CN117171877A - Design method of maneuvering penetration strategy for hypersonic aircraft based on timing game - Google Patents

Abstract

The invention discloses a hypersonic aircraft maneuvering burst prevention strategy design method based on an opportunity game, which comprises the steps of firstly providing a game burst prevention strategy based on a burst prevention window based on the analysis of the advantages and disadvantages of a hypersonic aircraft in near-range countermeasure; then establishing an attack and defense countermeasure mathematical model under the approximate reverse rail interception situation in a transverse lateral plane; then, based on game burst prevention strategies of burst prevention windows, performing Monte Carlo simulation on different combat situations, friend or foe maneuver strategies, maneuver capacity and the like in engineering application to generate a game countermeasure database; and finally, offline learning is carried out on the database through a neural network, and an on-line calculation generation burst prevention window is used for guiding the hypersonic aircraft to finish burst prevention of different scenes. In the online calculation process, aiming at uncertain enemy information and situation information, the input item can take an extreme value or a plurality of values by combining with a database, and finally a public interval is searched in a plurality of generated windows, namely a public defense-burst window.

Description

Design method of maneuvering penetration strategy for hypersonic aircraft based on timing game

Technical field

The invention belongs to the technical field of aircraft, and specifically relates to a method for designing a maneuvering penetration strategy for hypersonic aircraft.

Background technique

During the short-range penetration process of hypersonic aircraft, the constraints of its own maneuverability and the uncertainty of the interceptor missile's maneuverability and guidance law have caused great difficulties to effective penetration in a short period of time. So how to Utilizing the maneuvering initiative and high-speed characteristics of the attacker, combined with intelligent learning methods, to propose an intelligent maneuvering penetration strategy for hypersonic aircraft, so as to achieve successful penetration of hypersonic aircraft under the above constraints and uncertain scenarios, is the key to be solved Scientific question.

Based on the current status of relevant research at home and abroad, for the penetration problem of hypersonic aircraft, more focus is on procedural maneuvering penetration strategies. For game maneuvering penetration, the penetration guidance law based on unilateral optimal theory and the penetration guidance law based on game maneuvering penetration are mainly studied. Penetration guidance law of differential countermeasures. The maneuvering penetration strategy of hypersonic aircraft derived by the above two methods introduces the unilateral/bilateral extreme value problem of mathematical functionals into the offensive and defensive confrontation model between hypersonic aircraft and anti-missile interceptors, and sets the penetration aircraft and interceptor missiles as two parties in the game. , adding terminal constraints such as re-entry point position and speed, maneuvering overload and control variable constraints, taking the terminal miss amount as performance indicators, and constructing a Hamilton function based on the motion model of the penetration aircraft and interceptor missile, and solving the optimal condition based on the necessary conditions for extreme values. Excellent penetration and interception strategies. The penetration guidance law based on the unilateral optimal theory requires the assumption of the guidance law of the enemy's interceptor missile in advance. This makes it difficult to obtain the enemy's guidance information in a real offensive and defensive confrontation scenario, thus causing certain difficulties in engineering implementation; The penetration guidance law based on differential game assumes that both the attacker and defender adopt optimal maneuver strategies at the same time. The designed penetration guidance law is relatively conservative and cannot fully utilize the penetration capability of the hypersonic aircraft. As for the combination of intelligent methods and penetration strategies, certain progress has been made in confrontation scenarios such as drones and cruise missiles. However, considering that the offensive and defensive confrontation scenarios of hypersonic aircraft have the characteristics of high dynamics and fast time-varying, the existing countermeasures against unmanned aerial vehicles have Intelligent mobile penetration strategies for confrontation scenarios such as man-machine and cruise missiles are not applicable.

Considering the engineering implementation of penetration strategies, in real offensive and defensive confrontation scenarios, there are often problems such as delays in obtaining information and poor information accuracy.

Contents of the invention

In order to overcome the shortcomings of the existing technology, the present invention provides a method for designing a maneuvering penetration strategy for hypersonic aircraft based on timing games. First, based on the analysis of the advantages and disadvantages of hypersonic aircraft in close confrontation, a game based on penetration windows is proposed. Penetration strategy; then establish a mathematical model of offensive and defensive confrontation in an approximate reverse-track interception situation in the lateral plane; and then develop a game penetration strategy based on the penetration window to analyze different combat situations, friendly and enemy maneuver strategies and maneuvers in engineering applications Monte Carlo simulation is performed on the capabilities and other capabilities to generate a game confrontation database; finally, the database is learned offline through neural network, and online calculation is performed to generate a penetration window to guide the hypersonic aircraft to complete penetration in different scenarios. During the online calculation process, for uncertain enemy information and situational information, the input item can be combined with the database to take the extreme value or multiple values, and finally find the common interval in the multiple generated windows, which is the public penetration window.

