Adapter pneumatic separation and trajectory prediction simulation analysis method and device

Abstract

The invention provides an adapter pneumatic separation and trajectory prediction simulation analysis method and device, and adopts a combined calculation method of dynamics, computational fluid mechanics and a six-degree-of-freedom trajectory calculation program. The method can comprehensively consider the influence of various factors such as the initial state of adapter separation, the separation force, the unboxing speed, the wind load and the shape of the adapter on the adapter separation process, effectively improves the simulation accuracy, reduces the use of simulation calculation resources, and reduces the simulation time.

Description

Technical Field

[0001] The invention relates to the technical field of dynamic characteristic analysis of a rocket hot launch process at sea, and in particular to an adapter aerodynamic separation and trajectory prediction simulation analysis method and device. Background Art

[0002] During the hot launch of a rocket at sea, an adapter is installed between the rocket and the launch frame rail to complete the functions of supporting, shock absorbing, guiding, and controlling the initial disturbance of the rocket during transportation and launch. Generally, the adapter will be separated from the rocket after it is taken out of the box. The separation of the adapter is affected by many factors such as separation force, box speed, wind load, and adapter shape. The scattering of adapters of some structural types is irregular, and its separation characteristics may have a negative impact on the flight dynamic characteristics of the rocket. During the separation process, it may collide with the surface of the rocket body for a second time, and may pose a certain threat to the launch platform and ground equipment when falling. Therefore, it is necessary to analyze the adapter separation process through simulation methods, identify risks in advance, and divide dangerous areas. The accuracy of the adapter separation simulation is very important for the overall design and planning of the equipment.

[0003] The existing adapter separation simulation analysis methods mainly include dynamic simulation and computational fluid dynamics simulation. The aerodynamic characteristics of the adapter are generally not considered during the adapter separation dynamics simulation process, and the influencing factors such as wind load and adapter shape cannot be considered during the simulation process, which will reduce the simulation accuracy; the adapter separation computational fluid dynamics simulation method uses dynamic grid technology, which requires more computing resources and takes a long time to simulate. Summary of the invention

[0004] The present invention aims to provide an adapter pneumatic separation and trajectory prediction simulation analysis method and device that overcomes the above problems or at least partially solves the above problems.

[0005] To achieve the above object, the technical solution of the present invention is specifically implemented as follows:

[0006] One aspect of the present invention provides an adapter pneumatic separation and trajectory prediction simulation analysis method, comprising:

[0007] Perform wind tunnel calculations on the adapter to generate aerodynamic parameter tables;

[0008] Performing a separation dynamics simulation calculation of the adapter to calculate an initial separation state of the adapter;

[0009] The adapter separation trajectory calculation is performed, and adapter motion process parameter data is output.

[0010] Optionally, performing numerical simulation wind tunnel calculation of the adapter to generate an aerodynamic parameter table includes:

[0011] The aerodynamic coefficient and aerodynamic moment coefficient of the adapter under different wind speeds and different motion postures are calculated, and the obtained speed, posture, aerodynamic coefficient and aerodynamic moment coefficient are compiled into the aerodynamic parameter table.

[0012] Optionally, the calculating of the aerodynamic force coefficient and aerodynamic moment coefficient of the adapter at different wind speeds and different motion postures, and compiling the obtained speeds, postures, aerodynamic force coefficients and aerodynamic moment coefficients into an aerodynamic parameter table comprises:

[0013] Calculating the x-, y- and z-direction component velocities according to different attitude angles of the adapter;

[0014] Modify the batch file in the computational fluid dynamics software and input the angle variable and the speed variable into the batch file;

[0015] Execute the modified batch file;

[0016] After the first-order difference format converges, save the first calculation result;

[0017] After the second-order difference format converges, save the second calculation result;

[0018] Reading aerodynamic coefficients from the first calculation result and the second calculation result files to create the aerodynamic coefficient table;

[0019] Determine whether all angles have been calculated. If not, return to execute the operation of calculating the x, y, and z direction component velocities according to the different posture angles of the adapter. If yes, the process ends.

