accuracy of attack area calculation can be improved.

Description

Background Art

[0002] The attack zone of an air-to-air missile refers to a spatial area near the carrier aircraft: when the carrier aircraft launches a missile to attack the target, the target is in this airspace, and the missile can kill the target with a probability not less than a given probability. The attack zone of an air-to-air missile plays an important role in the assessment and judgment of the air combat situation, and can provide a key basis for our combat decision-making. It is also one of the important performances of air-to-air missiles. The range of the attack zone of an air-to-air missile depends not only on the performance of the air-to-air missile itself and the initial launch conditions, but also on the maneuver of the target, which will have a great impact on its calculation results.

[0003] The current air-to-air missile attack zone calculation method usually only considers the target maneuver as uniform linear motion and is limited to a two-dimensional plane. In actual air combat, the maneuvers performed by the target aircraft are usually complex and difficult to predict. Although the attack zone calculated by simplifying the target maneuver as uniform linear motion has a larger range, in actual air combat, when the target performs other more complex maneuvers, the attack zone information calculated by this method has limited auxiliary significance for the pilot. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a method, system and electronic equipment for determining the attack zone of a confrontational air-to-air missile in view of the deficiencies in the prior art.

[0005] The technical solution of a method for determining a confrontational air-to-air missile attack zone of the present invention is as follows:

[0006] Establish a maneuver model of a target with confrontation, and establish an air-to-air missile model by combining the impact of the attack angle and sideslip angle of the air-to-air missile on the aerodynamic characteristics and flight motion of the air-to-air missile;

[0007] According to the target maneuver model and the air-to-air missile model, a trajectory simulation model for simulating the attack process of the air-to-air missile on the maneuverable target is obtained;

[0008] The initial value of the entry angle, the initial value of the altitude, and the initial value of the speed of the air-to-air missile in the air-to-air missile model are set, and the initial value of the altitude, the initial value of the speed, and the initial position of the maneuvering target in the target maneuvering model are set; a ballistic simulation model is used and based on a binary method, a maximum distance at which the air-to-air missile hits the maneuvering target corresponding to the initial value of the entry angle is calculated; the initial value of the entry angle is changed to obtain the maximum distances corresponding to specific values ​​of different entry angles; and based on all the maximum distances, an attack zone corresponding to the air-to-air missile at the initial value of the altitude and the initial value of the speed is obtained.

[0009] The technical solution of a system for determining a confrontational air-to-air missile attack zone of the present invention is as follows:

[0010] It includes a modeling module and a simulation determination module;

[0011] The modeling module is used to:

[0012] Establish a maneuver model of a target with confrontation, and establish an air-to-air missile model by combining the impact of the attack angle and sideslip angle of the air-to-air missile on the aerodynamic characteristics and flight motion of the air-to-air missile;

[0013] According to the target maneuver model and the air-to-air missile model, a trajectory simulation model for simulating the attack process of the air-to-air missile on the maneuverable target is obtained;

[0014] The simulation determination module is used for:

[0015] The initial value of the entry angle, the initial value of the altitude, and the initial value of the speed of the air-to-air missile in the air-to-air missile model are set, and the initial value of the altitude, the initial value of the speed, and the initial position of the maneuvering target in the target maneuvering model are set; a ballistic simulation model is used and based on a binary method, a maximum distance at which the air-to-air missile hits the maneuvering target corresponding to the initial value of the entry angle is calculated; the initial value of the entry angle is changed to obtain the maximum distances corresponding to specific values ​​of different entry angles; and based on all the maximum distances, an attack zone corresponding to the air-to-air missile at the initial value of the altitude and the initial value of the speed is obtained.

[0016] A storage medium according to an embodiment of the present invention stores instructions, and when a computer reads the instructions, the computer executes any one of the above-mentioned methods for determining an attack zone of a confrontational air-to-air missile.

