A method, device, medium, and product for hypersonic missile penetration.

Abstract

The application discloses a hypersonic missile penetration method, device, medium and product, relates to the technical field of hypersonic missile penetration, and comprises the following steps: acquiring initial parameters of a hypersonic missile, a first interceptor and a second interceptor; calculating the hitting time of the first interceptor and the hitting time of the second interceptor according to the initial parameters; determining the predicted flight time of the hypersonic missile according to the hitting time of the first interceptor and the hitting time of the second interceptor; determining a maneuvering time interval according to the predicted flight time; determining a plurality of initial penetration parameter combinations according to the maneuvering time interval, additional overload and a maneuvering penetration guidance model; screening the initial penetration parameter combinations to obtain a plurality of specific penetration parameter combinations; calculating the penetration effectiveness evaluation value of each specific penetration parameter combination through a penetration effectiveness evaluation function, and determining an optimal penetration parameter combination, so that the penetration capability of the hypersonic missile in the face of two interceptors is improved.

Description

Technical Field

[0001] This invention relates to the field of hypersonic missile penetration technology, and in particular to a method, device, medium, and product for hypersonic missile penetration under multiple interceptor missile interception scenarios. Background Technology

[0002] Hypersonic missiles possess advantages such as high speed, wide attack range, and strong maneuverability, making them of significant strategic value in modern warfare. However, with the rapid development of air defense and anti-missile technologies, two or more interceptor missiles can coordinate to intercept hypersonic missiles at different stages of their flight, weakening their strategic deterrent capability. Therefore, improving the survivability of hypersonic missiles is urgently needed. Employing a maneuverable, coordinated penetration approach can leverage the high maneuverability of hypersonic missiles to evade coordinated interception, thereby enhancing their survivability and transforming them into a modern weapon with strong penetration capabilities and high accuracy.

[0003] Currently, early research on hypersonic missile penetration typically employed pre-set maneuvers such as serpentine and spiral maneuvers, or obstacle avoidance trajectory planning methods, such as traditional algorithms like the Gauss pseudospectral method and prediction correction method, or intelligent algorithms like ant colony and bee colony algorithms, to achieve penetration by avoiding threat zones. However, in modern battlefields, missiles with pre-set maneuver patterns lack flexibility and are easily identified and intercepted by interceptor missiles; penetration methods based on threat zone avoidance may cause missiles to take longer routes, consuming excessive energy and thus affecting the terminal velocity of subsequent targets.

[0004] In recent years, hypersonic missile penetration technology has been a research hotspot and has received a great deal of attention in the defense industry. However, to date, most penetration research results have only considered the case where the attacking missile encounters a single interceptor missile, and there are few studies that consider the case where the attacking missile encounters two or more interceptor missiles.

[0005] For hypersonic missiles, trajectory optimization is an effective method for achieving penetration. Wang Bo improved the ant colony algorithm to optimize the trajectory of the vehicle, enhancing its penetration capability. Jorris and Cobb studied two-dimensional planar trajectory planning for hypersonic vehicles restricted by no-fly zones and waypoint constraints, and extended this trajectory optimization method to the study of three-dimensional trajectories for hypersonic gliders. Even with optimized trajectories, hypersonic missiles still face the risk of being identified and intercepted by interceptor missiles in offensive and defensive confrontations. Considering the confrontation between the offensive and defensive sides, differential game theory was first applied in hypersonic missile penetration research. Sun Shouming et al. studied mid-course maneuvering penetration based on differential game theory, obtaining the optimal solution for the guidance law of both sides. Zhang Shixiong designed a maneuvering penetration guidance law using the rate of change of line-of-sight tilt angle and line-of-sight deflection angle as control variables of differential game theory. Differential game theory requires comprehensive knowledge of the interceptor missile; however, in actual combat, information acquisition is limited, making it difficult to apply. Another important practical method is to use warhead maneuvering technology. Gao Puyun designed a passive-segment ballistic design method based on pulse-ignition warhead spatial maneuvering to improve the penetration capability of attacking missiles. In response to interception threats, Trotman and Mauro, in their research on maneuvering penetration technology, typically design maneuvering penetration guidance laws targeting a specific segment of the missile's flight path. Zhang Kenan designed multiple maneuvering penetration modes based on the distribution and type of waypoints and no-fly zones in flight missions.

[0006] Existing research shows that only a few studies have addressed the issue of hypersonic missiles encountering two interceptor missiles and attempting to penetrate defenses. Furthermore, considering real-world environmental noise and missile actuator errors, there is currently no method to improve the success rate of missile penetration by maneuvering when facing two interceptor missiles.

