Sniper trajectory crosswind influence correction method, system and device

Abstract

The application discloses a sniping trajectory crosswind influence correction method, system and device, relates to the field of trajectory correction, and the method is characterized in that: a projectile aerodynamic database containing static and dynamic aerodynamic parameters is constructed through CFD numerical simulation; a six-degree-of-freedom rigid body trajectory model is established, and the aerodynamic database is dynamically coupled with the model to form a high-fidelity aerodynamic coupling trajectory solver; a crosswind condition is modeled as a time-space distribution sequence set along a preset trajectory track in sections, is input into the solver for trajectory calculation, and a lateral deviation is output; the time-space cumulative effect of the crosswind disturbance is quantified by analyzing the deviation difference of the projectile in the front and rear sections of the trajectory under the same wind disturbance; and a target range-equivalent wind speed-lateral deviation three-dimensional query table is generated based on the calculation result. The application realizes high-precision trajectory prediction and rapid correction of complex changing crosswind for the first time, and significantly improves the long-range shooting precision and actual combat efficiency of the sniping rifle under complex meteorological conditions.

Description

Technical Field

[0001] This invention relates to the field of ballistic correction, and more specifically, to a method, system, and apparatus for correcting the effects of crosswinds on sniper ballistics. Background Technology

[0002] In sniper operations, especially in ultra-long-range precision shooting, crosswinds are the most significant environmental interference factor causing projectiles to deviate from their expected trajectories and affecting first-shot hit probability. Traditional sniper trajectory correction relies primarily on firing tables and the shooter's experience. Standard firing tables are typically compiled under the simplified assumption of constant crosswinds, but in actual combat, wind fields are complex and variable, and wind speed and direction often exhibit significant spatial inhomogeneities and temporal instabilities along the bullet's flight path (trajectory). This simplification leads to a significant deviation between the actual lateral trajectory deviation (lateral deflection) and the firing table predictions in complex weather and terrain conditions, especially at ranges exceeding 800 meters. This necessitates heavy reliance on the shooter's personal experience for estimation and compensation, making it difficult to guarantee accuracy and consistency.

[0003] At the technical level, existing computer-based ballistic prediction methods suffer from two major bottlenecks: First, aerodynamic data accuracy and dynamic mismatch. Most methods rely on empirical formulas or static aerodynamic coefficients obtained from steady-state wind tunnel tests, failing to accurately reflect the aerodynamic forces and moments generated by dynamic changes in the angle of attack during actual flight. In particular, they lack crucial dynamic derivatives such as the pitch damping moment coefficient, leading to distortion in long-range ballistic attitude simulations. Second, crosswind modeling is overly idealized. Existing models generally treat crosswinds as a single constant acting on the entire trajectory, failing to describe the true spatiotemporal distribution of wind speed and direction along the trajectory, and even less able to quantify and analyze the differences in the impact of crosswind disturbances on the final impact point at different flight stages (such as the initial and terminal phases) (i.e., spatiotemporal cumulative effect). Summary of the Invention

[0004] The present invention aims to overcome the above-mentioned defects of the prior art and provide a method, system and device for correcting the crosswind influence of sniper ballistics. This method can construct a high-precision dynamic aerodynamic database, realize the fine modeling and calculation of complex crosswind fields, quantify the crosswind disturbance law and form a practical correction tool.

[0005] To achieve the above-mentioned objectives, this invention provides a method, system, and apparatus for correcting the crosswind effect on sniper ballistics, comprising the following steps:

[0006] Step S1: Establish a three-dimensional geometric model of the projectile, and use the CFD numerical simulation method to calculate the flow field of the projectile within a preset Mach number range and a preset angle of attack range based on the three-dimensional geometric model of the projectile. Calculate the forces and torques on the projectile in the flow field, and construct a database of projectile aerodynamic parameters containing multiple flight states.

[0007] Step S2: Establish a six-degree-of-freedom rigid body ballistic model, which includes the equations of motion describing the translation of the center of mass and the dynamic equations describing the rotation about the center of mass; in the process of solving the six-degree-of-freedom rigid body ballistic model, according to the real-time flight state of the projectile, the corresponding aerodynamic parameters are dynamically obtained from the projectile aerodynamic parameter database, and the aerodynamic force and torque on the projectile are calculated based on the aerodynamic parameters to obtain an aerodynamically coupled ballistic solver;

[0008] Step S3: After setting the environmental conditions, set the crosswind conditions, which include wind speed, wind direction, and the spatiotemporal distribution data of the two along the projectile's preset trajectory; using the crosswind conditions as the environmental input, run the aerodynamically coupled ballistic solver to solve the actual flight trajectory of the projectile, output the lateral offset of the projectile at multiple target range points, and obtain the solution results.

[0009] Step S4: Based on the solution results, generate correction data reflecting the correspondence between target range, wind speed and lateral offset; query the correction data according to the actual target range and actual wind speed to obtain the corresponding lateral offset, and correct the aiming point of the sniper rifle based on the obtained lateral offset.

[0010] This method establishes a complete closed-loop technical process, encompassing the construction of a high-precision aerodynamic database, dynamic coupling solution of a six-degree-of-freedom ballistic trajectory, ballistic calculation under complex crosswind conditions, and the generation and application of practical correction data. It achieves the construction of a high-precision dynamic aerodynamic database, accurately acquiring complete aerodynamic parameters (including static coefficients and dynamic derivatives) of the projectile across its entire envelope through CFD numerical simulations covering both steady-state and transient states, laying a high-precision data foundation for ballistic calculations. It achieves refined modeling and calculation of complex crosswind fields, abandoning the constant crosswind assumption in traditional techniques. Instead, it models the crosswind as a vector sequence distributed spatiotemporally along a pre-defined trajectory, and uses a six-degree-of-freedom ballistic model coupled with high-precision aerodynamic data for calculation, realistically reproducing the projectile's trajectory in changing wind fields. It quantifies the crosswind disturbance laws and forms a practical correction tool. Through systematic calculation, it reveals and quantifies key laws such as the spatiotemporal cumulative effect of crosswind disturbances, ultimately condensing the complex physical model calculation results into correction data that can be quickly queried and applied by shooters, achieving efficient transformation from cutting-edge simulation technology to practical battlefield tools. This solution addresses systemic problems inherent in traditional methods, such as inaccurate aerodynamic data, disconnect between model calculations and actual physical processes, inability to handle complex crosswinds, and difficulty in rapidly correcting results for real-world combat. It provides a comprehensive, high-precision ballistic correction solution covering the entire chain from basic data preparation to final battlefield application.

