Aircraft scissor moving speed optimization method

Abstract

The invention discloses an aircraft scissor maneuvering speed optimization method, which belongs to the technical field of air combat maneuvering confrontation, and comprises the following steps: obtaining initial situation information of an aircraft and an enemy plane at the beginning of air combat confrontation; constructing an optimization model according to the initial situation information, wherein the optimization target is that the speed of the nose of the airplane pointing to the enemy plane is greater than the speed of the nose of the enemy plane pointing to the airplane; traversing all allowable flight speeds of the aircraft, and obtaining air combat confrontation time corresponding to each allowable flight speed and a final distance between the two aircrafts through the optimization model; the target flight speed is obtained according to the air combat confrontation time and the final distance between the two aircrafts, the corresponding scissor maneuver speed is obtained according to the target flight speed, and the target flight speed is the allowable flight speed enabling the speed of the aircraft nose pointing to the enemy aircraft to be the fastest. The aircraft scissor maneuvering speed optimization method provided by the invention can provide technical support for flight mission planning, air combat tactical formulation and training teaching.

Description

Technical Field

[0001] The present application relates to a method for optimizing the speed of an aircraft scissors maneuver, and belongs to the technical field of air combat maneuver confrontation. Background Art

[0002] When two aircraft are at a large cross-angle and have sufficient distance between their routes, they will enter a scissors maneuver. The scissors maneuver refers to a series of head-on turns and forward dashes in the same maneuvering plane in order to gain a rear hemisphere advantage. The flight trajectories of the two aircraft look like a series of reversed and repeated flight paths. In the scissors maneuver, the flight speed determines the turning radius and the turning rate. You need to choose a suitable flight speed so that the nose of your aircraft points to the opponent first to gain an angle advantage.

[0003] The current scissors maneuver speed selection method is mainly based on the turning characteristics of the aircraft. The stable turning radius and turning rate are calculated according to the aircraft's flight speed. The better the turning rate, the smaller the turning radius of the slower aircraft, and it is easier to gain an angle advantage and put oneself on the inside of the opponent's turn. However, the limitation of this method is that it does not take into account the initial situation of the two-aircraft confrontation, especially the distance situation information of the two-aircraft confrontation, and the initial distance situation information of the two-aircraft confrontation will have a significant impact on the results of the air combat confrontation. In addition, in close-range air combat, this method cannot analyze the flight speed of its own aircraft, resulting in a long time of air combat confrontation and affecting the efficiency of air combat. Summary of the invention

[0004] The purpose of this application is to provide a method for optimizing the speed of an aircraft scissors maneuver, which comprehensively considers the initial situation information of the two aircraft to obtain the optimal scissors maneuver speed for the own aircraft to win and the distance between the two aircraft at the end of the air combat confrontation, and intuitively presents the maneuver confrontation process.

[0005] To achieve the above-mentioned purpose, the first aspect of the present application provides a method for optimizing the maneuvering speed of an aircraft scissors, comprising:

[0006] Acquiring initial situation information of the aircraft and the enemy aircraft at the beginning of the air combat confrontation, wherein the initial situation information includes an initial distance between the aircraft and the enemy aircraft, and a flight speed, a turning angular velocity, and a turning radius of each of the aircraft and the enemy aircraft;

[0007] Constructing an optimization model according to the initial situation information, wherein the optimization target of the optimization model is that the speed at which the nose of the aircraft points to the enemy aircraft is greater than the speed at which the nose of the enemy aircraft points to the aircraft;

[0008] Traversing all the allowed flight speeds of the aircraft, and obtaining the air combat confrontation time and the final distance between the two aircrafts corresponding to each of the allowed flight speeds through the optimization model, wherein the air combat confrontation time is the time taken for the nose of the aircraft to point to the enemy aircraft or the time taken for the nose of the enemy aircraft to point to the aircraft, and the final distance between the two aircrafts is the final distance between the aircraft and the enemy aircraft at the end of the air combat confrontation;

[0009] A target flight speed is obtained according to each of the air combat confrontation times and each of the final distances between the two aircraft, and a corresponding scissors maneuver speed is obtained according to the target flight speed, wherein the target flight speed is the fastest allowable flight speed that enables the nose of the aircraft to point toward the enemy aircraft.