[0007] The evasive penetration strategy of hypersonic missiles refers to the attacking hypersonic missile, in the terminal phase of its trajectory, controlling the rotation of control surfaces or the maneuvering of the warhead according to a specific program, thereby altering its flight trajectory in three-dimensional space and evading interceptor missiles. However, in actual combat environments, noise from the missile's seeker and errors in its actuators are unavoidable. Furthermore, the missile's maneuverability is limited by its own weight, the amount of fuel it carries, and other factors, resulting in limited energy for penetration. Therefore, it is necessary to consider environmental errors and, at specific times, set specific maneuvering overloads to achieve effective missile penetration. Summary of the Invention

[0008] The purpose of this invention is to provide a method, device, medium, and product for hypersonic missile penetration, which can improve the penetration capability of hypersonic missiles against two interceptor missiles and increase the success rate of penetration.

[0009] To achieve the above objectives, the present invention provides the following solution:

[0010] A method for hypersonic missile penetration includes:

[0011] Acquire the initial parameters of the hypersonic missile, the first interceptor missile, and the second interceptor missile; the initial parameters include initial position and initial velocity;

[0012] The hit time of the first interceptor and the hit time of the second interceptor are calculated based on the initial parameters of the hypersonic missile, the first interceptor, and the second interceptor; the hit time is the estimated flight time of the interceptor hitting the hypersonic missile.

[0013] The predicted flight time of the hypersonic missile is determined based on the hit time of the first interceptor missile and the hit time of the second interceptor missile.

[0014] The start and end times of the evasive maneuver for the hypersonic missile are determined based on the predicted flight time; a maneuver time interval is determined based on the start and end times of the evasive maneuver for the hypersonic missile; several initial penetration parameter combinations are determined based on the maneuver time interval, the additional overload of the hypersonic missile, and the maneuver penetration guidance model; each initial penetration parameter combination includes a maneuver start time, a maneuver end time, additional overload, a first miss distance, and a second miss distance; the first miss distance and the second miss distance are the miss distances of the first interceptor missile and the second interceptor missile against the hypersonic missile, respectively.

[0015] Based on the penetration conditions, all initial penetration parameter combinations are screened to obtain several specific penetration parameter combinations; the penetration conditions are the constraints for hypersonic missiles to penetrate the first and second interceptor missiles.

[0016] For each specific combination of penetration parameters, the maneuver start time, maneuver end time, additional overload, first miss distance and second miss distance in the specific combination of penetration parameters are input into the penetration effectiveness evaluation function to obtain the penetration effectiveness evaluation value corresponding to each specific combination of penetration parameters.

[0017] The optimal penetration parameter combination is determined based on the penetration effectiveness evaluation value corresponding to all specific penetration parameter combinations; the optimal penetration parameter combination is used for hypersonic missiles to conduct coordinated penetration against the first and second interceptor missiles.

[0018] A computer device includes: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the hypersonic missile penetration method described above.

[0019] A computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of the aforementioned hypersonic missile penetration method.

[0020] A computer program product includes a computer program that, when executed by a processor, implements the steps of the aforementioned hypersonic missile penetration method.

[0021] According to specific embodiments provided by the present invention, the following technical effects are disclosed: The present invention provides a method, apparatus, medium, and product for hypersonic missile penetration, which acquires initial parameters of a hypersonic missile, a first interceptor missile, and a second interceptor missile; the initial parameters include initial position and initial velocity; the impact time of the first interceptor missile and the second interceptor missile are calculated based on the initial parameters of the hypersonic missile, the first interceptor missile, and the second interceptor missile; the impact time is the estimated flight time of the interceptor missile hitting the hypersonic missile; the predicted flight time of the hypersonic missile is determined based on the impact time of the first interceptor missile and the second interceptor missile; the start and end times of the hypersonic missile's evasive maneuvers are determined based on the predicted flight time; and based on... The hypersonic missile's evasive maneuver initiation and termination times determine the maneuver time interval. Based on the maneuver time interval, the hypersonic missile's additional overload, and the maneuver penetration guidance model, several initial penetration parameter combinations are determined. Each initial penetration parameter combination includes the maneuver initiation time, maneuver termination time, additional overload, first miss distance, and second miss distance. The first and second miss distances are the miss distances of the first and second interceptor missiles against the hypersonic missile, respectively. Several specific penetration parameter combinations are obtained by screening the initial penetration parameter combinations. The penetration effectiveness evaluation value of each specific penetration parameter combination is calculated using a penetration effectiveness evaluation function. The optimal penetration parameter combination is determined based on the penetration effectiveness evaluation values ​​corresponding to all specific penetration parameter combinations. This invention optimizes the key parameters for hypersonic missile penetration (maneuver initiation time, maneuver termination time, additional overload, first miss distance, and second miss distance) through online optimization, obtaining key parameters for hypersonic missile penetration that include optimal additional overload and maneuver time, thereby improving the hypersonic missile's penetration capability against two interceptor missiles. Even with environmental errors in key parameters, the penetration success rate of hypersonic missiles can still be significantly improved. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the hypersonic missile penetration method provided in Embodiment 1 of the present invention;

[0024] Figure 2 This is a schematic flowchart of a method for a hypersonic missile to penetrate two interceptor missiles, as provided in Embodiment 1 of the present invention.

