A method for correcting the fire control data of a high-velocity gun of a vehicle-mounted complex in a key area based on deformation variables

Abstract

The application provides a key point vehicle-mounted high gun fire control shooting parameter correction method based on a deformation variable, that is, firstly, a full-cannon finite element parameterized model is established, Isight software is combined with ABAQUS software, and an approximate model of the time length and the stable deformation amplitude when the chassis deformation reaches a stable state is constructed, secondly, a real-time deformation variable function taking a sine function as a base function is established, thirdly, the real-time chassis deformation variable is decomposed into a roll angle and a pitch angle, and finally, the roll angle and the pitch angle are used to correct target tracking data and parameter data in a fire control calculation process, so as to improve the accuracy of the key point vehicle-mounted high gun fire control shooting parameter. The principle of the application is clear, the method effectively solves the fire control parameter error problem caused by the attitude change of the vehicle body deformation during the shooting of the vehicle-mounted high gun, and provides a reference for the key point vehicle-mounted high gun fire control parameter correction.

Description

Technical Field

[0001] This invention belongs to the technical field of vehicle-mounted anti-aircraft gun weapon systems for key locations, specifically relating to a method for correcting the fire control firing parameters of a vehicle-mounted integrated anti-aircraft gun based on deformation. Background Technology

[0002] Anti-aircraft artillery systems, serving as the last line of defense in terminal air defense and missile defense, possess advantages such as a small firing arc, high rate of fire, short reaction time, and strong sustained strike capability. With the development of anti-aircraft artillery fire control technology, the firing accuracy of these systems has improved significantly, making direct-hit systems a possibility. However, any external factors causing firing errors will affect the system's hit probability. In vehicle-mounted integrated anti-aircraft artillery systems, chassis deformation caused by recoil is a critical factor influencing the hit probability. Therefore, for vehicle-mounted anti-aircraft artillery systems used in key positions, reducing the firing errors caused by chassis deformation due to recoil is beneficial for improving the accuracy of fire control calculations during firing, thereby increasing the system's hit probability.

[0003] Taking a vehicle-mounted integrated anti-aircraft gun weapon system at a key location as an example, the tracking sensor is installed on the anti-aircraft gun, which is mounted on the chassis of the vehicle. During combat use, the chassis needs to be leveled. The recoil generated during firing causes elastic deformation of the chassis. This deformation causes the integrated anti-aircraft gun mounted on the vehicle to tilt upwards in the firing direction. To maintain stable tracking of the target, the tracking sensor on the gun will quickly "drag its head down." The fire control equipment interprets this action as the target moving downwards, resulting in a sudden change in the elevation aiming angle during fire control calculations. This causes a significant error in target prediction and hit determination, leading to a substantial decrease in firing accuracy. Therefore, to improve the firing accuracy of the anti-aircraft gun, researching how to obtain real-time chassis deformation and how to correct it in fire control calculations is of great significance for improving the system's firing accuracy.

[0004] Traditional engineering methods for correcting vehicle deformation involve using trigonometric models to compensate only for the elevation angles of the tracking sensors during the deformation process (from the start of deformation to deformation stabilization). Once deformation stabilizes, no further corrections are made. This method is heavily reliant on human experience and lacks effective mathematical models and methods. Furthermore, some vehicle-mounted anti-aircraft gun systems in key locations completely ignore chassis deformation during firing, resulting in limited accuracy or even failure to hit targets during live-fire exercises. Summary of the Invention

[0005] In view of this, the purpose of this invention is to provide a method for correcting the fire control firing parameters of anti-aircraft guns in key vehicle-mounted complexes based on deformation.

