CN117171877A - Hypersonic aircraft maneuver burst prevention strategy design method based on opportunity game - Google Patents
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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
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a hypersonic aircraft maneuvering sudden-prevention strategy design method.
Background
In the short-distance burst prevention process of the hypersonic aircraft, the hypersonic aircraft is constrained by the self-maneuvering ability and the uncertainty of the interception bullet maneuvering ability and the guidance law, so that great difficulty is caused to effective burst prevention in short-distance time, and therefore, how to utilize the maneuver initiative and the high-speed characteristic of an attack party and to provide an intelligent maneuver burst prevention strategy of the hypersonic aircraft by combining an intelligent learning method, thereby realizing successful burst prevention of the hypersonic aircraft under the constraint and uncertain scene is a key scientific problem to be solved.
The method is characterized in that the current situation of relevant research at home and abroad is integrated, the sudden prevention problem of the hypersonic aircraft is concentrated on a program maneuver sudden prevention strategy, and the sudden prevention guidance law based on the unilateral optimal theory and the sudden prevention guidance law based on differential countermeasures are mainly researched in the aspect of game maneuver sudden prevention. The hypersonic aircraft maneuver defense strategy deduced by the two methods introduces the single/double extreme value problem of mathematical functional functions into an attack defense countermeasure model of the hypersonic aircraft and the reverse-guiding interceptor, sets the defense aircraft and the interceptor as two game parties, adds terminal constraints such as reentry point positions, speeds and the like, maneuver overload and control variable constraints, takes the off-target quantity of the terminal and the like as performance indexes, combines the motion models of the defense aircraft and the interceptor to construct a Hamilton function, and solves the optimal defense and interception strategy by the necessary condition of the extreme value. The sudden prevention guidance law based on the unilateral optimal theory needs to assume the guidance law of the enemy interception bullet in advance, so that the guidance information of the enemy in the real attack-prevention countermeasure scene is difficult to acquire, and a certain difficulty is caused to engineering realization; the defending and bursting guidance law based on differential countermeasures assumes that both the attacking and the defending adopt the optimal maneuvering strategy at the same time, the designed defending and bursting guidance law is relatively conservative, and the defending and bursting capability of the hypersonic aircraft cannot be fully exerted. The combination of the intelligent method and the defense-against strategy makes a certain progress in the fight scenes of unmanned aerial vehicles, cruise missiles and the like, but the existing intelligent maneuver defense-against strategies for the fight scenes of the unmanned aerial vehicles, the cruise missiles and the like are not applicable in consideration of the characteristics of high dynamic time-varying properties of the fight scenes of hypersonic aircrafts and the like.
Considering the engineering realization of the defense strategy, in a real attack and defense countermeasure scene, the problems of information acquisition delay, poor information accuracy and the like often exist.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a hypersonic aircraft maneuvering burst prevention strategy design method based on an opportunity game, which is characterized in that firstly, a burst prevention strategy based on a burst prevention window is provided based on the analysis of the advantages and disadvantages of the hypersonic aircraft in the short-distance 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.
The technical scheme adopted by the invention for solving the technical problems comprises the following steps:
step 1: based on the analysis of the merits and merits of hypersonic aircrafts in the short-distance countermeasure, the fight concept of the burst prevention window is provided;
the burst prevention window is a relative distance interval for realizing burst prevention of the intercepted missile by the hypersonic aircraft through full overload maneuver; the near range refers to the detection range of the hypersonic aircraft;
step 2: establishing an attack and defense countermeasure mathematical model under an approximate reverse rail interception situation in a transverse lateral plane;
step 3: utilizing Monte Carlo simulation to traverse different fight situations, dynamic strategies and mechanical capacities in engineering application to generate a game countermeasure database;
step 4: and (3) offline learning is carried out on the game countermeasure database generated in the step (3) based on the BP neural network.
