An air-based boost phase interception pre-judgment method, system, device and medium

Abstract

The application belongs to the technical field of aircraft guidance, and discloses an air-based boost phase interception prediction method, system, device and medium; the air-based boost phase interception prediction method comprises the following steps: S1, obtaining a predicted interception point sequence from a target predicted trajectory sequence obtained in advance; S2, judging whether each predicted interception point meets feasibility, and all predicted interception points meeting the feasibility constitute a predicted interception arc segment; S3, taking a midpoint of the predicted interception arc segment as a final predicted interception point, and calculating a line-of-sight deflection angle of the air-based platform and the final predicted interception point; if the difference between the line-of-sight deflection angle and the velocity azimuth angle of the air-based platform is less than a preset threshold ε2, the final predicted interception point is taken as a result output, otherwise, the state of the air-based platform is updated, and the step S1 is executed. The application provides a new rapid interception prediction method for air-based boost phase anti-missile interception, and can provide theoretical support for the technical development of boost phase anti-missile interception.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft guidance, and particularly relates to an air-based boost phase interception prediction method, system, device and medium. BACKGROUND

[0002] Ballistic missile defense is mainly divided into boost phase interception, midcourse interception and terminal phase interception. The currently active missile defense system mainly targets midcourse and terminal phase interception, and boost phase interception is still in the research and development stage. To explain further, the target in the boost phase has the characteristics of low flight speed, simple trajectory and obvious infrared characteristics. Boost phase anti-missile has the advantage of early interception, can improve the defense area and cost-effectiveness ratio, provide more interception windows for anti-missile systems, and further improve the interception capability of the entire anti-missile defense system.

[0003] Air-based boost phase anti-missile uses aircraft, unmanned aerial vehicles and other aircraft as the carrying platform of interceptor missiles to carry out boost phase anti-missile interception. The air-based interception system has the real possibility of realizing boost phase interception due to the good maneuverability and rapid response capability of the air platform and the reliance on front-line airfields and sea-based aircraft carrier battle groups. Therefore, the advantages of air-based boost phase anti-missile are paid more and more attention and valued by more and more countries.

[0004] The boost phase anti-missile interceptor needs to make an interception prediction according to the predicted trajectory of the target before launch, and calculate a predicted interception point. The predicted interception point is crucial as the guidance target of the initial and intermediate guidance of the interceptor missile, and affects the residual energy at the handover time in the terminal guidance phase, and further affects the final interception result. The traditional interception prediction method is for ground-based and sea-based anti-missile interception combat scenarios. The initial position of the interceptor missile is fixed, but in air-based boost phase anti-missile interception, the interceptor missile moves with the air-based platform before launch. The existing interception prediction method suitable for ground-based and sea-based interception is not applicable to the above-mentioned air-based scenario, and a new air-based boost phase interception prediction scheme is urgently needed. SUMMARY

[0005] The purpose of the present application is to provide an air-based boost phase interception prediction method, system, device and medium to solve one or more of the above technical problems. The technical solution provided by the present application breaks through the limitation of the fixed initial position of the existing traditional interception prediction method, and provides a new rapid interception prediction method for air-based boost phase anti-missile interception, which can provide theoretical support for the technical development of boost phase anti-missile interception.

[0006] To achieve the above-mentioned purpose, the following technical solutions are adopted in the present application:

[0007] The first aspect of the present application provides an air-based boost phase interception prediction method, comprising:

[0008] S1, obtaining a predicted interception point sequence from a pre-acquired target predicted trajectory sequence based on the interception capability of the interceptor missile, and jumping to step S2;

[0009] S2, judging whether each predicted interception point in the predicted interception point sequence satisfies feasibility, and all predicted interception points satisfying feasibility forming a predicted interception arc segment, and jumping to step S3;

[0010] S3, taking the midpoint of the predicted interception arc segment as a final predicted interception point, calculating the line-of-sight angle between the air-based platform and the final predicted interception point, and if the difference between the line-of-sight angle and the velocity azimuth angle of the air-based platform is less than a preset threshold ε2, outputting the final predicted interception point as an air-based boost phase interception prediction result, otherwise updating the state of the air-based platform and jumping to step S1.