[0020] Optionally, performing the adapter separation dynamics simulation calculation to calculate the adapter separation initial state includes:

[0021] Establishing a rocket adapter separation dynamics model in multi-body dynamics software, wherein the rocket adapter separation dynamics model includes a rocket body, an adapter, a launch frame, and ground equipment;

[0022] Establish mass properties, constraint relationships and load drivers;

[0023] The adapter separation initial state is calculated, and the adapter separation initial state includes: position, posture, speed and angular velocity.

[0024] Optionally, performing the adapter separation trajectory calculation and outputting adapter motion process parameter data includes:

[0025] Determine the adapter motion parameters at the current moment;

[0026] Calculate the current adapter force based on the aerodynamic data;

[0027] Iteratively solve the adapter motion parameters at the next moment based on the adapter 6DOF ordinary differential equations;

[0028] Determine whether the calculation has reached the termination condition;

[0029] If otherwise return to perform the operation of calculating the current adapter force based on the pneumatic data;

[0030] If yes, outputting adapter motion process parameter data is executed, and adapter motion data processing and motion visualization operations are performed according to the adapter motion process parameter data.

[0031] Another aspect of the present invention provides an adapter pneumatic separation and trajectory prediction simulation analysis device, comprising:

[0032] A generation module is used to perform numerical simulation wind tunnel calculations on the adapter and generate aerodynamic parameter tables;

[0033] A calculation module, used for performing a simulation calculation of the adapter separation dynamics and calculating an initial state of the adapter separation;

[0034] The output module is used to calculate the adapter separation trajectory and output adapter motion process parameter data.

[0035] Optionally, the generating module performs numerical simulation wind tunnel calculation of the adapter to generate an aerodynamic parameter table in the following manner:

[0036] The aerodynamic coefficient and aerodynamic moment coefficient of the adapter under different wind speeds and different motion postures are calculated, and the obtained speed, posture, aerodynamic coefficient and aerodynamic moment coefficient are compiled into the aerodynamic parameter table.

[0037] Optionally, the generation module calculates the aerodynamic force coefficient and aerodynamic moment coefficient of the adapter at different wind speeds and different motion postures in the following manner, and compiles the obtained speed, posture, aerodynamic force coefficient, and aerodynamic moment coefficient into an aerodynamic parameter table:

[0038] Calculating the x-, y- and z-direction component velocities according to different attitude angles of the adapter;

[0039] Modify the batch file in the computational fluid dynamics software and input the angle variable and the speed variable into the batch file;

[0040] Execute the modified batch file;

[0041] After the first-order difference format converges, save the first calculation result;

[0042] After the second-order difference format converges, save the second calculation result;

[0043] Reading aerodynamic coefficients from the first calculation result and the second calculation result files to create the aerodynamic coefficient table;

[0044] Determine whether all angles have been calculated. If not, return to execute the operation of calculating the x, y, and z direction component velocities according to the different posture angles of the adapter. If yes, the process ends.

[0045] Optionally, the calculation module performs the adapter separation dynamics simulation calculation to calculate the adapter separation initial state in the following manner:

[0046] Establishing a rocket adapter separation dynamics model in multi-body dynamics software, wherein the rocket adapter separation dynamics model includes a rocket body, an adapter, a launch frame, and ground equipment;

[0047] Establish mass properties, constraint relationships and load drivers;

[0048] The adapter separation initial state is calculated, and the adapter separation initial state includes: position, posture, speed and angular velocity.

[0049] Optionally, the output module performs the adapter separation trajectory calculation and outputs adapter motion process parameter data in the following manner:

[0050] Determine the adapter motion parameters at the current moment;

[0051] Calculate the current adapter force based on the aerodynamic data;

[0052] Iteratively solve the adapter motion parameters at the next moment based on the adapter 6DOF ordinary differential equations;

[0053] Determine whether the calculation has reached the termination condition;

[0054] If otherwise return to perform the operation of calculating the current adapter force based on the pneumatic data;

[0055] If yes, outputting adapter motion process parameter data is executed, and adapter motion data processing and motion visualization operations are performed according to the adapter motion process parameter data.