[0017] An electronic device according to an embodiment of the present invention includes a processor and the above-mentioned storage medium, and the processor executes instructions in the storage medium.

[0018] The beneficial effects of the present invention are as follows:

[0019] A maneuver model of a confronted target is established, and when establishing an air-to-air missile model, the effects of the angle of attack and sideslip angle on the movement of the air-to-air missile are considered, so that the trajectory simulation results are more in line with the actual situation, thereby improving the accuracy of the attack area, providing pilots with more effective information, and making better air combat command decisions. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0021] Figure 1 One of the flow charts of a method for determining an attack zone of a confrontation-type air-to-air missile according to an embodiment of the present invention;

[0022] Figure 2 The second flowchart of a method for determining an attack zone of a confrontation-type air-to-air missile according to an embodiment of the present invention;

[0023] Figure 3 Schematic diagram of the process of searching the model for the attack zone boundary;

[0024] Figure 4 The present invention is a schematic diagram of the structure of a system for determining a confrontational air-to-air missile attack zone according to an embodiment of the present invention. DETAILED DESCRIPTION

[0025] like Figure 1 and Figure 2 As shown, a method for determining a confrontational air-to-air missile attack zone according to an embodiment of the present invention comprises the following steps:

[0026] S1. Establish a maneuver model of a target with confrontation, and establish an air-to-air missile model by combining the impact of the attack angle and sideslip angle of the air-to-air missile on the aerodynamic characteristics and flight motion of the air-to-air missile;

[0027] S2. According to the target maneuver model and the air-to-air missile model, a ballistic simulation model for simulating the attack process of the air-to-air missile on the maneuverable target is obtained;

[0028] S3, setting the initial value of the entry angle, the initial value of the altitude, and the initial value of the speed of the air-to-air missile in the air-to-air missile model, and setting the initial value of the altitude, the initial value of the speed, and the initial position of the maneuvering target in the target maneuvering model, using the ballistic simulation model and based on the binary method, calculating the maximum distance at which the air-to-air missile hits the maneuvering target corresponding to the initial value of the entry angle, changing the initial value of the entry angle, obtaining the maximum distances corresponding to specific values ​​of different entry angles, and obtaining the attack zone corresponding to the air-to-air missile at the initial value of the altitude and the initial value of the speed based on all the maximum distances.

[0029] Optionally, in the above technical solution, in S1, the process of establishing the air-to-air missile model includes:

[0030] S10. Use Missile Datcom to estimate the aerodynamic parameters of the air-to-air missile. According to the aerodynamic equations and using the interpolation method, solve the angle of attack and sideslip angle of the air-to-air missile during the movement. Combined with the influence of the angle of attack and sideslip angle of the air-to-air missile on the aerodynamic characteristics and flight motion of the air-to-air missile, establish a three-degree-of-freedom air-to-air missile model including nonlinear aerodynamic characteristics. Specifically:

[0031] The aerodynamic parameters of air-to-air missiles are estimated by using Missile Datcom, and the angle of attack and sideslip angle of air-to-air missiles are solved according to the aerodynamic equations and the idea of ​​interpolation method. Then, the influence of the angle of attack and sideslip angle of air-to-air missiles on the movement of air-to-air missiles is considered in the establishment of missile kinematic models, so as to obtain more accurate trajectory simulation results.

[0032] At present, a six-degree-of-freedom air-to-air missile model is often established. The reasons why the present invention simplifies the six-degree-of-freedom air-to-air missile model into a three-degree-of-freedom air-to-air missile model are as follows:

[0033] 1) Since the main research in the process of calculating the range of the air-to-air missile attack zone is the change of the three-dimensional spatial position coordinates of the air-to-air missile's center of mass, by comparing the position relationship between the air-to-air missile's center of mass and the maneuvering target's center of mass, it is judged whether the air-to-air missile can hit the target, thereby obtaining the boundary value of the air-to-air missile's attack zone, rather than studying the change of the air-to-air missile's attitude angle in the process of chasing the target. Therefore, it is reasonable to ignore the change of the air-to-air missile's attitude angle in the process of calculating the attack zone.

