Method for online prediction guidance of near-hypersonic target gliding maneuver interception and electronic device

Abstract

The application discloses a near-hypersonic target gliding maneuver interception online prediction guidance method and electronic equipment, and comprises the following steps: in the first step, a non-cooperative near-hypersonic target is simplified into an isohypse uniform-speed flat flight or an isohypse uniform-deceleration flat flight analytic trajectory according to a power form; in the second step, a predicted interception point is selected based on the target analytic predicted trajectory, and a star-down point projection velocity and relative distance information of the interception aircraft are used as main analytic parameters; in the third step, a flight attack angle sequence of the interception aircraft is solved by using a difference value online based on the predicted interception point selection result, an instant drag overload requirement and an aerodynamic parameter database of the intersection aircraft; and in the fourth step, a flight direction azimuth is selected based on the predicted interception point and the intersection projection in the instant shooting plane direction of the interception aircraft, and a velocity roll angle is solved online. The near-space gliding weapon is used to realize online rapid prediction guidance for the hypersonic target interception.

Description

Technical Field

[0001] This invention belongs to the field of ballistic guidance design for near-space vehicles, and relates to an online predictive guidance method and electronic equipment for intercepting glide maneuvers of near-hypersonic targets. Background Technology

[0002] In recent years, with the continuous emergence of near-space hypersonic vehicles, interception technology for near-hypersonic targets has also developed rapidly.

[0003] Hypersonic targets in near space fly at high speeds and possess strong maneuverability, making traditional defense and interception methods technically challenging. Therefore, employing near-space hypersonic gliders to achieve rapid rendezvous and interception of hypersonic targets at comparable speeds in near space has become an important approach.

[0004] Near-space hypersonic targets fly at high speeds and can perform long-duration, wide-range maneuvers using aerodynamic forces. If they are non-cooperative targets, their motion state and maneuvering strategies are unknown, making it impossible to obtain accurate trajectory predictions. During their flight, they are affected by complex mechanical environments, including gravity, lift, and drag, resulting in complex dynamic models. Unlike atmospheric rendezvous, which can simplify dynamic models to achieve online real-time interception and guidance command calculations, these models are not readily available.

[0005] Therefore, a novel online predictive guidance algorithm is needed for intercepting hypersonic targets undergoing gliding maneuvers. This algorithm would enable online trajectory prediction on the missile's onboard computer and generate online guidance trajectories for rendezvous vehicles. The algorithm must meet the limitations of the missile's onboard computer. Summary of the Invention

[0006] The technical problem solved by this invention is to overcome the shortcomings of the prior art, provide an online predictive guidance method and electronic equipment for intercepting glide maneuvers of hypersonic targets in near space, realize online rapid guidance for intercepting glide maneuvers of near space, and create the best initial conditions for optical detection of rendezvous vehicles in the terminal guidance phase.

[0007] The technical solution of this invention is:

[0008] This invention discloses an online predictive guidance method for intercepting glide maneuvers of hypersonic targets in close proximity, characterized by comprising:

[0009] Step 1: Based on the target's current flight trajectory and the assumption of balanced gliding flight, calculate the target's predicted flight trajectory using a target trajectory prediction analytical algorithm.

[0010] Step 2: Select the predicted hit point on the target's predicted flight trajectory;

[0011] Step 3: Based on the position and speed information of the intercepting weapon, determine whether the predicted hit point meets the requirements using a prediction and analysis algorithm; if not, modify the predicted hit point and return to step 2; if yes, proceed to step 4.

[0012] Step 4: Based on the selection of the predicted hit point, solve the flight drag constraint of the interceptor weapon, calculate the angle of attack difference, and obtain the flight angle of attack of the interceptor weapon;

[0013] Step 5: Calculate the interceptor weapon's velocity tilt angle based on the interceptor weapon's flight angle and the total lift required for its balanced flight. By determining the projection information of the target position onto the interceptor weapon's velocity system, calculate the positive and negative values ​​of the interceptor weapon's velocity tilt angle.

[0014] Step 6: Based on the interceptor weapon's flight angle of attack and velocity tilt angle, perform ballistic integration using the dynamic model, calculate acceleration, and solve for relative distance in real time;

[0015] Step 7: Determine whether the relative distance is less than or equal to the terminal guidance constraint index. If yes, end the calculation and successfully switch to terminal guidance; otherwise, repeat steps 1 to 6.