[0056] It can be seen that from the perspective of improving the accuracy of adapter separation simulation and reducing the demand for simulation computing resources, the adapter aerodynamic separation and trajectory prediction simulation analysis method and device provided by the present invention adopts a joint calculation method of dynamics, computational fluid dynamics, and a six-degree-of-freedom trajectory calculation program. It can comprehensively consider the influence of various factors on the adapter separation process, such as the initial state of adapter separation, separation force, out-of-box speed, wind load, and adapter shape, thereby effectively improving the simulation accuracy, reducing the use of simulation computing resources, and reducing the simulation time. BRIEF DESCRIPTION OF THE DRAWINGS

[0057] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying creative work.

[0058] Figure 1 A flow chart of the adapter pneumatic separation and trajectory prediction simulation analysis method provided by an embodiment of the present invention;

[0059] Figure 2 A schematic diagram of a numerical simulation wind tunnel calculation process provided by an embodiment of the present invention;

[0060] Figure 3 A schematic diagram of the flow chart of the adapter separation trajectory program provided by an embodiment of the present invention;

[0061] Figure 4 A schematic structural diagram of an adapter pneumatic separation and trajectory prediction simulation analysis device provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0062] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0063] The core of the present invention lies in: the present invention is based on multi-body dynamics software, computational fluid dynamics software, and a six-degree-of-freedom trajectory calculation program. During the dynamic simulation process of the multi-body dynamics software, the initial state of adapter separation is calculated and used as the input of the trajectory calculation. The trajectory calculation program calls the aerodynamic parameters of the adapter calculated by the computational fluid dynamics software corresponding to the adapter posture in real time to complete the simulation analysis of the adapter separation process taking into account factors such as different wind loads, different adapter postures, and different adapter shapes.

[0064] Figure 1 FIG. 1 is a flow chart showing the adapter pneumatic separation and trajectory prediction simulation analysis method provided by an embodiment of the present invention, see Figure 1 The adapter aerodynamic separation and trajectory prediction simulation analysis method provided by the embodiment of the present invention includes:

[0065] S1, perform numerical simulation wind tunnel calculation of the adapter and generate aerodynamic parameter table.

[0066] The present invention performs numerical simulation wind tunnel calculation of the adapter to generate an aerodynamic parameter table, including: calculating the aerodynamic force coefficient and aerodynamic moment coefficient of the adapter at different wind speeds and different motion postures, and compiling the obtained speed, posture, aerodynamic force coefficient, and aerodynamic moment coefficient into an aerodynamic parameter table. Specifically, the present invention calculates the aerodynamic force coefficient and aerodynamic moment coefficient of the adapter at different wind speeds and different motion postures, and compiles the obtained speed, posture, aerodynamic force coefficient, and aerodynamic moment coefficient into an aerodynamic parameter table for subsequent simulation calls.

[0067] As an optional implementation of the embodiment of the present invention, see Figure 2 The present invention calculates the aerodynamic coefficient and aerodynamic moment coefficient of the adapter at different wind speeds and different motion postures, and compiles the obtained speed, posture, aerodynamic coefficient, and aerodynamic moment coefficient into an aerodynamic parameter table including:

[0068] Calculate the velocity in the x, y and z directions according to the different attitude angles of the adapter;

[0069] Modify the batch file in the computational fluid dynamics software and input the angle variable and the speed variable into the batch file;

[0070] Execute the modified batch file;

[0071] After the first-order difference format converges, save the first calculation result;

[0072] After the second-order difference format converges, save the second calculation result;

[0073] Reading aerodynamic coefficients from the first calculation result and the second calculation result files to create an aerodynamic coefficient table;

[0074] Determine whether all angles have been calculated. If not, return to execute the operation of calculating the speed in the x, y, and z directions according to the different posture angles of the adapter. If so, the process ends.

