Folding wing locking mechanism equivalent modeling method and system based on ABAQUS secondary development

Abstract

The invention discloses a folding wing locking mechanism equivalent modeling method and system based on ABAQUS secondary development, and relates to the technical field of missile folding wing simulation analysis. The method comprises the following steps: constructing a folding wing finite element model based on ABAQUS software, pre-processing the model, and submitting and solving the model; and performing simulation analysis on the folding wing model by utilizing an Abaqus-Python secondary development function, simulating an unfolding and locking process of the gas actuating cylinder type folding wing, outputting unfolding angles at typical positions at different moments, and obtaining a solved INP file. Under different load working conditions, by automatically submitting, calculating and reading the unfolding time of rotation in place, modifying an original INP file and triggering and locking after unfolding at a specific angle, the method can adapt to different pulse force amplitudes and different impact force acting time, the time of complex entity modeling of a traditional locking mechanism is saved, and rapid simulation analysis is achieved.

Description

Technical Field

[0001] The invention relates to the technical field of missile folding wing simulation analysis, and in particular to an equivalent modeling method and system for a folding wing locking mechanism based on secondary development of ABAQUS. Background Art

[0002] With the continuous advancement of modern aerospace technology, folding wing technology is increasingly used in hypersonic aircraft, missiles and other fields. Especially in hypersonic flight environments above Mach 7, folding wings can provide excellent flight performance and maneuverability. However, the smooth deployment of the folding wing mechanism under such extremely unstable external load conditions will severely test the structural strength and functional reliability of the mechanism. In order to study the deployment rate evaluation, impact response analysis and locking oscillation of the folding wing mechanism under different impulse forces, it is necessary to simplify the modeling of the folding wing locking mechanism.

[0003] Currently, a series of numerical analysis and experimental research methods have been developed for the dynamic analysis and reliability design of folding wing mechanisms. Finite element simulation analysis can reduce design costs and provide guidance for ground tests. ABAQUS, as a powerful engineering simulation software, is widely used in the structural simulation of folding wing mechanisms. However, the folding wing involves complex nonlinear dynamic behaviors during the deployment process, and the locking mechanism and its connecting entities are complex to model. Therefore, we propose an equivalent modeling method and system for the folding wing locking mechanism based on the secondary development of ABAQUS. Summary of the invention

[0004] The purpose of the present invention is to provide an equivalent modeling method and system for a folding wing locking mechanism based on secondary development of ABAQUS, so as to realize simulation analysis of the folding wing deployment and locking process and improve the efficiency of modeling and analysis.

[0005] According to a first aspect of the present invention, in order to achieve the above-mentioned purpose, the present invention provides the following technical solution: an equivalent modeling method of a folding wing locking mechanism based on secondary development of ABAQUS comprises the following steps:

[0006] Construct a folding wing finite element model based on ABAQUS software, pre-process the model, and submit it for solution;

[0007] The Abaqus-Python secondary development function is used to simulate the folding wing model, simulate the gas-actuated cylinder folding wing deployment and locking process, output the deployment angles at the shaft at different times, and obtain the solved INP file;

[0008] According to the obtained angle and time data, the cubic spline interpolation method is used to calculate the deployment time of the folding wings when rotating at a specific angle. The deployment time in the INP file is modified and the calculation is resubmitted to release the pin after the folding wings are deployed at a specific angle.

[0009] Furthermore, the folding wing finite element model constructed based on ABAQUS software includes an inner wing, an outer wing, a rotation axis and four latches.

[0010] Furthermore, the folding wing finite element model is pre-processed as follows:

[0011] (31) Building each component according to predetermined dimensions of the inner wing, outer wing, shaft, and latch;

[0012] (32) Assign material properties: Using composite materials, input density, elastic modulus, and Poisson’s ratio.

