Course stability evaluation method, device, equipment and storage medium

Abstract

The application provides a heading dynamic stability evaluation method, device, equipment and storage medium, wherein the method comprises the following steps: establishing a lateral heading third-order matrix representing aircraft motion, and converting the lateral heading third-order matrix into a general characteristic equation; converting the general characteristic equation into a decomposition formula in the subsonic, transonic and supersonic stages, solving the motion frequency and damping value under the Dutch roll mode through the decomposition formula, setting the damping value as a preset size in the hypersonic stage, and solving the motion frequency under the Dutch roll mode through an angle of attack formula; combining the motion frequency and the damping value to obtain the Dutch roll mode characteristic root; judging the current flight state under the Dutch roll mode according to the Dutch roll mode characteristic root, and evaluating the current dynamic stability of the aircraft according to the current flight state by using the corresponding evaluation rule. The application establishes a lateral heading third-order matrix considering only the roll and Dutch roll, and improves the accuracy of the evaluation of the dynamic stability related index calculation.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a method, apparatus, device, and storage medium for evaluating azimuth dynamic stability. Background Technology

[0002] Forward dynamic stability refers to the ability of an aircraft to automatically return to its original heading state after being disturbed during flight. Wide-speed-range aircraft have a wide flight speed range and a large range of flight altitude variations, which leads to significant changes in the dynamic stability of the aircraft.

[0003] In assessing heading dynamic stability, the heading dynamic stability of a wide-speed-range aircraft exhibits a significant nonlinear variation with changes in flight speed and altitude, making it impossible to accurately calculate the values ​​of indices related to dynamic stability assessment. The conventional method involves establishing and linearizing the aircraft's equations of motion and solving for eigenvalues ​​to determine dynamic stability. However, this approach considers too many irrelevant factors, leading to inaccurate model establishment and the absence of reasonable constraint boundaries when assessing dynamic stability.

[0004] Based on the above analysis of the development status of this technical field, the existing technical solutions lack an evaluation scheme that only considers roll and Dutch roll solutions. Summary of the Invention

[0005] The purpose of this invention is to provide a method, apparatus, device, and storage medium for evaluating directional dynamic stability, in order to solve the aforementioned problems in the prior art.

[0006] According to a first aspect of the present invention, a method for evaluating heading dynamic stability is provided, comprising:

[0007] Establish a third-order lateral navigation matrix to represent the aircraft's motion, and transform the third-order lateral navigation matrix into a general characteristic equation;

[0008] In the subsonic, transonic and supersonic stages, the general characteristic equation is transformed into a decomposition formula, and the motion frequency and damping value under the Dutch roll mode are solved by the decomposition formula. In the hypersonic stage, the damping value is set to a preset value, and the motion frequency under the Dutch roll mode is solved by the angle of attack formula.

[0009] By combining the motion frequency and damping value, the eigenvalues ​​of the Dutch rolling mode are obtained;

[0010] The current flight state under the Dutch rolling mode is determined based on the eigenvalues ​​of the Dutch rolling mode, and the current dynamic stability of the aircraft is evaluated using the corresponding evaluation rules based on the current flight state.

[0011] According to a second aspect of the present invention, a heading dynamic stability assessment device is provided, comprising:

[0012] The matrix creation module is used to create a third-order lateral navigation matrix representing the aircraft's motion and to transform the third-order lateral navigation matrix into a general characteristic equation.

[0013] The motion frequency and damping value calculation module is used to transform the general characteristic equation into a decomposition in the subsonic, transonic and supersonic stages, and solve the motion frequency and damping value in the Dutch roll mode through the decomposition. In the hypersonic stage, the damping value is set to a preset value, and the motion frequency in the Dutch roll mode is solved through the angle of attack formula.

[0014] The Dutch roll mode eigenvalue solving module is used to combine motion frequency and damping value to obtain the Dutch roll mode eigenvalues;

[0015] The dynamic stability assessment module is used to determine the current flight state under the Dutch roll mode based on the eigenvalues ​​of the Dutch roll mode, and to assess the current dynamic stability of the aircraft using the corresponding assessment rules based on the current flight state.