[0075] When the numerical simulation wind tunnel calculation of the adapter of the present invention is specifically implemented, the separation and scattering relative speed of the adapter is generally 0m / s-50m / s, which belongs to a low-speed motion state. After preliminary calculation and analysis, the relevant aerodynamic parameters of the adapter do not change much with the relative speed. The aerodynamic parameters obtained when the wind speed is 10m / s are selected as the benchmark, so that the errors of all aerodynamic parameters are controlled within 1.5%, that is, the change of aerodynamic parameters with speed is not considered. The aerodynamic parameters obtained when the wind speed is 10m / s are selected as the standard, and only the change of aerodynamic parameters with the posture of the adapter is considered. According to the calculation results of the numerical simulation wind tunnel, an aerodynamic parameter table of the adapter in different postures can be formed to meet the calculation of the aerodynamic load during the separation process of the adapter.

[0076] S2, perform adapter separation dynamics simulation calculation to calculate the initial state of adapter separation.

[0077] The present invention performs adapter separation dynamics simulation calculation, and calculating the initial state of adapter separation includes: establishing a rocket adapter separation dynamics model in multi-body dynamics software, wherein the rocket adapter separation dynamics model includes a rocket body, an adapter, a launch frame, and ground equipment; establishing mass attributes, constraint relationships, and load drive; calculating the initial state of adapter separation, wherein the initial state of adapter separation includes: position, attitude, velocity, and angular velocity. Specifically, the present invention establishes a rocket adapter separation dynamics model in multi-body dynamics software, which generally includes relevant components such as a rocket body, an adapter, a launch frame, and ground equipment, and establishes mass attributes, constraint relationships, and load drive according to traditional dynamics simulation methods. Use multi-body dynamics software to obtain the initial state of adapter separation, including position, attitude, velocity, angular velocity, and the like.

[0078] When the adapter separation dynamics simulation calculation of the present invention is specifically implemented, a rocket adapter separation dynamics model is established in a multi-body dynamics software, which generally includes relevant components such as a rocket body, an adapter, a launch frame, and ground equipment. The mass attributes, constraint relationships, and rocket body thrust drive are established according to the traditional dynamics simulation method. By adjusting the rocket body thrust, different out-of-box speeds of the adapter can be achieved. The separation spring between the adapter and the rocket body is simulated by a unidirectional force. The relationship between the value of the separation unidirectional force and the distance between the adapter and the rocket body is defined according to the mechanical properties of the separation spring. The action phase of the separation unidirectional force is controlled by a simulation script to accurately simulate the separation process of the adapter. In this way, the initial state of the adapter separation can be obtained, including position, attitude, speed, angular velocity, etc.

[0079] S3, calculate the adapter separation trajectory and output the adapter motion process parameter data.

[0080] In the six-degree-of-freedom trajectory calculation program, the present invention uses the initial state of adapter separation in step S2 as the posture input for calculation, and obtains the posture and speed of the adapter in real time; and uses this to call the aerodynamic coefficients and aerodynamic torque coefficients of the corresponding posture and speed in the aerodynamic parameter table generated in step S1, and calculates the force and torque applied to the adapter according to relevant calculation formulas as the real-time force and torque input.

[0081] As an optional implementation of the embodiment of the present invention, see Figure 3 The present invention performs adapter separation trajectory calculation and outputs adapter motion process parameter data including:

[0082] Determine the adapter motion parameters at the current moment;

[0083] Calculate the current adapter force based on the aerodynamic data;

[0084] Iteratively solve the adapter motion parameters at the next moment based on the adapter 6DOF ordinary differential equations;

[0085] Determine whether the calculation has reached the termination condition;

[0086] If otherwise return to perform the operation of calculating the current adapter force based on the pneumatic data;

[0087] If yes, the adapter motion process parameter data is output, and the adapter motion data processing and motion visualization operations are performed according to the adapter motion process parameter data.