[0011] Preferably, in step S1, the CFD numerical simulation method adopts the Reynolds-averaged Navier-Stokes method, and the turbulence model adopts the Realizable-k-ε model; the preset Mach number range is 0.5 to 2.5, and the preset angle of attack range is 0 to 15 degrees.

[0012] Preferably, the steps for constructing the projectile aerodynamic parameter database specifically include:

[0013] Step a: Obtain the raw data and coefficients;

[0014] Step b: Perform parameter processing on the original data and coefficients;

[0015] Step c: Integrate the data obtained in steps a and b to construct the aerodynamic parameter database for the projectile;

[0016] Specifically, step a includes:

[0017] Step a1: Mesh the three-dimensional geometric model of the projectile to generate a structured mesh containing the boundary layer mesh;

[0018] Step a2: Based on the structured grid, perform steady-state CFD calculations to obtain the discrete static aerodynamic forces and moment coefficients of the projectile at multiple different angles of attack as raw data;

[0019] Step a3: Drive the projectile's three-dimensional geometric model to perform periodic pitching motion using a user-defined function, perform transient CFD calculations, and obtain the projectile's pitching damping moment coefficient.

[0020] This document describes the detailed construction steps of the projectile aerodynamic parameter database, including the system process of data production, processing, and integration. It emphasizes obtaining the key dynamic parameter, the pitch damping moment coefficient, through transient CFD, thus solving the problem of missing or inaccurate estimation of this parameter in traditional methods. It ensures the completeness and physical accuracy of the database content, particularly including key parameters describing the dynamic stability of the projectile.

[0021] Preferably, step b specifically includes: standardizing the original data and calculating the aerodynamic derivatives for ballistic calculation by differentiating or second-ordering the angle of attack. This generates high-precision aerodynamic derivative data that can be directly interpolated for a six-degree-of-freedom rigid body ballistic model, realizing the connection between CFD simulation and ballistic calculation, and improving the solution accuracy of the ballistic model.

[0022] Preferably, the steps specifically include: integrating the original data, the pitch damping moment coefficient, and the aerodynamic derivative to form the projectile aerodynamic parameter database.

[0023] Preferably, the definition and solution of the six-degree-of-freedom rigid body ballistic model in step S2 is based on the transformation of four coordinate systems: ground coordinate system, reference coordinate system, velocity coordinate system and projectile axis coordinate system; the motion state of the projectile is decomposed and described through Euler angle transformation between the four coordinate systems.

[0024] The six-DOF rigid body ballistic model in this method is constructed based on four specific coordinate systems: the ground frame, the reference frame, the velocity frame, and the projectile axis frame, and the transformation relationships established through Euler angles. These coordinate systems and transformation relationships allow for the precise description of the projectile's attitude, velocity direction, and aerodynamic force / torque components in each direction. This ensures the accuracy and completeness of the ballistic model, distinguishing it from traditional simplified point mass ballistic models, and enabling high-precision simulation of projectile flight attitude and trajectory.

[0025] Preferably, the solution of the six-degree-of-freedom rigid body ballistic model in step S2 adopts the fourth-order Runge-Kutta algorithm; in each step of the iterative solution of the six-degree-of-freedom rigid body ballistic model, the aerodynamic parameters at the current moment are obtained by real-time interpolation from the aerodynamic parameter database based on the current Mach number and angle of attack of the projectile.

[0026] The high-precision numerical method of the fourth-order Runge-Kutta (RK4) algorithm was employed to solve the ballistic differential equations. At each step, aerodynamic parameters were interpolated from a database based on real-time flight conditions (MAG, angle of attack). This solved the stability and accuracy problems of numerically solving complex differential equations and achieved real-time, dynamic, and bidirectional coupling between the aerodynamic environment and projectile motion (motion state determines aerodynamic parameters, and aerodynamic parameters influence motion state). This ensured high precision and numerical stability in the ballistic calculation process.

[0027] Preferably, in step S3, the crosswind conditions are modeled as a time sequence that includes wind speed and wind direction, set in segments along the preset trajectory of the projectile.

[0028] The crosswind condition is defined as a time-series pattern that varies segmentally along a preset ballistic trajectory; that is, a set of data indicating wind speed and direction at a specific location and time on the trajectory. This breaks through the assumption of constant crosswinds, enabling the model to realistically reflect the complex and ever-changing wind field structure in actual combat. It also expands the applicable scenarios and prediction accuracy of this method, making it suitable for combat areas with extremely complex wind field environments, such as mountains, canyons, and urban complexes.

[0029] Preferably, in step S3, the spatiotemporal cumulative effect of crosswind disturbance is quantified by comparing and analyzing the difference in lateral deviation caused by crosswind disturbance in the early and late stages of the projectile's flight trajectory. Through comparative simulation experiments with wind in the early and late stages, the differences in the impact of the same wind disturbance on the final lateral deviation at different stages of the trajectory are directly analyzed and quantified. This achieves the quantitative analysis of the spatiotemporal cumulative effect of crosswind disturbance, realizing full-trajectory wind field detection.

[0030] The present invention also provides a sniper ballistic crosswind correction system, the system comprising:

[0031] The projectile aerodynamic parameter database unit is used to establish a three-dimensional geometric model of the projectile, and to calculate the flow field of the projectile within a preset Mach number range and a preset angle of attack range based on the CFD numerical simulation method, thereby constructing a projectile aerodynamic parameter database containing multiple flight states.

[0032] An aerodynamically coupled ballistic solver unit is used to establish a six-degree-of-freedom rigid body ballistic model, which includes the equations of motion describing the translation of the center of mass and the dynamic equations describing the rotation about the center of mass. During the solution process of the six-degree-of-freedom rigid body ballistic model, the corresponding aerodynamic parameters are dynamically obtained from the projectile aerodynamic parameter database according to the real-time flight state of the projectile. Based on the aerodynamic parameters, the aerodynamic forces and torques acting on the projectile are calculated to obtain the aerodynamically coupled ballistic solver.

[0033] The solution unit is used to set crosswind conditions, which include wind speed, wind direction, and spatiotemporal distribution data of the two along the preset trajectory of the projectile; using the crosswind conditions as environmental input, the aerodynamically coupled ballistic solver is run to solve the actual flight trajectory of the projectile, output the lateral offset of the projectile at multiple target range points, and obtain the solution results.

[0034] The correction unit is used to generate correction data reflecting the correspondence between target range, wind speed and lateral offset based on the solution results; query the correction data according to the actual target range and actual wind speed to obtain the corresponding lateral offset; and correct the aiming point of the sniper rifle based on the obtained lateral offset.