[0006] A method for correcting the firing parameters of anti-aircraft guns in key vehicle-mounted complexes based on deformation variables, comprising:

[0007] Step 1: Establish a finite element parametric model of the entire gun;

[0008] Step 2: Establish a polynomial response surface approximation model for the duration of chassis deformation reaching a steady state and the stable deformation:

[0009]

[0010]

[0011] Where, γ p For elevation angles, λ represents the azimuth angle, and λ represents the radio frequency mode. This is an approximate model of the deformation response steady-state time. For the approximate model of deformation amplitude, m i n i k i g i h i f i Let be the fitting coefficients of the i-th order, a and b be constants, and M and N be the orders of the polynomial functions;

[0012] Step 3: Using the elevation and azimuth angles of the anti-aircraft gun as input variables, the vehicle deformation as the response, and a sine function as the basis function, establish a function of real-time chassis deformation versus time:

[0013]

[0014] Step 4: Decompose the real-time deformation of the chassis along the direction of the vehicle's front and perpendicular to the direction of the vehicle's front to obtain the lateral and longitudinal tilt angles of the anti-aircraft gun base relative to the horizontal plane, specifically including:

[0015] Let α be the angle between the vehicle's stable plane and the inclined plane, which is the amount of vehicle deformation △(t);

[0016] Decompose angle α into a lateral tilt angle θ perpendicular to the direction of the vehicle's nose in the horizontal plane and a longitudinal tilt angle ψ in the direction of the vehicle's nose. Let β be the angle between the tilting plane in the tilting direction and the direction of the vehicle's nose. Then the magnitude of the longitudinal tilt angle is:

[0017] ψ = arcsin(sinα·cosβ)

[0018] The tilt angle is:

[0019] θ = arcsin(sinα·sinβ)

[0020] Step 5: During fire control calculations, the fire control equipment utilizes the vehicle heading angle C. wThe tilt angle θ and pitch angle ψ are used to perform coordinate transformation on the target tracking data, changing the target position (x, y, z) from the vehicle's unstable coordinate system to the vehicle's geographic coordinate system, as follows:

[0021]

[0022] in:

[0023]

[0024]

[0025]

[0026] Step 6: The fire control equipment uses the vehicle heading angle, lateral tilt angle and longitudinal tilt angle to perform coordinate transformation on the data in the vehicle geographic coordinate system obtained by the fire control solution, so as to obtain the data in the unstable coordinate system of the vehicle, and sends it to the anti-aircraft gun in real time.

[0027] Among them, the fire control calculation obtains the azimuth angle γ and elevation angle of stable data in the vehicle geographic coordinate system. Decompose it into a Cartesian coordinate system based on the vehicle's geographic coordinate system, and represent it as:

[0028]

[0029] Then, through vehicle orientation transformation M Cw Pitch transformation M ψ , tilt transformation M θ The azimuth angle γ of the data converted into the vehicle-mounted unstable coordinate system b and elevation angle Represented as:

[0030]

[0031] Obtain the azimuth angle γ of the data in the unstable vehicle coordinate system. b and elevation angle

[0032]

[0033] This completes the correction of parameters.

[0034] Preferably, in step 1, a finite element parametric model of the entire gun is established in the finite element software ABAQUS; wherein, the chassis, as a key deformation component, is discretized as a flexible body component using shell elements.

[0035] Preferably, step 2 establishes an approximate model of the time it takes for the chassis deformation to reach a stable state and the stable deformation quantity, specifically including:

[0036] (a) Generate sample data using experimental design methods based on variable constraints:

[0037] Independent variable: The vehicle's attitude response during the firing process of the vehicle-mounted anti-aircraft gun is related to the firing angle, with the elevation angle γ as the independent variable. p and azimuth As the independent variable;

[0038] (b) Integrate the ABAQUS parametric program into the Isight software interface to establish an automated simulation process. Integrate the Design of Experiments (DOE) module, the approximate modeling module, and the external analysis interface module together. In the Design of Experiments (DOE) module, establish firing angle sample data. Integrate the full gun parametric model file into the external analysis interface module. Perform dynamic simulation analysis based on the firing angle sample data generated by the Design of Experiments module.