[0011] Further improvement of the method of the application is that,

[0012] In step S1, the method for obtaining the pre-acquired target predicted trajectory sequence adopts an analytic geometry method, a numerical integration method or a trajectory prediction method based on LSTM.

[0013] Further improvement of the method of the application is that,

[0014] In step S2, the step of judging whether each predicted interception point in the predicted interception point sequence satisfies feasibility specifically comprises:

[0015] For each predicted interception point in the predicted interception point sequence, the predicted flight time of the interceptor missile and the line-of-sight elevation angle between the air-based platform and the predicted interception point are obtained according to the state information of the air-based platform; the predicted flight time and the line-of-sight elevation angle are substituted into the motion model of the interceptor missile to obtain a predicted flight distance; the obtained predicted flight distance is compared with the distance from the air-based platform to the predicted interception point, and if the difference between the two is less than a preset threshold ε1, the predicted interception point satisfies feasibility.

[0016] Further improvement of the method of the application is that,

[0017] In step S2, the motion model f(t, θ) of the interceptor missile is,

[0018]

[0019] In the formula, R fly is the predicted flight distance, R i is the flight distance of the i-th segment of the interceptor missile, d is an adjustment coefficient, t i is the i-th flight time, t go is the predicted flight time, V i-1 is the initial speed of the i-th segment, a i is the i-th segment acceleration, and n is the number of flight stages.

[0020] The method further improves in that,

[0021] In the motion model f(t, θ) of the interceptor,

[0022]

[0023] In the formula, T i is the average thrust of the ith segment, m i is the average mass of the ith segment, g is the acceleration of gravity, θ is the line-of-sight angle between the air-based platform and the predicted interception point, D i is the estimated resistance of the ith segment;

[0024] D i = D i0 + k i θ;

[0025] In the formula, D i0 and k i are correction coefficients, and θ is the line-of-sight angle between the air-based platform and the predicted interception point.

[0026] The method further improves in that,

[0027] The air-based platform state information at least includes position, speed and attitude information.

[0028] The method further improves in that,

[0029] In step S3, the calculation expression of the line-of-sight deflection angle η and the speed azimuth angle ψ v of the air-based platform is,

[0030]

[0031]

[0032] In the formula, R X , R Z are the relative position vectors R pip of the air-based platform and the predicted interception point in the inertial coordinate system, V X , V Z are the components of the speed V0 of the air-based platform in the inertial coordinate system in the X axis and the Z axis.

[0033] The second aspect of the present application provides an air-based boost phase interception pre-judgment system, comprising:

[0034] A predicted interception point sequence acquisition module is configured to acquire a predicted interception point sequence from a pre-acquired target predicted trajectory sequence based on the interception capability of the interceptor, and jump to execute a predicted interception arc segment acquisition module.

[0035] The prediction interception arc segment acquisition module is configured to determine whether each prediction interception point in the prediction interception point sequence satisfies feasibility, and all prediction interception points satisfying feasibility constitute a prediction interception arc segment.

[0036] The judgment output module takes the midpoint of the prediction interception arc segment as a final prediction interception point, calculates the line-of-sight deflection angle between the air-based platform and the final prediction interception point, and if the difference between the line-of-sight deflection angle and the velocity azimuth angle of the air-based platform is less than a preset threshold ε2, the final prediction interception point is taken as an air-based boost phase interception prediction result output, otherwise, the state of the air-based platform is updated, and the prediction interception point sequence acquisition module is executed.

[0037] The electronic device provided in the third aspect of the present application comprises:

[0038] at least one processor; and

[0039] a memory in communication connection with the at least one processor; wherein

[0040] The memory stores instructions executable by the at least one processor, and the instructions are executed by the at least one processor to enable the at least one processor to execute the air-based boost phase interception prediction method according to any one of the first aspect of the present application.