[0025] Figure 3 This is a schematic diagram of the penetration simulation situation of a hypersonic missile without a penetration strategy, provided in Embodiment 1 of the present invention.

[0026] Figure 4 This is a schematic diagram of the miss distance of the first interceptor missile against the hypersonic missile provided in Embodiment 1 of the present invention;

[0027] Figure 5 This is a schematic diagram of the miss distance of the second interceptor missile against the hypersonic missile provided in Embodiment 1 of the present invention;

[0028] Figure 6 This is a simulation diagram of the penetration strategy employed by a hypersonic missile in Embodiment 1 of the present invention.

[0029] Figure 7 This is a schematic diagram of the miss distance of the first interceptor missile against the hypersonic missile provided in Embodiment 1 of the present invention;

[0030] Figure 8 This is a schematic diagram of the miss distance of the second interceptor missile against the hypersonic missile provided in Embodiment 1 of the present invention;

[0031] Figure 9 An internal structural diagram of a computer device provided in an embodiment of the present invention. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] The purpose of this invention is to provide a method, apparatus, medium, and product for hypersonic missile penetration. It aims to optimize key parameters for hypersonic missile penetration (maneuver initiation time, maneuver end time, additional overload, first miss distance, and second miss distance) through online optimization, obtaining key parameters for hypersonic missile penetration that include optimal additional overload and maneuver time, thereby improving the hypersonic missile's penetration capability against two interceptor missiles. Even with environmental errors in the key parameters, the penetration success rate of the hypersonic missile can still be significantly improved.

[0034] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0035] Example 1

[0036] like Figure 1 and Figure 2 As shown, this embodiment provides a method for hypersonic missile penetration, including:

[0037] S1: Obtain the initial parameters of the hypersonic missile, the first interceptor missile, and the second interceptor missile; the initial parameters include the initial position and the initial velocity.

[0038] S2: Calculate the hit time of the first interceptor and the hit time of the second interceptor based on the initial parameters of the hypersonic missile, the first interceptor, and the second interceptor; the hit time is the estimated flight time of the interceptor hitting the hypersonic missile.

[0039] S3: Determine the predicted flight time of the hypersonic missile based on the hit time of the first interceptor missile and the hit time of the second interceptor missile.

[0040] S4: Determine the start and end times of the evasive maneuver performed by the hypersonic missile based on the predicted flight time; determine the maneuver time interval based on the start and end times of the evasive maneuver performed by the hypersonic missile; determine several initial penetration parameter combinations based on the maneuver time interval, the additional overload of the hypersonic missile, and the maneuver penetration guidance model; each initial penetration parameter combination includes the maneuver start time, the maneuver end time, the additional overload, the first miss distance, and the second miss distance; the first miss distance and the second miss distance are the miss distances of the first interceptor missile and the second interceptor missile against the hypersonic missile, respectively.

[0041] S5: Based on the penetration conditions, all initial penetration parameter combinations are screened to obtain several specific penetration parameter combinations; the penetration conditions are the constraints for the hypersonic missile to penetrate the first and second interceptor missiles.

[0042] S6: For each specific combination of penetration parameters, input the maneuver start time, maneuver end time, additional overload, first miss distance and second miss distance in the specific combination of penetration parameters into the penetration effectiveness evaluation function to obtain the penetration effectiveness evaluation value corresponding to each specific combination of penetration parameters.

[0043] S7: Determine the optimal penetration parameter combination based on the penetration effectiveness evaluation value corresponding to all specific penetration parameter combinations; the optimal penetration parameter combination is used for hypersonic missiles to conduct coordinated penetration against the first and second interceptor missiles.

[0044] In this embodiment, in step S1, the initial positions and initial velocities of the first and second interceptor missiles are obtained by radar or satellite measurements.