[0035] The present invention also provides a sniper ballistic crosswind influence correction device, including a memory and a processor, wherein the memory is used to store a computer program, and the processor is used to implement the sniper ballistic crosswind influence correction method when executing the computer program.

[0036] One or more technical solutions provided by this invention have at least the following technical effects or advantages:

[0037] This method can construct a high-precision dynamic aerodynamic database, realize refined modeling and calculation of complex crosswind fields, quantify the crosswind disturbance law and form a practical correction tool, and realize high-fidelity ballistic simulation under complex meteorological conditions. Attached Figure Description

[0038] The accompanying drawings, which are provided to further illustrate embodiments of the invention and constitute a part of this invention, are not intended to limit the scope of the invention.

[0039] Figure 1 A flowchart illustrating the method for correcting the crosswind effect on sniper ballistics;

[0040] Figure 2 This is a diagram illustrating the angle of attack of a projectile.

[0041] Figure 3 A schematic diagram showing the flow field division in the area affected by the projectile;

[0042] Figure 4 This is a schematic diagram of the mesh division on the surface of the projectile. Detailed Implementation

[0043] To better understand the above-mentioned objectives, features, and advantages of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, where there is no conflict, the embodiments of the present invention and the features thereof can be combined with each other.

[0044] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and therefore the scope of protection of the invention is not limited to the specific embodiments disclosed below.

[0045] Those skilled in the art should understand that, in the disclosure of this invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the above terms should not be construed as limiting this invention.

[0046] It is understood that the term "a" should be understood as "at least one" or "one or more", that is, in one embodiment, the number of an element can be one, while in another embodiment, the number of the element can be multiple, and the term "a" should not be understood as a limitation on the number.

[0047] Example 1;

[0048] Please refer to Figure 1 , Figure 1 This is a flowchart illustrating a method for correcting the effects of crosswinds on sniper ballistics. Embodiment 1 of the present invention provides a method for correcting the effects of crosswinds on sniper ballistics, comprising the following steps:

[0049] Step S1: Aerodynamic parameter database construction: Establish a three-dimensional geometric model of the projectile, use CFD numerical simulation method to calculate the flow field of the projectile in the preset Mach number range and preset angle of attack range based on the three-dimensional geometric model of the projectile, calculate the force and torque on the projectile in the flow field, and construct a projectile aerodynamic parameter database containing multiple flight states.

[0050] Step S2: Ballistic Modeling and Dynamic Coupling: A six-degree-of-freedom rigid body ballistic model is established, which includes the equations of motion describing the translation of the center of mass and the dynamic equations describing the rotation about the center of mass. During the solution process of the six-degree-of-freedom rigid body ballistic model, the corresponding aerodynamic parameters are dynamically obtained from the aerodynamic parameter database of the projectile according to the real-time flight state of the projectile. The aerodynamic force and torque acting on the projectile are calculated according to the existing classical aerodynamic formulas (standard form of aerodynamic force / torque calculation, refer to the research on the compilation method of sniper weapon firing tables based on CFD - Wu Dongsheng - Harbin Institute of Technology). This realizes the coupled solution of fluid dynamics and rigid body dynamics, thus obtaining an aerodynamically coupled ballistic solver.

[0051] Step S3: Complex crosswind ballistics calculation: After setting the environmental conditions, set the crosswind conditions, which include wind speed, wind direction, and the spatiotemporal distribution data of the two along the projectile's preset trajectory; using the crosswind conditions as the environmental input, run the aerodynamically coupled ballistic solver to solve the actual flight trajectory of the projectile, output the lateral offset of the projectile at multiple target range points, and obtain the solution results;

[0052] Step S4: Correction data generation and application: Based on the solution results, generate correction data reflecting the correspondence between target range, wind speed and lateral offset; query the correction data according to the actual target range and actual wind speed to obtain the corresponding lateral offset, and correct the aiming point of the sniper rifle based on the obtained lateral offset.

[0053] In this method, the ballistic solver is a complete program that realizes a closed loop of real-time aerodynamic parameter query, force / torque calculation, and ballistic state update. It is a custom numerical calculation program, and its specific implementation is as follows:

[0054] This invention constructs an aerodynamically coupled ballistic solver through a self-developed program. This ballistic solver uses the fourth-order Runge-Kutta method for numerical integration, and its core coupling process is as follows:

[0055] 1. Input and initialization: Read in the aerodynamic parameter database of the projectile that has been established in advance through CFD simulation, and set the initial state of the projectile (initial velocity, launch angle, etc.) and crosswind conditions.

[0056] 2. Real-time aerodynamic calculation cycle: Within each integration time step:

[0057] a. Calculation of state parameters: Calculate the relative velocity v from the current velocity vector v and the wind speed vector w. r This leads to the current Mach number Ma and the total angle of attack α.

[0058] b. Database query: Using (Ma, α, etc.) as key parameters, obtain the aerodynamic coefficients (such as C) at the current moment from the projectile aerodynamic parameter database through linear interpolation. D and C L ) and torque coefficient (such as C) m ).

[0059] c. Force and torque calculation: Calculate forces and torques using standard aerodynamic formulas.

[0060] 3. Ballistic State Update: The calculated aerodynamic forces and moments, along with gravity, are substituted into the six-DOF rigid body ballistic differential equations. The fourth-order Runge-Kutta method is used to solve these equations, updating all state variables of the projectile, including position, velocity, and attitude angles.

[0061] 4. Loop and Output: Repeat steps 2-3 until the projectile hits the ground. Record the trajectory throughout the entire process and output the lateral offset at a specific range.

[0062] Through the above steps, dynamic and closed-loop coupling of CFD aerodynamic data and a six-degree-of-freedom ballistic model is achieved, forming the aerodynamic coupled ballistic solver of this invention.

[0063] In this embodiment of the invention, the crosswind condition is modeled as a time sequence including wind speed and direction, segmented along the preset trajectory of the projectile. The specific implementation method is as follows:

[0064] To reflect the spatiotemporal variation of crosswinds along the ballistic trajectory, this embodiment defines crosswind conditions as a piecewise linear time sequence bound to the ballistic position. The specific implementation method is as follows:

[0065] Definition of the crosswind data structure:

[0066] In the solver, a crosswind profile table is defined. The core of this table is to record the wind conditions at different points along a preset trajectory (i.e., an ideal trajectory without considering crosswind interference), starting from the firing point. Each record contains the following fields: range (cumulative range along the preset trajectory), wind... speed (Horizontal wind speed at that point), winddirection (Wind direction (degrees), with the direction of firing as 0°, clockwise as positive).