[0016] According to a third aspect of the present invention, an electronic device is provided, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the computer program, when executed by the processor, implements the steps of the heading dynamic stability assessment method provided in the first aspect of the present disclosure.

[0017] According to a fourth aspect of the present invention, a computer-readable storage medium is provided, on which an information transmission implementation program is stored, which, when executed by a processor, implements the steps of the heading dynamic stability evaluation method provided in the first aspect of the present disclosure.

[0018] The technical solution provided by the embodiments of the present invention has the following beneficial effects: it establishes a third-order lateral matrix that only considers roll and Dutch roll, takes into account the differences in sound speed stages when calculating the motion frequency and damping value under Dutch roll mode, improves the accuracy of the calculation of dynamic stability related indicators, and defines the boundary of judgment through accurate evaluation rules.

[0019] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit this disclosure. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in one or more embodiments of this specification or in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this specification. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1This is a flowchart of the heading dynamic stability evaluation method according to an embodiment of the present invention;

[0022] Figure 2 This is a schematic diagram comparing the eigenvalues ​​and accurate values ​​of the Dutch rolling mode according to an embodiment of the present invention;

[0023] Figure 3 This is a schematic diagram illustrating the dynamic stability determination in an embodiment of the present invention;

[0024] Figure 4 This is a schematic diagram of the heading dynamic stability evaluation device according to an embodiment of the present invention;

[0025] Figure 5 This is a schematic diagram of an electronic device according to an embodiment of the present invention. Detailed Implementation

[0026] To enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the technical solutions in one or more embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this specification, and not all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of this document.

[0027] Method Implementation Examples

[0028] According to an embodiment of the present invention, a method for evaluating heading dynamic stability is provided. Figure 1 This is a flowchart of the heading dynamic stability evaluation method according to an embodiment of the present invention, such as... Figure 1 As shown, the heading dynamic stability assessment method according to an embodiment of the present invention specifically includes:

[0029] In step S110, a third-order lateral heading matrix representing the aircraft's motion is established, and this matrix is ​​transformed into a general characteristic equation. Specifically, this includes:

[0030] The vertical tail and ventral fin areas of wide-speed-range aircraft are relatively small, and the magnitudes of the lateral aerodynamic coefficients—the derivatives of the side force with respect to the sideslip angle, the side force with respect to the roll angular velocity, the side force with respect to the yaw angular velocity, and the roll moment with respect to the yaw angular velocity—are also relatively small. Therefore, they have little impact on the roll and Dutch roll modes. In approximate calculations and analyses, these aerodynamic parameters are ignored. Thus, only the motion including the rollers and Dutch roll is considered. The third-order lateral matrix of the aircraft's motion is established using Equation 1:

[0031]

[0032] Among them, A lat This represents a third-order matrix for the transverse direction. This represents the large derivative of the rolling torque with respect to the sideslip angle. This represents the large derivative of the rolling torque with respect to the rolling angular velocity. This represents the large derivative of the yaw moment with respect to the sideslip angle. This represents the large derivative of the yaw moment with respect to the roll angular velocity. It represents the large derivative of the yaw moment with respect to the yaw angular velocity.

[0033] Equation 2 transforms the transverse 3D matrix into a general characteristic equation:

[0034]

[0035] in, λ represents the eigenvalue.

[0036] In step S120, the general characteristic equation is transformed into a decomposition equation in the subsonic, transonic, and supersonic stages. The motion frequency and damping value in the Dutch roll mode are solved using the decomposition equation. In the hypersonic stage, the damping value is set to a preset value, and the motion frequency in the Dutch roll mode is solved using the angle of attack formula. Specifically, this includes:

[0037] In the subsonic, transonic, and supersonic stages, the general characteristic equation is transformed into a decomposition expression. The specific methods for solving the motion frequency and damping value under the Dutch roll mode using this decomposition expression include:

[0038] The general characteristic equation is transformed into a decomposition using Formula 3:

[0039] (λ+a)(λ 2 +bλ+c)=0 Formula 3;

[0040] Where 'a' represents the parameter related to the characteristic root of the roller mode, and 'b' and 'c' represent the parameters related to the characteristic root of the Dutch roller mode. Comparing the expansion of Equation 3 with Equation 2 yields the result shown in Equation 4:

[0041]

[0042] The results are obtained through comparison in Formula 4. Where, λ r Let a and λ represent the static modal eigenvalues ​​of the roller. r Related to static stability, in this embodiment it is used to derive the values ​​of parameters or roots related to dynamic stability, but is not included in the calculation when determining dynamic stability.