[0045] Step S2 is as follows: Based on the initial positions of the hypersonic missile and the two interceptor missiles in the ground coordinate system, and the initial velocities of the hypersonic missile and the two interceptor missiles, the flight times of the two interceptor missiles when they hit the hypersonic missile are estimated, assuming the hypersonic missile does not employ a maneuvering penetration strategy. The calculation formulas for the hit time of the first interceptor missile and the hit time of the second interceptor missile are as follows:

[0046]

[0047] Where t1 represents the impact time of the first interceptor missile, i.e., the estimated flight time of the first interceptor missile hitting the hypersonic missile; R1 represents the initial relative distance between the hypersonic missile and the first interceptor missile, calculated from their initial positions; V0 represents the initial velocity of the hypersonic missile; V i,1 t1 represents the initial velocity of the first interceptor missile; t2 represents the time of impact of the second interceptor missile, i.e., the estimated flight time of the second interceptor missile hitting the hypersonic missile; R2 represents the initial relative distance between the hypersonic missile and the second interceptor missile, calculated from their initial positions; V i,2 This indicates the initial velocity of the second interceptor missile. Subscript 1 indicates the first interceptor missile, and subscript 2 indicates the second interceptor missile.

[0048] In step S3, the predicted flight time of the hypersonic missile is determined based on the hit time of the first interceptor missile and the hit time of the second interceptor missile. Specifically, this includes determining the hit time with the largest median of the hit times of the first interceptor missile and the second interceptor missile as the predicted flight time of the hypersonic missile.

[0049] After obtaining the estimated flight times of the two interceptor missiles, the maximum value is selected as the reference time for the hypersonic missile to adopt a penetration strategy, i.e., the predicted flight time t of the hypersonic missile. pre :

[0050] t pre =max(t1,t2) (2).

[0051] Step S4 is used to determine the maneuver time interval and overload range, and to perform online optimization. The specific process is as follows:

[0052] The initial value of the hypersonic missile's maneuver initiation time T1 is set to... The initial value of the maneuver end time T2 is set to t. pre T1 increases to t in fixed time steps.pre Meanwhile, T2 remains unchanged, and this serves as the first loop; T2 is reduced to a fixed time step. For each change in the value of T2, T1 needs to execute the first loop, thus constructing a double loop. Since the start time of the maneuver must be earlier than the end time of the maneuver (the start time of the maneuver is less than the end time of the maneuver), if a situation occurs where T1 > T2 during the optimization process, then this set of optimizations can be skipped, thereby improving optimization efficiency.

[0053] After determining the maneuver time interval (T1, T2), the selection range for additional overload during hypersonic missile maneuvering penetration is given. Under the condition of satisfying the hypersonic vehicle's overload constraints and not exceeding the maximum overload provided by the control surfaces, the selection range for additional overload is defined as: n pulse ∈[5g,6g].

[0054] Given the maneuver time interval (T1, T2), n pulse By increasing the step size from 5g to 6g with a fixed step size, specific parameter combinations (T1, T2, n) are obtained based on the maneuver penetration guidance model. pulse The miss distances of the next two interceptor missiles, miss1 and miss2, are used to obtain several initial penetration parameter combinations.

[0055] Among them, the maneuvering penetration guidance model includes the kinematic equations of a hypersonic missile attacking a target, the missile dynamics model, the flight trajectory model, the proportional guidance relationship equations of the interceptor in the longitudinal and lateral planes, the guidance law of the interceptor in the longitudinal and lateral planes, and the penetration guidance law of the hypersonic missile.

[0056] To study the penetration and guidance problems of hypersonic missiles, it is first necessary to establish kinematic and dynamic models of hypersonic missiles and interceptors. In practical applications, missile offense and defense confrontations take place in three-dimensional space. The spatial motion of a hypersonic missile can be regarded as the motion of an object with constant mass in three-dimensional space. Its maneuvering penetration and guidance problem needs to reflect the trajectory in three-dimensional space. Therefore, a three-degree-of-freedom point mass model can be used to represent hypersonic missiles.

[0057] As an offensive weapon, the primary mission of a hypersonic missile is to strike a target. The purpose of establishing a kinematic model of a hypersonic missile is to determine the trajectory of its center of mass relative to the ground coordinate system during its attack on the target. The kinematic equations of a hypersonic missile attacking a target are as follows:

[0058]

[0059] Where y represents the altitude of the hypersonic missile in the ground coordinate system, x and z represent the coordinate positions of the hypersonic missile on the ground in the ground coordinate system, V represents the flight speed of the hypersonic missile, θ represents the trajectory inclination angle of the hypersonic missile, ψ represents the trajectory deflection angle of the hypersonic missile, and t represents the time.

[0060] During the execution of a combat mission, the speed of a hypersonic missile changes due to air resistance. Therefore, in this embodiment, when the hypersonic missile is studied as a point mass, the missile dynamics model mainly considers the change in velocity, resulting in the following missile dynamics model:

[0061]

[0062] Where m represents the weight of the hypersonic missile, and D F The value represents the air resistance encountered by a hypersonic missile during flight. The subscript F represents force, and g represents gravitational acceleration.