[0067] Input and preparation of crosswind data:

[0068] The crosswind profile data in the above crosswind profile table can be generated based on battlefield weather reconnaissance, historical wind field statistics, or tactical settings, and stored in a text file format. The solver reads this file during initialization and loads it into memory.

[0069] Real-time invocation within the ballistics solving loop:

[0070] At each time step of the ballistic solution, perform the following operations to determine the current wind vector:

[0071] (1) Positioning: Obtain the current position (x, y, z) of the projectile in the ground coordinate system, and calculate its projection point along the preset trajectory to obtain the current range R. current .

[0072] (2) Query and interpolation: In memory, find R current The interval in which it is located.

[0073] (3) Calculate the current wind vector: Perform linear interpolation on the wind speed and wind direction to obtain the current wind speed WS and the current wind direction WD.

[0074] (4) Vector synthesis: Based on the current wind speed WS and the current wind direction WD, the horizontal wind speed is decomposed into components W in the ground coordinate system according to the current wind direction. x (Vertical), W z (Horizontal).

[0075] (5) Application: W x ,0,W z The current environmental wind vector is used to calculate the relative velocity of the projectile, and then to solve for the aerodynamic force and trajectory.

[0076] Through the above process, the solver dynamically incorporates complex crosswind conditions that vary along the trajectory into the ballistic calculation.

[0077] In step S3, the preset environmental conditions typically refer to atmospheric environment, gravitational field, Earth's rotation parameters, initial position, etc. These preset conditions construct a stable and repeatable baseline trajectory. By inputting defined, variable crosswind conditions along the trajectory, the net impact of crosswind disturbances on the trajectory can be clearly and independently analyzed, thus ensuring the accuracy of the experimental conclusions.

[0078] In this embodiment of the invention, the difference in lateral offset caused by crosswind disturbance in the early stage of the flight trajectory and the same crosswind disturbance in the later stage is compared and analyzed to quantify the spatiotemporal cumulative effect of crosswind disturbance.

[0079] To quantify the spatiotemporal cumulative effect of crosswind disturbance, this invention employs the following comparative experimental method, which is a specific application of the aforementioned aerodynamically coupled ballistic solver:

[0080] 1. Experimental design and crosswind condition setting:

[0081] This embodiment designs two sets of comparative experiments, changing only the ballistic range affected by crosswinds while keeping all other initial conditions (initial velocity, angle of attack, projectile parameters, etc.) completely consistent.

[0082] Experiment A (Front-end wind group): The crosswind conditions are set as follows: within the 0 to 500-meter range of the preset trajectory, there is a constant right wind of 5 m / s (wind direction 90°); within the 500-meter range to the endpoint, the wind speed is 0.

[0083] Experiment B (Later Wind Group): The crosswind conditions were set as follows: the wind speed was 0 in the 0 to 500 meter range; and there was a completely identical crosswind (5 m / s, 90°) in the 500 meter to the end point range.

[0084] 2. Ballistics calculation and data acquisition:

[0085] Using the two sets of crosswind conditions described above as environmental inputs, the aerodynamically coupled ballistic solver was run. The lateral displacement of the projectile at its endpoint (e.g., 1000 meters) under both experimental conditions was obtained and denoted as follows:

[0086] Forward deviation: Lateral deviation at the end point of Experiment A (front section exposed to wind).

[0087] Backward deviation: Lateral deviation at the end point of Experiment B (rear wind exposure).

[0088] 3. Quantitative calculation of spatiotemporal cumulative effects:

[0089] By comparing and analyzing the differences between the two experimental results, the spatiotemporal cumulative effect coefficient K is calculated to quantify the effect.

[0090] The spatiotemporal cumulative effect coefficient K = forward offset / backward offset. If K > 1, it proves that the same crosswind disturbance has a greater impact in the forward phase of the trajectory than in the backward phase, that is, there is a positive spatiotemporal cumulative effect. The larger the K value, the more significant the cumulative effect.

[0091] 4. Examples of experimental results and conclusions:

[0092] Taking a certain type of sniper ammunition as an example, the above experiment yielded the following results: forward offset = 8.75 meters, backward offset = 3.05 meters, and the calculated value was K = 8.75 / 3.05 ≈ 2.87. This result indicates that for this type of ammunition, the effect of crosswinds acting on the initial stage of the trajectory on the final deviation is approximately 2.87 times greater than that acting on the later stage. This quantitative conclusion can be directly applied to actual combat: snipers should prioritize ensuring accurate measurement of the wind field in the first half of the trajectory, especially within the 300-500 meter range near the muzzle, as this has a decisive impact on accuracy. Through the above standardized comparative experimental procedure, this invention, for the first time, transforms the spatiotemporal cumulative effect of crosswind disturbances from a qualitative understanding into quantifiable technical parameters.

[0093] This invention employs a research method combining computational fluid dynamics (CFD) and a six-degree-of-freedom rigid body ballistic model. First, precise aerodynamic parameters of the projectile within the Mach 0.5-2.5 range at angles of attack of 0-15 degrees are obtained through CFD simulation. Then, a ballistic model considering the dynamic effects of the angle of attack is established. Finally, the aerodynamic parameters are imported into the six-degree-of-freedom rigid body ballistic model, and the trajectory is calculated under complex crosswind conditions. The study focuses on the ballistic characteristics under constant and varying wind speeds, quantifying the cumulative effect of segmented wind speeds on the lateral deviation of the trajectory. This provides a more accurate correction tool for sniper training and actual combat, and offers new evidence for trajectory correction under complex weather conditions.

[0094] The ballistic modeling method is as follows:

[0095] This invention employs a combination of computational fluid dynamics (CFD) simulation and a six-degree-of-freedom rigid body ballistic model (see Han Zipeng, "External Ballistics of Projectiles and Rockets" - Beijing Institute of Technology Press, and Sun Daoqiu, "Research and Implementation of Sniper Rifle Ballistic Solution Algorithm and Electron Mirror Differentiation Plate" - Xiangtan University) to analyze ballistic characteristics under crosswind conditions. The overall technical solution comprises three key parts: aerodynamic parameter calculation (see Yan Yanjun, Yu Lei, Peng Zhizhao, et al., "Research on Automatic Correction Method of Sniper Rifle Aiming System" - Journal of Ballistics, and Zhao Gou, "Research on Projectile Aerodynamic Parameter Identification Based on Target Trajectory Shadow Photography" - Nanjing University of Science and Technology Dissertation), ballistic solution, and data analysis.