[0041] The computer readable storage medium provided in the fourth aspect of the present application stores a computer program, and when the computer program is executed by a processor, the air-based boost phase interception prediction method according to any one of the first aspect of the present application is realized.

[0042] Compared with the prior art, the present application has the following beneficial effects:

[0043] The present application provides an air-based boost phase interception prediction method, which breaks through the limitation of the initial position of the existing traditional interception prediction method, provides a new rapid interception prediction method for air-based boost phase anti-missile interception, and can provide technical support for boost phase anti-missile interception systems.

[0044] Specifically, the existing interception prediction method is for ground-based and sea-based anti-missile interception combat scenarios, the interception missile starting position is fixed, the predicted interception point is determined according to the interception capability interval, and the launch time is further determined, but in the air-based boost phase anti-missile interception, the interception missile will move with the air-based platform before launching. In the process of moving the air-based platform, the interception missile launch time cannot be determined before completing the interception prediction and launch subscription, that is, the initial position of the launch cannot be determined, and the interception prediction cannot be calculated according to the existing traditional scheme. To solve this problem, the present application can quickly and accurately calculate the predicted interception interval by fitting the motion model of the interception missile and iteratively calculating during the movement of the air-based platform, and completing the interception prediction.

[0045] In addition, the existing solution mainly uses the shooting method for interception prediction, which consumes a large amount of computing power and takes a long time to calculate. The motion model fitted by the present application is close to the real motion state of the interception missile, which can greatly reduce the calculation amount and realize the rapid calculation of interception prediction. BRIEF DESCRIPTION OF DRAWINGS

[0046] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following briefly introduces the drawings needed to be used in the embodiments or prior art description; obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can obtain other drawings according to these drawings without creative labor.

[0047] Figure 1 is a flowchart of an air-based boost phase interception prediction method provided by an embodiment of the present application;

[0048] Figure 2 is a specific flowchart of air-based boost phase anti-missile interception prediction in an embodiment of the present application;

[0049] Figure 3 is a case simulation comparison diagram of the motion model of the interception missile in an embodiment of the present application; wherein the solid line is the predicted data of the model, and the dotted line is the simulation result data;

[0050] Figure 4 is a Monte Carlo simulation experiment result diagram in an embodiment of the present application. DETAILED DESCRIPTION

[0051] In the following, the technical solutions in the embodiments of the present application will be described clearly and completely in conjunction with the accompanying drawings of the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all the other embodiments obtained by a person of ordinary skill in the art without creative effort should fall within the protection scope of the present application.

[0052] It should be noted that the terms "first", "second", and the like in the specification and claims of the present application and the above-described accompanying drawings are used to distinguish similar objects, and do not necessarily have to be used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged under appropriate circumstances, so that the embodiments of the application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion, for example, a process, method, system, product or device including a series of steps or units does not have to be limited to those steps or units clearly listed, but can include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0053] The present application will be described in further detail below in conjunction with the accompanying drawings:

[0054] Please refer to Figure 1 The air-based boost phase interception prediction method provided by the embodiments of the present application includes the following steps:

[0055] S1, based on the interception capability of the interceptor missile, a predicted interception point sequence is obtained from a pre-acquired target predicted trajectory sequence, and step S2 is executed; for example, the method for obtaining the pre-acquired target predicted trajectory sequence can use analytical geometry method, numerical integration method, trajectory prediction method based on LSTM, etc.

[0056] S2, it is judged whether each predicted interception point in the predicted interception point sequence satisfies the feasibility; all predicted interception points satisfying the feasibility constitute a predicted interception arc segment, and step S3 is executed.

[0057] S3, the midpoint of the predicted interception arc segment is taken as the final predicted interception point, and the line-of-sight angle between the air-based platform and the final predicted interception point is calculated; if the difference between the line-of-sight angle and the velocity azimuth angle of the air-based platform is less than a preset threshold ε2, the final predicted interception point is taken as the air-based boost phase interception prediction result and output, otherwise the state of the air-based platform is updated and step S1 is executed; for example, the state of the air-based platform is updated, that is, it is explained that the current is not suitable for launching.