Further, the step 2 specifically includes:
the approximate reverse rail interception situation refers to a specific angle range, and when the initial speed pointing deviation of the hypersonic aircraft and the interception bomb is larger than or equal to the angle range, the hypersonic aircraft can finish the abrupt defense by utilizing the self speed without performing the maneuvering abrupt defense; when the initial speed pointing deviation of the two parties is smaller than the angle range, maneuver burst prevention is needed;
the mathematical description of the interceptor spring at the terminal guidance section is as follows:
wherein V is m (t) represents an intercept bullet motion velocity vector; gamma ray m Representing the ballistic deflection of the interceptor projectile; n is n zm Indicating the actual flight overload of the interceptor projectile; g represents gravitational acceleration;representing a velocity component of the interceptor spring on the x-axis; />Representing a velocity component of the interceptor spring in the z-axis; />The method is used for intercepting bullet guidance rules in engineering practice, and comprises a proportion guidance rule PN, a corrected proportion guidance rule APN and self-adaptionSliding mode guidance law ASMG; the three interceptor spring disciplines in the lateral plane are expressed as follows:
proportional guidance law:
correction ratio guidance law:
self-adaptive sliding mode guidance law:
wherein:is the angular velocity of the line of sight from the point of view of the interceptor projectile; v (V) c The approach speed is the approach speed of both attack and defense; n, epsilon and delta are guidance law parameters; a, a h Representing the actual acceleration of the hypersonic aircraft in flight, the correction term ensuring that the interceptor bomb takes overload compensation measures when the target makes a constant maneuver; u (u) m Indicating the commanded acceleration using different pilot laws to intercept the projectile; />Representing an azimuthal velocity from the view of the interceptor projectile;
meanwhile, the intercepting bullet adopts an STT control mode in the whole intercepting process, and the intercepting bullet is limited by the maximum available overload constraint n zmmax Expressed as:
|n zm |≤n zmmax
for hypersonic aircraft, it is described in detail as follows:
wherein V is h (t) represents hypersonic aircraft motion velocity vector, gamma h Representing the ballistic deflection angle, τ, of a hypersonic aircraft h Representing a first-order link time constant, n, of a hypersonic aircraft zhc Indicating overload command of hypersonic aircraft, n zh Indicating an actual flight overload of the hypersonic aircraft,representing the velocity component of a hypersonic vehicle in the x-axis,/for>Representing a velocity component of the hypersonic vehicle in the z-axis;
the hypersonic aircraft is constrained by:
n zh ≤n zhmax
according to the existing simulation result, the angle range of the approximate reverse track interception situation is set to be +/-3.2 degrees, namely:
|γ h0 -γ m0 +π|<3.2°
wherein n is zhmax Representing a maximum usable overload of the hypersonic aircraft; gamma ray h0 ,γ m0 The initial moment is the ballistic deflection angle of the hypersonic aircraft and the interception bomb respectively.
Preferably, the step 3 specifically comprises the following steps:
step 3-1: taking the reference parameter as an initial condition, and simulating under the condition of not carrying out parameter bias: the initial burst prevention moment takes a fixed value, and state parameter changes in the game process of the aircraft are obtained, so that the initial distance between two subsequent parties, the overload of the interception bomb and the emission angle between the two parties are obtained as initial deflection pulling quantity reference quantity;
step 3-2: taking the conclusion and the angle limitation in the step 3-1 as initial conditions, and carrying out simulation under the condition of random bias of a plurality of parameters: constructing an attack and defense countermeasure database by simulating multiple maneuver defense under different initial conditions, traversing initial situation information and maneuver strategies possibly adopted by interceptors, and providing training and verification data for the follow-up offline learning of the database through a neural network.
Preferably, the BP neural network in the step 4 is provided with two hidden layers and selects a tan sig activation function, and specific parameter settings of the neural network are shown in the following table:
table 1 neural network parameter settings
The beneficial effects of the invention are as follows:
the invention provides a design method of a hypersonic aircraft defense strategy under the condition of delay and inaccuracy of information acquisition in a real attack and defense countermeasure scene based on active game maneuvering. There are two types of advantages. Firstly, compared with optimal control and differential countermeasures, the own maneuvering strategy mainly depends on self short-distance early warning capability and maneuvering capability, does not depend on the assumption of the interception bullet guidance law, has small uncertainty, and is easy for engineering realization. Secondly, the designed anti-burst strategy has simple self-maneuvering instruction form, does not need complex calculation, has no real-time and other barriers, and is easy for engineering realization.
Drawings
FIG. 1 is a flowchart of the hypersonic aircraft burst prevention window calculation of the present invention.
Fig. 2 is a conceptual diagram of a hypersonic vehicle burst prevention window according to the present invention, wherein (a) the hypersonic vehicle maneuvers within the burst prevention window, (b) the hypersonic vehicle maneuvers too early outside the burst prevention window, and (c) the hypersonic vehicle maneuvers too late outside the burst prevention window.