[0043] To adapt to a wide range of flight speed variations, wide-speed-range aircraft have smaller aerodynamic components such as wingspan, vertical tail, and ventral fins, resulting in weaker aerodynamic damping. However, during supersonic and subsonic flight, the aerodynamic stabilizer still provides some damping, therefore... Equivalent to a>b, substituting the calculated a into the equations ab+c and ac in formula 4 to calculate the values ​​of b and c, we obtain... as well as Because wide-speed-range aircraft have a small aspect ratio and low lateral stability, but due to the large derivative L of the rolling moment with respect to the rolling angular velocity... p Although the values ​​are relatively small, the parameters p1 and p2 may still be large and cannot be ignored. Therefore, p1 and p2 are treated as constants.

[0044] Since the general form of the second-order vibration equation is λ 2 +2ζ d ω d +ω d 2 =0, compared with the second term in Formula 3, the motion frequency under the Dutch roll mode is calculated using Formula 5, and the damping value under the Dutch roll mode is calculated using Formula 6:

[0045]

[0046]

[0047] Where, ω d ζ represents the motion frequency in the Dutch rolling mode. d This represents the damping value under the Dutch rolling mode.

[0048] In the hypersonic phase, the damping value is set to a preset value, and the motion frequency under the Dutch roll mode is solved using the angle-of-attack formula, specifically including:

[0049] In the hypersonic phase, the damping value is defined as 0, and the motion frequency in the Dutch roll mode is solved using the angle of attack formula in Equation 7:

[0050]

[0051] Where, ω d This indicates the motion frequency in the Dutch rolling mode. This represents the large derivative of the yaw moment with respect to the sideslip angle. α0 represents the large derivative of the rolling torque with respect to the sideslip angle, and α0 represents the equilibrium angle of attack in the typical state. S represents dynamic pressure. ref Indicates the reference area, l ref Indicates the reference length, I zz C represents the yaw moment of inertia. nβ_dyn This represents the dynamic divergence parameter of yaw.

[0052] In step S130, the motion frequency and damping value are combined to obtain the eigenvalues ​​of the Dutch roll mode. Specifically, this includes:

[0053] The eigenvalues ​​of the Dutch rolling mode are obtained using Equation 8:

[0054]

[0055] Where, λ d1 and λ d2 The eigenvalue represents the dynamic Dutch roll mode characteristic root, and i represents the imaginary unit.

[0056] In step S140, the current flight state under the Dutch roll mode is determined based on the eigenvalues ​​of the Dutch roll mode, and the current dynamic stability of the aircraft is evaluated using the corresponding evaluation rules based on the current flight state. Specifically, this includes:

[0057] Based on the eigenvalues ​​of the Dutch rolling mode, the current flight state is determined to be either divergent or stable.

[0058] If the current flight state is divergent, meaning the current flight state is disturbed, then the divergence amplitude time is calculated using the motion frequency, and the divergence amplitude time T is calculated using Formula 9. 2_d :

[0059]

[0060] Compare the divergence amplitude time with the time threshold. If the divergence amplitude time is greater than the time threshold, the current dynamic stability is determined to be good. In this embodiment, the time threshold is 0.5s.

[0061] If the current flight state is stable, the motion frequency is compared with the frequency threshold. If the motion frequency is less than or equal to the frequency threshold, the current dynamic stability is determined to be good. In this embodiment, the frequency threshold is 5 rad / s.

[0062] The above technical solutions of the embodiments of the present invention will be illustrated with reference to the following accompanying drawings.