[0096] The aerodynamic parameters were calculated based on the Reynolds-averaged Navier-Stokes (RANS) method, an existing method which will not be elaborated upon in this embodiment. Instead, an improved Realizable k-ε turbulence model was used for numerical simulation. A three-dimensional geometric model of the projectile was established and a structured mesh (approximately 450,000 mesh elements) was created. The flow field characteristics under different Mach numbers (0.5-2.5 Ma) and angles of attack (0-15°) were calculated (refer to Liu Guoqing, Xu Cheng - Research on High-Precision Sniper Rifle Ammunition and Gun Matching Design Method - Acta Ordnanceica Sinica; Wu Zhilin, Tao Jiabin - Simulation of Aerodynamic Characteristics of Micro-Modified Ammunition Based on FLUENT - Computer Simulation; Shen Zhongshu, Liu Yafei - Projectile Aerodynamics - National Defense Industry Press). Specifically, a boundary layer mesh was generated near the projectile surface to accurately capture boundary layer flow characteristics, and a user-defined function (UDF) was used to dynamically simulate the periodic pitching motion of the projectile.

[0097] The ballistics calculation section constructs a complete set of six-degree-of-freedom rigid body motion equations (see Guo Xifu, Zhao Zihua - Fire Control Ballistics Model Theory and Application - National Defense Industry Press; Jin Dagen, Ren Guomin, Su Genliang - Experimental External Ballistics - Ordnance Industry Press), containing differential equations for 12 state variables:

[0098] 1) Equation of motion of the center of mass: describes the three-axis translation of the projectile in the velocity coordinate system.

[0099] 2) Equation of rotation about the center of mass: characterizes the attitude dynamics of the projectile in the projectile axis coordinate system.

[0100] 3) Kinematic equations: Establish the transformation relationships between different coordinate systems.

[0101] The fourth-order Runge-Kutta (RK4) algorithm was used for numerical solution with a time step of 0.001s. In each iteration, the aerodynamic parameter database obtained by CFD calculation was interpolated in real time to realize the dynamic coupling of fluid and rigid body dynamics.

[0102] The data analysis section generates impact point distribution matrices under different wind speeds (0-5 m / s) and pitch angles (0-45°) by batch running a ballistic program based on the six-degree-of-freedom ballistic equations described later. A three-dimensional lookup table (i.e., corrected data) of range-wind speed-lateral deviation is established to analyze the influence weight of each factor on the lateral deviation. A comparative experiment with varying wind speeds is also designed to study the spatiotemporal cumulative effect of crosswind disturbance.

[0103] Coordinate system setting method:

[0104] In ideal ballistic models, the angle of attack is typically ignored. However, in actual flight, projectiles are subject to various disturbances. External disturbances cause a deviation between the projectile's axis and its center of mass trajectory; this angular deviation is defined as the angle of attack. This phenomenon induces additional aerodynamic torque, which in turn alters the projectile's rotational state. This rotational motion then reacts on the center of mass trajectory, creating a coupling effect. To accurately simulate ballistic characteristics, a computational model incorporating the dynamic effects of the angle of attack is needed to simultaneously analyze the interaction between angular motion and translational trajectory. Please refer to [reference needed]. Figure 2 , Figure 2 This is a diagram illustrating the angle of attack of a projectile.

[0105] The projectile's motion remains unchanged regardless of the chosen coordinate system, but the choice of coordinate system significantly impacts the ease of solving the ballistic equations and their readability. Therefore, this invention establishes four coordinate systems: a ground coordinate system, a reference coordinate system, a velocity coordinate system, and a projectile-axis coordinate system. Each coordinate system achieves motion decomposition through Euler angle transformation. The velocity system describes aerodynamic effects, while the projectile-axis system characterizes attitude dynamics. Both are coupled with the reference system via rotation matrices, forming the fundamental framework for solving the ballistic equations.

[0106] The gravitational field adopts a uniform assumption: based on the fact that the range of a sniper rifle (<2000m) is much smaller than the Earth's radius, the slight variation of gravitational acceleration with altitude is ignored. Regarding projectile dynamics, relying on the rigid projectile assumption, the cross-sectional area is set to be constant during flight to ensure aerodynamic parameter stability. Initial conditions are standardized: uniform propellant charge, projectile mass, and barrel parameters are used for firearms of the same model to ensure consistent initial velocity. Environmental parameters are treated as a steady-state model: within the effective range, meteorological elements such as air density, temperature, and humidity are equivalent to muzzle measurements, ignoring changes in meteorological gradients along the trajectory. This series of simplified processing (uniform gravity, rigid body assumption, parameter standardization, and steady-state environment) significantly reduces the complexity of solving the ballistic differential equations while maintaining computational accuracy, making it suitable for the engineering calculation needs of sniper ballistics.

[0107] Aerodynamic parameter acquisition:

[0108] The specific methods for projectile modeling and mesh generation are as follows:

[0109] After completing the 3D model based on the projectile's geometric parameters, the model was imported into the fluid dynamics simulation software Fluent for mesh generation. A hexahedral mesh was used, with cylindrical regions of ±0.1m along the projectile's axial direction (X-axis), and cylinders with a radius of 0.3m constructed radially (YZ plane). Furthermore, hemispherical closed structures of the same diameter were added at both ends of the axial direction. Figure 3 As shown, Figure 3 This is a schematic diagram showing the flow field division within the projectile's affected region. The projectile surface mesh is as follows: Figure 4 As shown, Figure 4This diagram illustrates the mesh generation on the projectile surface. Considering the influence of the projectile's bands, a boundary layer mesh is generated near the projectile surface to capture boundary layer information. The mesh count is approximately 450,000, meeting mesh quality inspection requirements.

[0110] Turbulence model selection:

[0111] The Reynolds-averaged Navier-Stokes (RANS) method, with its combined advantages of high computational efficiency, strong robustness, and good prediction accuracy, has become the mainstream technical framework for engineering turbulence analysis. Within the RANS model system, while the standard k-epsilon model has limitations in simulating complex flows, its improved Realizable-k-epsilon model, by introducing positive definite constraints on the Reynolds stress tensor, constructs a mathematically consistent turbulence viscosity correction equation. This improved model, while maintaining the two-equation framework, significantly improves the prediction accuracy of complex turbulence characteristics such as vortex separation and strong pressure gradients by asymptotically satisfying the realizability criterion. Its calculation results are more consistent with physical reality than the standard model, making it an important tool for numerical simulation of engineering turbulence. The model equations are as follows:

[0112] ;

[0113] ;

[0114] in, , For position vectors, It is a velocity vector. air density, Where μ is the turbulent kinetic energy and μ is the molecular viscosity. The turbulent viscosity coefficient, It is a constant. =1.0. This is due to the generation of turbulent kinetic energy caused by the average velocity gradient. This is due to the generation of turbulent kinetic energy caused by the effect of buoyancy. The effect of compressible turbulent fluctuations on the total dissipation rate is given by ε, where ε is the turbulent kinetic energy dissipation rate. The Prandtl number represents the turbulent kinetic energy dissipation rate. Let v be the source term, and v be the velocity component parallel to the direction of gravity. , , , Let the strain rate tensor be... All are constants.