[0063] During flight, changes in velocity and overload cause variations in the angular rates of the trajectory tilt and deflection, thus controlling the missile's flight path. The flight path model is shown below:

[0064]

[0065] in, The angular velocity n represents the inclination angle of a hypersonic missile's trajectory. y This indicates the overload of a hypersonic missile in the longitudinal plane, with the subscript y indicating that the corresponding parameter belongs to the longitudinal plane; The angular velocity n represents the trajectory deflection angle of a hypersonic missile. z denoted by , indicating the hypersonic missile's overload in the transverse plane, and z indicates that the corresponding parameter belongs to the transverse plane.

[0066] Under nominal conditions, the interceptor missile uses a three-dimensional proportional guidance method to intercept hypersonic missiles. Under nominal conditions, the proportional guidance relationship equations of the interceptor missile in the longitudinal and transverse planes are shown in equations (6) and (7), respectively:

[0067] angular relationships within the longitudinal plane:

[0068]

[0069] Among them, K y q represents the proportional guidance coefficient of the interceptor missile in the longitudinal plane. i,y This represents the line-of-sight angle of the interceptor missile relative to the hypersonic missile in the longitudinal plane, with the subscript i indicating the interceptor missile.

[0070] The angular relationship within the horizontal plane is as follows:

[0071]

[0072] Among them, K z q represents the proportional guidance coefficient of the interceptor missile in the lateral plane. i,z This indicates the line-of-sight angle of the interceptor missile relative to the hypersonic missile in the lateral plane, with the subscript i representing the interceptor missile.

[0073] The guidance laws for the interceptor missile in the longitudinal and lateral planes are as follows:

[0074]

[0075] Among them, a y This indicates the interceptor missile's overload in the longitudinal plane. This represents the angular velocity of the interceptor missile relative to the hypersonic missile's line-of-sight angle in the longitudinal plane. z This indicates the interceptor missile's overload in the lateral plane. The angular rate of the interceptor missile relative to the hypersonic missile's line-of-sight angle in the transverse plane.

[0076] After establishing the hypersonic attack missile model and the interceptor missile model, the proposed hypersonic missile penetration guidance method against two interceptor missiles is as follows: the hypersonic missile uses proportional guidance to strike the ground target under nominal conditions. When encountering enemy interceptor missiles, the hypersonic missile adds a maneuver term in the longitudinal overload, while still using the original guidance law in the lateral plane. The penetration guidance law of the hypersonic missile is given as shown in formulas (9) and (10):

[0077]

[0078]

[0079] Where, n y n represents the overload of a hypersonic missile in the longitudinal plane. z K represents the overload of a hypersonic missile in the lateral plane. M,y K represents the proportional guidance coefficient of a hypersonic missile in the longitudinal plane. M,z The subscript M represents the hypersonic missile's proportional guidance coefficient in the lateral plane, the subscript y represents the longitudinal plane, and the subscript z represents the lateral plane. The angular rate of a hypersonic missile relative to a ground target in the longitudinal plane is represented by its line-of-sight angle; n pulse T represents the additional overload gained by the hypersonic vehicle through the control surfaces during the penetration process; t represents the flight time; T1 represents the start time of the hypersonic missile's evasive maneuver, i.e., the start time of the maneuver; T2 represents the end time of the hypersonic missile's evasive maneuver, i.e., the end time of the maneuver.

[0080] Steps S5-S7 are used to determine the optimal combination of penetration parameters based on the miss distance requirement and the maximum value of the evaluation function, as follows:

[0081] After the aforementioned steps, the hypersonic missile obtained several initial penetration parameter combinations against the two interceptors, including specific key parameters and miss distances. For the hypersonic missile to simultaneously penetrate the defenses of two interceptors, the time interval and overload for both interceptors should be identical, and the miss distances for both interceptors should be greater than 10 meters. The mathematical description of these penetration conditions is as follows:

[0082]

[0083] In T1 and T2, the added superscript 'i' represents the interceptor missile, and the numbers 1 and 2 following 'i' represent the first and second interceptor missiles, respectively. i,1 and T1 i,2 These represent the initial moments of the hypersonic missile's maneuver against the first and second interceptor missiles, respectively. and These represent the moments when the hypersonic missile ends its maneuver against the first and second interceptor missiles, respectively; n pulse The subscripts 1 and 2 indicate that the hypersonic missile's additional overload targets the first and second interceptor missiles, respectively. pulse,1 and n pulse,2 These represent the additional overload of the hypersonic missile against the first and second interceptor missiles, respectively; miss1 represents the first miss distance; and miss2 represents the second miss distance.