[0034] 2) Simplifying the six-degree-of-freedom air-to-air missile model into a three-degree-of-freedom air-to-air missile model can shorten the time required for the ballistic simulation of each air-to-air missile attack on a maneuvering target, thereby increasing the speed of calculating the missile attack area.

[0035] The parameters involved in establishing the air-to-air missile of the present invention are shown in Table 1. The calculation relationship between the parameters is calculated by the first formula to the seventh formula. The first formula is: The second formula is: The third formula is: The fourth formula is: ; The fifth formula is: The sixth formula is: The seventh formula is:

[0037] Table 1:

[0038]

[0039]

[0040] In summary, establishing a three-degree-of-freedom air-to-air missile model including nonlinear aerodynamic characteristics can not only meet the requirements of simulation result accuracy, but also reduce the time required for calculating the attack area.

[0041] Another point that needs to be explained is that, compared with the traditional three-degree-of-freedom air-to-air missile model, the present invention takes into account the impact of the attack angle and sideslip angle of the air-to-air missile on the movement of the air-to-air missile, and obtains a trajectory simulation result that is more in line with the actual situation. A target model that takes into account confrontation is established, so that the maneuverability of the maneuvering target can be in line with the actual combat situation, and a more meaningful attack zone calculation result is obtained.

[0042] Optionally, in the above technical solution, in S1, establishing a maneuver model of a target with confrontation includes:

[0043] S11. Based on the actual motion data of the target aircraft when the air-to-air missile pursues the target aircraft, a target maneuver model with confrontation is established.

[0044] The target model established is a target maneuver model that takes into account confrontation. The model is modeled as close as possible to the actual movement of the target aircraft when it is pursued by an air-to-air missile, so that the calculation results of the attack zone have greater auxiliary significance. Among them, the actual movement data of the target aircraft is: the actual movement data of the target aircraft when performing target maneuvers. The target maneuvers include:

[0045] When the air-to-air missile is launched, the target turns horizontally with a fixed overload until the position of the air-to-air missile is in the negative direction of the target aircraft's speed. After the target aircraft and the air-to-air missile move along the same straight line, the target stops turning and escapes with maximum acceleration. That is, after the air-to-air missile is launched, the target turns horizontally with a fixed overload until the position of the air-to-air missile is in the negative direction of the target aircraft's speed. After the target aircraft and the air-to-air missile move along the same straight line, the target stops turning and escapes with maximum acceleration. The overload refers to acceleration. The eighth formula is used to establish a target maneuver model with confrontation. The eighth formula is:

[0046]

[0047] The parameters used in the eighth formula are shown in Table 2.

[0048] Table 2:

[0049] <![CDATA[v t ]]> Target speed <![CDATA[θ t ]]> Target pitch angle <![CDATA[ψ Vt ]]> Target yaw angle g Gravity acceleration <![CDATA[n yt ,n zt ]]> Target Normal Overload <![CDATA[x t ,y t ,z t ]]> Target position coordinates in the ground coordinate system

[0050] In S3, the initial value of the entry angle, the initial value of the altitude, and the initial value of the speed of the air-to-air missile in the air-to-air missile model are set, and the initial value of the altitude, the initial value of the speed, and the initial position of the maneuvering target in the target maneuvering model are set. The ballistic simulation model is used, and based on the binary method, the maximum distance at which the air-to-air missile hits the maneuvering target corresponding to the initial value of the entry angle is calculated. The initial value of the entry angle is changed to obtain the maximum distance corresponding to the specific values ​​of different entry angles. According to all the maximum distances, the attack area corresponding to the air-to-air missile at the initial value of the altitude and the initial value of the speed is obtained. The specific explanation is as follows:

[0051] The air-to-air missile attack zone calculation method is achieved by realizing the ballistic simulation of the air-to-air missile attacking the mobile target, and then designing the algorithm to change the repeated simulation process to calculate the boundary value of the attack zone. That is, two models need to be established in the calculation process: establish the air-to-air missile and target models to realize the ballistic simulation of the air-to-air missile attacking the mobile target; establish the attack zone boundary search model, constantly change the conditions and repeat the ballistic simulation to realize the calculation of the attack zone boundary value.