[0039] (c) Extract the duration and magnitude of the stable deformation of the chassis deformation corresponding to the sample data through the ABAQUS software post-processing module, and establish a polynomial response surface approximation model of the duration and magnitude of the stable deformation of the chassis deformation.

[0040] Preferably, in step 2,

[0041] Establish constraints:

[0042] Where, γ min As the lower limit of elevation angle, γ max This is the upper limit of the elevation angle; The left limit of the azimuth angle. This is the right limit of the azimuth angle.

[0043] The present invention has the following beneficial effects:

[0044] This invention addresses the problem of fire control data errors caused by attitude changes due to vehicle deformation during firing of vehicle-mounted anti-aircraft guns. It proposes a deformation-based method for correcting fire control firing data for vehicle-mounted anti-aircraft guns in key positions. First, a finite element parameterized model of the entire gun is established. Isight and ABAQUS software are combined to construct an approximate model of the duration and amplitude of the stable deformation of the chassis. Second, a real-time deformation function is established using a sine function as the basis function. Third, the real-time chassis deformation is decomposed into heel and pitch angles. Finally, during fire control calculations, the heel and pitch angles are used to correct target tracking data and data parameters in real time, thereby improving the accuracy of fire control firing data for vehicle-mounted anti-aircraft guns in key positions. The principle of this invention is clear, and this method effectively solves the problem of fire control data errors caused by attitude changes due to vehicle deformation during firing of vehicle-mounted anti-aircraft guns, providing a reference for the correction of fire control data for vehicle-mounted anti-aircraft guns in key positions. Attached Figure Description

[0045] Figure 1 This is the specific implementation procedure for correcting the fire control parameters of the vehicle-mounted anti-aircraft gun of the present invention.

[0046] Figure 2 A schematic diagram of the finite element model of key components of a vehicle-mounted anti-aircraft gun for key locations.

[0047] Figure 3 Create an architecture diagram for the approximate model.

[0048] Figure 4 This is a schematic diagram of the chassis deformation curve.

[0049] Figure 5 This is a schematic diagram of the vehicle body attitude angle vector decomposition.

[0050] Figure 6 This is a schematic diagram illustrating the coordinate transformation of target tracking data and metadata.

[0051] Figure 7 Design a distribution map of sampled data for the experiment. Detailed Implementation

[0052] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0053] A method for correcting the firing parameters of a vehicle-mounted anti-aircraft gun for key positions based on deformation is proposed. First, a finite element parameterized model of the entire gun is established. Then, Isight and ABAQUS software are combined to construct an approximate model of the duration and amplitude of the stable deformation when the chassis deformation reaches a steady state. Next, a real-time deformation function is established using a sine function as the basis function. Then, the real-time chassis deformation is decomposed into heel and pitch angles. Finally, during the fire control calculation process, the heel and pitch angles are used to correct the target tracking data and parameter data in real time, thereby improving the accuracy of the firing parameters of the vehicle-mounted anti-aircraft gun for key positions.

[0054] Step 1: Establish a full-gun finite element parametric model in the finite element software ABAQUS.

[0055] Among these methods, a full-gun finite element parametric model was established using the finite element software ABAQUS. For example... Figure 2 As shown, the frame, as a key deformation component, is discretized as a flexible body using shell elements. A parametric model file (.py file) was written using Python secondary development.

[0056] Step 2: Integrate the ABAQUS parametric program file into the Isight software interface to establish an automatic simulation process. Based on the variable constraints, use experimental design methods to generate sample data. Extract the duration and magnitude of the stable deformation corresponding to the chassis deformation from the sample data using the software post-processing module. Then, establish an approximate model of the duration and magnitude of the stable deformation when the chassis deformation reaches a stable state. Specifically, this includes:

[0057] (a) Based on the variable constraints, use experimental design methods to generate sufficient sample data.