[0016] In the above guidance method, step 1 involves calculating the target's predicted flight trajectory based on the target's current flight trajectory and the assumption of balanced gliding flight, using a target trajectory prediction analytical algorithm. The specific method is as follows:

[0017]

[0018]

[0019] Where: R l0 v l0 For the current interception weapon position and speed information, R l (t), v l (t) represents the position and velocity information of the interceptor weapon at time t, μ is the Earth's gravitational coefficient, and R l0 This represents the distance between the Earth's center and the Earth's core at the current moment.

[0020] In the above guidance method, step 2, selecting the predicted hit point on the target predicted trajectory, specifically involves:

[0021] If this is the first selection, then ts(t) = t0; where t0 is the earliest interceptable time; ts(t) is the predicted hit point at time t;

[0022] Otherwise, ts(t) = ts(t-1) + Δts; where Δts is the step size for calculating the predicted hit point; ts(t-1) is the predicted hit point at time t-1.

[0023] In the above guidance method, step 3 involves determining whether the predicted hit point meets the requirements based on the interceptor weapon's position and velocity information using a predictive analysis algorithm. The specific method is as follows:

[0024] Based on the predicted hit point location, time information, and the current location and speed information of the interceptor weapon; with the speed and dynamic pressure at the mid-to-late shift handover position as constraints, the average speed information and average drag acceleration information of the interceptor weapon required for the aircraft to reach the predicted hit point are calculated; if the average speed of the interceptor weapon is greater than the speed at the current moment, and the average drag acceleration is greater than the aircraft's capability range, then the predicted hit point cannot meet the requirements.

[0025] In the above guidance method, step 4 involves solving the drag constraint based on the predicted hit point selection, calculating the angle of attack difference, and obtaining the interceptor weapon's angle of attack. Specifically:

[0026]

[0027] Where: α 需求 For the required interception angle of attack, Cx 需求 Cx is the drag coefficient calculated based on drag requirements. 需求-1 Cx 需求+1 These represent the larger and smaller drag coefficient values ​​in the aerodynamic parameter table, α. 需求-1 α 需求+1 , which represent the corresponding angles of attack.

[0028] In the above guidance method, step 5 involves calculating the interceptor weapon's velocity roll angle based on the interceptor weapon's flight angle of attack and the total lift required for its balanced flight. The specific method is as follows:

[0029]

[0030] Where: β is the velocity tilt angle, a z This represents the total lift of the aircraft. The total lift is projected laterally.

[0031] In the above guidance method, step 6, calculating the acceleration, specifically involves:

[0032] g = g r r+g ωe ω e

[0033] Where g is acceleration and r is the distance from the Earth's center; g we To intercept the creolic acceleration of the weapon, g r For the entrainment acceleration, ω e This is the Earth's rotational angular velocity.

[0034] In the above guidance method, the Creool acceleration and entrainment acceleration of the interceptor weapon are specifically as follows:

[0035]

[0036] Among them, g we To intercept the creolic acceleration of the weapon, g r For the entrainment acceleration, μ e Where J is the Earth's gravitational coefficient and J is the Earth's oblateness term; a e Φ is the semi-major axis of the Earth's ellipsoid, and Φ is the geocentric latitude.

[0037] In the above guidance method, step 6 involves performing ballistic integration based on the interceptor weapon's angle of attack and velocity tilt angle, combined with a dynamic model, to obtain the position and velocity information at the next time point, and calculating the relative distance in real time. The specific method is as follows:

[0038]

[0039] Among them, Rx 目标 Ry 目标 、Rz 目标 For target location information, Rx 拦截 Ry 拦截 、Rz 拦截 H represents the relative distance, used to intercept weapon location information.

[0040] This invention discloses an electronic device, including a memory and a processor.

[0041] The memory is used to store one or more computer instructions;

[0042] The processor is configured to execute one or more computer instructions to perform the following steps:

[0043] Step S1: Based on the target's current flight trajectory and the assumption of balanced gliding flight, calculate the target's predicted flight trajectory using a target trajectory prediction analytical algorithm.