[0063] Figure 2 This is a schematic diagram comparing the eigenvalues ​​of the Dutch rolling mode with the accurate values ​​according to an embodiment of the present invention, as shown below. Figure 2 As shown, a comparison is presented between the eigenvalues ​​of the Dutch roll mode obtained by the present invention and the accurate values ​​calculated using accurate numerical methods. Figure 3 This is a schematic diagram of the dynamic stability determination according to an embodiment of the present invention, as shown below. Figure 3 As shown, the dynamic stability judgment is performed when the current flight state is stable. The result is obtained by comparing the motion frequency with the frequency threshold.

[0064] In summary, to address the existing problems, this invention proposes a forward dynamic stability assessment method. It establishes a third-order lateral forward matrix considering only roll and Dutch roll, transforming the general characteristic equation corresponding to the third-order lateral forward matrix into a decomposition. The resulting decomposition is similar in form to the general form of the second-order vibration equation. Through comparison and derivation, the motion frequency and damping value under the Dutch roll mode are obtained. Furthermore, the calculation of motion frequency and damping value considers the differences in sound speed stages, improving the accuracy of dynamic stability-related index calculations. Accurate assessment rules define the judgment boundaries, using different assessment methods based on the divergent or stable current flight state. The dynamic stability assessment results are obtained by comparing with the corresponding dynamic stability threshold boundaries, and the setting of the judgment constraint threshold boundaries is relatively reasonable.

[0065] Device Examples

[0066] According to an embodiment of the present invention, a heading dynamic stability evaluation device is provided. Figure 4 This is a schematic diagram of the heading dynamic stability evaluation device according to an embodiment of the present invention, as shown below. Figure 4 As shown, the heading dynamic stability evaluation device according to an embodiment of the present invention specifically includes:

[0067] Matrix creation module 40 is used to create a third-order lateral navigation matrix representing the aircraft's motion, transforming the third-order lateral navigation matrix into a general characteristic equation. Specifically, it is used for:

[0068] The third-order lateral navigation matrix of the aircraft's motion is established using Equation 1:

[0069]

[0070] Among them, A lsy This represents a third-order matrix for the transverse direction. This represents the large derivative of the rolling torque with respect to the sideslip angle. This represents the large derivative of the rolling torque with respect to the rolling angular velocity. This represents the large derivative of the yaw moment with respect to the sideslip angle. This represents the large derivative of the yaw moment with respect to the roll angular velocity. It represents the large derivative of the yaw moment with respect to the yaw angular velocity.

[0071] The transverse 3D matrix is ​​transformed into a general equation using Equation 2:

[0072] λ 3 +b1λ 2 +b2λ+b3=0 Formula 2;

[0073] in, λ represents the eigenvalue.

[0074] The motion frequency and damping value calculation module 42 is used to transform the general characteristic equation into a decomposition expression in the subsonic, transonic, and supersonic stages, and solve for the motion frequency and damping value in the Dutch roll mode using the decomposition expression. In the hypersonic stage, the damping value is set to a preset value, and the motion frequency in the Dutch roll mode is solved using the angle of attack formula. Specifically used for:

[0075] In the subsonic, transonic, and supersonic stages, the general characteristic equation is transformed into a decomposition using Equation 3:

[0076] (λ+a)(λ 2 +bλ+c)=0 Formula 3;

[0077] Where 'a' represents the parameter related to the characteristic root of the roller mode, and 'b' and 'c' represent the parameters related to the characteristic root of the Dutch roller mode. Comparing the expansion of Equation 3 with Equation 2 yields the result shown in Equation 4:

[0078]

[0079] The results are obtained through comparison in Formula 4. Where, λ r Let 'a' represent the static modal eigenvalues ​​of the roller. Substituting the calculated 'a' into the equations ab+c and ac in Formula 4, we can calculate the values ​​of b and c, thus obtaining... as well as

[0080] The motion frequency under the Dutch rolling mode is calculated using Formula 5, and the damping value under the Dutch rolling mode is calculated using Formula 6.

[0081]

[0082]

[0083] Where, ω d ζ represents the motion frequency in the Dutch rolling mode. d This represents the damping value under the Dutch rolling mode.