[0010] In one embodiment, obtaining initial situation information of the aircraft and the enemy aircraft at the beginning of the air combat confrontation includes:

[0011] Get the flight speed of the aircraft and the enemy aircraft respectively;

[0012] The turning angular velocity and turning radius of the aircraft and the enemy aircraft are obtained respectively according to the flight speed.

[0013] In one embodiment, obtaining the turning angular velocity and turning radius of the aircraft and the enemy aircraft respectively according to the flight speed includes:

[0014] According to the flight speed, the turning radius of the aircraft or the enemy aircraft is:

[0015]

[0016] According to the relationship between flight speed and turning angular velocity, the turning angular velocity of the aircraft or the enemy aircraft is:

[0017] w=V / R

[0018] Among them, R is the turning radius of the aircraft or enemy aircraft, V is the flight speed of the aircraft or enemy aircraft, w is the turning angular velocity of the aircraft or enemy aircraft, and n y Normal overload of the aircraft or enemy aircraft.

[0019] In one embodiment, constructing an optimization model according to the initial situation information includes:

[0020] Setting a rectangular coordinate system according to the initial situation information;

[0021] Determine the first angle and the second angle according to the rectangular coordinate system, wherein the direction pointed by the nose of the aircraft is the first straight line, the direction pointed by the nose of the enemy aircraft is the second straight line, and the straight line formed by the line connecting the aircraft and the enemy aircraft is the third straight line, the first angle is the angle between the first straight line and the third straight line, and the second angle is the angle between the second straight line and the third straight line;

[0022] Calculating the tangent values ​​of the first angle and the second angle respectively;

[0023] Obtaining the air combat confrontation time according to the tangent value of the first angle or the tangent value of the second angle;

[0024] The final distance between the two aircraft is calculated according to the air combat confrontation time, and the optimization model is obtained.

[0025] In one implementation, calculating the tangent value of the first angle and the second angle includes:

[0026] respectively determining the slopes of the first straight line, the second straight line and the third straight line;

[0027] The tangent values ​​of the first angle and the second angle are calculated respectively according to the slope:

[0028]

[0029]

[0030] Among them, θ1 is the angle of the first angle, θ2 is the angle of the second angle, k1 is the slope of the first straight line, k2 is the slope of the second straight line, and k 12 is the slope of the third straight line.

[0031] In one embodiment, obtaining the air combat confrontation time according to the tangent value of the first angle or the tangent value of the second angle includes:

[0032] When the time taken for the tangent value of the first angle to decrease to 0 is less than the time taken for the tangent value of the second angle to decrease to 0, the air combat confrontation time is obtained according to the tangent value of the first angle;

[0033] When the time taken for the tangent value of the first angle to decrease to 0 is greater than the time taken for the tangent value of the second angle to decrease to 0, the air combat confrontation time is obtained according to the tangent value of the second angle.

[0034] In one embodiment, calculating the final distance between two aircrafts according to the air combat confrontation time includes:

[0035] Calculate the position coordinates of the aircraft at the end of the air combat confrontation:

[0036]

[0037] Calculate the position coordinates of the enemy aircraft at the end of the air combat confrontation:

[0038]

[0039] The final distance between the two aircrafts is obtained based on the position coordinates of the aircraft and the enemy aircraft:

[0040]

[0041] Among them, R1 is the turning radius of the aircraft, w1 is the turning angular velocity of the aircraft, R2 is the turning radius of the enemy aircraft, w1 is the turning angular velocity of the enemy aircraft, S is the initial distance, T total Fight against time for air combat.

[0042] In one embodiment, after obtaining the target flight speed according to each of the air combat confrontation times and each of the two-aircraft final distances, the following further comprises:

[0043] Dividing the air combat confrontation time corresponding to the target flight speed according to a preset time period to obtain a plurality of time points;

[0044] The position coordinates of the aircraft at each time point are calculated, and the dynamic flight trajectory of the aircraft when flying at the target flight speed is obtained according to each position coordinate.

[0045] The second aspect of the present application provides an electronic device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the first aspect or any one of the embodiments of the first aspect when executing the computer program.

[0046] A third aspect of the present application provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps in the first aspect or any implementation of the first aspect are implemented.