The technical solution adopted by the present invention to solve the technical problems includes the following steps:

Step 1: Based on the analysis of the advantages and disadvantages of hypersonic aircraft in close confrontation, propose an operational concept of penetration window;

The penetration window refers to the relative distance interval within which the hypersonic aircraft can penetrate the interceptor missile through full overload maneuvers; the short range refers to the detection range of the hypersonic aircraft;

Step 2: Establish a mathematical model of offensive and defensive confrontation in an approximate reverse orbit interception situation in the lateral plane;

Step 3: Use Monte Carlo simulation to traverse different combat situations, enemy and friendly maneuver strategies, and maneuver capabilities in engineering applications, and generate a game confrontation database;

Step 4: Perform offline learning on the game confrontation database generated in step 3 based on BP neural network.

Further, the step 2 is specifically:

The approximate reverse-orbit interception situation refers to a specific angular range. When the initial speed pointing deviation of both the hypersonic aircraft and the interceptor missile is greater than or equal to this angular range, the hypersonic aircraft does not need to maneuver for penetration and can complete the penetration using its own speed. ; When the initial speed pointing deviation of both parties is less than this angle range, a maneuverable penetration is required;

The mathematical description of the interceptor missile in the terminal guidance section is as follows:

In the formula, V _m (t) represents the velocity vector of the interceptor; γ _m represents the ballistic deflection angle of the interceptor; n _zm represents the actual flight overload of the interceptor; g represents the acceleration of gravity; Represents the velocity component of the interceptor on the x-axis;/> Represents the velocity component of the interceptor on the z-axis;/> It is the guidance law of interceptor missiles in actual engineering, including proportional guidance law PN, modified proportional guidance law APN and adaptive sliding mode guidance law ASMG; these three types of interceptor missile guidance laws in the lateral plane are expressed as follows:

Proportional guiding law:

Modified proportional guidance law:

Adaptive sliding mode guidance law:

In the formula: is the line-of-sight angular velocity from the perspective of the interceptor; V _c is the approach speed of both attackers and defenders; N, ε and δ are all guidance law parameters; a _h represents the actual acceleration of the hypersonic aircraft flight. This correction term ensures that when the target is a constant When maneuvering, the interceptor missile adopts overload compensation measures; u _m represents the command acceleration of the interceptor missile using different guidance laws;/> Represents the azimuth angular velocity from the interceptor's perspective;

At the same time, the interceptor adopts the STT control method during the entire interception process, and its constraints are only the maximum available overload constraint n _zmmax , expressed as:

|n _zm |≤n _zmmax

For hypersonic aircraft, its specific description is as follows:

Among them, V _h (t) represents the velocity vector of the hypersonic aircraft, γ _h represents the ballistic deflection angle of the hypersonic aircraft, τ _h represents the first-order link time constant of the hypersonic aircraft, n _zhc represents the overload command of the hypersonic aircraft, n _zh represents the actual flight overload of the hypersonic vehicle, Represents the velocity component of the hypersonic aircraft on the x-axis,/> Represents the velocity component of the hypersonic aircraft on the z-axis;

The control constraints of a hypersonic aircraft are:

n _zh ≤ n _zhmax

According to the existing simulation results, the angle range of the approximate reverse orbit interception situation is set to ±3.2°, that is:

|γ _h0 -γ _m0 +π|<3.2°

In the formula, n _zhmax represents the maximum available overload of the hypersonic aircraft; γ _h0 and γ _m0 are the ballistic deflection angles of the hypersonic aircraft and the interceptor at the initial moment, respectively.

Preferably, the step 3 is as follows:

Step 3-1: Simulate with the baseline parameters as the initial conditions and without parameter deviation: the initial penetration moment is set to a fixed value, and the state parameter changes during the game of the aircraft are obtained to obtain the initial distance between the two parties and the overload of the interceptor missile. , the launch angles of both sides are used as the reference for the initial deviation amount;

Step 3-2: Taking the conclusion and angle limit in step 3-1 as the initial conditions, conduct a simulation under the condition of random deviation of multiple parameters: build an offensive and defensive confrontation database by simulating multiple maneuver penetrations under different initial conditions, and traverse The initial situation information and possible maneuvering strategies of the interceptor provide training and verification data for subsequent offline learning of the database through neural networks.