[0084] The initial penetration parameter combination that meets the above penetration conditions is determined as the specific penetration parameter combination. In actual combat environments, hypersonic missiles have limited penetration capabilities; the additional overload provided by the control surfaces cannot exceed 10g, and unlimited maneuvering penetration is impossible throughout the flight. Furthermore, in evasive maneuvering penetration guidance methods, the missile's maneuvering penetration time should be as short as possible. The specific penetration parameter combination data (T1, T2, n) that meets the above penetration conditions is... pulse Since there is more than one group (miss1, miss2), it is necessary to establish a penetration effectiveness evaluation function to optimize the key parameters of missile penetration. The established penetration effectiveness evaluation function is as follows:

[0085]

[0086] Where J is the penetration effectiveness evaluation function; k1, k2, k3, k4 are the coefficients of the evaluation function, which are the coefficients of each term on the right side of the evaluation function, and are all positive numbers; T2-T1 in the first term represents the duration of the maneuver penetration. Setting the maneuver duration in the denominator indicates that the shorter the maneuver duration, the larger the value of the first term; T1 represents the start time of the hypersonic missile's maneuver; T2 represents the end time of the hypersonic missile's maneuver; the additional overload n in the second term... pulse The value of the second term is set in the denominator, indicating that the smaller the value of the additional overload, the larger the value of the second term; miss1 represents the first miss amount, the miss amount of the first interceptor missile against the hypersonic missile; in the third term, miss1 represents the miss amount of the first interceptor missile against the hypersonic missile, and the larger the miss amount, the larger the value of the third term; miss2 represents the second miss amount, the miss amount of the second interceptor missile against the hypersonic missile; in the fourth term, miss2 represents the miss amount of the second interceptor missile against the hypersonic missile, and the larger the miss amount, the larger the value of the fourth term.

[0087] A hypersonic missile can evade the interception of two interceptor missiles, and the prerequisite for achieving penetration is that both miss1 and miss2 are greater than 10m.

[0088] Based on the above penetration effectiveness evaluation function, the maneuver start time T1, maneuver end time T2, and additional overload n can be determined. pulse It is a key parameter for hypersonic missile penetration.

[0089] Step S6 is as follows: The key parameters for hypersonic missile penetration are optimized using an online optimization method. Specifically, the penetration effectiveness evaluation function J is used for optimization. The specific penetration parameter combinations obtained in step S5 are sequentially input into the penetration effectiveness evaluation function J to obtain the penetration effectiveness evaluation value corresponding to each specific penetration parameter combination. In step S7, the optimal penetration parameter combination is determined based on the penetration effectiveness evaluation values ​​corresponding to all specific penetration parameter combinations. This specifically includes determining the specific penetration parameter combination corresponding to the largest penetration effectiveness evaluation value as the optimal penetration parameter combination.

[0090] The maximum value among all penetration effectiveness evaluation values ​​obtained by function J is used to determine the corresponding parameter, which is the optimal penetration parameter combination.

[0091] The above method was used to simulate the coordinated penetration of hypersonic missiles (hypersonic missiles can also be called "offensive missiles") under multiple interceptor missile scenarios. The results are as follows:

[0092] The scene simulation parameters are shown in Tables 1 and 2:

[0093] Table 1 Initial parameters for simulation

[0094]

[0095]

[0096] Table 2. Errors of Hypersonic Missiles

[0097] Offensive missile error conditions Error value Line-of-sight angular rate noise <![CDATA[[-5,5]×10 -5 rad / s random distribution Motor overload error [-5%, 5%] random distribution Maneuver start delay [0, 0.05s] random distribution Delay of maneuver end [0, 0.05s] random distribution

[0098] The motor overload in Table 2 is the additional overload.

[0099] Using the parameters in Tables 1 and 2 above, the Monte Carlo simulation of the hypersonic missile's penetration when encountering two interceptor missiles without employing a penetration strategy is as follows: Figure 3 As shown, the x-axis represents the position in the x-direction on the ground, in km; the z-axis represents the position in the z-direction on the ground, in km; and the y-axis represents the altitude, in km.

[0100] When a hypersonic missile does not employ a penetration strategy, the miss distance of the first interceptor missile against the hypersonic missile is recorded as follows: Figure 4 As shown, the x-axis represents the number of simulations, and the y-axis represents the miss distance of the first interceptor missile against the hypersonic missile, in meters.

[0101] When the hypersonic missile does not employ a penetration strategy, the miss distance of the second interceptor missile against the hypersonic missile is recorded as follows: Figure 5 The x-axis represents the number of simulations, and the y-axis represents the miss distance of the second interceptor missile against the hypersonic missile, in meters.