[0047] As can be seen from the above, the present application provides a method for optimizing the speed of an aircraft scissors maneuver, which comprehensively analyzes the initial situation information and turning characteristics of the aircraft and the enemy aircraft during close-range air combat confrontation, and takes the fastest pointing of the aircraft nose at the enemy aircraft as the optimization goal. By establishing an optimization model, the optimal flight speed of the own aircraft is calculated, and then the optimal scissors maneuver speed is obtained. The distance between the two aircraft at the end of the air combat confrontation is analyzed and calculated, and the maneuvering confrontation process is intuitively presented, so that the two aircraft close-range air combat scissors maneuver can win and improve the efficiency of air combat. The aircraft scissors maneuver speed optimization method provided by the present application can provide technical support for flight mission planning, air combat tactics formulation, and training and teaching, and has promotion and application value. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0049] Figure 1 A schematic diagram of a rectangular coordinate system provided in an embodiment of the present application;

[0050] Figure 2 A schematic diagram of a dynamic flight trajectory at a first time point provided in an embodiment of the present application;

[0051] Figure 3 A schematic diagram of a dynamic flight trajectory at a second time point provided in an embodiment of the present application;

[0052] Figure 4 A schematic diagram of a dynamic flight trajectory at a third time point provided in an embodiment of the present application. DETAILED DESCRIPTION

[0053] In the following description, specific details such as specific system structures, technologies, etc. are provided for the purpose of illustration rather than limitation, so as to provide a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to prevent unnecessary details from obstructing the description of the present application.

[0054] It should be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of described features, integers, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or groups thereof.

[0055] It should also be understood that the terms used in this application specification are only for the purpose of describing specific embodiments and are not intended to limit the application. As used in this application specification and the appended claims, the singular forms "a", "an" and "the" are intended to include plural forms unless the context clearly indicates otherwise.

[0056] The following is a clear and complete description of the technical solutions in the embodiments of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0057] In the following description, many specific details are set forth to facilitate a full understanding of the present application, but the present application may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present application. Therefore, the present application is not limited to the specific embodiments disclosed below.

[0058] Embodiment 1

[0059] The present application embodiment provides a method for optimizing the maneuvering speed of an aircraft scissors, the method comprising:

[0060] S100 acquires initial situation information of the aircraft and the enemy aircraft at the beginning of the air combat confrontation, wherein the initial situation information includes an initial distance between the aircraft and the enemy aircraft, and a flight speed, a turning angular velocity, and a turning radius of each of the aircraft and the enemy aircraft;

[0061] Optionally, the obtaining of initial situation information of the aircraft and the enemy aircraft at the beginning of the air combat confrontation includes:

[0062] Get the flight speed of the aircraft and the enemy aircraft respectively;

[0063] The turning angular velocity and turning radius of the aircraft and the enemy aircraft are obtained respectively according to the flight speed.

[0064] In one embodiment, in the scissor maneuver, the nose of the own aircraft is pointed at the enemy aircraft first, and the antenna offset angle is reduced to obtain an angle advantage. First, the turning radius of the aircraft or the enemy aircraft is obtained according to the flight speed:

[0065]

[0066] According to the relationship between flight speed and turning angular velocity, the turning angular velocity of the aircraft or the enemy aircraft is:

[0067] w=V / R

[0068] Among them, R is the turning radius of the aircraft or enemy aircraft, V is the flight speed of the aircraft or enemy aircraft, w is the turning angular velocity of the aircraft or enemy aircraft, and n y It is the normal overload of the aircraft or enemy aircraft, and its value is related to the flight performance of the aircraft.

[0069] S200 constructs an optimization model according to the initial situation information, wherein an optimization target of the optimization model is that a speed at which the nose of the aircraft points to the enemy aircraft is greater than a speed at which the nose of the enemy aircraft points to the aircraft;

[0070] In one embodiment, the scissors maneuver refers to a pair of opponents trying to gain an offensive advantage in a fight so that the nose of their own aircraft is turned preferentially toward the body of the opponent's aircraft. Assuming that the maneuvering rates of the two aircraft remain unchanged, when the nose of one's own aircraft is preferentially pointed at the body of the enemy aircraft, it indicates victory in the air combat confrontation. Therefore, the embodiment of the present application constructs an optimization model based on the initial posture of the aircraft at the beginning of the air combat confrontation and the turning characteristics of the aircraft, and based on the flight speed of the enemy aircraft, with the speed at which the nose of the aircraft is pointed at the enemy aircraft being greater than the speed at which the nose of the enemy aircraft is pointed at the aircraft as the optimization goal, so as to obtain the optimal scissors maneuver speed of one's own aircraft.