[0013] Furthermore, the folding wing model is simulated and analyzed to simulate the deployment and locking process of the gas-actuated cylinder folding wing, and the deployment angles at typical positions at different times are output, as follows:

[0014] (41) Setting the analysis step: In the setting of the analysis step, the unfolding and locking process of the folding wing is divided into two implicit dynamic analysis steps for solution, named "Step-1" and "Step-2" respectively. The time of the first implicit dynamic analysis step is set to 1 s to analyze the unfolding process of the folding wing; the time of the second implicit dynamic analysis step is set to 0.2 s to analyze the process of the pin locking when the folding wing is unfolded into place;

[0015] (42) Set material parameters: Material is set to GH4099;

[0016] (43) Setting boundary conditions: In the “Step-1” analysis step, the inner wing of the folding wing mechanism and the rotating surface of the shaft are fixedly constrained, the freedom of the shaft movement direction is released, and the spring used to drive the latch is compressed; in “Step-2”, the freedom of the latch movement direction is released;

[0017] (44) Setting interaction: applying pulse force on the rotating surface of the shaft to represent the impact force of the gas actuator, the pulse force amplitude is 20 MPa, the action time is 0.3 s, the four pins are fixedly connected to form a whole to achieve synchronous movement, the spring stiffness coefficient is set to 100 N / mm, and the spring compression length is 45 mm;

[0018] (45) Couple the outer wing axis surface to the geometric node, and add the output of the rotation angle of the node to the historical variable output;

[0019] (46) Using the secondary development function of ABAQUS, first call the Angle_and_time.py program in ABAQUS to automatically submit the calculation. The output ODB result file is named "Job-1" by default. Set the file path, copy the result file to new.odb when the job is running, set the file to be readable and writable by all users, read the node rotation angle set in the new.odb historical output every ten seconds, and write the rotation time and angle to the file ur1_data.csv. When the rotation angle is read to be greater than 100°, stop the current calculation.

[0020] Furthermore, based on the obtained angle and time data, the cubic spline interpolation method is used to calculate the deployment time of the folding wings when rotating at a specific angle. The deployment time in the INP file is modified and the calculation is resubmitted to realize the release of the pin after the folding wings are deployed at a specific angle, thereby achieving the deployment locking effect, as follows:

[0021] (1) Based on the output deployment angle data at typical positions at different times, the calculation.py program is called in ABAQUS to obtain the deployment time of the folding wing through the cubic spline interpolation method;

[0022] (2) Modify the time of Step-1 in the original INP file and submit the calculation to trigger the locking mechanism when the folding wings are fully unfolded.

[0023] According to a second aspect of the present invention, the present invention provides an equivalent modeling system for a folding wing locking mechanism based on secondary development of ABAQUS, which is used to implement the above-mentioned equivalent modeling system for a folding wing locking mechanism based on secondary development of ABAQUS, comprising:

[0024] The construction module is used to construct a folding wing finite element model based on ABAQUS software, pre-process the model, and submit it for solution;

[0025] The solution module is used to use the Abaqus-Python secondary development function to simulate the folding wing model, simulate the deployment and locking process of the gas-actuated cylinder folding wing, output the deployment angles at typical positions at different times, and obtain the solved INP file;

[0026] The calculation output module is used to calculate the deployment time of the folding wings when rotating at a specific angle based on the obtained angle and time data using the cubic spline interpolation method, modify the deployment time in the INP file and resubmit the calculation to release the pin after the folding wings are deployed at a specific angle.

[0027] According to a third aspect of the present invention, the present invention provides a terminal device, including a memory, a processor, and a computer program stored in the memory and capable of running on the processor, wherein the memory stores a computer program capable of running on the processor, and when the processor loads and executes the computer program, the above-mentioned folding wing locking mechanism equivalent modeling method based on ABAQUS secondary development is adopted.

[0028] The present invention has at least the following beneficial effects:

[0029] Under different load conditions, the present invention automatically submits calculations to read the deployment time of rotation into place and modifies the original INP file, triggers locking after deployment at a specific angle, and can adapt to different pulse force amplitudes and different impact force action times, saving the time of complex entity modeling of traditional locking mechanisms and realizing rapid simulation analysis.

[0030] Of course, any product implementing the present invention does not necessarily need to achieve all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 Flow chart of the method of the present invention.

[0032] Figure 2 The following is the boundary condition setting in ABAQUS according to the embodiment of the present invention.

[0033] Figure 3 Schematic diagram of the pin rigid connection according to an embodiment of the present invention.

[0034] Figure 4 FIG. 4 is a graph showing the relationship between the unfolding angle of the folding wings and time according to an embodiment of the present invention.

[0035] Figure 5 This is a diagram showing the effect of the folding wings of an embodiment of the present invention being unfolded and locked. DETAILED DESCRIPTION

[0036] The following will be combined with the drawings in the embodiments of the present disclosure to clearly and completely describe the technical solutions in the embodiments of the present disclosure. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all the embodiments. Based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present disclosure.