[0058] Independent variable: The vehicle's attitude response during the firing process of the vehicle-mounted anti-aircraft gun is related to the firing angle, with the elevation angle γ as the independent variable. p and azimuth As the independent variable;

[0059] Establish constraints:

[0060] Among them, g min As the lower limit of the elevation angle, g max This is the upper limit of the elevation angle; The left limit of the azimuth angle. This is the right limit of the azimuth angle;

[0061] (b) Integrate ABAQUS parameterized program files into the Isight software interface to establish an automatic simulation process.

[0062] like Figure 3 As shown, an automated simulation process is established by integrating the Design of Experiments (DOE) module, the Approximation module, and the external analysis interface (Simcode) module. The DOE DOE DOE module generates sample data of firing angles, and the Simcode module integrates the full gun parametric model file .py. Based on the sample data generated by the DOE, dynamic simulation analysis is automatically performed.

[0063] (c) Extract the duration and magnitude of the stable deformation of the chassis corresponding to the sample data from the ABAQUS software post-processing module, and establish a polynomial response surface approximation model of the duration and magnitude of the stable deformation of the chassis when it reaches a stable state:

[0064]

[0065]

[0066] Among them, g p For elevation angles, λ represents the azimuth angle, and λ represents the radio frequency mode, which can be type I, type II, or type III. This is an approximate model of the deformation response steady-state time. For the approximate model of deformation amplitude, m i n i k i g i h i f idenoted as the i-th order fitting coefficient, where a and b are constants, and M and N are the orders of the polynomial function. The order is related to the number of variables and the sample size. The order can be first, second, third, fourth, or higher. The higher the order, the stronger the ability to approximate the nonlinear function.

[0067] Step 3: Based on the chassis deformation curve characteristics obtained from the sample data analysis, and using the sine function as the basis function, establish a function of real-time chassis deformation versus time, specifically as follows:

[0068] Using the elevation and azimuth angles of the anti-aircraft gun as input variables and the vehicle body deformation as the response, a function of the real-time deformation of the chassis versus time is established using a sine function as the basis function.

[0069] Let time t be the independent variable of the function, and the deformation law of the vehicle body is as follows: Figure 4 Based on the characteristics of the deformation curve, a sine function is selected as the basis function and characteristic function to obtain the characterization of the vehicle body deformation Δ(t):

[0070]

[0071] Step 4: Decompose the real-time deformation of the chassis along the direction of the vehicle's front and perpendicular to the direction of the vehicle's front to obtain the lateral and longitudinal tilt angles of the anti-aircraft gun base relative to the horizontal plane. Specifically, this includes:

[0072] Define the vehicle geographic coordinate system OX n Y n Z n Let O be the center of the anti-aircraft gun base, and OX be the origin O. n Axis and OY n The plane formed by the axes OY is parallel to the horizontal plane. n The axis pointing due north is positive, OX n Axis and OY n The axis is vertical, and the direction pointing due east is positive, OZ. n Axis and OX n Axis, OY n The axes form a right-handed coordinate system. Define the vehicle's stable coordinate system OX. w Y w Z w Let O be the center of the anti-aircraft gun base, and OX be the origin O. w Axis and OY w The plane formed by the axes OY is parallel to the horizontal plane. w The axis pointing in the direction of the car's front is positive, OX w Axis and OY w The axis is vertical, pointing to the right side of the vehicle body as positive, OZ w Axis and OX w Axis, OY w The axes form a right-handed coordinate system. Define the unstable coordinate system OX for the vehicle. b Yb Z b Let O be the center of the anti-aircraft gun base, and OX be the origin O. b Axis and OY b The plane formed by the axes is parallel to the vehicle plane, OY b The axis points towards the front of the car, OX b Axis and OY b The axis is vertical, pointing to the right side of the vehicle body as positive, OZ b Axis and OX b Axis, OY b The axes form a right-handed coordinate system.