[0071] Optionally, constructing an optimization model according to the initial situation information includes:

[0072] Setting a rectangular coordinate system according to the initial situation information;

[0073] Determine the first angle and the second angle according to the rectangular coordinate system, wherein the direction pointed by the nose of the aircraft is the first straight line, the direction pointed by the nose of the enemy aircraft is the second straight line, and the straight line formed by the line connecting the aircraft and the enemy aircraft is the third straight line, the first angle is the angle between the first straight line and the third straight line, and the second angle is the angle between the second straight line and the third straight line;

[0074] Calculating the tangent values ​​of the first angle and the second angle respectively;

[0075] Obtaining the air combat confrontation time according to the tangent value of the first angle or the tangent value of the second angle;

[0076] The final distance between the two aircraft is calculated according to the air combat confrontation time, and the optimization model is obtained.

[0077] In one embodiment, if Figure 1As shown, the position of the aircraft at the beginning of the air combat confrontation is taken as the center o, and the direction of the line connecting the aircraft and the enemy aircraft is taken as the x-axis. Then, at the beginning of the air combat confrontation, the position coordinates of the aircraft are (0,0), and the position coordinates of the enemy aircraft are (S,0), where S is the initial distance between the aircraft and the enemy aircraft, the turning radius of the aircraft is R1, and the center of the turning circle of the aircraft is o1, the turning radius of the enemy aircraft is R2, and the center of the turning circle of the enemy aircraft is o2. When the flight time is t(s), the position coordinates of the aircraft are (R1-R1*cos(w1t), R1*sin(w1t)), and the position coordinates of the enemy aircraft are (S-(R2-R2*cos(w2t)), R2*sin(w2t)), where R1 is the turning radius of the aircraft, w1 is the turning angular velocity of the aircraft, R2 is the turning radius of the enemy aircraft, and w1 is the turning angular velocity of the enemy aircraft. The first angle is θ1, and the second angle is θ2. As the flight time increases, the values ​​of θ1 and θ2 both decrease. If one of θ1 and θ2 decreases to 0 first, it means that the nose of the corresponding aircraft is pointing to another aircraft. Alternatively, in other embodiments, other methods can be used to establish the coordinate system, as long as the positional relationship between the aircraft and the enemy aircraft can be reflected, which is not limited here.

[0078] Optionally, calculating the tangent value of the first angle and the second angle includes:

[0079] respectively determining the slopes of the first straight line, the second straight line and the third straight line;

[0080] The tangent values ​​of the first angle and the second angle are calculated respectively according to the slope:

[0081]

[0082]

[0083] Among them, θ1 is the angle of the first angle, θ2 is the angle of the second angle, k1 is the slope of the first straight line, k2 is the slope of the second straight line, and k 12 is the slope of the third straight line.

[0084] Optionally, obtaining the air combat confrontation time according to the tangent value of the first angle or the tangent value of the second angle includes:

[0085] When the time taken for the tangent value of the first angle to decrease to 0 is less than the time taken for the tangent value of the second angle to decrease to 0, the air combat confrontation time is obtained according to the tangent value of the first angle;

[0086] When the time taken for the tangent value of the first angle to decrease to 0 is greater than the time taken for the tangent value of the second angle to decrease to 0, the air combat confrontation time is obtained according to the tangent value of the second angle.

[0087] In one embodiment, the initial values ​​of θ1 and θ2 are both 90°. As the aircraft turns, θ1 and θ2 gradually decrease. When one angle decreases to 0 first, that is, tan(θ1) or tan(θ2) takes 0, the air combat confrontation is considered to be over, and the air combat confrontation time is recorded as T. total .