[0058] The method provided by the embodiment of the application breaks the limitation of the initial position of the existing traditional interception prediction method, provides a new fast interception prediction method for air-based boost phase anti-missile interception, and can provide theoretical support for the development of boost phase anti-missile interception technology.

[0059] In step S2, the method provided by the embodiment of the application specifically comprises the following steps of judging whether each predicted interception point in the predicted interception point sequence satisfies feasibility.

[0060] For each predicted interception point in the predicted interception point sequence, the predicted flight time of the interceptor and the line-of-sight elevation angle of the air-based platform and the predicted interception point are calculated according to the state information of the air-based platform (explanatorily, at least including position, speed, attitude information, etc.); the predicted flight distance is obtained by substituting the predicted flight time and the line-of-sight elevation angle into the interceptor motion model; and the obtained predicted flight distance is compared with the distance from the air-based platform to the predicted interception point, and if the difference between the two is less than a preset threshold value ε1, the predicted interception point satisfies feasibility.

[0061] Please refer to Figure 2 The air-based boost phase interception prediction method provided by the embodiment of the application is specifically a fast interception prediction method for air-based boost phase anti-missile interception, and comprises the following steps.

[0062] Step 1: a predicted interception point (T pip ,R pip ) is taken out from the predicted trajectory of a target;

[0063] Step 2: based on the obtained predicted interception point, the predicted flight time T go of the interceptor and the line-of-sight elevation angle θ of the air-based platform and the predicted interception point are calculated according to the current state of the air-based platform; the predicted flight distance R go is obtained by substituting the predicted flight time T fly and the line-of-sight elevation angle θ into the interceptor motion model f(t, θ);

[0064] Step 3: the predicted flight distance obtained in step 1 is compared with the distance from the air-based platform to the predicted interception point: if the difference between the two is less than a preset threshold value ε1, the predicted interception point corresponding to the predicted flight distance is taken as a feasible predicted interception point, and step 4 is executed; otherwise, the next predicted interception point in the predicted trajectory is selected, and step 2 is executed; preferably, in the design of the threshold value ε1, ε1 should be greater than the error of the interceptor motion model (explanatorily, the error can be 1 km);

[0065] Step 4: whether the search of the predicted interception points in the predicted trajectory is completed is judged: if yes, step 5 is executed; otherwise, the next predicted interception point in the predicted trajectory is selected, and step 2 is executed;

[0066] Step 5, the midpoint of the selected interception arc segment is taken as a predicted interception point, the line-of-sight angle η of the air-based platform and the selected predicted interception point is calculated; if the difference between the line-of-sight angle η and the velocity azimuth angle ψ of the air-based platform is less than a preset threshold value ε2, the selected predicted interception point is output, otherwise it is indicated that the current is not suitable for launching, the state of the air-based platform is updated, and step 1 is performed; wherein, v

[0067]

[0068]

[0069] In the formula, R X , R Z is the relative position vector R pip of the air-based platform and the predicted interception point in the inertial coordinate system, V X , V Z are the components of the velocity V0 of the air-based platform in the inertial coordinate system in the X axis and the Z axis.

[0070] In the air-based boost phase interception pre-judgment method provided by the embodiment of the application, the initial position of the interceptor is iterated, the motion model of the interceptor is fitted, and the predicted interception interval is quickly solved in combination with the predicted trajectory of the target, so that the limitation of the fixed initial position in the existing traditional interception pre-judgment method is broken through; in addition, the influence of the selection of the predicted interception point on the interception probability is obtained through the Monte Carlo simulation experiment, and then the selection strategy of the predicted interception point is determined.

[0071] The interceptor motion model f(t, θ) used in step 2 is further explained in the embodiment of the application, and is as follows,

[0072]

[0073] In the formula, R fly is the predicted flight distance, R i is the flight distance of the i-th segment of the interceptor, d is an adjustment coefficient, t i is the i-th flight time, t go is the predicted flight time, V i-1 is the initial speed of the i-th segment, a i is the i-th segment acceleration, and n is the number of flight stages.