[0115] Simulation settings:

[0116] First, steady-state calculations are performed with a residual of 0.00001. The convergence criterion is reached after approximately 1000 steps. After convergence, the forces and moments in the X, Y, and Z directions are read. Then, a UDF file is imported to define the projectile's motion, assigning the following values ​​to the projectile's periodic pitch motion:

[0117] ;

[0118] in, Let θ be the pitch angle as a function of time t, and let the pitch angle amplitude be θ. A The initial angle is θ0 = 0º, the angular frequency is w = 16π rad / s, t is time, the vibration period is 0.125s, and the frequency is 8Hz. A transient simulation is performed. The dynamic mesh settings are: re-mesh (check "re-mesh"), mesh reconstruction interval is set to 1, time step is set to 0.001s, maximum number of iterations is set to 200, and time step count is set to 500.

[0119] In this invention, the method simulates angles of attack (0°, 2°, 5°, 10°, and 15°) at speeds ranging from Mach 0.5 to 2.5. Steady-state simulation applies a fixed angle of attack and rotational speed to the projectile, yielding all aerodynamic parameters except for the pitch damping coefficient. Magnus force and its torque can be derived from lateral forces and torques; lift and static torque can be derived from normal forces and torques; and roll damping force and torque can be derived from axial forces and torques. These aerodynamic parameters are then standardized and / or differentiated with respect to the angle of attack to obtain the aerodynamic derivatives. To calculate the pitch damping torque coefficient, the projectile undergoes a two-dimensional sinusoidal pitch motion. Data extraction from the transient calculation results yields the pitch damping torque coefficient.

[0120] For the calculation of the trajectory, please refer to Han Zipeng - External Ballistics of Projectiles and Rockets - Beijing Institute of Technology Press. This embodiment of the invention will not elaborate further. The motion of the projectile can be divided into the motion of the center of mass and rotation around the center of mass. The motion of the center of mass is determined by the theorem of motion of the center of mass, and the rotation around the center of mass is described by the theorem of angular momentum. To improve the readability of the trajectory equations, the vector equations of the center of mass motion are decomposed into the velocity coordinate system, and the vector equations of the motion around the center of mass are decomposed into the projectile axis coordinate system, resulting in a scalar equation system. The equations involved in the trajectory calculation include: the equations of motion of the projectile's center of mass in the velocity coordinate system, the equations of angular momentum of the projectile's rotation around the center of mass in the projectile axis coordinate system, the equations of motion of the projectile around the center of mass, the equations of rigid body motion, and the equations of the six-degree-of-freedom trajectory model. The fourth-order Runge-Kutta method (RK4) is used to solve the six-degree-of-freedom rigid body trajectory differential equations. This method discretizes the motion equations containing 12 state variables, including spatial coordinates, velocity components, Euler angles, and angular velocities, and performs time integration with a fixed step size. Each time step executes a four-stage iterative calculation: first, the initial derivative is calculated based on the current ballistic state; then, the intermediate state is predicted using a half-step method; and finally, the weighted update of the state variables is achieved using a full-step end-effector evaluation. A dynamic coupling of fluid dynamics and rigid body dynamics is realized through a three-dimensional aerodynamic parameter database of Mach number, angle of attack, and rotational speed calculated via real-time interpolation CFD.

[0121] Multi-condition crosswind ballistic analysis:

[0122] The above equations were written using Visual Studio. The system architecture adopts a modular design, constructing a four-layer system that includes kinematics solution, aerodynamic calculation, environmental modeling, and data output. Substituting crosswinds of 1-5 m / s, the projectile's height and lateral deflection are given at different pitch angles as it passes through the x-axis at 100m, 200m, 300m, and up to 1000m.

[0123] Taking a crosswind speed of 5 m / s as an example, Table 1 below shows the lateral deviation of the shot at a fixed length on the x-axis (ground coordinate system) for different shooting elevation angles, and Table 2 shows the projectile height at a fixed length, in meters.

[0124] Table 1 shows the lateral deflection of fire at various positions with different firing elevation angles at a wind speed of 5 m / s.

[0125]

[0126] Table 2 shows the projectile height at various locations with different firing elevation angles at a wind speed of 5 m / s.

[0127]

[0128] It can be seen that when the crosswind speed is 5 m / s, the lateral deviation of the shot increases significantly with the increase of the range, and the increase is faster at a longer range. At the same horizontal distance, the larger the pitch angle, the greater the lateral deviation. The lateral deviation is more significant at different pitch angles when the range is long. The lateral deviation is affected by both factors, showing the rule that the longer the range and the larger the pitch angle, the more significant the lateral deviation.

[0129] Next, we changed the shooting elevation angle to 0 degrees and conducted an experiment. Table 3 below shows the bullet lateral deviation within a range of 1000 meters under crosswinds of 0m / s to 4m / s.

[0130] Table 3 shows the firing lateral deflection at various positions with a 0-degree firing elevation angle under different wind speeds.

[0131]

[0132] As can be seen, when the wind speed is 0 m / s, the Magnus force caused by the projectile's rotation results in lateral deflection. Similarly, when the wind speed is fixed at a certain value, the lateral deflection increases significantly with increasing range, and the increase is faster at longer ranges. The greater the wind speed, the greater the lateral deflection.

[0133] To investigate the effect of crosswind changes on ballistic lateral deviation and whether the bullet is affected by inertia when the crosswind stops, two experiments were designed for comparison: Table 4 below shows the crosswind conditions for the first 500 meters as described above, and the crosswind conditions for the last 500 meters as described above; Table 5 below shows the crosswind conditions for the first 500 meters as described above, and the crosswind conditions for the last 500 meters as described above.

[0134] Table 4 shows the lateral deflection at various locations with a 0-degree pitch angle under different wind speeds.

[0135]

[0136] Table 5 shows the lateral deflection at various locations with a 0-degree pitch angle under different wind speeds.