[0037] See also Figure 1-Figure 5 The present invention provides a technical solution: an equivalent modeling method of a folding wing locking mechanism based on secondary development of ABAQUS, comprising the following steps:

[0038] S1. Construct a folding wing finite element model based on ABAQUS software, pre-process the model, and submit it for solution;

[0039] It should be noted that the folding wing finite element model constructed based on ABAQUS software includes an inner wing, an outer wing, a rotation axis, and four latches;

[0040] The folding wing finite element model is pre-processed as follows:

[0041] (S11) establishing each component according to the predetermined dimensions of the inner wing, the outer wing, the shaft and the latch;

[0042] (S12) Assigning material properties: Using composite materials, input density, elastic modulus, and Poisson's ratio;

[0043] S2. Use the Abaqus-Python secondary development function to simulate the folding wing model, simulate the gas-actuated cylinder folding wing deployment and locking process, output the deployment angles at the shaft at different times, and obtain the solved INP file, as follows:

[0044] (S21) Setting the analysis step: In the setting of the analysis step, the unfolding and locking process of the folding wing is divided into two implicit dynamic analysis steps for solution, which are named "Step-1" and "Step-2" respectively. The time of the first implicit dynamic analysis step is set to 1s, which is used to analyze the unfolding process of the folding wing; the time of the second implicit dynamic analysis step is set to 0.2s, which is used to analyze the process of the pin locking when the folding wing is unfolded in place;

[0045] (S22) Setting material parameters: the material is set to GH4099;

[0046] (S23) Setting boundary conditions: In the "Step-1" analysis step, the inner wing of the folding wing mechanism and the rotating surface of the shaft are fixed, the freedom of the shaft movement direction is released, and the spring used to drive the latch is compressed; in "Step-2", the freedom of the latch movement direction is released, such as Figure 2 As shown;

[0047] (S24) Set up interactions: Figure 3 As shown, a pulse force is applied to the rotating surface of the shaft to represent the impact force of the gas actuator. The pulse force amplitude is 20MPA, the action time is 0.3s, and the four pins are fixedly connected to form a whole to achieve synchronous movement. The spring stiffness coefficient is set to 100N / mm, and the spring compression length is 45mm;

[0048] (S25) coupling the outer wing rotation axis surface to the geometric node, and adding the output of the rotation angle of the node to the historical variable output;

[0049] It should be noted that the mesh node itself only has displacement degrees of freedom, which is usually used to describe the translational motion of the node, and does not directly output the rotation angle. ABAQUS cannot output the rotation angle of the mesh node, and needs to be coupled to the geometric node, which has rotational degrees of freedom.

[0050] (S26) Using the secondary development function of ABAQUS, first call the Angle_and_time.py program in ABAQUS to automatically submit the calculation. The output ODB result file is named "Job-1" by default. Set the file path, copy the result file to new.odb when the job is running, set the file to be readable and writable by all users, read the node rotation angle set in the new.odb historical output every ten seconds, and write the rotation time and angle to the file ur1_data.csv. When the rotation angle is read to be greater than 100°, stop the current calculation, such as Figure 4 As shown;

[0051] S3. According to the obtained angle and time data, use the cubic spline interpolation method to calculate the deployment time of the folding wing when rotating at a specific angle, modify the deployment time in the INP file and resubmit the calculation to realize the release of the pin after the folding wing is deployed at a specific angle, as follows:

[0052] (S31) according to the output deployment angle data at typical positions at different times, the calculation.py program is called in ABAQUS to obtain the deployment time of the folding wings by cubic spline interpolation method;

[0053] (S32) Modify the time of Step-1 in the original INP file and submit the calculation to trigger the locking mechanism when the folding wings are fully unfolded.

[0054] In summary, the present invention automatically submits calculations to read the deployment time of rotation under different load conditions and modifies the original INP file, triggering the lock after a specific deployment angle. It can adapt to different pulse force amplitudes and different impact force action times, saving the time of complex entity modeling of traditional locking mechanisms and achieving rapid simulation analysis.