[0074]

[0075] In the formula, T i is the average thrust of the i-th segment, m i is the average mass of the i-th segment, g is the gravity acceleration, θ is the line-of-sight elevation angle of the air-based platform and the predicted interception point, and D i is the estimated resistance of the i-th segment.​

[0076] D i = D i0 + k i θ

[0077] wherein D i0 and k i are correction coefficients, and θ is the angle of line of sight between the base platform and the predicted interception point.

[0078] Referring to Figure 3 , in the embodiment of the present application, the setting parameters are shown in Table 1, the flight distance predicted by the fitted motion model is compared with the flight distance of the simulation flight as shown in Figure 3 , and the simulation error of the fitted model is within 1km.

[0079] Table 1. Model parameters of the interception projectile in use case

[0080] Model parameters Parameter value Unit Adjustment coefficient d 3000 m Stage number n 3 1 Duration of each phase [t1, t2, t3] [2,20,t-22] s Sight line elevation angle θ 0.7 rad phases thrust [T1, T2, T3]] [40000,5000,0] N Resistance [D 10 ,D 20 ,D 30 ]]]> [2000,1250,320] N Average quality per stage [m1, m2, m3] [146.5,108.5,85.5] kg [Design parameters [k1, k2, k3]] [20,30,40] 1 initial velocity V0 400 m / s

[0081] To analyze the efficiency of the selection strategy for the predicted interception point in step five of the present application, 9 points are equally spaced in the predicted interception interval, the standard deviation of error is set to 10%, the allowed miss distance is 1m, and 500 Monte Carlo simulations are performed for each point, the simulation results are shown in Table 2, and it is found that the interception probability is higher when the middle region of the predicted interception interval is selected, as shown in Figure 4 . This is because the speed of the interception projectile is smaller than the speed of the target, and there is no speed advantage, so the interception needs to be head-on, and earlier and later predicted interception points will cause tail-chasing interception, resulting in an increased probability of interception failure.

[0082] Table 2. Influence of predicted interception point selection on interception success rate (Monte Carlo simulation results)

[0083]

[0084]

[0085] The embodiment of the present application can quickly calculate the interception prediction, and compared with the traditional shooting method, the running speed is greatly improved; in the embodiment of the present application, the simulation comparison of the operation speed of the two methods is performed, both methods search for the predicted interception point in an interval length of 35s, and both methods take 0.2s as the step length, the simulation step length of the shooting method is 0.1s, and the final calculation time and interception miss distance are shown in Table 3. From the simulation results, the technical scheme of the embodiment of the present application can greatly shorten the calculation time, and at the same time can guarantee basically the same calculation accuracy as the shooting method.

[0086] Table 3. Comparison of the effects of the present application and the shooting method

[0087]

[0088] The following is an apparatus embodiment of the present application, which can be used to execute the method embodiment of the present application. For details not disclosed in the apparatus embodiment, please refer to the method embodiment of the present application.

[0089] In another embodiment of the present application, an air-based boost phase interception pre-judgment system is provided, comprising:

[0090] A predicted interception point sequence acquisition module is configured to acquire a predicted interception point sequence from the pre-acquired target predicted trajectory sequence based on the interception capability of the interceptor, and jump to execute the predicted interception arc segment acquisition module.

[0091] A predicted interception arc segment acquisition module is configured to judge whether each predicted interception point in the predicted interception point sequence satisfies feasibility, and all predicted interception points satisfying feasibility constitute a predicted interception arc segment, and jump to execute the judgment output module.

[0092] The judgment output module takes the midpoint of the predicted interception arc segment as a final predicted interception point, calculates the line-of-sight deflection angle between the air-based platform and the final predicted interception point, and if the difference between the line-of-sight deflection angle and the velocity azimuth angle of the air-based platform is less than a preset threshold ε2, the final predicted interception point is taken as an air-based boost phase interception pre-judgment result output, otherwise, the state of the air-based platform is updated, and the predicted interception point sequence acquisition module is executed.