Preferably, the BP neural network described in step 4 is provided with two hidden layers and a tansig activation function is selected. The specific parameter settings of the neural network are as shown in the following table:

Table 1 Neural network parameter settings

The beneficial effects of the present invention are as follows:

The present invention proposes a design method for a hypersonic aircraft penetration strategy based on active game maneuvers in real attack and defense confrontation scenarios where information acquisition is delayed and inaccurate. There are two types of advantages. First, compared with optimal control and differential countermeasures, one's own maneuver strategy mainly relies on its own short-range early warning capability and maneuverability, and does not rely on assumptions about the guidance law of interceptor missiles. It has low uncertainty and is easy to implement in engineering. Second, the designed penetration strategy has a simple form of maneuver instructions, does not require complex calculations, has no obstacles such as real-time performance, and is easy to implement in engineering.

Description of drawings

Figure 1 is a flow chart for calculating the penetration window of a hypersonic aircraft according to the present invention.

Figure 2 is a conceptual diagram of the penetration window of the hypersonic aircraft of the present invention, in which (a) the hypersonic aircraft maneuvers within the "penetration window", (b) the hypersonic aircraft maneuvers prematurely outside the "penetration window", (c) The hypersonic vehicle maneuvered too late outside the "penetration window".

Figure 3 is a schematic diagram of the approximate reverse orbit interception situation of the present invention.

Figure 4 is a schematic diagram of the offensive and defensive confrontation in the approximate reverse orbit interception situation in the lateral plane of the present invention.

Figure 5 is a schematic diagram of the Monte Carlo simulation of the "penetration window" without deflection according to the embodiment of the present invention. (a) The guidance law of the interceptor missile is a proportional guidance law, (b) the guidance law of the interceptor missile is a modified proportional guidance law. (c) The interceptor missile guidance law is an adaptive sliding mode guidance law.

Figure 6 is a schematic diagram of the Monte Carlo simulation of the "penetration window" under the condition of random deflection according to the embodiment of the present invention. (a) The guidance law of the interceptor missile is a proportional guidance law, (b) the guidance law of the interceptor missile is a modified proportional guidance law. (c) The interceptor missile guidance law is an adaptive sliding mode guidance law.

Figure 7 shows the fitting effect of the "penetration window" neural network when the minimum error of the training target is 0.001 according to the embodiment of the present invention. (a) The guidance law of the interceptor missile is a proportional guidance law, (b) the guidance law of the interceptor missile is a modified proportional guidance law. The guidance law, (c) the interceptor missile guidance law is an adaptive sliding mode guidance law.

Detailed ways

The present invention will be further described below in conjunction with the accompanying drawings and examples.

In order to solve the problem of poor robustness of existing penetration strategies designed based on classical methods and intelligent methods in real attack and defense confrontation scenarios, combined with the neural network, which does not rely on explicit mathematical models and can fit complex nonlinear mapping relationships, Advantages: The full overload maneuvering range of the hypersonic aircraft fitted through the neural network can not only complete the successful penetration of enemy interceptors, but also enhance the robustness of the penetration strategy to information delays and poor accuracy.

The technical solution of the present invention is:

Step 1. Based on the analysis of the advantages and disadvantages of hypersonic aircraft in close confrontation, the concept of "penetration window" is proposed.

As shown in Figure 2, the "penetration window" refers to the relative distance range in which a hypersonic aircraft can achieve penetration of an interceptor missile through full overload maneuvers. When the interceptor missile has formed a similar reverse-orbit interception situation against the maneuverable orbit-changing aircraft, the speed advantage of the maneuverable orbit-changing aircraft cannot be fully utilized during the penetration process. The main advantage that can be utilized is the maneuvering initiative of the attacker and the successful penetration. The required miss amount is smaller, and the disadvantage is that the overload capability is much weaker than that of interceptors. Therefore, when the maneuver is too early, it will be intercepted due to the longer exposure time of the overload disadvantage; conversely, when the maneuver is too late, the required miss amount cannot be achieved laterally. When and only when the penetration maneuver is performed within the "penetration window", the attacker's maneuvering initiative can be fully utilized, combined with the rapid approach speed of both parties, to create a miss distance of more than 1m required for penetration in a short period of time. At the same time, It also avoided its own overload disadvantage as much as possible and completed effective penetration of interceptor missiles in a small area.