[0044] Step S2: Select the predicted hit point on the predicted flight trajectory of the target;

[0045] Step S3: Based on the position and speed information of the intercepting weapon, determine whether the predicted hit point meets the requirements using a prediction and analysis algorithm; if not, modify the predicted hit point and return to step S2; if yes, proceed to step S4.

[0046] Step S4: Based on the selection of the predicted hit point, solve the flight drag constraint of the interceptor weapon, perform angle of attack difference calculation, and obtain the flight angle of attack of the interceptor weapon;

[0047] Step S5: Calculate the interceptor weapon's velocity tilt angle based on the interceptor weapon's flight angle of attack and the total lift required for the interceptor weapon's balanced flight. By determining the projection information of the target position in the interceptor weapon's velocity system, calculate the positive and negative values ​​of the interceptor weapon's velocity tilt angle.

[0048] Step S6: Based on the interceptor weapon's flight angle of attack and velocity tilt angle, perform ballistic integration using the dynamic model, calculate acceleration, and solve for relative distance in real time;

[0049] Step S7: Determine whether the relative distance is less than or equal to the terminal guidance constraint index. If yes, end the calculation and successfully switch to terminal guidance; otherwise, repeat steps S1 to S6.

[0050] The advantages of this invention compared to the prior art are:

[0051] (1) This invention realizes online rapid guidance for intercepting hypersonic targets using near-space hypersonic glide weapons, and has the capability for onboard computation.

[0052] (2) The online predictive guidance algorithm of this invention meets the requirements for the zero-control towed target quantity in the mid-to-terminal guidance phase, creating conditions for aircraft interception and countermeasures and guidance control in the terminal guidance phase.

[0053] (3) The online predictive guidance algorithm of the present invention simultaneously meets the requirements of terminal guidance velocity and dynamic pressure constraint, creating ideal conditions for terminal guidance detection, etc. Attached image description:

[0054] Figure 1 This is the implementation process of an online predictive guidance method for intercepting glide maneuvers of hypersonic targets near the target, as described in this invention.

[0055] Figure 2 This invention relates to a target trajectory analysis and prediction method;

[0056] Figure 3 This is the design sequence for the angle of attack of the interceptor aircraft of the present invention;

[0057] Figure 4 This is the design sequence for the velocity tilt angle of the present invention;

[0058] Figure 5 This describes the implementation of the trajectory and velocity constraints for the interceptor aircraft according to the present invention.

[0059] Figure 6 These are the simulation results of the present invention;

[0060] Figure 7 This is the basic simulation scenario of the present invention. Detailed Implementation

[0061] The working principle and process of the present invention will be further explained and described below with reference to the accompanying drawings.

[0062] This invention discloses an online predictive guidance method for intercepting glide maneuvers of hypersonic targets in close proximity, characterized by comprising:

[0063] Step 1: Based on the target's current flight trajectory and the assumption of balanced gliding flight, calculate the target's predicted flight trajectory using a target trajectory prediction analytical algorithm.

[0064] Step 2: Select the predicted hit point on the target's predicted flight trajectory;

[0065] Step 3: Based on the position and speed information of the intercepting weapon, determine whether the predicted hit point meets the requirements using a prediction and analysis algorithm; if not, modify the predicted hit point and return to step 2; if yes, proceed to step 4.

[0066] Step 4: Based on the selection of the predicted hit point, solve the flight drag constraint of the interceptor weapon, calculate the angle of attack difference, and obtain the flight angle of attack of the interceptor weapon;

[0067] Step 5: Calculate the interceptor weapon's velocity tilt angle based on the interceptor weapon's flight angle and the total lift required for its balanced flight. By determining the projection information of the target position onto the interceptor weapon's velocity system, calculate the positive and negative values ​​of the interceptor weapon's velocity tilt angle.

[0068] Step 6: Based on the interceptor weapon's flight angle of attack and velocity tilt angle, perform ballistic integration using the dynamic model, calculate acceleration, and solve for relative distance in real time;

[0069] Step 7: Determine whether the relative distance is less than or equal to the terminal guidance constraint index. If yes, end the calculation and successfully switch to terminal guidance; otherwise, repeat steps 1 to 6.