[0073] like Figure 5 As shown, when the anti-aircraft gun is not firing, the plane on which the anti-aircraft gun base is located is horizontal. However, when the anti-aircraft gun is firing, because the anti-aircraft gun base is fixed to the vehicle body, the deformation of the vehicle body causes the plane on which the anti-aircraft gun base is located to no longer be horizontal, but rather an inclined plane with a certain angle relative to the horizontal plane. The angle between the inclined plane and the horizontal plane is α, which is numerically equivalent to the deformation of the vehicle body Δ(t). It is assumed that the position of the center point O of the anti-aircraft gun base remains unchanged before and after deformation. The angle α between the inclined plane and the horizontal plane is decomposed along the direction of the vehicle head and perpendicular to the direction of the vehicle head in the vehicle plane, into the lateral tilt angle θ (positive for the left side of the vehicle body facing upward) and the longitudinal tilt angle ψ (positive for the front of the vehicle body facing upward) of the anti-aircraft gun base relative to the horizontal plane. The direction of the angle between the inclined plane and the horizontal plane corresponds to the azimuth direction β of the anti-aircraft gun, which is a known quantity. In the unstable coordinate system OX of the vehicle... b Y b Z b Inside, in X b OY b Unit circles are defined on the plane. Let point M be the intersection of the inclined plane and its unit circle along the inclined direction. Points M1 and M2 are the points on the OY plane, respectively. b Direction, OX b The intersection point of the direction with the unit circle of the inclined plane. Draw a perpendicular line from point M to the vehicle's stable plane, with the foot of the perpendicular at N. Connect OM and ON. Then ∠MON is the inclination angle α between the two planes. Draw perpendicular lines from point M1 to the stable plane and the line of intersection of the two planes, with the feet of the perpendiculars at N1 and O1 respectively. Connect O1N1. ∠M1O1N1=α. Similarly, we can obtain ∠M2O2N2=α.

[0074] According to geometric relationships:

[0075] In △M1O1N1

[0076]

[0077]

[0078]

[0079] Combining the above formulas, we can obtain:

[0080] sinψ=sinα·cosβ

[0081] Therefore, the pitch angle is:

[0082] ψ = arcsin(sinα·cosβ)

[0083] In △M2O2N2

[0084]

[0085]

[0086]

[0087] Combining the above formulas, we can obtain:

[0088] sinθ=sinα·sinβ

[0089] Therefore, the magnitude of the tilt angle is:

[0090] θ = arcsin(sinα·sinβ)

[0091] Step 5: During fire control calculation, the fire control equipment uses the vehicle heading angle, lateral tilt angle, and longitudinal tilt angle to perform coordinate transformation on the target tracking data to obtain the target data under the vehicle's geographical coordinates, and then performs filtering and hit detection.

[0092] For integrated anti-aircraft guns, such as Figure 6 The diagram shows the target tracking data and the coordinate transformation of the data. The tracking sensor tracks the target in the bracket coordinate system. First, the target position should be transformed to the unstable vehicle coordinate system through coordinate transformation and baseline correction, obtaining (x, y, z). However, since the fire control solution for hitting the target is usually performed in the stable vehicle geographic coordinate system, it is necessary to transform the tracking data to the vehicle geographic coordinate system through inverse roll angle transformation, inverse pitch angle transformation, and inverse vehicle orientation transformation, denoted as (x...). d ,y d ,z d Then, in the vehicle's geographic coordinate system, the fire control system calculates the target motion parameters and the hit rate.

[0093] Remember C w The azimuth angle is the angle from due north, clockwise to the direction of the vehicle's front. This is due to the transformation M from the vehicle's geographic coordinate system to the unstable vehicle coordinate system. Cw Pitch transformation M ψ , tilt transformation M θ It consists of three steps, with the following transformation matrices:

[0094]

[0095]

[0096]

[0097] Therefore, the transformation matrix from the vehicle's geographic coordinate system to its unstable coordinate system is M. d M d =M θ ·M ψ ·M Cw Therefore, the transformation from the vehicle's unstable coordinate system to the vehicle's geographic coordinate system consists of three steps: inverse lateral tilt transformation, inverse longitudinal tilt transformation, and inverse vehicle orientation transformation, with the transformation matrix being M. d -1 M d -1 =(M θ ·M ψ ·M Cw ) -1 .