[0055] Embodiment 2:

[0056] According to a second aspect of the present invention, the present invention provides an equivalent modeling system for a folding wing locking mechanism based on secondary development of ABAQUS, which is used to implement the above-mentioned equivalent modeling system for a folding wing locking mechanism based on secondary development of ABAQUS, comprising:

[0057] The construction module is used to construct a folding wing finite element model based on ABAQUS software, pre-process the model, and submit it for solution;

[0058] The solution module is used to use the Abaqus-Python secondary development function to simulate the folding wing model, simulate the deployment and locking process of the gas-actuated cylinder folding wing, output the deployment angles at typical positions at different times, and obtain the solved INP file;

[0059] The calculation output module is used to calculate the deployment time of the folding wings when rotating at a specific angle based on the obtained angle and time data using the cubic spline interpolation method, modify the deployment time in the INP file and resubmit the calculation to release the pin after the folding wings are deployed at a specific angle.

[0060] Specifically, the above-mentioned building module, solution module and calculation output module can be embedded in a computer processing system. The computer calls the above-mentioned modules to complete the task of modeling and analyzing the model according to the above-mentioned multi-node communication path selection method based on terrain perception; the above-mentioned building module, solution module and calculation output module can perform operations according to the specific steps given in the multi-node communication path selection method based on terrain perception.

[0061] It should be noted that it should be understood that the division of the various modules of the above system is only the division of logical functions. In actual implementation, they can be fully or partially integrated into one physical entity, or they can be physically separated, and these modules can all be implemented in the form of software calling through processing elements; they can also be all implemented in the form of hardware; some modules can also be implemented in the form of software calling through processing elements, and some modules can be implemented in the form of hardware. For example, the terrain perception module can be a separate processing element, or it can be integrated in a chip of the above device. In addition, it can also be stored in the memory of the above device in the form of program code, and called and executed by a processing element of the above device. The implementation of other modules is similar. In addition, these modules can be fully or partially integrated together, or they can be implemented independently. The processing element described here can be an integrated circuit with signal processing capabilities. In the implementation process, each step of the above method or each module can be completed by the hardware integrated logic circuit in the processor element or the instructions in the form of software.

[0062] For example, the above modules may be one or more integrated circuits configured to implement the above methods, such as one or more application specific integrated circuits (ASIC), or one or more digital singnal processors (DSP), or one or more field programmable gate arrays (FPGA). For another example, when a module is implemented in the form of a processing element scheduling program code, the processing element may be a general-purpose processor, such as a central processing unit (CPU) or other processors that can call program code. For another example, these modules may be integrated together and implemented in the form of a system-on-a-chip (SOC).

[0063] Embodiment three:

[0064] The present invention provides a terminal device, including a memory, a processor, and a computer program stored in the memory and capable of running on the processor, wherein the memory stores a computer program capable of running on the processor, and when the processor loads and executes the computer program, the above-mentioned folding wing locking mechanism equivalent modeling method based on ABAQUS secondary development is adopted.

[0065] It should be noted that the terminal device can be a computer device such as a desktop computer, a laptop computer or a cloud server, and the terminal device includes but is not limited to a processor and a memory. For example, the terminal device can also include input and output devices, network access devices and buses.

[0066] Furthermore, the processor may adopt a central processing unit (CPU). Of course, according to actual usage, other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGAs) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. may also be adopted. The general-purpose processor may adopt a microprocessor or any conventional processor, etc., and the present application does not impose any restrictions on this.

[0067] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0068] For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances. When an element is referred to as being "assembled on", "installed on", "fixed on" or "set on" another element, it can be directly on the other element or there can also be a centered element. When an element is considered to be "connected" to another element, it can be directly connected to the other element or there may be a centered element at the same time. The terms "vertical", "horizontal", "up", "down", "left", "right" and similar expressions used herein are only for illustrative purposes and are not intended to be the only implementation method.

[0069] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

[0070] In the description of this specification, the description with reference to the terms "one embodiment", "example", "specific example", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present disclosure. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

Claims

1. The equivalent modeling method of the folding wing locking mechanism based on the secondary development of ABAQUS is characterized by: The following steps are involved: Construct a folding wing finite element model based on ABAQUS software, pre-process the model, and submit it for solution; The Abaqus-Python secondary development function is used to simulate the folding wing model, simulate the gas-actuated cylinder folding wing deployment and locking process, output the deployment angles at the shaft at different times, and obtain the solved INP file; According to the obtained angle and time data, the cubic spline interpolation method is used to calculate the deployment time of the folding wings when rotating at a specific angle. The deployment time in the INP file is modified and the calculation is resubmitted to release the pin after the folding wings are deployed at a specific angle.