[0070] In step 1, based on the target's current flight trajectory and the assumption of balanced gliding flight, the target's predicted flight trajectory is calculated using a target trajectory prediction analytical algorithm. The specific method is as follows:

[0071]

[0072]

[0073] Where: R l0 v l0 For the current interception weapon position and speed information, R l (t), v l (t) represents the position and velocity information of the interceptor weapon at time t, μ is the Earth's gravitational coefficient, and R l0 This represents the distance between the Earth's center and the Earth's core at the current moment.

[0074] In step 2, the predicted hit point is selected on the target predicted trajectory, specifically as follows:

[0075] If this is the first selection, then ts(t) = t0; where t0 is the earliest interceptable time; ts(t) is the predicted hit point at time t;

[0076] Otherwise, ts(t) = ts(t-1) + Δts; where Δts is the step size for calculating the predicted hit point; ts(t-1) is the predicted hit point at time t-1.

[0077] In step 3, based on the position and velocity information of the intercepting weapon, a predictive analysis algorithm is used to determine whether the predicted hit point meets the requirements. The specific method is as follows:

[0078] Based on the predicted hit point location, time information, and the current location and speed information of the interceptor weapon; with the speed and dynamic pressure at the mid-to-late shift handover position as constraints, the average speed information and average drag acceleration information of the interceptor weapon required for the aircraft to reach the predicted hit point are calculated; if the average speed of the interceptor weapon is greater than the speed at the current moment, and the average drag acceleration is greater than the aircraft's capability range, then the predicted hit point cannot meet the requirements.

[0079] In step 4, based on the selected predicted hit point, the drag constraint is solved, and the angle of attack difference is calculated to obtain the angle of attack of the interceptor weapon, specifically:

[0080]

[0081] Where: α 需求 For the required interception angle of attack, Cx 需求 Cx is the drag coefficient calculated based on drag requirements. 需求-1 Cx 需求+1 These represent the larger and smaller drag coefficient values ​​in the aerodynamic parameter table, α. 需求-1 α 需求+1 , which represent the corresponding angles of attack.

[0082] In step 5, the interceptor weapon's velocity roll angle is calculated based on its flight angle of attack and the total lift required for balanced flight. The specific method is as follows:

[0083]

[0084] Where: β is the velocity tilt angle, a z This represents the total lift of the aircraft. The total lift is projected laterally.

[0085] In step 6, the acceleration is calculated, specifically:

[0086] g = g rr+g ωe ω e

[0087] Where g is acceleration and r is the distance from the Earth's center; g we To intercept the creolic acceleration of the weapon, g r For the entrainment acceleration, ω e This is the Earth's rotational angular velocity.

[0088] The crioli acceleration and entrainment acceleration of the interceptor weapon are as follows:

[0089]

[0090] Among them, g we To intercept the creolic acceleration of the weapon, g r For the entrainment acceleration, μ e Where J is the Earth's gravitational coefficient and J is the Earth's oblateness term; a e Φ is the semi-major axis of the Earth's ellipsoid, and Φ is the geocentric latitude.

[0091] In step 6, based on the interceptor weapon's angle of attack and velocity tilt angle, ballistic integration is performed using a dynamic model to obtain the position and velocity information at the next time point, and the relative distance is calculated in real time. The specific method is as follows:

[0092]

[0093] Among them, Rx 目标 Ry 目标 、Rz 目标 For target location information, Rx 拦截 Ry 拦截 、Rz 拦截 H represents the relative distance, used to intercept weapon location information.

[0094] This invention discloses an electronic device, including a memory and a processor.

[0095] The memory is used to store one or more computer instructions;

[0096] The processor is configured to execute one or more computer instructions to perform the following steps:

[0097] Step S1: Based on the target's current flight trajectory and the assumption of balanced gliding flight, calculate the target's predicted flight trajectory using a target trajectory prediction analytical algorithm.

[0098] Step S2: Select the predicted hit point on the predicted flight trajectory of the target;

[0099] Step S3: Based on the position and speed information of the intercepting weapon, determine whether the predicted hit point meets the requirements using a prediction and analysis algorithm; if not, modify the predicted hit point and return to step S2; if yes, proceed to step S4.

[0100] Step S4: Based on the selection of the predicted hit point, solve the flight drag constraint of the interceptor weapon, perform angle of attack difference calculation, and obtain the flight angle of attack of the interceptor weapon;

[0101] Step S5: Calculate the interceptor weapon's velocity tilt angle based on the interceptor weapon's flight angle of attack and the total lift required for the interceptor weapon's balanced flight. By determining the projection information of the target position in the interceptor weapon's velocity system, calculate the positive and negative values ​​of the interceptor weapon's velocity tilt angle.