[0093] In another embodiment of the present application, a computer device is provided, which comprises a processor and a memory. The memory is configured to store a computer program, the computer program comprises program instructions, and the processor is configured to execute the program instructions stored in the computer storage medium. The processor can be a central processing unit (CPU), and can 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 gates or transistor logic devices, discrete hardware components, etc. It is the computing core and control core of the terminal, which is suitable for implementing one or more instructions, and is specifically suitable for loading and executing one or more instructions in the computer storage medium to implement a corresponding method process or a corresponding function. The processor in the embodiment of the present application can be used for the operation of the air-based boost phase interception pre-judgment method.

[0094] In still another embodiment, the present application provides a storage medium, specifically a computer readable storage medium (Memory), which is a memory device in a computer device, for storing programs and data. It should be understood that the computer readable storage medium here can include an internal storage medium in the computer device, and of course can also include an extended storage medium supported by the computer device. The computer readable storage medium provides a storage space, which stores an operating system of the terminal. In addition, one or more instructions suitable for being loaded and executed by the processor are also stored in the storage space, and these instructions can be one or more computer programs (including program codes). It should be noted that the computer readable storage medium here can be a high-speed RAM memory, or a non-volatile memory such as at least one disk memory. The one or more instructions stored in the computer readable storage medium can be loaded and executed by the processor to implement the corresponding steps of the air-based boost phase interception prediction method in the above embodiments.

[0095] Those skilled in the art should understand that the embodiments of the present application can be provided as a method, a system, or a computer program product. Therefore, the present application can take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. In addition, the present application can take the form of a computer program product implemented on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROMs, optical storage, etc.) containing computer-usable program code.

[0096] The present application is described with reference to the flowcharts and / or block diagrams according to the methods, devices (systems), and computer program products of the embodiments of the present application. It should be understood that each flow and / or block in the flowcharts and / or block diagrams, and the combination of the flows and / or blocks in the flowcharts and / or block diagrams can be implemented by computer program instructions. These computer program instructions can be provided to a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing devices generate a means for implementing the functions specified in the flowcharts and / or block diagrams. Figure 1 The functions specified in one or more flows and / or blocks Figure 1 The means for implementing the functions specified in one or more flows and / or blocks.

[0097] These computer program instructions can also be stored in a computer readable storage medium, which can guide the computer or other programmable data processing devices to work in a specific manner, so that the instructions stored in the computer readable storage medium produce a product including instruction means, which implements the functions specified in the flowcharts and / or block diagrams. Figure 1 The functions specified in one or more flows and / or blocksFigure 1 the function specified in the one or more blocks.

[0098] These computer program instructions can also be loaded into computer or other programmable data processing devices, so that a series of operation steps are performed on the computer or other programmable data processing devices to generate computer-implemented processes, thus the instructions executed on the computer or other programmable data processing devices provide a process for implementing the flow Figure 1 the flow or flows and / or blocks Figure 1 the steps of the function specified in the one or more blocks.

[0099] Finally, it should be noted that: the above examples are only used to illustrate the technical solutions of the present application, but not to limit it, although the above embodiments of the present application have been described in detail, those skilled in the art should understand: the specific embodiments of the present application can be modified or replaced by the same, without departing from the spirit and scope of the present application, any modification or equivalent replacement, which should be covered within the scope of protection of the claims of the present application.

Claims

1. A method for predicting interception during the space-based booster phase, characterized in that, include: S1, Based on the interception capability of the interceptor missile, obtain the predicted interception point sequence from the pre-acquired target prediction trajectory sequence, and jump to step S2; S2, determine whether each predicted interception point in the predicted interception point sequence is feasible, all predicted interception points that are feasible constitute a predicted interception arc segment, and proceed to step S3; S3, take the midpoint of the predicted interception arc as the final predicted interception point, calculate the line-of-sight angle between the air-based platform and the final predicted interception point; if the difference between the line-of-sight angle and the velocity azimuth angle of the air-based platform is less than the preset threshold ε2, then output the final predicted interception point as the predicted interception result of the air-based booster segment; otherwise, update the air-based platform status and jump to step S1.