2. The equivalent modeling method of the folding wing locking mechanism based on ABAQUS secondary development according to claim 1 is characterized in that: The folding wing finite element model constructed based on ABAQUS software includes an inner wing, an outer wing, a rotation axis and four latches.

3. The equivalent modeling method of the folding wing locking mechanism based on ABAQUS secondary development according to claim 2 is characterized in that: The folding wing finite element model is pre-processed as follows: (31) Building each component according to predetermined dimensions of the inner wing, outer wing, shaft, and latch; (32) Assign material properties: Using composite materials, input density, elastic modulus, and Poisson’s ratio.

4. The equivalent modeling method of the folding wing locking mechanism based on ABAQUS secondary development according to claim 3 is characterized in that: The folding wing model is simulated and analyzed to simulate the deployment and locking process of the gas-actuated cylinder folding wing, and the deployment angles at typical positions at different times are output, as follows: (41) Setting the analysis step: In the setting of the analysis step, the unfolding and locking process of the folding wing is divided into two implicit dynamic analysis steps for solution, named "Step-1" and "Step-2" respectively. The time of the first implicit dynamic analysis step is set to 1s, which is used to analyze the unfolding process of the folding wing; the time of the second implicit dynamic analysis step is set to 0.2s, which is used to analyze the process of the pin locking when the folding wing is unfolded in place; (42) Set material parameters: Material is set to GH4099; (43) Setting boundary conditions: In the "Step-1" analysis step, the inner wing of the folding wing mechanism and the rotating surface of the shaft are fixed, the freedom of the shaft movement direction is released, and the spring used to drive the latch is compressed; in "Step-2", the freedom of the latch movement direction is released; (44) Setting interaction: applying pulse force on the rotating surface of the shaft to represent the impact force of the gas actuator, the pulse force amplitude is 20 MPa, the action time is 0.3 s, the four pins are fixedly connected to form a whole to achieve synchronous movement, the spring stiffness coefficient is set to 100 N / mm, and the spring compression length is 45 mm; (45) Couple the outer wing axis surface to the geometric node, and add the output of the rotation angle of the node to the historical variable output; (46) Using the secondary development function of ABAQUS, first call the Angle_and_time.py program in ABAQUS to automatically submit the calculation. The output ODB result file is named "Job-1" by default. Set the file path, copy the result file to new.odb when the job is running, set the file to be readable and writable by all users, read the node rotation angle set in the new.odb historical output every ten seconds, and write the rotation time and angle to the file ur1_data.csv. When the rotation angle is read to be greater than 100°, stop the current calculation.

5. The equivalent modeling method of the folding wing locking mechanism based on ABAQUS secondary development according to claim 4 is characterized in that: According to the obtained angle and time data, the cubic spline interpolation method is used to calculate the deployment time of the folding wings when rotating at a specific angle. The deployment time in the INP file is modified and the calculation is resubmitted to realize the release of the pin after the folding wings are deployed at a specific angle to achieve the deployment locking effect, as follows: (51) According to the output deployment angle data at typical positions at different times, the calculation.py program is called in ABAQUS to obtain the deployment time of the folding wings through the cubic spline interpolation method; (52) Modify the time of Step-1 in the original INP file and submit the calculation to trigger the locking mechanism when the folding wings are fully unfolded.

6. The folding wing locking mechanism equivalent modeling system based on ABAQUS secondary development is used to implement the folding wing locking mechanism equivalent modeling system based on ABAQUS secondary development according to any one of claims 1 to 5, characterized in that: include: The construction module is used to construct a folding wing finite element model based on ABAQUS software, pre-process the model, and submit it for solution; The solution module is used to use the Abaqus-Python secondary development function to simulate the folding wing model, simulate the gas-actuated cylinder folding wing deployment and locking process, output the deployment angles at typical positions at different times, and obtain the solved INP file; The calculation output module is used to calculate the deployment time of the folding wings when the folding wings are rotated to a specific angle according to the obtained angle and time data using the cubic spline interpolation method, modify the deployment time in the INP file and resubmit the calculation to release the pins after the folding wings are deployed to a specific angle.

7. A terminal device, comprising a memory, a processor, and a computer program stored in the memory and capable of running on the processor, characterized in that: The memory stores a computer program that can be run on the processor. When the processor loads and executes the computer program, the equivalent modeling method of the folding wing locking mechanism based on ABAQUS secondary development described in any one of claims 1 to 5 is adopted.

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