Step 2: Establish a mathematical model of offensive and defensive confrontation in an approximate reverse orbit interception situation in the lateral plane.

The maneuvering flight of a hypersonic aircraft can be divided into longitudinal and lateral maneuvers according to the direction of maneuvering. The two maneuvers can exist alone or at the same time. The present invention preferentially chooses to complete the penetration through lateral maneuvers. The reason is that the lateral maneuvers can be carried out when the aircraft is at a fixed altitude and speed, which avoids the need for control due to changes in speed and altitude during the penetration process. influence of the device.

As shown in Figure 3, the approximate reverse-orbit interception situation refers to a specific angular range. When the initial speed pointing deviation of both the hypersonic aircraft and the interceptor missile is greater than this angular range, the hypersonic aircraft does not need to maneuver for penetration and can use its own speed. Complete the penetration; when the initial speed direction deviation of both parties is less than this angle range, a maneuverable penetration is required.

Step 3: Based on the concept of "penetration window", Monte Carlo simulation is used to traverse different combat situations, enemy and friendly maneuver strategies, maneuver capabilities, etc. in engineering applications as much as possible to generate a game confrontation database.

Step 4: Perform offline learning on the database based on BP neural network.

In the new offensive and defensive confrontation scenario, situational parameters, aircraft capability parameters, enemy and friendly maneuver strategies, etc. are used as inputs. The unknown parameters can select multiple sets of values within the boundary range to generate multiple windows. Offline training will obtain reliable results. Online Output the penetration maneuver window (the common area of multiple windows), and the maneuverable orbit-changing aircraft can complete small-scale and efficient penetration of interceptors by relying on the customized maneuver strategy within this window. The “penetration window” calculation process is shown in Figure 1.

Example:

Step 1: Establish a mathematical model of offensive and defensive confrontation in an approximate reverse orbit interception situation in the lateral plane.

When there is a single interceptor missile, the schematic diagram of the offensive and defensive confrontation in the lateral plane and the definition of relevant angles are shown in Figure 4. Among them, H is the hypersonic aircraft and M is the interceptor missile. In Figure 4, without loss of generality, the initial line of sight direction of H-M is taken as the X-axis, and the Z-axis is perpendicular to the X-axis in the fixed height plane. The relevant symbol definitions in the figure are shown in Table 1.

Table 1 Comparison of parameter names of aircraft on both sides of attack and defense

In the table: i=h,m. h represents the hypersonic vehicle and m represents the interceptor missile. The line of sight azimuth angle λ _hm is defined as from the interceptor missile to the hypersonic aircraft. In Figure 4, λ _hm <0.

Combined with the two-dimensional planar offensive and defensive confrontation form shown in Figure 4, the mathematical description of the interceptor missile in the terminal guidance section can be constructed as follows:

In the formula, It is a typical interceptor missile guidance law in engineering practice, including Proportional Navigation (PN), Augmented Proportional Navigation (APN) and Adaptive Sliding Mode Guidance (ASMG). wait. These three interceptor missile guidance laws in the lateral plane can be expressed as follows:

Proportional guiding law:

Modified proportional guidance law:

Adaptive sliding mode guidance law:

In the formula: is the line-of-sight angular velocity from the perspective of the interceptor; V _c is the approaching speed of both attacker and defender; N, ε and δ are all guidance law parameters.

At the same time, the interceptor uses the STT control method during the entire interception process, and its constraints are only the maximum available

Overload constraints, expressed as:

|n _zm |≤n _zmmax

For hypersonic aircraft, its specific description is as follows:

The control constraints of a hypersonic aircraft are:

n _zh ≤ n _zhmax

According to the existing simulation results, the angle range of the approximate reverse orbit interception situation is set to ±3.2°, that is:

|γ _h0 -γ _m0 +π|<3.2°

In the formula, γ _h0 and γ _m0 are the ballistic deflection angles of the hypersonic aircraft and the interceptor missile at the initial moment, respectively.

Step 2: Based on the concept of "penetration window", Monte Carlo simulation is used to traverse as many different combat situations, enemy and friendly maneuver strategies, maneuver capabilities, etc. as possible in engineering applications to generate a game confrontation database. It contains the following sub-steps.