[0052] Among them, the attack area boundary search model:

[0053] The algorithm is designed with the idea of ​​dichotomy to realize the search for the boundary value of the attack zone. Each round of search can obtain the boundary of the attack zone under a certain initial condition. By changing the initial condition and repeating the search process, the boundary value of the attack zone under different initial conditions can be obtained, and finally the attack zone range of the air-to-air missile can be obtained. Specifically:

[0054] S30, setting the initial conditions of the air-to-air missile in the air-to-air missile model and the maneuvering target in the target maneuvering model, specifically:

[0055] Setting the initial value of the entry angle, the initial value of the altitude, and the initial value of the speed of the air-to-air missile in the air-to-air missile model, and setting the initial value of the altitude, the initial value of the speed, and the initial position of the maneuvering target in the target maneuvering model;

[0056] S31, take the upper limit value m and the lower limit value n respectively, form a search interval [n, m], set the distance between the target and the missile equal to the average value l of the upper limit value and the lower limit value, and use the established model to perform trajectory simulation. If the simulation result is that the target is hit, then the average value l is used as the lower limit value, the upper limit value m remains unchanged, and the average of the upper and lower limits is taken as the distance between the target and the missile, and the next cycle is entered; if the simulation result is that the target is not hit, then the average value l is used as the upper limit value, the lower limit value n remains unchanged, and the average of the upper and lower limits is taken as the distance between the target and the missile, and the next cycle is entered; until the calculation result meets the set accuracy, such as Figure 3 shown.

[0057] In the above embodiments, although the steps are numbered S1, S2, etc., these are only specific embodiments given in the present application. Those skilled in the art may adjust the execution order of S1, S2, etc. according to actual conditions, which is also within the scope of protection of the present invention. It can be understood that in some embodiments, some or all of the above embodiments may be included.

[0058] like Figure 4 As shown, a system 200 for determining a confrontational air-to-air missile attack zone according to an embodiment of the present invention includes a modeling module 210 and a simulation determination module 220;

[0059] The modeling module 210 is used to:

[0060] Establish a maneuver model of a target with confrontation, and establish an air-to-air missile model by combining the impact of the attack angle and sideslip angle of the air-to-air missile on the aerodynamic characteristics and flight motion of the air-to-air missile;

[0061] According to the target maneuver model and the air-to-air missile model, a ballistic simulation model for simulating the attack process of the air-to-air missile on the maneuvering target is obtained;

[0062] The simulation determination module 220 is used to:

[0063] The initial value of the entry angle, the initial value of the altitude, and the initial value of the speed of the air-to-air missile in the air-to-air missile model are set, and the initial value of the altitude, the initial value of the speed, and the initial position of the maneuvering target in the target maneuvering model are set. The ballistic simulation model is used and based on the binary method, the maximum distance at which the air-to-air missile hits the maneuvering target corresponding to the initial value of the entry angle is calculated. The initial value of the entry angle is changed to obtain the maximum distances corresponding to specific values ​​of different entry angles. According to all the maximum distances, the attack zone corresponding to the air-to-air missile at the initial values ​​of the altitude and the initial values ​​of the speed is obtained.