[0102] Step S6: Based on the interceptor weapon's flight angle of attack and velocity tilt angle, perform ballistic integration using the dynamic model, calculate acceleration, and solve for relative distance in real time;

[0103] Step S7: Determine whether the relative distance is less than or equal to the terminal guidance constraint index. If yes, end the calculation and successfully switch to terminal guidance; otherwise, repeat steps S1 to S6.

[0104] Example

[0105] This embodiment provides an online predictive guidance method for intercepting glide maneuvers of nearby hypersonic targets, the specific implementation of which is as follows:

[0106] Step 1: The information support system captures target information and obtains the target's current trajectory through tracking filtering, including target position and velocity information, such as... Figure 1 As shown;

[0107] Step 2: Based on the target's current position and velocity information, and using the equilibrium gliding assumption, assuming that the air resistance experienced by the target aircraft remains constant and continues in the negative velocity direction, the assumed trajectory of the target aircraft is a quasi-circular motion in the longitudinal direction and a uniformly decelerated motion in the lateral direction. Based on these flight trajectory characteristics, a variable-rate turning model is used to simulate the velocity and position vector changes caused by aerodynamic forces, obtaining the analytical solution of the target aircraft's trajectory, as follows: Figure 2 As shown;

[0108]

[0109]

[0110] Where: R l0 v l0 For the current interception weapon position and speed information, R l (t), v l(t) represents the position and velocity information of the interceptor weapon at time t, μ is the Earth's gravitational coefficient, and R l0 The distance between the Earth's center and the Earth's core at the current moment;

[0111] Step 3: Calculate the target's predicted trajectory using an analytical algorithm;

[0112] Step 4: Define the earliest interceptable time t0. Select an appropriate value Δts as the step size for calculating the predicted hit point. On the predicted trajectory, select ts = t0 as the initial predicted hit point.

[0113] Step 5: Input the current position and velocity information of the interceptor weapon, with the terminal velocity of the interceptor weapon as the primary constraint;

[0114] Step 6: Determine whether the predicted hit point meets the requirements using an analytical algorithm. This is based on: (1) the predicted hit point location and time information; and (2) the current position and speed information of the interceptor aircraft. Using the speed and dynamic pressure at the mid-to-late shift handover position as constraints, calculate the average speed and average drag acceleration information of the interceptor weapon required for the aircraft to reach the predicted hit point. If the average speed of the interceptor weapon is greater than the current speed, and the average drag acceleration is greater than the aircraft's capability range, then the predicted hit point does not meet the requirements.

[0115] If the predicted hit point does not meet the requirements, modify the predicted hit point ts = ts + Δts and return to step 4. If the predicted hit point meets the requirements, proceed to step 7.

[0116] Step 7: Based on the selected hit point, solve the drag constraint and proceed to the angle of attack difference calculation stage. Based on the monotonically increasing relationship between the angle of attack and the drag under the current high speed and flight speed of the interceptor weapon, establish a data table on the relationship between the flight drag and the flight angle of attack of the interceptor weapon, and use the linear difference method to calculate the angle of attack of the interceptor weapon required to meet the drag constraint.

[0117] Step 8: Calculate the angle of attack scheme α for the interceptor weapon. m ,like Figure 3 As shown.

[0118] Step 9: Calculate the interceptor weapon's velocity tilt angle by solving for the total lift projected onto the interceptor weapon's velocity system and the target position information. First, based on the lift requirement for the interceptor weapon's balanced flight at the current moment, project the total lift direction onto the interceptor weapon's velocity system to calculate the modulus of the velocity tilt angle. Then, cross-multiply the interceptor weapon's current position, velocity information, and target position information. By determining the target's position and direction, calculate the positive and negative values ​​of the velocity tilt angle, such as... Figure 4 As shown.

[0119]

[0120] Where: α is the angle of attack; β is the velocity roll angle, a z For total lift, The total lift is projected laterally.