[0098]

[0099] Step 6: The fire control equipment uses the vehicle heading angle, lateral tilt angle and longitudinal tilt angle to perform coordinate transformation on the data in the vehicle geographic coordinate system obtained by the fire control solution, so as to obtain the data in the unstable coordinate system of the vehicle, and sends it to the anti-aircraft gun in real time.

[0100] like Figure 6 The diagram shows the coordinate transformation of target tracking data and data parameters. The fire control system calculates the stable data parameters azimuth angle g and elevation angle in the vehicle's geographic coordinate system. Decompose it into a Cartesian coordinate system based on the vehicle's geographic coordinate system, and represent it as:

[0101]

[0102] Then, through vehicle orientation transformation M Cw Pitch transformation M ψ , tilt transformation M θ Convert data to data in the vehicle-unstable coordinate system γ b and Represented as:

[0103]

[0104] Thus, the following data are obtained in the unstable coordinate system of the vehicle:

[0105]

[0106] The following description uses a vehicle-mounted anti-aircraft gun weapon system in a key location as an example:

[0107] In step 2, the elevation angle of a certain vehicle-mounted anti-aircraft gun ranges from 0° to 75°, and the azimuth angle ranges from -120° to 120°.

[0108] Then the constraints are:

[0109] Simulation conditions were established using optimal Latin hypercube experimental design, such as... Figure 7 As shown, a total of 20 simulation samples were established. An automated simulation process was created by integrating the ABAQUS interface into the Isight software. Numerical simulations were performed on the sample conditions in step 2, that is, the parameterized model file (.py) was integrated with the Isight software interface to establish an automated simulation process. The duration and magnitude of the stable deformation of the chassis corresponding to the sample data were extracted using the software's post-processing module. An approximate modeling method was used to establish a polynomial response surface model of the anti-aircraft gun firing angle and the duration and magnitude of the stable deformation of the chassis. To ensure the accuracy of the approximate model, the order of the constructed polynomial functions was all fourth order.

[0110] Table 1 shows the relationship between the vehicle deformation amplitudes of all samples when the firing frequency is Type I, i.e., 3000 rounds / min.

[0111] Table 1. Relevant data on firing frequency for Type I.

[0112]

[0113] A fourth-order polynomial response surface approximation model of the relationship between the duration of chassis deformation reaching a steady state and the anti-aircraft gun firing angle:

[0114] A fourth-order polynomial response surface approximation model between chassis stability deformation and anti-aircraft gun firing angle:

[0115]

[0116] Table 2 shows the elevation and elevation miss rates of the first 20 shots from a vehicle-mounted anti-aircraft gun weapon system at a key location, with and without correction for chassis deformation, and with correction using the method of this patented invention. The results show a significant improvement in elevation and elevation miss rates.

[0117] Table 2 compares the height and target miss distances with and without chassis deformation correction.

[0118] Average high and low miss distance 2.43 1.51 37.8

[0119] Furthermore, without the modified algorithm, the system conducted two live-fire tests against the air, missing the target in one test and hitting the target with only one shot in the other, without shooting it down. After adopting the algorithm of this patented invention, the system conducted three live-fire tests, shooting down the target in all three.