[0064] Optionally, in the above technical solution, the process of the modeling module 210 establishing the air-to-air missile model includes:

[0065] The aerodynamic parameters of the air-to-air missile are estimated using Missile Datcom. According to the aerodynamic equations and the interpolation method, the angle of attack and sideslip angle of the air-to-air missile during movement are solved. Combined with the influence of the angle of attack and sideslip angle of the air-to-air missile on the aerodynamic characteristics and flight motion of the air-to-air missile, a three-degree-of-freedom air-to-air missile model including nonlinear aerodynamic characteristics is established.

[0066] Optionally, in the above technical solution, the process of the modeling module 210 establishing the maneuver model of the target with confrontation includes:

[0067] According to the actual motion data of the target aircraft when the air-to-air missile pursues the target aircraft, a confrontational target maneuver model is established.

[0068] Optionally, in the above technical solution, the actual motion data of the target machine is: the actual motion data of the target machine when performing a target maneuver, and the target maneuver includes:

[0069] When the air-to-air missile is launched, the target makes a horizontal turn with a fixed overload in the direction of the air-to-air missile's advance. When the target and the air-to-air missile move along the same straight line, the target stops turning and escapes at maximum acceleration.

[0070] The above-mentioned parameters and steps for each unit module to implement corresponding functions in the system 200 for determining a confrontational air-to-air missile attack zone of the present invention can refer to the parameters and steps in the embodiment of the method for determining a confrontational air-to-air missile attack zone described above, and will not be repeated here.

[0071] A storage medium according to an embodiment of the present invention stores instructions. When a computer reads the instructions, the computer executes any one of the above methods for determining an attack zone of a confrontational air-to-air missile.

[0072] An electronic device according to an embodiment of the present invention includes a processor and the above-mentioned storage medium, wherein the processor executes instructions in the storage medium. The electronic device may be a computer, a mobile phone, etc.

[0073] Those skilled in the art will appreciate that the present invention may be implemented as a system, method or computer program product.

[0074] Therefore, the present disclosure may be specifically implemented in the following forms, namely: it may be completely hardware, it may be completely software (including firmware, resident software, microcode, etc.), or it may be a combination of hardware and software, generally referred to herein as a "circuit", "module" or "system". In addition, in some embodiments, the present invention may also be implemented in the form of a computer program product in one or more computer-readable media, and the computer-readable medium contains computer-readable program code.

[0075] Any combination of one or more computer-readable media may be used. A computer-readable medium may be a computer-readable signal medium or a computer-readable storage medium. A computer-readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or device, or any combination thereof. More specific examples (a non-exhaustive list) of computer-readable storage media include: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In this document, a computer-readable storage medium may be any tangible medium containing or storing a program that may be used by or in conjunction with an instruction execution system, device, or device.

[0076] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A method for determining an attack zone of a confrontational air-to-air missile, characterized in that: include: Establish a maneuver model of a target with confrontation, and establish an air-to-air missile model by combining the impact of the attack angle and sideslip angle of the air-to-air missile on the aerodynamic characteristics and flight motion of the air-to-air missile; According to the target maneuver model and the air-to-air missile model, a trajectory simulation model for simulating the attack process of the air-to-air missile on the maneuverable target is obtained; The initial value of the entry angle, the initial value of the altitude, and the initial value of the speed of the air-to-air missile in the air-to-air missile model are set, and the initial value of the altitude, the initial value of the speed, and the initial position of the maneuvering target in the target maneuvering model are set; the trajectory simulation model is used, and based on the binary method, the maximum distance at which the air-to-air missile hits the maneuvering target corresponding to the initial value of the entry angle is calculated; the initial value of the entry angle is changed to obtain the maximum distances corresponding to specific values ​​of different entry angles; and based on all the maximum distances, the attack zone corresponding to the air-to-air missile at the initial value of the altitude and the initial value of the speed is obtained.