[0121] Step 10: Based on the dynamic model and the parameter information of the angle of attack, velocity, and roll angle schemes, and combined with the ballistic integral of the dynamic model, integrate to the next cycle. The aircraft dynamic model adopts a model considering the J2 term perturbation, calculates aerodynamic parameters, lift, and drag through the flight angle of attack, integrates using an ODE45 integrator, and calculates the relative distance to the target based on the real-time integrated position and velocity.

[0122] g = g r r+g ωe ω e

[0123]

[0124] Where: μ e ω is the Earth's gravitational coefficient. e where J is the Earth's rotational angular velocity and J is the Earth's oblateness term; a e Φ is the semi-major axis of the Earth's ellipsoid; Φ is the geocentric latitude, and r is the geocentric distance. we The Creool acceleration is used to intercept the weapon.

[0125] Step 11: Continue until the relative distance is less than or equal to the terminal guidance constraint. At this point, terminal guidance has been successfully initiated, and the constraint conditions meet the terminal guidance requirements. Figure 5 As shown.

[0126]

[0127] Among them, R 目标 R 拦截 These are the target and interceptor weapon location information, respectively, with H representing the relative distance.

[0128] Step 12: Finally, the interception trajectory scenario is formed, such as... Figures 6-7 As shown, where, Figure 6 To intercept the trajectory under three-dimensional conditions of the interception scene, Figure 7 To intercept the trajectory of points below the star in the scene.

[0129] The above embodiments are merely explanations of the present invention and should not be construed as limiting the present invention. Therefore, any implementation methods similar to the present invention or implementation methods used in other similar structures but with similar concepts to the present invention are within the protection scope of the present invention.

[0130] The above description is only the best specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the protection scope of the present invention.

[0131] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A method for online predictive guidance for intercepting glide maneuvers of hypersonic targets in near proximity, characterized in that, include: Step 1: Based on the target's current flight trajectory and the assumption of balanced gliding flight, calculate the target's predicted flight trajectory using a target trajectory prediction analytical algorithm. Step 2: Select the predicted hit point on the target's predicted flight trajectory; Step 3: Based on the position and speed information of the intercepting weapon, determine whether the predicted hit point meets the requirements using a prediction and analysis algorithm; if not, modify the predicted hit point and return to step 2; if yes, proceed to step 4. Step 4: Based on the selection of the predicted hit point, solve the flight drag constraint of the interceptor weapon, calculate the angle of attack difference, and obtain the flight angle of attack of the interceptor weapon; Step 5: Calculate the interceptor weapon's velocity tilt angle based on the interceptor weapon's flight angle and the total lift required for its balanced flight. By determining the projection information of the target position onto the interceptor weapon's velocity system, calculate the positive and negative values ​​of the interceptor weapon's velocity tilt angle. Step 6: Based on the interceptor weapon's flight angle of attack and velocity tilt angle, perform ballistic integration using the dynamic model, calculate acceleration, and solve for relative distance in real time; Step 7: Determine whether the relative distance is less than or equal to the terminal guidance constraint index. If yes, end the calculation and successfully switch to terminal guidance; otherwise, repeat steps 1 to 6.

2. The online predictive guidance method for intercepting glide maneuvers of hypersonic targets near the target according to claim 1, characterized in that: In step 1, based on the target's current flight trajectory and the assumption of balanced gliding flight, the target's predicted flight trajectory is calculated using a target trajectory prediction analytical algorithm. The specific method is as follows: Where: R l0 v l0 For the current interception weapon position and speed information, R l (t), v l (t) represents the position and velocity information of the interceptor weapon at time t, μ is the Earth's gravitational coefficient, and R l0 This represents the distance between the Earth's center and the Earth's core at the current moment.

3. The online predictive guidance method for intercepting glide maneuvers of hypersonic targets near the target according to claim 1, characterized in that: In step 2, selecting the predicted hit point on the target predicted trajectory specifically involves: If this is the first selection, then ts(t) = t0; where t0 is the earliest interceptable time; ts(t) is the predicted hit point at time t; Otherwise, ts(t) = ts(t-1) + Δts; where Δts is the step size for calculating the predicted hit point; ts(t-1) is the predicted hit point at time t-1.