[0088] Optionally, the air combat confrontation time T total Calculation of the final distance D between the two machines includes:

[0089] Calculate the position coordinates of the aircraft at the end of the air combat confrontation:

[0090]

[0091] Calculate the position coordinates of the enemy aircraft at the end of the air combat confrontation:

[0092]

[0093] The final distance between the two aircrafts is obtained based on the position coordinates of the aircraft and the enemy aircraft:

[0094]

[0095] Among them, R1 is the turning radius of the aircraft, w1 is the turning angular velocity of the aircraft, R2 is the turning radius of the enemy aircraft, w1 is the turning angular velocity of the enemy aircraft, S is the initial distance, T total Fight against time for air combat.

[0096] S300 traverses all the allowed flight speeds of the aircraft, and obtains the air combat confrontation time and the final distance between the two aircrafts corresponding to each of the allowed flight speeds through the optimization model, wherein the air combat confrontation time is the time taken for the nose of the aircraft to point to the enemy aircraft or the time taken for the nose of the enemy aircraft to point to the aircraft, and the final distance between the two aircrafts is the final distance between the aircraft and the enemy aircraft at the end of the air combat confrontation;

[0097] In one embodiment, the air combat confrontation is deemed to be over when the nose of either of the two aircraft points to the other aircraft. In order to obtain the optimal flight speed that enables the own aircraft to win, the embodiment of the present application, after determining the flight speed of the enemy aircraft, traverses all the allowable flight speeds of the own aircraft, and calculates them respectively according to the optimization model to obtain the corresponding air combat confrontation times and the final distances between the two aircraft when the aircraft fly at each allowable flight speed, which lays a basis for subsequently obtaining the target flight speed.

[0098] S400 obtains a target flight speed according to each of the air combat confrontation times and each of the final distances between the two aircraft, and obtains a corresponding scissors maneuver speed according to the target flight speed, wherein the target flight speed is the fastest allowable flight speed that enables the nose of the aircraft to point toward the enemy aircraft.

[0099] Optionally, by analyzing the air combat confrontation time and the final distance between the two aircraft, the flight speed that makes the own aircraft win and the flight time is the shortest, and then the optimal scissors maneuver speed is obtained. total , combined with the turning radius and flight time of the aircraft, the distance between the two aircraft at the end of the air battle can be obtained.

[0100] Optionally, after obtaining the target flight speed according to each of the air combat confrontation times and each of the two-aircraft final distances, the method further includes:

[0101] Dividing the air combat confrontation time corresponding to the target flight speed according to a preset time period to obtain a plurality of time points;

[0102] The position coordinates of the aircraft at each time point are calculated, and the dynamic flight trajectory of the aircraft when flying at the target flight speed is obtained according to each position coordinate, so as to intuitively present the maneuvering confrontation process.

[0103] In one embodiment, according to the calculated air combat confrontation time T total , every T total / 300 time to calculate the position coordinates of the aircraft and the enemy aircraft, and draw the corresponding flight trajectory points to achieve a dynamic display of the flight trajectories of the aircraft and the enemy aircraft. The dynamic demonstration diagram of the flight trajectory is as follows Figure 2-4 As shown, Figure 2 It shows the turning process of two aircraft at a certain point in time. Figure 3 The turning process of the two aircraft at another point in time is shown. Figure 4 The nose of the plane on the middle right is pointed at the plane on the left, and the air combat confrontation between the two planes ends.

[0104] As can be seen from the above, the aircraft scissors maneuver speed optimization method provided in the embodiment of the present application comprehensively analyzes the initial situation information and the turning characteristics of the aircraft and the enemy aircraft during close-range air combat confrontation, and takes the fastest pointing of the aircraft nose at the enemy aircraft as the optimization goal. By establishing an optimization model, the optimal flight speed of the own aircraft is calculated, and then the optimal scissors maneuver speed is obtained. The distance between the two aircraft at the end of the air combat confrontation is analyzed and calculated, and the maneuver confrontation process is intuitively presented, so that the two aircraft close-range air combat scissors maneuver can be achieved to win, thereby improving the efficiency of air combat.

[0105] Embodiment 2

[0106] An embodiment of the present application provides an electronic device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the memory is used to store software programs and modules, and the processor executes various functional applications and data processing by running the software programs and modules stored in the memory. The memory and the processor are connected via a bus. Specifically, the processor implements any step in the first embodiment above by running the computer program stored in the memory.