[0084] In the hypersonic stage, the damping value is defined as 0. Based on existing experience, the motion frequency in the Dutch roll mode is solved using the angle of attack formula in Equation 7:

[0085]

[0086] Where, ω d This indicates the motion frequency in the Dutch rolling mode. This represents the large derivative of the yaw moment with respect to the sideslip angle. α0 represents the large derivative of the rolling torque with respect to the sideslip angle, and α0 represents the equilibrium angle of attack in the typical state. S represents dynamic pressure. refIndicates the reference area, l ref Indicates the reference length, I zz C represents the yaw moment of inertia. nβ_dyn This represents the dynamic divergence parameter of yaw.

[0087] The Dutch roll mode eigenvalue solving module 44 is used to combine the motion frequency and damping value to obtain the Dutch roll mode eigenvalues. Specifically, it is used for:

[0088] Combining the motion frequency and damping value, the eigenvalues ​​of the Dutch rolling mode are obtained, specifically including:

[0089] The eigenvalues ​​of the Dutch rolling mode are obtained using Equation 8:

[0090]

[0091] Where, λ d1 and λ d2 The eigenvalue represents the dynamic Dutch roll mode characteristic root, and i represents the imaginary unit.

[0092] The dynamic stability assessment module 46 is used to determine the current flight state under the Dutch roll mode based on the eigenvalues ​​of the Dutch roll mode, and to assess the current dynamic stability of the aircraft using the corresponding evaluation rules based on the current flight state. Specifically, it is used for:

[0093] Based on the eigenvalues ​​of the Dutch rolling mode, the current flight state is determined to be either divergent or stable.

[0094] If the current flight state is divergent, the divergence amplitude time is calculated by the motion frequency, and the divergence amplitude time is compared with the time threshold. If the divergence amplitude time is greater than the time threshold, the current dynamic stability is determined to be good.

[0095] If the current flight state is stable, the motion frequency is compared with the frequency threshold. If the motion frequency is less than or equal to the frequency threshold, the current dynamic stability is determined to be good.

[0096] In summary, to address the existing problems, this invention provides a lateral dynamic stability assessment device. It establishes a third-order lateral matrix considering only roll and Dutch roll, transforming the general characteristic equation corresponding to the third-order lateral matrix into a decomposition. The resulting decomposition is similar in form to the general form of the second-order vibration equation. Through comparison and derivation, the motion frequency and damping value under the Dutch roll mode are obtained. Furthermore, the calculation of motion frequency and damping value considers the differences in sound speed stages, improving the accuracy of dynamic stability-related index calculations. Accurate assessment rules define the judgment boundaries, using different assessment methods based on the divergent or stable current flight state. The dynamic stability assessment results are obtained by comparing with the corresponding dynamic stability threshold boundaries, and the setting of the judgment constraint threshold boundaries is relatively reasonable.

[0097] Electronic device examples

[0098] Figure 5 This is a schematic diagram of an electronic device according to an embodiment of the present invention. The electronic device 500 may include at least one processor 510 and a memory 520. The processor 510 can execute instructions stored in the memory 520. The processor 510 is communicatively connected to the memory 520 via a data bus. In addition to the memory 520, the processor 510 can also be communicatively connected to an input device 530, an output device 540, and a communication device 550 via the data bus.

[0099] Processor 510 can be any conventional processor, such as a commercially available CPU. The processor may also include, for example, a Graphics Processing Unit (GPU), a Field Programmable Gate Array (FPGA), a System on Chip (SOC), an Application Specific Integrated Circuit (ASIC), or a combination thereof.

[0100] The memory 520 can be implemented by any type of volatile or non-volatile storage device or a combination thereof, such as static random access memory (SRAM), electrically erasable programmable read-only memory (EEPROM), erasable programmable read-only memory (EPROM), programmable read-only memory (PROM), read-only memory (ROM), magnetic storage, flash memory, magnetic disk or optical disk.

[0101] In this embodiment of the present disclosure, the memory 520 stores executable instructions, and the processor 510 can read the executable instructions from the memory 520 and execute the instructions to implement all or part of the steps of any of the heading dynamic stability assessment methods in the exemplary embodiments described above.