4. The online predictive guidance method for intercepting glide maneuvers of hypersonic targets near the target according to claim 1, characterized in that: In step 3, based on the position and velocity information of the intercepting weapon, a predictive analysis algorithm is used to determine whether the predicted hit point meets the requirements. The specific method is as follows: Based on the predicted hit point location, time information, and the current location and speed information of the interceptor weapon; with the speed and dynamic pressure at the mid-to-late shift handover position as constraints, the average speed information and average drag acceleration information of the interceptor weapon required for the aircraft to reach the predicted hit point are calculated; if the average speed of the interceptor weapon is greater than the speed at the current moment, and the average drag acceleration is greater than the aircraft's capability range, then the predicted hit point cannot meet the requirements.

5. The online predictive guidance method for intercepting glide maneuvers of near-hypersonic targets according to claim 1, characterized in that: In step 4, based on the predicted hit point selection, the drag constraint is solved, and the angle of attack difference is calculated to obtain the angle of attack of the interceptor weapon. Specifically: Where: α 需求 For the required interception angle of attack, Cx 需求 Cx is the drag coefficient calculated based on drag requirements. 需求-1 Cx 需求+1 These represent the larger and smaller drag coefficient values ​​in the aerodynamic parameter table, α. 需求-1 α 需求+1 , which represent the corresponding angles of attack.

6. The online predictive guidance method for intercepting glide maneuvers of near-hypersonic targets according to claim 1, characterized in that: In step 5, the interceptor weapon's velocity roll angle is calculated based on its flight angle of attack and the total lift required for balanced flight. The specific method is as follows: Where: β is the velocity tilt angle, a z This represents the total lift of the aircraft. The total lift is projected laterally.

7. The online predictive guidance method for intercepting glide maneuvers of hypersonic targets near the target according to claim 1, characterized in that: In step 6, the acceleration is calculated as follows: g=g r r+g ωe oh e Where g is the acceleration and r is the distance from the Earth's center; g we To intercept the creolic acceleration of the weapon, g r For the entrainment acceleration, ω e This is the Earth's rotational angular velocity.

8. The online predictive guidance method for intercepting glide maneuvers of hypersonic targets near the target according to claim 7, characterized in that: The Creool acceleration and entrainment acceleration of the interceptor weapon are specifically as follows: Among them, g we To intercept the creolic acceleration of the weapon, g r For the entrainment acceleration, μ e Where J is the Earth's gravitational coefficient, and J is the Earth's oblateness term; a e Φ is the semi-major axis of the Earth's ellipsoid, and Φ is the geocentric latitude.

9. The online predictive guidance method for intercepting glide maneuvers of near-hypersonic targets according to claim 1, characterized in that: In step 6, based on the interceptor weapon's angle of attack and velocity tilt angle, ballistic integration is performed using a dynamic model to obtain the position and velocity information at the next time point, and the relative distance is calculated in real time. The specific method is as follows: Among them, Rx 目标 Ry 目标 、Rz 目标 For target location information, Rx 拦截 Ry 拦截 、Rz 拦截 H represents the relative distance, used to intercept weapon location information.

10. An electronic device, characterized in that, Including memory and processor, The memory is used to store one or more computer instructions; The processor is configured to execute one or more computer instructions to perform the following steps: Step S1: Based on the target's current flight trajectory and the assumption of balanced gliding flight, calculate the target's predicted flight trajectory using a target trajectory prediction analytical algorithm. Step S2: Select the predicted hit point on the predicted flight trajectory of the target; Step S3: Based on the position and speed information of the intercepting weapon, determine whether the predicted hit point meets the requirements using a prediction and analysis algorithm; if not, modify the predicted hit point and return to step S2; if yes, proceed to step S4. Step S4: Based on the selection of the predicted hit point, solve the flight drag constraint of the interceptor weapon, perform angle of attack difference calculation, and obtain the flight angle of attack of the interceptor weapon; Step S5: Calculate the interceptor weapon's velocity tilt angle based on the interceptor weapon's flight angle of attack and the total lift required for the interceptor weapon's balanced flight. By determining the projection information of the target position in the interceptor weapon's velocity system, calculate the positive and negative values ​​of the interceptor weapon's velocity tilt angle. Step S6: Based on the interceptor weapon's flight angle of attack and velocity tilt angle, perform ballistic integration using the dynamic model, calculate acceleration, and solve for relative distance in real time; Step S7: Determine whether the relative distance is less than or equal to the terminal guidance constraint index. If yes, end the calculation and successfully switch to terminal guidance; otherwise, repeat steps S1 to S6.

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