Step 2.1, use the benchmark parameters as the initial conditions and simulate without parameter deviation: the initial penetration moment is set to a fixed value, and the state parameter changes during the aircraft game are obtained to obtain the subsequent initial distance between the two parties, interceptor overload, and both sides. Reference quantity of initial pull deviation such as launch angle.

Table 2 Parameter settings related to simulation of mobile penetration method based on the concept of "penetration window"

When the interceptor missile adopts proportional guidance law, modified proportional guidance law and adaptive sliding mode guidance law respectively, the offensive and defensive confrontation between the hypersonic aircraft and the interceptor missile is shown in Figure 5.

Step 2.2, use the conclusion and angle limit in step 2.1 as the initial conditions, and conduct a simulation with multiple parameters randomly biased: by simulating multiple maneuver penetrations under different initial conditions, build an offensive and defensive confrontation database, traverse the initial situation information and interception The possible maneuvering strategies can be adopted to provide training and verification data for subsequent offline learning of the database through neural networks.

Table 3 Relevant bias parameter settings

The Monte Carlo simulation results are shown in Figure 6.

Step 3: Use the 500 sets of "penetration window" data obtained by randomly pulling the bias parameters in step 2.2 as the training set, and use the BP neural network for fitting. The network has two hidden layers and selects the tansig activation function. After multiple trainings and adjusting parameters, the network with the best results is retained for subsequent testing.

Table 4 Neural network parameter settings

The fitting results of the "penetration window" neural network are shown in Figure 7.

Ultimately, the trained neural network can be used to predict the "penetration window" of hypersonic vehicle maneuvers given initial conditions. Assume that the initial state of the enemy interceptor is as follows: initial relative distance R0 = 11km, ballistic deflection angle γ _m0 = 181°, maximum available overload u _mmax = 7g;

1) When the enemy interceptor missile guidance law adopts the proportional guidance law, the upper bound of the actual "penetration window" of the hypersonic aircraft is 10km and the lower bound is 1.3km. The final trained BP neural network is used for window prediction to predict the "penetration window". The upper bound of "anti-window" is 9.99km, the lower bound is 1.33km, and the errors are 0.01 and 0.03 respectively.

2) When the enemy interceptor missile guidance law adopts the modified proportional guidance law, the upper bound of the actual "penetration window" of the hypersonic aircraft is 5.3km and the lower bound is 1..4km. The final trained BP neural network is used for window prediction. , the upper bound of the "penetration window" is predicted to be 5.215km, and the lower bound of the "penetration window" is 1.422km, with errors of 0.085 and 0.022 respectively.

3) When the enemy interceptor missile guidance law adopts the adaptive sliding mode guidance law, the upper bound of the actual "penetration window" of the hypersonic aircraft is 8.1km and the lower bound is 1.4km. The final trained BP neural network is used for window prediction. , the upper bound of the "penetration window" is predicted to be 8.175km, and the lower bound of the "penetration window" is 1.475km, with errors of 0.075 and 0.075 respectively.

Combining the above three "penetration windows" calculated using different guidance laws for enemy interceptors, the final public "penetration window" is △R=[1.475,5.215], and the hypersonic aircraft operates within this interval With full overload maneuver, you can successfully penetrate enemy interceptors.

Conclusion: Based on the analysis of the advantages and disadvantages of hypersonic aircraft in close confrontation, this invention proposes the operational concept of "penetration window"; builds an offensive and defensive confrontation database, traverses the initial situation information and possible maneuvering strategies of the interceptor, and uses BP neural network to The database is studied offline, and the online calculation generates a "penetration window" to guide the hypersonic aircraft to complete penetration in different scenarios. During the online calculation process, for uncertain enemy information and situational information, the input item can be combined with the database to take the extreme value or multiple values, and finally find a common interval in the multiple generated windows, which is the common "sudden moment". Anti-window". The design concept of the public "penetration window" avoids subjective estimation of uncertain information, making the designed penetration strategy universal and robust.