[0102] When a hypersonic missile employs a penetration strategy, the Monte Carlo simulation scenario of its penetration encountering two interceptor missiles is as follows: Figure 6 As shown, the x-axis represents the position in the x-direction on the ground, in km; the z-axis represents the position in the z-direction on the ground, in km; and the y-axis represents the altitude, in km.

[0103] When a hypersonic missile employs a penetration strategy, the miss distance of the first interceptor missile against the hypersonic missile is recorded as follows: Figure 7 As shown, the x-axis represents the number of simulations, and the y-axis represents the miss distance of the first interceptor missile against the hypersonic missile, in meters.

[0104] When a hypersonic missile employs a penetration strategy, the miss distance of the second interceptor missile against the hypersonic missile is recorded as follows: Figure 8 As shown, the x-axis represents the number of simulations, and the y-axis represents the miss distance of the second interceptor missile against the hypersonic missile, in meters.

[0105] This embodiment has the following beneficial effects:

[0106] In modern battlefield environments, hypersonic missiles, as offensive missiles, face the threat of at least two interceptor missiles, leading to a decrease in survivability. To improve the survivability of hypersonic missiles, penetration is necessary when encountering interceptor missiles. However, in actual combat, hypersonic missiles inevitably encounter factors affecting penetration, such as seeker noise and actuator errors. Furthermore, the missile's maneuverability is limited by its own weight and fuel capacity, resulting in limited energy for penetration. This embodiment proposes an evasive maneuver penetration method that controls the hypersonic missile's control surfaces to further control missile overload. Through online optimization of key parameters for hypersonic missile penetration (maneuver initiation time, maneuver end time, and additional overload), key parameters for hypersonic missile penetration, including optimal additional overload and maneuver time, are obtained, improving the hypersonic missile's penetration capability against two interceptor missiles. Even with environmental errors in key parameters, the penetration success rate of hypersonic missiles can still be significantly improved.

[0107] Example 2

[0108] A computer device includes: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of a hypersonic missile penetration method according to Embodiment 1.

[0109] Example 3

[0110] A computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of a hypersonic missile penetration method in Embodiment 1.

[0111] Example 4

[0112] A computer program product includes a computer program that, when executed by a processor, implements the steps of a hypersonic missile penetration method as described in Embodiment 1.

[0113] Example 5

[0114] A computer device, which may be a database, may have an internal structure diagram as shown below. Figure 9As shown, the computer device includes a processor, memory, input / output (I / O) interfaces, and a communication interface. The processor, memory, and I / O interfaces are connected via a system bus, and the communication interface is also connected to the system bus via the I / O interfaces. The processor provides computational and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system, computer programs, and a database. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage media. The database stores pending transactions. The I / O interfaces are used for exchanging information between the processor and external devices. The communication interface is used for communicating with external terminals via a network connection. When the computer program is executed by the processor, it implements a hypersonic missile penetration method as described in Embodiment 1.

[0115] It should be noted that the object information (including but not limited to object device information, object personal information, etc.) and data (including but not limited to data used for analysis, data stored, data displayed, etc.) involved in this invention are all information and data authorized by the object or fully authorized by all parties, and the collection, use and processing of related data must comply with the relevant laws, regulations and standards of the relevant countries and regions.

[0116] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium. When executed, the computer program can include the processes of the embodiments described above. Any references to memory, databases, or other media used in the embodiments provided by this invention can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetic random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM can take many forms, such as Static Random Access Memory (SRAM) or Dynamic Random Access Memory (DRAM). The databases involved in the embodiments provided by this invention may include at least one type of relational database and non-relational database. Non-relational databases may include, but are not limited to, blockchain-based distributed databases. The processors involved in the embodiments provided by this invention may be general-purpose processors, central processing units, graphics processing units, digital signal processors, programmable logic devices, quantum computing-based data processing logic devices, etc., and are not limited to these.