2. The method for predicting interception during the space-based booster phase according to claim 1, characterized in that, In step S1, the method for obtaining the pre-acquired target prediction trajectory sequence is an analytical geometry method, a numerical integration method, or a trajectory prediction method based on LSTM.

3. The method for predicting interception during the space-based booster stage according to claim 1, characterized in that, Step S2, the step of determining whether each predicted interception point in the predicted interception point sequence satisfies the feasibility requirement, specifically includes: For each predicted interception point in the predicted interception point sequence, the expected flight time of the interceptor missile and the line-of-sight elevation angle between the air-based platform and the predicted interception point are calculated based on the air-based platform status information; the expected flight time and line-of-sight elevation angle are substituted into the interceptor missile motion model to obtain the expected flight distance; the obtained expected flight distance is compared with the distance from the air-based platform to the predicted interception point, and if the difference between the two is less than a preset threshold ε1, the predicted interception point is feasible.

4. The method for predicting interception during the space-based booster phase according to claim 3, characterized in that, In step S2, the interceptor missile's motion model f(t,θ) is: In the formula, R fly To estimate the flight distance, R i Let d be the flight distance of the interceptor missile in the i-th segment, d be the adjustment coefficient, and t be the distance of the interceptor missile in the i-th segment. i Let t be the flight time of the i-th segment. go For the estimated flight time, V i-1 Let a be the initial velocity of the i-th segment. i The acceleration of segment i, where n is the number of flight stages.

5. The method for predicting interception during the space-based booster stage according to claim 4, characterized in that, In the interceptor missile's motion model f(t,θ), In the formula, T i Let m be the average thrust of the i-th segment. i The average mass of the i-th segment, g is the gravitational acceleration, θ is the elevation angle between the airborne platform and the predicted interception point, and D i The resistance is estimated for the i-th segment; D i =D i0 +k i I; In the formula, D i0 and k i The correction factor is θ, which is the elevation angle between the airborne platform and the predicted interception point.

6. The method for predicting interception during the space-based booster phase according to claim 3, characterized in that, The status information of the airborne platform includes at least position, velocity, and attitude information.

7. The method for predicting interception during the space-based booster stage according to claim 1, characterized in that, In step S3, the line-of-sight deflection angle η and the velocity azimuth angle ψ of the airborne platform are... v The calculation expression is, In the formula, R X R Z Let R be the relative position vector between the airborne platform and the predicted interception point in the inertial coordinate system. pip In the components of the X and Z axes, V X V Z Let V0 be the components of the velocity V0 of the air-based platform in the inertial coordinate system along the X and Z axes.

8. A space-based booster-stage interception prediction system, characterized in that, include: The predicted interception point sequence acquisition module is used to obtain the predicted interception point sequence from the pre-acquired target predicted trajectory sequence based on the interception capability of the interceptor missile, and then jump to execute the predicted interception arc segment acquisition module. The prediction interception arc acquisition module is used to determine whether each prediction interception point in the prediction interception point sequence meets the feasibility requirement. All prediction interception points that meet the feasibility requirement constitute a prediction interception arc, and then the execution jumps to the judgment output module. The judgment output module takes the midpoint of the predicted interception arc as the final predicted interception point and calculates the line-of-sight angle between the air-based platform and the final predicted interception point. If the difference between the line-of-sight angle and the velocity azimuth angle of the air-based platform is less than a preset threshold ε2, the final predicted interception point is output as the predicted interception result of the air-based booster segment. Otherwise, the air-based platform status is updated, and the module jumps to execute the predicted interception point sequence acquisition module.

9. An electronic device, characterized in that, include: At least one processor; as well as, A memory communicatively connected to the at least one processor; wherein, The memory stores instructions that can be executed by the at least one processor, which, when executed by the at least one processor, enables the at least one processor to perform the air-based boost phase interception prediction method as described in any one of claims 1 to 7.

10. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the air-based booster interception prediction method as described in any one of claims 1 to 7.

Images