Claims (4)

1. A method for designing a maneuvering penetration strategy for hypersonic aircraft based on timing games, which is characterized by including the following steps: Step 1: Based on the analysis of the advantages and disadvantages of hypersonic aircraft in close confrontation, propose an operational concept of penetration windows; The penetration window refers to the relative distance interval within which the hypersonic aircraft can penetrate the interceptor missile through full overload maneuvers; the short range refers to the detection range of the hypersonic aircraft; Step 2: Establish a mathematical model of offensive and defensive confrontation in an approximate reverse orbit interception situation in the lateral plane; Step 3: Use Monte Carlo simulation to traverse different combat situations, enemy and friendly maneuver strategies, and maneuver capabilities in engineering applications, and generate a game confrontation database; Step 4: Perform offline learning on the game confrontation database generated in step 3 based on BP neural network. 2. A method for designing a maneuvering penetration strategy for hypersonic aircraft based on timing games according to claim 1, characterized in that the step 2 is specifically: The approximate reverse-orbit interception situation refers to a specific angular range. When the initial speed pointing deviation of both the hypersonic aircraft and the interceptor missile is greater than or equal to this angular range, the hypersonic aircraft does not need to maneuver for penetration and can complete the penetration using its own speed. ; When the initial speed pointing deviation of both parties is less than this angle range, a maneuverable penetration is required; The mathematical description of the interceptor missile in the terminal guidance section is as follows: In the formula, V _m (t) represents the velocity vector of the interceptor; γ _m represents the ballistic deflection angle of the interceptor; n _zm represents the actual flight overload of the interceptor; g represents the acceleration of gravity; Represents the velocity component of the interceptor on the x-axis;/> Represents the velocity component of the interceptor on the z-axis;/> It is the guidance law of interceptor missiles in actual engineering, including proportional guidance law PN, modified proportional guidance law APN and adaptive sliding mode guidance law ASMG; these three types of interceptor missile guidance laws in the lateral plane are expressed as follows: Proportional guiding law: Modified proportional guidance law: Adaptive sliding mode guidance law: In the formula: is the line-of-sight angular velocity from the perspective of the interceptor; V _c is the approach speed of both attackers and defenders; N, ε and δ are all guidance law parameters; a _h represents the actual acceleration of the hypersonic aircraft flight. This correction term ensures that when the target is a constant When maneuvering, the interceptor missile adopts overload compensation measures; u _m represents the command acceleration of the interceptor missile using different guidance laws;/> Represents the azimuth angular velocity from the interceptor's perspective; At the same time, the interceptor adopts the STT control method during the entire interception process, and its constraints are only the maximum available overload constraint n _{zm max} , expressed as: |n _zm |≤n _{zm max} For hypersonic aircraft, the specific description is as follows: Among them, V _h (t) represents the velocity vector of the hypersonic aircraft, γ _h represents the ballistic deflection angle of the hypersonic aircraft, τ _h represents the first-order link time constant of the hypersonic aircraft, n _zhc represents the overload command of the hypersonic aircraft, n _zh represents the actual flight overload of the hypersonic vehicle, Represents the velocity component of the hypersonic aircraft on the x-axis,/> Represents the velocity component of the hypersonic aircraft on the z-axis; The control constraints of a hypersonic aircraft are: n _zh ≤ n _{zh max} According to the existing simulation results, the angle range of the approximate reverse orbit interception situation is set to ±3.2°, that is: |γ _h0 -γ _m0 +π|<3.2° In the formula, n _{zh max} represents the maximum available overload of the hypersonic aircraft; γ _h0 and γ _m0 are the ballistic deflection angles of the hypersonic aircraft and the interceptor at the initial moment, respectively. 3. A method for designing a maneuvering penetration strategy for hypersonic aircraft based on timing games according to claim 2, characterized in that the step 3 is as follows: Step 3-1: Simulate with the baseline parameters as the initial conditions and without parameter deviation: the initial penetration moment is set to a fixed value, and the changes in state parameters during the game of the aircraft are obtained to obtain the initial distance between the two parties and the overload of the interceptor missile. , the launch angles of both sides are used as the reference for the initial deviation amount; Step 3-2: Taking the conclusion and angle limit in step 3-1 as the initial conditions, conduct a simulation under the condition of random deviation of multiple parameters: build an offensive and defensive confrontation database by simulating multiple maneuver penetrations under different initial conditions, and traverse The initial situation information and possible maneuvering strategies of the interceptor provide training and verification data for subsequent offline learning of the database through neural networks. 4. A method for designing a maneuvering penetration strategy for hypersonic aircraft based on timing games according to claim 3, characterized in that the BP neural network described in step 4 is provided with two hidden layers and tansig is selected for activation. function; Table 1 Neural network parameter settings The specific parameter settings of the neural network are shown in Table 1.