[0120] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for correcting firing parameters of anti-aircraft guns in key vehicle-mounted complexes based on deformation, characterized in that, include: Step 1: Establish a finite element parametric model of the entire gun; Step 2: Establish a polynomial response surface approximation model for the duration of chassis deformation reaching a steady state and the stable deformation: Among them, g p For elevation angles, λ represents the azimuth angle, and λ represents the radio frequency mode. This is an approximate model of the deformation response steady-state time. For the approximate model of deformation amplitude, m i n i k i g i h i f i Let be the fitting coefficients of the i-th order, a and b be constants, and M and N be the orders of the polynomial functions; Step 3: Using the elevation and azimuth angles of the anti-aircraft gun as input variables, the vehicle deformation as the response, and a sine function as the basis function, establish a function of real-time chassis deformation versus time: Step 4: Decompose the real-time deformation of the chassis along the direction of the vehicle's front and perpendicular to the direction of the vehicle's front to obtain the lateral and longitudinal tilt angles of the anti-aircraft gun base relative to the horizontal plane, specifically including: Let α be the angle between the vehicle's stable plane and the inclined plane, which is the amount of vehicle deformation △(t); Decompose angle α into a lateral tilt angle θ perpendicular to the direction of the vehicle's nose in the horizontal plane and a longitudinal tilt angle ψ in the direction of the vehicle's nose. Let β be the angle between the tilting plane in the tilting direction and the direction of the vehicle's nose. Then the magnitude of the longitudinal tilt angle is: ψ = arcsin(sinα·cosβ) The tilt angle is: θ = arcsin(sinα·sinβ) Step 5: During fire control calculations, the fire control equipment utilizes the vehicle heading angle C. w The tilt angle θ and pitch angle ψ are used to perform coordinate transformation on the target tracking data, changing the target position (x, y, z) from the vehicle's unstable coordinate system to the vehicle's geographic coordinate system, as follows: in: Step 6: The fire control equipment uses the vehicle heading angle, lateral tilt angle and longitudinal tilt angle to perform coordinate transformation on the data in the vehicle geographic coordinate system obtained by the fire control solution, so as to obtain the data in the unstable coordinate system of the vehicle, and sends it to the anti-aircraft gun in real time. Among them, the fire control calculation obtains the azimuth angle γ and elevation angle of stable data in the vehicle geographic coordinate system. Decompose it into a Cartesian coordinate system based on the vehicle's geographic coordinate system, and represent it as: Then, through vehicle orientation transformation M Cw Pitch transformation M ψ , tilt transformation M θ The azimuth angle γ of the data converted into the vehicle-mounted unstable coordinate system b and elevation angle Represented as: Obtain the azimuth angle γ of the data in the unstable vehicle coordinate system. b and elevation angle This completes the correction of parameters.

2. The method for correcting the firing parameters of anti-aircraft guns in key vehicle-mounted complexes based on deformation variables as described in claim 1, characterized in that, In step 1, a finite element parametric model of the entire gun is established in the finite element software ABAQUS; the chassis, as a key deformation component, is discretized as a flexible body component using shell elements.

3. The method for correcting the firing parameters of anti-aircraft guns in key vehicle-mounted complexes based on deformation variables as described in claim 1, characterized in that, Step 2 establishes an approximate model of the time it takes for the chassis deformation to reach a stable state and the amount of stable deformation, specifically including: (a) Generate sample data using experimental design methods based on variable constraints: Independent variable: The vehicle's attitude response during the firing process of the vehicle-mounted anti-aircraft gun is related to the firing angle, with the elevation angle γ as the independent variable. p and azimuth As the independent variable; (b) Integrate the ABAQUS parametric program into the Isight software interface to establish an automated simulation process. Integrate the Design of Experiments (DOE) module, the approximate modeling module, and the external analysis interface module together. In the Design of Experiments (DOE) module, establish firing angle sample data. Integrate the full gun parametric model file into the external analysis interface module. Perform dynamic simulation analysis based on the firing angle sample data generated by the Design of Experiments module. (c) Extract the duration and magnitude of the stable deformation of the chassis deformation corresponding to the sample data through the ABAQUS software post-processing module, and establish a polynomial response surface approximation model of the duration and magnitude of the stable deformation of the chassis deformation.

4. The method for correcting the firing parameters of anti-aircraft guns in key vehicle-mounted complexes based on deformation variables as described in claim 3, characterized in that, In step 2, Establish constraints: Where, γ min As the lower limit of elevation angle, γ max This is the upper limit of the elevation angle; This is the left limit of the azimuth angle. This is the right limit of the azimuth angle.

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