FIG. 3 is a schematic diagram of an approximate backtrack intercept situation of the present invention.
Fig. 4 is a schematic diagram of attack and defense countermeasures in a lateral-to-lateral plane similar to a countertrack interception situation.
Fig. 5 is a schematic diagram of a monte carlo simulation of a "burst prevention window" without bias in an embodiment of the present invention, (a) the guidance law of the intercepted charges is a proportional guidance law, (b) the guidance law of the intercepted charges is a modified proportional guidance law, and (c) the guidance law of the intercepted charges is a self-adaptive sliding mode guidance law.
Fig. 6 is a schematic diagram of a monte carlo simulation of a "burst prevention window" under a random bias condition in an embodiment of the present invention, (a) the guidance law of the intercepted charges is a proportional guidance law, (b) the guidance law of the intercepted charges is a modified proportional guidance law, and (c) the guidance law of the intercepted charges is a self-adaptive sliding mode guidance law.
Fig. 7 shows the fitting effect of the neural network of the "burst prevention window" when the minimum error of the training target is 0.001, (a) the intercepted bullet guidance law is a proportional guidance law, (b) the intercepted bullet guidance law is a modified proportional guidance law, and (c) the intercepted bullet guidance law is a self-adaptive sliding mode guidance law.
Detailed Description
The invention will be further described with reference to the drawings and examples.
In order to solve the problem that the robustness of the conventional defense strategy designed based on the classical method and the intelligent method is poor in a real attack and defense countermeasure scene, the advantages of the neural network, such as no dependence on an explicit mathematical model, fitting of a complex nonlinear mapping relation, and fitting of the neural network through a hypersonic aircraft full overload maneuvering section can be achieved, successful defense against enemy interception bullets can be achieved, and meanwhile robustness of the defense strategy to information delay and poor accuracy can be enhanced.
The technical scheme of the invention is as follows:
step 1, based on the analysis of the merits of hypersonic aircrafts in short-range countermeasure, the concept of a sudden defense window is provided.
As shown in fig. 2, the "burst window" refers to a relative distance interval in which the hypersonic vehicle can achieve burst of an intercepted missile by full-overload maneuver. When the interception bomb forms an approximate reverse rail interception situation for the movable orbit transfer aircraft, the speed advantage of the movable orbit transfer aircraft in the outburst prevention process can not be fully exerted, the main advantage is that the maneuvering initiative as an attack party and the off-target quantity required by successful outburst prevention are smaller, and the disadvantage is that the overload capacity is far weaker than that of the interception bomb. Thus, when maneuvers are too early, interception can occur due to longer exposure times of overload disadvantages; conversely, if the maneuver is too late, the desired off-target amount cannot be achieved laterally. If and only if the sudden defense maneuver is carried out in the sudden defense window, the initiative of the sudden defense maneuver can be fully utilized, the approach speed of both parties is combined, more than 1m off-target quantity required by the sudden defense is created in a short time, meanwhile, the overload disadvantage of the own party is avoided as much as possible, and the effective sudden defense of the interception bomb is completed in a small range.
And 2, establishing an attack and defense countermeasure mathematical model under the approximate reverse rail interception situation in the transverse and lateral planes.
The maneuver of the hypersonic aircraft can be divided into longitudinal maneuver and transverse maneuver according to the maneuver proceeding direction, and the two maneuvers can exist independently or simultaneously. The invention preferably completes burst prevention through lateral maneuver, because: the transverse lateral maneuver burst prevention can be performed under the condition of fixed altitude and fixed speed of the aircraft, so that the influence on a controller due to the change of speed and altitude in the burst prevention process is avoided.
As shown in fig. 3, the approximate reverse rail interception situation refers to a specific angle range, and when the initial speed pointing deviation of the hypersonic aircraft and the interception bomb is larger than the angle range, the hypersonic aircraft does not need to maneuver and burst, and burst can be completed by utilizing the self speed; when the initial speed direction deviation of both sides is smaller than the angle range, the maneuver burst prevention is needed.
And 3, based on the concept of a 'burst prevention window', utilizing Monte Carlo simulation to traverse different combat situations, friend or foe maneuver strategies, maneuverability and the like in engineering application as much as possible, and generating a game countermeasure database.
And 4, performing offline learning on the database based on the BP neural network.