[0088] When the adapter separation trajectory calculation of the present invention is specifically implemented, the motion of the adapter in the free wind field can be simplified to the motion of a rigid body. Based on theoretical mechanics and rigid body dynamics related dynamic motion equations, a group of dynamic control equations for the wind-loaded motion of the adapter is constructed, and then the development of the adapter's 6DOF trajectory program is completed based on the 4th-order Longo Kutta display iteration algorithm. It can achieve (1) the input of the initial state of the three-dimensional motion posture and three-dimensional motion speed of the target adapter relative to the earth coordinate system; (2) according to the acquired posture and speed of the target adapter, the corresponding aerodynamic force coefficient and aerodynamic torque coefficient are called in the aerodynamic parameter table; (3) according to the called aerodynamic parameters, the speed information of the adapter, and the calculated environmental wind speed information, the three-dimensional forces and torques of the adapter are calculated and output in real time, and the aerodynamic force and aerodynamic torque under the corresponding speed and posture can be loaded on the target adapter in real time.

[0089] It can be seen that through the adapter aerodynamic separation and trajectory prediction simulation analysis method provided by the embodiment of the present invention, from the aspect of simulation accuracy, the adapter separation simulation analysis method involved in this patent can comprehensively consider the influence of multiple factors such as the initial state of adapter separation, separation force, out-of-box speed, wind load, adapter shape, etc. on the adapter separation process, thereby improving the simulation accuracy; from the aspect of simulation resource usage, the computing resources occupied by the adapter separation simulation analysis method involved in this patent are 30%-60% less than the computing resources required for calculations based solely on computational fluid dynamics methods or secondary development of computational fluid dynamics and dynamics software subroutines combined with calculations, thereby reducing the calculation time.

[0090] Figure 4 The schematic diagram of the structure of the adapter pneumatic separation and trajectory prediction simulation analysis device provided by the embodiment of the present invention is shown. The adapter pneumatic separation and trajectory prediction simulation analysis device applies the above method. The following is only a brief description of the structure of the adapter pneumatic separation and trajectory prediction simulation analysis device. For other matters not covered, please refer to the relevant description of the adapter pneumatic separation and trajectory prediction simulation analysis method. Figure 4 The adapter pneumatic separation and trajectory prediction simulation analysis device provided by the embodiment of the present invention comprises:

[0091] A generation module is used to perform numerical simulation wind tunnel calculations on the adapter and generate aerodynamic parameter tables;

[0092] A calculation module, used for performing adapter separation dynamics simulation calculation and calculating the adapter separation initial state;

[0093] The output module is used to calculate the adapter separation trajectory and output the adapter motion process parameter data.

[0094] As an optional implementation of the embodiment of the present invention, the generation module performs numerical simulation wind tunnel calculation of the adapter to generate an aerodynamic parameter table in the following manner:

[0095] The aerodynamic coefficient and aerodynamic moment coefficient of the adapter under different wind speeds and different motion postures are calculated, and the obtained speed, posture, aerodynamic coefficient and aerodynamic moment coefficient are compiled into an aerodynamic parameter table.

[0096] As an optional implementation of the embodiment of the present invention, the generation module calculates the aerodynamic coefficient and aerodynamic moment coefficient of the adapter at different wind speeds and different motion postures in the following manner, and compiles the obtained speed, posture, aerodynamic coefficient, and aerodynamic moment coefficient into an aerodynamic parameter table:

[0097] Calculate the velocity in the x, y and z directions according to the different attitude angles of the adapter;

[0098] Modify the batch file in the computational fluid dynamics software and input the angle variable and the speed variable into the batch file;

[0099] Execute the modified batch file;

[0100] After the first-order difference format converges, save the first calculation result;

[0101] After the second-order difference format converges, save the second calculation result;

[0102] Reading aerodynamic coefficients from the first calculation result and the second calculation result files to create an aerodynamic coefficient table;

[0103] Determine whether all angles have been calculated. If not, return to execute the operation of calculating the speed in the x, y, and z directions according to the different posture angles of the adapter. If so, the process ends.