[0107] It should be understood that in the embodiments of the present application, the processor referred to may be a central processing unit (CPU), and the processor may also be other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. A general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc.

[0108] The memory may include a read-only memory, a flash memory, and a random access memory, and provides instructions and data to the processor. A part or all of the memory may also include a nonvolatile random access memory.

[0109] As can be seen from the above, the electronic device provided in the embodiment of the present application implements the aircraft scissors maneuver speed optimization method as described in Example 1 by running a computer program, calculates the optimal flight speed of one's own aircraft by establishing an optimization model, and then obtains the optimal scissors maneuver speed, and analyzes and calculates the distance between the two aircraft at the end of the air combat confrontation, intuitively presents the maneuver confrontation process, realizes the scissors maneuver to win in close-range air combat between two aircraft, and improves air combat efficiency.

[0110] It should be understood that the above-mentioned integrated module / unit, if implemented in the form of a software functional unit and sold or used as an independent product, can be stored in a computer-readable storage medium. Based on such an understanding, the present application implements all or part of the processes in the above-mentioned embodiment method, and can also be completed by instructing the relevant hardware through a computer program. The above-mentioned computer program can be stored in a computer-readable storage medium, and the computer program can implement the steps of the above-mentioned various method embodiments when executed by the processor. Among them, the above-mentioned computer program includes computer program code, and the above-mentioned computer program code can be in source code form, object code form, executable file or some intermediate form. The above-mentioned computer-readable medium may include: any entity or device capable of carrying the above-mentioned computer program code, recording medium, U disk, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), electric carrier signal, telecommunication signal and software distribution medium. It should be noted that the content contained in the above-mentioned computer-readable storage medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction.

[0111] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

[0112] The technicians in the relevant field can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional units and modules is used as an example for illustration. In practical applications, the above-mentioned function allocation can be completed by different functional units and modules as needed, that is, the internal structure of the above-mentioned device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiment can be integrated in a processing unit, or each unit can exist physically separately, or two or more units can be integrated in one unit. The above-mentioned integrated unit can be implemented in the form of hardware or in the form of software functional units. In addition, the specific names of the functional units and modules are only for the convenience of distinguishing each other, and are not used to limit the scope of protection of this application. The specific working process of the units and modules in the above-mentioned system can refer to the corresponding process in the aforementioned method embodiment, which will not be repeated here.

[0113] It should be noted that the methods and detailed examples provided in the above embodiments can be combined with the devices and equipment provided in the embodiments, and references can be made to each other, and no further details will be given.

[0114] Those of ordinary skill in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.

[0115] In the embodiments provided in the present application, it should be understood that the disclosed apparatus / terminal equipment and method can be implemented in other ways. For example, the apparatus / equipment embodiments described above are only schematic, for example, the division of the above modules or units is only a logical function division, and in actual implementation, other division methods can be used, for example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed.

[0116] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application, and should all be included in the protection scope of the present application.

Claims

1. A method for optimizing the maneuvering speed of aircraft scissors, characterized in that: include: Acquiring initial situation information of the aircraft and the enemy aircraft at the beginning of the air combat confrontation, wherein the initial situation information includes an initial distance between the aircraft and the enemy aircraft, and a flight speed, a turning angular velocity, and a turning radius of each of the aircraft and the enemy aircraft; Constructing an optimization model according to the initial situation information, wherein the optimization target of the optimization model is that the speed at which the nose of the aircraft points to the enemy aircraft is greater than the speed at which the nose of the enemy aircraft points to the aircraft; Traversing all the allowed flight speeds of the aircraft, and obtaining the air combat confrontation time and the final distance between the two aircrafts corresponding to each of the allowed flight speeds through the optimization model, wherein the air combat confrontation time is the time taken for the nose of the aircraft to point to the enemy aircraft or the time taken for the nose of the enemy aircraft to point to the aircraft, and the final distance between the two aircrafts is the final distance between the aircraft and the enemy aircraft at the end of the air combat confrontation; A target flight speed is obtained according to each of the air combat confrontation times and each of the final distances between the two aircraft, and a corresponding scissors maneuver speed is obtained according to the target flight speed, wherein the target flight speed is the fastest allowable flight speed that enables the nose of the aircraft to point toward the enemy aircraft.