In a new attack and defense countermeasure scene, situation parameters, aircraft capability parameters, a friend maneuver strategy and the like are taken as inputs, wherein a plurality of groups of values can be selected from unknown parameters within a boundary range, a plurality of windows are generated, a reliable result can be obtained through offline training, an attack and defense maneuver window (a common interval of the plurality of windows) is output on line, and the movable orbit-changing aircraft can finish small-range efficient attack and defense on the interception bomb by virtue of a custom maneuver strategy in the window. The calculation flow of the anti-burst window is shown in figure 1.
Examples:
step 1, establishing an attack and defense countermeasure mathematical model under an approximate reverse rail interception situation in a transverse and lateral plane.
When a single interception bomb exists, the schematic diagram of attack and defense countermeasure of the transverse and lateral planes and the definition of the related angles are shown in fig. 4. Wherein H is a hypersonic aircraft, and M is an interception bomb. In fig. 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 aircraft parameter name controls for both the offender and the defensive
In the table: i=h, m. h represents a hypersonic aircraft and m represents an interceptor bomb. Azimuth angle lambda of line of sight hm Defined as pointing from the interceptor bomb towards the hypersonic aircraft, lambda in figure 4 hm <0。
By combining the two-dimensional plane attack and defense countermeasure form shown in fig. 4, the mathematical description of the interceptor bomb in the terminal guidance section can be constructed as follows:
in the method, in the process of the invention,typical interception bullet guidance laws in engineering practice include a proportional guidance law (Proportional Navigation, PN), a modified proportional guidance law (Augmented Proportional Navigation, APN), an adaptive sliding mode guidance law (Adaptive Sliding Mode Guidance, ASMG) and the like. These 3 interceptor spring disciplines in the lateral plane can be expressed as follows:
proportional guidance law:
correction ratio guidance law:
self-adaptive sliding mode guidance law:
wherein:is the angular velocity of the line of sight from the point of view of the interceptor projectile; v (V) c The approach speed is the approach speed of both attack and defense; n, ε, and δ are guidance law parameters.
Meanwhile, the intercepting bullet adopts an STT control mode in the whole intercepting process, and the intercepting bullet is limited to be only maximally available
Overload constraints, expressed as:
|n zm |≤n zmmax
for hypersonic aircraft, it is described in detail as follows:
the hypersonic aircraft is constrained by:
n zh ≤n zhmax
according to the existing simulation result, the angle range of the approximate reverse track interception situation is set to be +/-3.2 degrees, namely:
|γ h0 -γ m0 +π|<3.2°
wherein, gamma h0 ,γ m0 The initial moments are the ballistic deflection angles of the hypersonic aircraft and the interception bomb respectively.
And 2, based on the concept of a 'burst prevention window', utilizing Monte Carlo simulation to traverse different combat situations, friend or foe maneuver strategies, maneuverability and the like in engineering application as much as possible, and generating a game countermeasure database. Which comprises the following substeps.
Step 2.1, taking the reference parameter as an initial condition, and simulating under the condition of not carrying out parameter bias: and the initial burst prevention moment is a fixed value, and the state parameter change in the game process of the aircraft is acquired, so that initial deflection pulling reference quantities such as the initial distance between two subsequent parties, overload of the interception bomb, the emission angle between the two parties and the like are acquired.
TABLE 2 Motor burst control method simulation related parameter settings based on the "burst control Window" concept
When the interception bomb adopts a proportional guiding law, a corrected proportional guiding law and a self-adaptive sliding mode guiding law respectively, the attack and defense countermeasure situation of the hypersonic aircraft and the interception bomb is shown in figure 5.
Step 2.2, taking the conclusion and the angle limitation in the step 2.1 as initial conditions, and carrying out simulation under the condition of random bias of a plurality of parameters: constructing an attack and defense countermeasure database by simulating multiple maneuver defense under different initial conditions, traversing initial situation information and maneuver strategies possibly adopted by interceptors, and providing training and verification data for the follow-up offline learning of the database through a neural network.
Table 3 related bias parameter settings
The results of the Monte Carlo simulation are shown in FIG. 6.
And 3, using 500 groups of 'anti-burst window' data obtained by the random bias drawing parameters in the step 2.2 as a training set, fitting by using a BP neural network, setting two hidden layers on the network, and selecting a tan sig activation function. And after the parameters are adjusted through multiple training, the network with the best result is reserved for subsequent testing.