[0104] As an optional implementation of the embodiment of the present invention, the calculation module performs adapter separation dynamics simulation calculation in the following manner to calculate the initial state of adapter separation:

[0105] A rocket adapter separation dynamics model is established in the multi-body dynamics software, wherein the rocket adapter separation dynamics model includes the rocket body, adapter, launch frame, and ground equipment;

[0106] Establish mass properties, constraint relationships and load drivers;

[0107] Calculate the initial state of the adapter separation, which includes: position, attitude, velocity and angular velocity.

[0108] As an optional implementation of the embodiment of the present invention, the output module performs adapter separation trajectory calculation and outputs adapter motion process parameter data in the following manner:

[0109] Determine the adapter motion parameters at the current moment;

[0110] Calculate the current adapter force based on the aerodynamic data;

[0111] Iteratively solve the adapter motion parameters at the next moment based on the adapter 6DOF ordinary differential equations;

[0112] Determine whether the calculation has reached the termination condition;

[0113] If otherwise return to perform the operation of calculating the current adapter force based on the pneumatic data;

[0114] If yes, the adapter motion process parameter data is output, and the adapter motion data processing and motion visualization operations are performed according to the adapter motion process parameter data.

[0115] It can be seen that, through the adapter aerodynamic separation and trajectory prediction simulation analysis device provided by the embodiment of the present invention, from the aspect of simulation accuracy, the adapter separation simulation analysis method involved in this patent can comprehensively consider the influence of various factors such as the initial state of adapter separation, separation force, out-of-box speed, wind load, adapter shape, etc. on the adapter separation process, thereby improving the simulation accuracy; from the aspect of simulation resource usage, the computing resources occupied by the adapter separation simulation analysis method involved in this patent are 30%-60% less than the computing resources required for calculations based solely on computational fluid dynamics methods or secondary development of computational fluid dynamics and dynamics software subroutines combined with calculations, thereby reducing the calculation time.

[0116] The above are only embodiments of the present application and are not intended to limit the present application. For those skilled in the art, the present application may have various changes and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included within the scope of the claims of the present application.

Claims

1. A method for analyzing adapter aerodynamic separation and trajectory prediction simulation, characterized in that: include: Perform wind tunnel calculations on the adapter to generate aerodynamic parameter tables; Performing a separation dynamics simulation calculation of the adapter to calculate an initial separation state of the adapter; The adapter separation trajectory calculation is performed, and adapter motion process parameter data is output.

2. The method according to claim 1, characterized in that: The performing of the numerical simulation wind tunnel calculation of the adapter to generate the aerodynamic parameter table comprises: The aerodynamic coefficient and aerodynamic moment coefficient of the adapter under different wind speeds and different motion postures are calculated, and the obtained speed, posture, aerodynamic coefficient, and aerodynamic moment coefficient are compiled into the aerodynamic parameter table.

3. The method according to claim 2, characterized in that The calculation of the aerodynamic coefficient and aerodynamic moment coefficient of the adapter at different wind speeds and different motion postures, and compiling the obtained speed, posture, aerodynamic coefficient, and aerodynamic moment coefficient into an aerodynamic parameter table includes: Calculating the x-, y- and z-direction component velocities according to different attitude angles of the adapter; Modify the batch file in the computational fluid dynamics software and input the angle variable and the speed variable into the batch file; Execute the modified batch file; After the first-order difference format converges, save the first calculation result; After the second-order difference format converges, save the second calculation result; Reading aerodynamic coefficients from the first calculation result and the second calculation result files to create the aerodynamic coefficient table; Determine whether all angles have been calculated. If not, return to execute the operation of calculating the x, y, and z direction component velocities according to the different posture angles of the adapter. If yes, the process ends.