[0102] Computer-readable storage medium embodiments

[0103] In addition to the methods and apparatus described above, exemplary embodiments of this disclosure may also be a computer program product or a computer-readable storage medium storing the computer program product, the computer product including computer program instructions that can be executed by a processor to implement all or part of the steps described in any of the heading dynamic stability assessment methods in the exemplary embodiments described above.

[0104] Computer program products can be written in any combination of one or more programming languages ​​to perform the operations of the embodiments of this application. Programming languages ​​include object-oriented programming languages ​​such as Java and C++, as well as conventional procedural programming languages ​​such as C or similar languages, and scripting languages ​​(e.g., Python). The program code can be executed entirely on the user's computing device, partially on the user's device, as a standalone software package, partially on the user's computing device and partially on a remote computing device, or entirely on a remote computing device or server.

[0105] Computer-readable storage media may take the form of any combination of one or more readable media. A readable medium may be a readable signal medium or a readable storage medium. A readable storage medium may, for example, include, but is not limited to, electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatuses, or devices, or any combination thereof. More specific examples of readable storage media include: static random access memory (SRAM) having one or more electrically connected wires, electrically erasable programmable read-only memory (EEPROM), erasable programmable read-only memory (EPROM), programmable read-only memory (PROM), read-only memory (ROM), magnetic storage, flash memory, magnetic disk or optical disk, or any suitable combination thereof.

[0106] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for evaluating heading dynamic stability, characterized in that, include: Establish a third-order lateral heading matrix to represent the aircraft's motion, and transform the third-order lateral heading matrix into a general characteristic equation, specifically including: The third-order lateral navigation matrix of the aircraft's motion is established using Equation 1: Formula 1: in, This represents a third-order matrix for the transverse direction. This represents the large derivative of the rolling torque with respect to the sideslip angle. This represents the large derivative of the rolling torque with respect to the rolling angular velocity. This represents the large derivative of the yaw moment with respect to the sideslip angle. This represents the large derivative of the yaw moment with respect to the roll angular velocity. This represents the large derivative of the yaw moment with respect to the yaw angular velocity; In the subsonic, transonic, and supersonic stages, the general characteristic equation is transformed into a decomposition expression, and the motion frequency and damping value in the Dutch roll mode are solved using the decomposition expression. In the hypersonic stage, the damping value is set to a preset value, and the motion frequency in the Dutch roll mode is solved using the angle of attack formula. Specifically, this includes: Damping value during hypersonic phase Defined as 0, the motion frequency under the Dutch roll mode is solved using the angle of attack formula in Formula 7: Formula 7: in, This indicates the motion frequency in the Dutch rolling mode. This represents the large derivative of the yaw moment with respect to the sideslip angle. This represents the large derivative of the rolling torque with respect to the sideslip angle. This represents the typical equilibrium angle of attack. Indicates dynamic pressure. Indicates the reference area. Indicates the reference length. Indicates the moment of inertia of yaw rotation. Indicates the dynamic divergence parameters of yaw; The motion frequency and the damping value are combined to obtain the characteristic roots of the Dutch roll mode; The current flight state under the Dutch roll mode is determined based on the eigenvalues ​​of the Dutch roll mode, and the current dynamic stability of the aircraft is evaluated using the corresponding evaluation rules based on the current flight state.

2. The method according to claim 1, characterized in that, The specific steps of transforming the transverse third-order matrix into a general characteristic equation include: The transverse 3rd order matrix is ​​transformed into a general characteristic equation using Equation 2: Formula 2: in, , , , Represents the eigenvalue.