Table 4 neural network parameter settings
The "burst prevention window" neural network fitting results are shown in fig. 7.
Finally, the trained neural network can be used to predict hypersonic aircraft maneuver "burst window" conditions given the initial conditions. Assume that the initial state of the enemy intercept bullet is as follows: initial relative distance r0=11 km, ballistic deflection angle γ m0 =181°, maximum available overload u mmax ＝7g；
1) When the enemy interception bullet guidance law adopts the proportional guidance law, the upper bound of the actual "burst prevention window" of the hypersonic aircraft is 10km, the lower bound is 1.3km, the window prediction is carried out by adopting the finally trained BP neural network, the upper bound of the predicted "burst prevention window" is 9.99km, the lower bound is 1.33km, and the errors are 0.01 and 0.03 respectively.
2) When the correction ratio guidance law is adopted by the enemy interception bullet guidance law, the upper bound of an actual "burst prevention window" of the hypersonic aircraft is 5.3km, the lower bound is 1..4km, the window prediction is carried out by adopting a finally trained BP neural network, the upper bound of the predicted "burst prevention window" is 5.215km, the lower bound of the "burst prevention window" is 1.422km, and the errors are respectively 0.085 and 0.022.
3) When the self-adaptive sliding mode guidance law is adopted by the enemy interception bullet guidance law, the upper boundary of an actual "burst prevention window" of the hypersonic aircraft is 8.1km, the lower boundary is 1.4km, the window prediction is carried out by adopting a finally trained BP neural network, the upper boundary of the predicted "burst prevention window" is 8.175km, the lower boundary of the "burst prevention window" is 1.475km, and the errors are respectively 0.075 and 0.075.
And combining the three 'sudden-prevention windows' calculated by adopting different guidance laws for the enemy-intercepting bullet, and finally obtaining that the public 'sudden-prevention window' is delta R= [1.475,5.215], and the hypersonic aircraft performs full overload maneuver in the interval, so that the enemy-intercepting bullet can be successfully sudden-prevented.
Conclusion: based on the analysis of the merits of hypersonic aircrafts in the near countermeasure, the invention provides the fight concept of a sudden defense window; constructing an attack-defense countermeasure database, traversing initial situation information and maneuver strategies possibly adopted by an interceptor, performing offline learning on the database through a BP neural network, and performing online calculation to generate an 'attack-defense window' to guide the hypersonic aircraft to finish the attack defense on 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 'sudden-prevention window'. The design concept of the public 'anti-burst window' avoids subjective estimation of uncertain information, so that the designed anti-burst strategy has universality and robustness.
Claims (4)
1. The hypersonic aircraft maneuver burst prevention strategy design method based on the opportunity game is characterized by comprising the following steps of:
step 1: based on the analysis of the merits and merits of hypersonic aircrafts in the short-distance countermeasure, the fight concept of the burst prevention window is provided;
the burst prevention window is a relative distance interval for realizing burst prevention of the intercepted missile by the hypersonic aircraft through full overload maneuver; the near range refers to the detection range of the hypersonic aircraft;
step 2: establishing an attack and defense countermeasure mathematical model under an approximate reverse rail interception situation in a transverse lateral plane;
step 3: utilizing Monte Carlo simulation to traverse different fight situations, dynamic strategies and mechanical capacities in engineering application to generate a game countermeasure database;
step 4: and (3) offline learning is carried out on the game countermeasure database generated in the step (3) based on the BP neural network.