4. The method according to claim 3, characterized in that The performing of the adapter separation dynamics simulation calculation to calculate the adapter separation initial state comprises: Establishing a rocket adapter separation dynamics model in multi-body dynamics software, wherein the rocket adapter separation dynamics model includes a rocket body, an adapter, a launch frame, and ground equipment; Establish mass properties, constraint relationships and load drivers; The adapter separation initial state is calculated, and the adapter separation initial state includes: position, posture, speed and angular velocity.

5. The method according to claim 4, characterized in that The performing of the adapter separation trajectory calculation and outputting the adapter motion process parameter data includes: Determine the adapter motion parameters at the current moment; Calculate the current adapter force based on the aerodynamic data; Iteratively solve the adapter motion parameters at the next moment based on the adapter 6DOF ordinary differential equations; Determine whether the calculation has reached the termination condition; If otherwise return to perform the operation of calculating the current adapter force based on the pneumatic data; If yes, outputting adapter motion process parameter data is executed, and adapter motion data processing and motion visualization operations are performed according to the adapter motion process parameter data.

6. An adapter pneumatic separation and trajectory prediction simulation analysis device, characterized in that: include: A generation module is used to perform numerical simulation wind tunnel calculations on the adapter and generate aerodynamic parameter tables; A calculation module, used for performing a simulation calculation of the adapter separation dynamics and calculating an initial state of the adapter separation; The output module is used to calculate the adapter separation trajectory and output adapter motion process parameter data.

7. The device according to claim 6, characterized in that The generation module performs numerical simulation wind tunnel calculation of the adapter to generate an aerodynamic parameter table in the following manner: The aerodynamic coefficient and aerodynamic moment coefficient of the adapter under different wind speeds and different motion postures are calculated, and the obtained speed, posture, aerodynamic coefficient, and aerodynamic moment coefficient are compiled into the aerodynamic parameter table.

8. The device according to claim 7, characterized in that The generation module calculates the aerodynamic coefficient and aerodynamic moment coefficient of the adapter at different wind speeds and different motion postures in the following manner, and compiles the obtained speed, posture, aerodynamic coefficient, and aerodynamic moment coefficient into an aerodynamic parameter table: Calculating the x-, y- and z-direction component velocities according to different attitude angles of the adapter; Modify the batch file in the computational fluid dynamics software and input the angle variable and the speed variable into the batch file; Execute the modified batch file; After the first-order difference format converges, save the first calculation result; After the second-order difference format converges, save the second calculation result; Reading aerodynamic coefficients from the first calculation result and the second calculation result files to create the aerodynamic coefficient table; Determine whether all angles have been calculated. If not, return to execute the operation of calculating the x, y, and z direction component velocities according to the different posture angles of the adapter. If yes, the process ends.

9. The device according to claim 8, characterized in that The calculation module performs the adapter separation dynamics simulation calculation to calculate the adapter separation initial state in the following manner: Establishing a rocket adapter separation dynamics model in multi-body dynamics software, wherein the rocket adapter separation dynamics model includes a rocket body, an adapter, a launch frame, and ground equipment; Establish mass properties, constraint relationships and load drivers; The adapter separation initial state is calculated, and the adapter separation initial state includes: position, posture, speed and angular velocity.

10. The device according to claim 9, characterized in that The output module calculates the adapter separation trajectory and outputs adapter motion process parameter data in the following manner: Determine the adapter motion parameters at the current moment; Calculate the current adapter force based on the aerodynamic data; Iteratively solve the adapter motion parameters at the next moment based on the adapter 6DOF ordinary differential equations; Determine whether the calculation has reached the termination condition; If otherwise return to perform the operation of calculating the current adapter force based on the pneumatic data; If yes, outputting adapter motion process parameter data is executed, and adapter motion data processing and motion visualization operations are performed according to the adapter motion process parameter data.

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