2. The method for determining the attack zone of a confrontational air-to-air missile according to claim 1, characterized in that: The process of establishing an air-to-air missile model includes: The aerodynamic parameters of the air-to-air missile are estimated using Missile Datcom. According to the aerodynamic equations and the interpolation method, the angle of attack and sideslip angle of the air-to-air missile during movement are solved. Combined with the influence of the angle of attack and sideslip angle of the air-to-air missile on the aerodynamic characteristics and flight motion of the air-to-air missile, a three-degree-of-freedom air-to-air missile model including nonlinear aerodynamic characteristics is established.

3. The method for determining the attack zone of a confrontational air-to-air missile according to claim 2, characterized in that: Build an opposed target maneuver model, including: According to the actual motion data of the target aircraft when the air-to-air missile pursues the target aircraft, a target maneuver model with confrontation is established.

4. The method for determining the attack zone of a confrontational air-to-air missile according to claim 3, characterized in that: The actual motion data of the target machine is: the actual motion data of the target machine when performing a target maneuver, and the target maneuver includes: When the air-to-air missile is launched, the target makes a horizontal turn with a fixed overload in the direction of the air-to-air missile's advance. When the target and the air-to-air missile move along the same straight line, the target stops turning and escapes at maximum acceleration.

5. A system for determining the attack zone of a confrontational air-to-air missile, characterized in that: It includes a modeling module and a simulation determination module; The modeling module is used to: Establish a maneuver model of a target with confrontation, and establish an air-to-air missile model by combining the impact of the attack angle and sideslip angle of the air-to-air missile on the aerodynamic characteristics and flight motion of the air-to-air missile; According to the target maneuver model and the air-to-air missile model, a trajectory simulation model for simulating the attack process of the air-to-air missile on the maneuverable target is obtained; The simulation determination module is used for: The initial value of the entry angle, the initial value of the altitude, and the initial value of the speed of the air-to-air missile in the air-to-air missile model are set, and the initial value of the altitude, the initial value of the speed, and the initial position of the maneuvering target in the target maneuvering model are set; the trajectory simulation model is used, and based on the binary method, the maximum distance at which the air-to-air missile hits the maneuvering target corresponding to the initial value of the entry angle is calculated; the initial value of the entry angle is changed to obtain the maximum distances corresponding to specific values ​​of different entry angles; and based on all the maximum distances, the attack zone corresponding to the air-to-air missile at the initial value of the altitude and the initial value of the speed is obtained.

6. A system for determining the attack zone of a confrontational air-to-air missile according to claim 5, characterized in that: The process of the modeling module establishing the air-to-air missile model includes: The aerodynamic parameters of the air-to-air missile are estimated using Missile Datcom. According to the aerodynamic equations and the interpolation method, the angle of attack and sideslip angle of the air-to-air missile during movement are solved. Combined with the influence of the angle of attack and sideslip angle of the air-to-air missile on the aerodynamic characteristics and flight motion of the air-to-air missile, a three-degree-of-freedom air-to-air missile model including nonlinear aerodynamic characteristics is established.

7. A system for determining the attack zone of a confrontational air-to-air missile according to claim 6, characterized in that: The process of the modeling module establishing the antagonistic target maneuver model includes: According to the actual motion data of the target aircraft when the air-to-air missile pursues the target aircraft, a target maneuver model with confrontation is established.

8. A system for determining the attack zone of a confrontational air-to-air missile according to claim 7, characterized in that: The actual motion data of the target machine is: the actual motion data of the target machine when performing a target maneuver, and the target maneuver includes: When the air-to-air missile is launched, the target makes a horizontal turn with a fixed overload in the direction of the air-to-air missile's advance. When the target and the air-to-air missile move along the same straight line, the target stops turning and escapes at maximum acceleration.

9. A storage medium, characterized in that: The storage medium stores instructions, and when a computer reads the instructions, the computer executes a method for determining an attack zone of a confrontational air-to-air missile as claimed in any one of claims 1 to 4.

10. An electronic device, characterized in that: The invention comprises a processor and the storage medium as claimed in claim 9, wherein the processor executes instructions in the storage medium.

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