3. The method according to claim 2, characterized in that, The process of transforming the general characteristic equation into a decomposition expression in the subsonic, transonic, and supersonic stages, and then solving for the motion frequency and damping value in the Dutch roll mode using the decomposition expression, specifically includes: The general characteristic equation is transformed into a decomposition using Formula 3: Formula 3: in, a This represents the parameters related to the eigenvalues ​​of the roller mode. b and c The parameters related to the eigenvalues ​​of the Dutch rolling mode are represented by the expansion of Equation 3, which is compared with Equation 2 to obtain the result shown in Equation 4: Formula 4: The results are obtained through comparison in Formula 4. ,in, The static modal eigenvalues ​​of the roller are obtained from the calculation. Substitute into the expression in formula 4 ab + c and expression ac Calculate the values ​​of b and c in the equation to obtain ,as well as ; The motion frequency under the Dutch rolling mode is calculated using Formula 5, and the damping value under the Dutch rolling mode is calculated using Formula 6. Formula 5: Formula 6: in, This indicates the motion frequency in the Dutch rolling mode. This represents the damping value under the Dutch rolling mode.

4. The method according to claim 3, characterized in that, The specific steps of combining the motion frequency and the damping value to obtain the eigenvalues ​​of the Dutch roll mode include: The eigenvalues ​​of the Dutch rolling mode are obtained using Equation 8: , Formula 8: in, and Represents the dynamic eigenvalues ​​of the Dutch roll mode. Indicates the imaginary part.

5. The method according to claim 1, characterized in that, The step of determining the current flight state under the Dutch roll mode based on the eigenvalues ​​of the Dutch roll mode, and evaluating the current dynamic stability of the aircraft using the corresponding evaluation rules based on the current flight state, specifically includes: The current flight state is determined to be divergent or stable based on the eigenvalues ​​of the Dutch rolling mode. If the current flight state is divergent, the divergence amplitude time is calculated based on the motion frequency, and the divergence amplitude time is compared with a time threshold. If the divergence amplitude time is greater than the time threshold, the current dynamic stability is determined to be good. If the current flight state is stable, then by comparing the motion frequency with the frequency threshold, if the motion frequency is less than or equal to the frequency threshold, then the current dynamic stability is determined to be good.

6. A heading dynamic stability assessment device, characterized in that, include: The matrix establishment module is used to establish a third-order lateral navigation matrix representing the aircraft's motion, and to transform the third-order lateral navigation matrix into a general characteristic equation. Specifically, it is used for: The third-order lateral navigation matrix of the aircraft's motion is established using Equation 1: Formula 1: in, This represents a third-order matrix for the transverse direction. This represents the large derivative of the rolling torque with respect to the sideslip angle. This represents the large derivative of the rolling torque with respect to the rolling angular velocity. This represents the large derivative of the yaw moment with respect to the sideslip angle. This represents the large derivative of the yaw moment with respect to the roll angular velocity. This represents the large derivative of the yaw moment with respect to the yaw angular velocity; The motion frequency and damping value calculation module is used to transform the general characteristic equation into a decomposition expression in the subsonic, transonic, and supersonic stages, and solve for the motion frequency and damping value in the Dutch roll mode using the decomposition expression. In the hypersonic stage, the damping value is set to a preset value, and the motion frequency in the Dutch roll mode is solved using the angle of attack formula. Specifically, it is used for: Damping value during hypersonic phase Defined as 0, the motion frequency under the Dutch roll mode is solved using the angle of attack formula in Formula 7: Formula 7: in, This indicates the motion frequency in the Dutch rolling mode. This represents the large derivative of the yaw moment with respect to the sideslip angle. This represents the large derivative of the rolling torque with respect to the sideslip angle. This represents the typical equilibrium angle of attack. Indicates dynamic pressure. Indicates the reference area. Indicates the reference length. Indicates the moment of inertia of yaw rotation. Indicates the dynamic divergence parameters of yaw; The Dutch roll mode eigenvalue solving module is used to combine the motion frequency and the damping value to obtain the Dutch roll mode eigenvalues; The dynamic stability determination module is used to determine the current flight state under the Dutch roll mode based on the eigenvalues ​​of the Dutch roll mode, and to evaluate the current dynamic stability of the aircraft using the corresponding evaluation rules based on the current flight state.

7. An electronic device, characterized in that, include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the computer program, when executed by the processor, implements the steps of the heading dynamic stability assessment method as described in any one of claims 1 to 5.

8. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores an implementation program for information transmission, which, when executed by a processor, implements the steps of the heading dynamic stability assessment method as described in any one of claims 1 to 5.

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