2. The hypersonic aircraft maneuver burst prevention strategy design method based on the opportunity game according to claim 1, wherein the step 2 is specifically:
the approximate reverse rail interception situation refers to a specific angle range, and when the initial speed pointing deviation of the hypersonic aircraft and the interception bomb is larger than or equal to the angle range, the hypersonic aircraft can finish the abrupt defense by utilizing the self speed without performing the maneuvering abrupt defense; when the initial speed pointing deviation of the two parties is smaller than the angle range, maneuver burst prevention is needed;
the mathematical description of the interceptor spring at the terminal guidance section is as follows:
wherein V is m (t) represents an intercept bullet motion velocity vector; gamma ray m Representing the ballistic deflection of the interceptor projectile; n is n zm Indicating the actual flight overload of the interceptor projectile; g represents gravitational acceleration;representing a velocity component of the interceptor spring on the x-axis; />Representing a velocity component of the interceptor spring in the z-axis; />The method is an interception bullet guidance law in engineering practice, and comprises a proportion guidance law PN, a corrected proportion guidance law APN and a self-adaptive sliding mode guidance law ASMG; the three interceptor spring disciplines in the lateral plane are expressed as follows:
proportional guidance law:
correction ratio guidance law:
self-adaptive sliding mode guidance law:
wherein:is the angular velocity of the line of sight from the point of view of the interceptor projectile; v (V) c The approach speed is the approach speed of both attack and defense; n, epsilon and delta are guidance law parameters; a, a h Representing the actual acceleration of the hypersonic aircraft in flight, the correction term ensuring that the interceptor bomb takes overload compensation measures when the target makes a constant maneuver; u (u) m Indicating the commanded acceleration using different pilot laws to intercept the projectile; />Representing an azimuthal velocity from the view of the interceptor projectile;
meanwhile, the intercepting bullet adopts an STT control mode in the whole intercepting process, and the intercepting bullet is limited by the maximum available overload constraint n zm max Expressed as:
|n zm |≤n zm max
for hypersonic aircraft, it is described in detail as follows:
wherein V is h (t) represents hypersonic aircraft motion velocity vector, gamma h Representing the ballistic deflection angle, τ, of a hypersonic aircraft h Representing a first-order link time constant, n, of a hypersonic aircraft zhc Indicating overload command of hypersonic aircraft, n zh Indicating an actual flight overload of the hypersonic aircraft,representing the velocity component of a hypersonic vehicle in the x-axis,/for>Representing a velocity component of the hypersonic vehicle in the z-axis;
the hypersonic aircraft is constrained by:
n zh ≤n zh max
according to the existing simulation result, the angle range of the approximate reverse track interception situation is set to be +/-3.2 degrees, namely:
|γ h0 -γ m0 +π|<3.2°
wherein n is zh max Representing a maximum usable overload of the hypersonic aircraft; gamma ray h0 ,γ m0 The initial moment is the ballistic deflection angle of the hypersonic aircraft and the interception bomb respectively.
3. The hypersonic aircraft maneuver anti-collision strategy design method based on the opportunity game as claimed in claim 2, wherein the step 3 is specifically as follows:
step 3-1: taking the reference parameter as an initial condition, and simulating under the condition of not carrying out parameter bias: the initial burst prevention moment takes a fixed value, and state parameter changes in the game process of the aircraft are obtained, so that the initial distance between two subsequent parties, the overload of the interception bomb and the emission angle between the two parties are obtained as initial deflection pulling quantity reference quantity;
step 3-2: taking the conclusion and the angle limitation in the step 3-1 as initial conditions, and carrying out simulation under the condition of random bias of a plurality of parameters: constructing an attack and defense countermeasure database by simulating multiple maneuver defense under different initial conditions, traversing initial situation information and maneuver strategies possibly adopted by interceptors, and providing training and verification data for the follow-up offline learning of the database through a neural network.
4. The hypersonic aircraft maneuver anti-collision strategy design method based on the opportunity game according to claim 3, wherein the BP neural network in the step 4 is provided with two hidden layers and selects a tan sig activation function;
table 1 neural network parameter settings
The specific parameter settings of the neural network are shown in table 1.
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| CN117852309A (en) * | 2024-03-06 | 2024-04-09 | 西北工业大学 | Index layering-based anti-burst performance evaluation method |
| CN117852415A (en) * | 2024-03-07 | 2024-04-09 | 西北工业大学 | Method and device for solving maneuvering space of ultra-high-speed aircraft based on variable stepping withdrawal method |
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| CN117852309A (en) * | 2024-03-06 | 2024-04-09 | 西北工业大学 | Index layering-based anti-burst performance evaluation method |
| CN117852309B (en) * | 2024-03-06 | 2024-05-24 | 西北工业大学 | Index layering-based anti-burst performance evaluation method |
| CN117852415A (en) * | 2024-03-07 | 2024-04-09 | 西北工业大学 | Method and device for solving maneuvering space of ultra-high-speed aircraft based on variable stepping withdrawal method |
| CN117852415B (en) * | 2024-03-07 | 2024-05-24 | 西北工业大学 | Method and device for solving maneuvering space of ultra-high-speed aircraft based on variable stepping withdrawal method |
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