[0137]

[0138] As shown in Tables 4 and 5, even when subjected to crosswinds at the halfway point, the bullets experiencing crosswinds in the first half of the trajectory deflect significantly more than those in the second half. This indicates that, due to inertia, bullets still experience substantial deviations in their subsequent trajectories when disturbed by crosswinds. The fact that the bullet's lateral deviation is greater in the latter 500 meters when exposed to wind than in the first 500 meters, possibly because the bullet's kinetic energy is lower in the latter 500 meters, suggests that its kinetic energy is lower at that point.

[0139] Meanwhile, it was noted that when the wind speed was fixed at a certain value, the lateral deviation increased significantly with increasing range, and the increase was faster at longer ranges. The initial hypothesis for this phenomenon is that it is due to time; as the range increases, the bullet's velocity decreases, and the time taken to travel different ranges becomes longer. Table 6 below shows the lateral deviation of the bullet at different wind speeds from 0.2 seconds, 0.4 seconds to 2 seconds at a 0-degree elevation angle.

[0140] Table 6 shows the lateral deflection at different times for a 0-degree pitch angle under different wind speeds.

[0141]

[0142] As shown in Table 6, before 1 second of flight time, the increase in lateral deflection gradually increases every 0.2 seconds. However, after 1 second, as time progresses, the increase in lateral deflection is almost constant every 0.2 seconds. This is likely because the change in velocity is very limited after 1 second, and the change in the bullet's kinetic energy is also very limited. Therefore, bullets with similar kinetic energy will produce similar lateral deflection when disturbed by crosswinds.

[0143] To investigate the importance of measuring wind speed at 50m intervals, the following experiment was designed: Within ten 100-meter intervals over a kilometer, the wind speed was uniformly varied from 5m / s to 1m / s (at 50m), and then uniformly varied from 1m / s back to 5m / s (at 100m). A control experiment was designed where the wind speed was kept constant at 5m / s.

[0144] Table 7 shows the lateral deflection at different times with a 0-degree pitch angle under varying wind speeds.

[0145]

[0146] The comparative analysis of data in Table 7 shows that the lateral deviation of the trajectory produced by the periodically changing crosswind environment (alternating between 5 m / s and 1 m / s) is significantly less than that under the constant 5 m / s wind speed condition. At a range of 1000 meters, the lateral deviation under the variable wind speed condition (8.753 m) is only 59.6% of that under the constant wind speed condition (14.687 m). This difference is mainly due to the periodic decrease in wind speed weakening the average intensity of the crosswind effect. It was also found that as the range increases, the difference in lateral deviation between the two conditions widens slightly, indicating that the influence of changing wind speed on the trajectory has a cumulative amplification effect.

[0147] Therefore, simply measuring the initial wind speed is far from sufficient; segmented wind speeds have a significant impact on bullet lateral deviation. To verify this conclusion, an experiment was designed with wind speeds of 5 m / s at 0-500 meters, 1 m / s at 500-700 meters, and 5 m / s at 700-1000 meters. Table 7 of the experiment was used as a control.

[0148] Table 8 shows the lateral deflection at different times for a 0-degree pitch angle under varying wind speeds.

[0149]

[0150] Under discontinuous crosswind conditions (5 m / s for the first 500 meters, 1 m / s for the middle 200 meters, and 5 m / s for the last 300 meters), the final lateral deviation of the projectile (12.656 m) still reached 86.2% of that under the constant wind speed condition of 5 m / s throughout the flight (14.687 m). This phenomenon reveals two important patterns: First, the brief decrease in wind speed in the middle section (1 m / s for 200 meters) can only partially offset the influence of the strong winds at the beginning and end, indicating that crosswind disturbance has a significant time cumulative effect; Second, when the projectile encounters a 5 m / s crosswind again in the final stage of flight (700-1000 meters), its average lateral deviation increase (0.329 m / 100 m) is slightly higher than that in the initial stage (0.294 m / 100 m), which reflects the moderating effect of the projectile's velocity decay on its crosswind sensitivity.

[0151] This invention, through systematic CFD simulation and six-degree-of-freedom ballistic calculations, reveals several key laws governing ballistic lateral deflection under crosswind disturbances. Specific experiments show that the projectile lateral deflection exhibits a significant nonlinear increase with increasing range. Under a 5 m / s crosswind, the lateral deflection at a range of 1000 meters can reach 14.7 meters, and the growth rate accelerates with increasing range. The pitch angle has a significant impact on the lateral deflection; the lateral deflection at a 45-degree pitch angle is more than twice that at 0 degrees, mainly due to the increased trajectory altitude and the longer exposure time to wind. Particularly noteworthy is the significant spatiotemporal cumulative effect of crosswind disturbances. The lateral deflection generated by wind disturbance at 1000 meters in the first half of the flight is 18.3% greater than that under the same conditions in the second half, indicating the persistence of the initial disturbance's influence. Furthermore, the wind speed distribution along the entire trajectory must be considered. These findings provide important theoretical basis for trajectory prediction and correction under complex weather conditions and have significant guiding significance for improving the accuracy of long-range firing.

[0152] This invention, through CFD simulation and six-degree-of-freedom ballistic modeling, reveals the fundamental laws governing ballistic deviation under crosswind conditions. The study found that the ballistic lateral deviation exhibits a significant nonlinear growth characteristic with increasing range, and this growth trend intensifies as the range extends. This invention particularly focuses on the influence of projectile attitude on lateral deviation, confirming that increasing the elevation angle significantly amplifies the crosswind disturbance effect. More importantly, this invention is the first to discover the spatiotemporal accumulation phenomenon of crosswind disturbance, meaning that wind disturbance in the initial stage of the trajectory has a persistent impact. These research results not only deepen the understanding of ballistic characteristics under complex meteorological conditions but also provide a solid theoretical foundation for developing precise ballistic correction methods, possessing significant guiding value and application prospects for improving the accuracy of long-range firing.

[0153] The trajectory of a sniper rifle is influenced by various factors, including temperature, air pressure, wind direction, wind speed, air humidity, angle of attack, projectile velocity, and gravity. Complex crosswind disturbances are a key environmental factor affecting long-range shooting accuracy. This invention, based on computational fluid dynamics (CFD) and a six-degree-of-freedom ballistic model, systematically studies the deflection characteristics of projectiles under different crosswind conditions. CFD numerical simulations were used to obtain aerodynamic parameters of the projectile at various angles of attack within the Mach 0.5–2.5 range, and a crosswind trajectory calculation model was established using rigid body dynamics equations. A three-dimensional lookup table of range, wind speed, and deflection was created to analyze the influence weight of each factor on the deflection. A comparative experiment with varying wind speeds was specifically designed to study the spatiotemporal cumulative effect of crosswind disturbances. Using this model reduces the error in the shooter's trajectory calculation, effectively improving the efficiency and accuracy of sniper rifle shooting. Snipers can quickly convert the table into their own shooting correction experience during this adjustment process. In live-fire training, snipers can use the aiming guidance provided by the crosswind trajectory calculation model to improve training efficiency. At the same time, it also provides a new guiding method for achieving rapid aiming and precise strikes in actual combat.