2. The method for optimizing the maneuvering speed of aircraft scissors according to claim 1, characterized in that: The acquisition of initial situation information of the aircraft and the enemy aircraft at the beginning of the air combat confrontation includes: Get the flight speed of the aircraft and the enemy aircraft respectively; The turning angular velocity and turning radius of the aircraft and the enemy aircraft are obtained respectively according to the flight speed.

3. The method for optimizing the maneuvering speed of aircraft scissors according to claim 2, characterized in that: The step of obtaining the turning angular velocity and turning radius of the aircraft and the enemy aircraft respectively according to the flight speed comprises: The turning radius of the aircraft or enemy aircraft is obtained according to the flight speed: According to the relationship between flight speed and turning angular velocity, the turning angular velocity of the aircraft or the enemy aircraft is: w=V / R Among them, R is the turning radius of the aircraft or enemy aircraft, V is the flight speed of the aircraft or enemy aircraft, w is the turning angular velocity of the aircraft or enemy aircraft, and n y Normal overload of the aircraft or enemy aircraft.

4. The method for optimizing the maneuvering speed of aircraft scissors according to claim 1, characterized in that: The constructing of the optimization model according to the initial situation information comprises: Setting a rectangular coordinate system according to the initial situation information; Determine the first angle and the second angle according to the rectangular coordinate system, wherein the direction pointed by the nose of the aircraft is the first straight line, the direction pointed by the nose of the enemy aircraft is the second straight line, and the straight line formed by the line connecting the aircraft and the enemy aircraft is the third straight line, the first angle is the angle between the first straight line and the third straight line, and the second angle is the angle between the second straight line and the third straight line; Calculating the tangent values ​​of the first angle and the second angle respectively; Obtaining the air combat confrontation time according to the tangent value of the first angle or the tangent value of the second angle; The final distance between the two aircraft is calculated according to the air combat confrontation time, and the optimization model is obtained.

5. The method for optimizing the maneuvering speed of aircraft scissors according to claim 4, characterized in that: The calculating the tangent value of the first angle and the second angle comprises: respectively determining the slopes of the first straight line, the second straight line and the third straight line; The tangent values ​​of the first angle and the second angle are calculated respectively according to the slope: Among them, θ1 is the angle of the first angle, θ2 is the angle of the second angle, k1 is the slope of the first straight line, k2 is the slope of the second straight line, and k 12 is the slope of the third straight line.

6. The method for optimizing the maneuvering speed of aircraft scissors according to claim 4, characterized in that: Obtaining the air combat confrontation time according to the tangent value of the first angle or the tangent value of the second angle comprises: When the time taken for the tangent value of the first angle to decrease to 0 is less than the time taken for the tangent value of the second angle to decrease to 0, the air combat confrontation time is obtained according to the tangent value of the first angle; When the time taken for the tangent value of the first angle to decrease to 0 is greater than the time taken for the tangent value of the second angle to decrease to 0, the air combat confrontation time is obtained according to the tangent value of the second angle.

7. The method for optimizing the maneuvering speed of aircraft scissors according to claim 4, characterized in that: Calculating the final distance between the two aircrafts according to the air combat confrontation time includes: Calculate the position coordinates of the aircraft at the end of the air combat confrontation: Calculate the position coordinates of the enemy aircraft at the end of the air combat confrontation: The final distance between the two aircrafts is obtained based on the position coordinates of the aircraft and the enemy aircraft: Among them, R1 is the turning radius of the aircraft, w1 is the turning angular velocity of the aircraft, R2 is the turning radius of the enemy aircraft, w1 is the turning angular velocity of the enemy aircraft, S is the initial distance, T total Fight against time for air combat.

8. The method for optimizing the maneuvering speed of aircraft scissors according to claim 1, characterized in that: After obtaining the target flight speed according to each of the air combat confrontation times and each of the final distances between the two aircrafts, the following further comprises: Dividing the air combat confrontation time corresponding to the target flight speed according to a preset time period to obtain a plurality of time points; The position coordinates of the aircraft at each time point are calculated, and the dynamic flight trajectory of the aircraft when flying at the target flight speed is obtained according to each position coordinate.

9. An electronic device, comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the method according to any one of claims 1 to 8 when executing the computer program.

10. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 8 are implemented.

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