[0117] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0118] This document uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. Furthermore, those skilled in the art will recognize that, based on the ideas of the present invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A method for hypersonic missile penetration, characterized in that, The application relates to a method for determining optimal evading parameters of a hypersonic missile. The method comprises the following steps: acquiring initial parameters of the hypersonic missile, a first interceptor missile and a second interceptor missile; the initial parameters include initial positions and initial velocities; calculating a hitting time of the first interceptor missile and a hitting time of the second interceptor missile according to the initial parameters of the hypersonic missile, the first interceptor missile and the second interceptor missile; the hitting time is an estimated flight time of the interceptor missile hitting the hypersonic missile; determining a predicted flight time of the hypersonic missile according to the hitting time of the first interceptor missile and the hitting time of the second interceptor missile; determining a maneuver starting time and a maneuver ending time of the hypersonic missile performing an evading maneuver according to the predicted flight time; determining a maneuver time interval according to the maneuver starting time and the maneuver ending time of the hypersonic missile performing the evading maneuver; determining a plurality of initial penetration parameter combinations according to the maneuver time interval, an additional overload of the hypersonic missile and a maneuver penetration guidance model; each initial penetration parameter combination comprises the maneuver starting time, the maneuver ending time, the additional overload, a first miss distance and a second miss distance; the first miss distance and the second miss distance are miss distances of the first interceptor missile and the second interceptor missile to the hypersonic missile respectively; screening all the initial penetration parameter combinations according to penetration conditions to obtain a plurality of specific penetration parameter combinations; the penetration conditions are constraint conditions for the hypersonic missile to realize penetration of the first interceptor missile and the second interceptor missile; for each specific penetration parameter combination, inputting the maneuver starting time, the maneuver ending time, the additional overload, the first miss distance and the second miss distance in the specific penetration parameter combination into a penetration efficiency evaluation function to obtain a penetration efficiency evaluation value corresponding to each specific penetration parameter combination; 2. The method of claim 1, wherein, determining an optimal penetration parameter combination according to the penetration efficiency evaluation values corresponding to all the specific penetration parameter combinations; the optimal penetration parameter combination is used for the hypersonic missile to perform cooperative penetration of the first interceptor missile and the second interceptor missile. Wherein, J is the defense effectiveness evaluation function; k1, k2, k3, k4 are evaluation function coefficients; T1 represents the maneuver starting time of the hypersonic missile; T2 represents the maneuver ending time of the hypersonic missile; n pulse represents the additional overload; miss1 represents the first miss distance, the miss distance of the first interceptor missile to the hypersonic missile; miss2 represents the second miss distance, the miss distance of the second interceptor missile to the hypersonic missile.

3. The method of claim 1, wherein, The calculation formula of the penetration efficiency evaluation function is as follows: wherein t1 represents the time of impact of the first interceptor missile; R1 represents the initial relative distance between the hypersonic missile and the first interceptor missile, which is calculated from the initial positions of the hypersonic missile and the first interceptor missile; V0 represents the initial speed of the hypersonic missile; V i,1 represents the initial speed of the first interceptor missile; t2 represents the time of impact of the second interceptor missile; R2 represents the initial relative distance between the hypersonic missile and the second interceptor missile, which is calculated from the initial positions of the hypersonic missile and the second interceptor missile; V i,2 represents the initial speed of the second interceptor missile.

4. The method of claim 1, wherein, The calculation formula of the hitting time of the first interceptor missile and the hitting time of the second interceptor missile is as follows: determining the predicted flight time of the hypersonic missile according to the hitting time of the first interceptor missile and the hitting time of the second interceptor missile, specifically comprising:

5. The method of claim 1, wherein, determining the hitting time with the maximum value as the predicted flight time of the hypersonic missile. wherein T1 i,1 and T1 i,2 represent the initial time of the maneuver of the hypersonic missile against the first interceptor and the second interceptor, respectively; T2 i,1 and T2 i,2 represent the end time of the maneuver of the hypersonic missile against the first interceptor and the second interceptor, respectively; n pulse,1 and n pulse,2 represent the additional overloads of the hypersonic missile against the first interceptor and the second interceptor, respectively; miss1 represents the first miss distance; and miss2 represents the second miss distance.

6. The method of claim 1, wherein, The penetration conditions are specifically as follows: determining the optimal penetration parameter combination according to the penetration efficiency evaluation values corresponding to all the specific penetration parameter combinations, specifically comprising:

7. The method of claim 1, wherein, determining the specific penetration parameter combination corresponding to the penetration efficiency evaluation value with the maximum value as the optimal penetration parameter combination. The maneuver penetration guidance model comprises a kinematics equation of the hypersonic missile attacking a target, a missile dynamics model, a flight trajectory model, a proportional guidance relationship equation of the interceptor missile in a longitudinal plane and a transverse plane, a guidance law of the interceptor missile in the longitudinal plane and the transverse plane and a penetration guidance law of the hypersonic missile.

8. A computer apparatus comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the hypersonic missile penetration method according to any one of claims 1-7.

9. A computer readable storage medium having stored thereon a computer program, characterized in that, The computer program is executed by the processor to implement the steps of the hypersonic missile penetration method according to any one of claims 1-7.

10. A computer program product comprising a computer program, characterized in that, The computer program is executed by the processor to implement the steps of the hypersonic missile penetration method according to any one of claims 1-7.

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