[0154] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention.

[0155] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A method for correcting the crosswind effect on sniper ballistics, characterized in that, Includes the following steps: Step S1: Establish a three-dimensional geometric model of the projectile, and use the CFD numerical simulation method to calculate the flow field of the projectile within a preset Mach number range and a preset angle of attack range based on the three-dimensional geometric model of the projectile. Calculate the forces and torques on the projectile in the flow field, and construct a database of projectile aerodynamic parameters containing multiple flight states. Step S2: Establish a six-degree-of-freedom rigid body ballistic model, which includes the equations of motion describing the translation of the center of mass and the dynamic equations describing the rotation about the center of mass; in the process of solving the six-degree-of-freedom rigid body ballistic model, according to the real-time flight state of the projectile, the corresponding aerodynamic parameters are dynamically obtained from the projectile aerodynamic parameter database, and the aerodynamic force and torque on the projectile are calculated based on the aerodynamic parameters to obtain an aerodynamically coupled ballistic solver; Step S3: After setting the environmental conditions, set the crosswind conditions, which include wind speed, wind direction, and the spatiotemporal distribution data of the two along the projectile's preset trajectory; using the crosswind conditions as the environmental input, run the aerodynamically coupled ballistic solver to solve the actual flight trajectory of the projectile, output the lateral offset of the projectile at multiple target range points, and obtain the solution results. Step S4: Based on the solution results, generate corrected data that reflects the relationship between target range, wind speed and lateral offset; The corrected data is queried based on the actual target range and actual wind speed to obtain the corresponding lateral offset. The aiming point of the sniper rifle is then corrected based on the obtained lateral offset.

2. The method for correcting the crosswind effect on sniper ballistics according to claim 1, characterized in that, In step S1, the CFD numerical simulation method adopts the Reynolds-averaged Navier-Stokes method, and the turbulence model adopts the Realizable-k-ε model; the preset Mach number range is 0.5 to 2.5, and the preset angle of attack range is 0 to 15 degrees.

3. The method for correcting the crosswind effect on sniper ballistics according to claim 2, characterized in that, The steps for constructing the projectile aerodynamic parameter database specifically include: Step a: Obtain the raw data and coefficients; Step b: Perform parameter processing on the original data and coefficients; Step c: Integrate the data obtained in steps a and b to construct the aerodynamic parameter database for the projectile; Specifically, step a includes: Step a1: Mesh the three-dimensional geometric model of the projectile to generate a structured mesh containing the boundary layer mesh; Step a2: Based on the structured grid, perform steady-state CFD calculations to obtain the discrete static aerodynamic forces and moment coefficients of the projectile at multiple different angles of attack as raw data; Step a3: Drive the projectile's three-dimensional geometric model to perform periodic pitching motion using a user-defined function, perform transient CFD calculations, and obtain the projectile's pitching damping moment coefficient.

4. The method for correcting the crosswind effect on sniper ballistics according to claim 3, characterized in that, Step b specifically includes: standardizing the original data and calculating the aerodynamic derivative used for ballistic calculation by differentiating or second-ordering the angle of attack.

5. The method for correcting the crosswind effect on sniper ballistics according to claim 4, characterized in that, The steps specifically include: integrating the original data, the pitch damping moment coefficient, and the aerodynamic derivative to form the projectile aerodynamic parameter database.

6. The method for correcting the crosswind effect on sniper ballistics according to claim 4, characterized in that, The definition and solution of the six-degree-of-freedom rigid body ballistic model in step S2 are based on the transformation of four coordinate systems: ground coordinate system, reference coordinate system, velocity coordinate system and projectile axis coordinate system; the motion state of the projectile is decomposed and described by Euler angle transformation between the four coordinate systems.

7. The method for correcting the crosswind effect on sniper ballistics according to claim 1 or 6, characterized in that, The solution of the six-degree-of-freedom rigid body ballistic model in step S2 adopts the fourth-order Runge-Kutta algorithm; in each step of the iterative solution of the six-degree-of-freedom rigid body ballistic model, the aerodynamic parameters at the current moment are obtained by real-time interpolation from the aerodynamic parameter database based on the current Mach number and angle of attack of the projectile.

8. The method for correcting the crosswind effect on sniper ballistics according to claim 1, characterized in that, In step S3, the crosswind conditions are modeled as a time sequence that includes wind speed and wind direction, set in segments along the preset trajectory of the projectile.

9. A sniper ballistic crosswind correction system, characterized in that, The system includes: The projectile aerodynamic parameter database unit is used to establish a three-dimensional geometric model of the projectile, and to calculate the flow field of the projectile within a preset Mach number range and a preset angle of attack range based on the CFD numerical simulation method, thereby constructing a projectile aerodynamic parameter database containing multiple flight states. An aerodynamically coupled ballistic solver unit is used to establish a six-degree-of-freedom rigid body ballistic model, which includes the equations of motion describing the translation of the center of mass and the dynamic equations describing the rotation about the center of mass. During the solution process of the six-degree-of-freedom rigid body ballistic model, the corresponding aerodynamic parameters are dynamically obtained from the projectile aerodynamic parameter database according to the real-time flight state of the projectile. Based on the aerodynamic parameters, the aerodynamic forces and torques acting on the projectile are calculated to obtain the aerodynamically coupled ballistic solver. The solution unit is used to set crosswind conditions, which include wind speed, wind direction, and spatiotemporal distribution data of the two along the preset trajectory of the projectile; using the crosswind conditions as environmental input, the aerodynamically coupled ballistic solver is run to solve the actual flight trajectory of the projectile, output the lateral offset of the projectile at multiple target range points, and obtain the solution results. The correction unit is used to generate correction data reflecting the correspondence between target range, wind speed and lateral offset based on the solution results; query the correction data according to the actual target range and actual wind speed to obtain the corresponding lateral offset; and correct the aiming point of the sniper rifle based on the obtained lateral offset.

10. A sniper ballistic crosswind correction device, characterized in that, It includes a memory and a processor, the memory being used to store a computer program, and the processor being used to execute the computer program to implement the sniper ballistic crosswind influence correction method as described in any one of claims 1 to 8.

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