Spacecraft flutter rapid analysis method suitable for cabin airfoil combination configuration

Abstract

The invention relates to a spacecraft flutter rapid analysis method suitable for cabin section airfoil combined configuration. The method comprises the steps that parametric modeling is conducted on an aircraft wing rudder structure; extracting key parameters to perform flutter analysis calculation by using the built aircraft wing rudder structure model; and based on the flutter analysis result, the flutter margin of the whole flight process is used as a constraint, and the wing rudder structure is optimized. The rapid parametric modeling and flutter analysis method can be provided for the initial stage of aircraft structure design, the analysis period is shortened, and the aircraft development efficiency is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of aeroelastic analysis, and relates to a spacecraft flutter rapid analysis method suitable for a cabin section wing surface combination configuration. Background Art

[0002] The development of spacecraft tends to reduce structural stiffness, resulting in a decrease in structural frequency, which increases the risk of structural flutter of the aircraft. At the same time, due to the lack of structural details and frequent adjustments to the structural scheme in the initial stage of aircraft development, it is difficult for the structural model to adapt to changes and flutter analysis to be carried out. In the existing aircraft development process, the analysis of flutter is often carried out after the structural scheme is specifically formed, which takes a long time. In addition, in the later stage of development, improvements to the aircraft structure design often require re-modeling for flutter analysis, which greatly reduces the efficiency of aircraft development. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and propose a rapid analysis method for spacecraft flutter suitable for the combined configuration of cabin and wing surfaces, which can provide a rapid parametric modeling and flutter analysis method for the early stage of aircraft structure design, shorten the analysis cycle, and improve the efficiency of aircraft development.

[0004] The solution of the present invention is: A fast flutter analysis method for spacecraft applicable to cabin-wing combination configuration, comprising: Parametric modeling of aircraft wing and rudder structures; Using the aircraft wing-rudder structure model, key parameters are extracted for flutter analysis and calculation; Based on the flutter analysis results, the wing-rudder structure is optimized with the flutter margin of the entire flight process as a constraint.

[0005] Preferably, the process of parametric modeling of the aircraft wing-rudder structure is as follows: 1.1 Extract initial modeling parameters; 1.2 Modeling of the fuselage compartment structure; 1.3 Model the wing-rudder structure; 1.4 Generate and divide the flat aerodynamic grid of the wing structure to obtain the finite element model of the aircraft wing and rudder structure; 1.5 According to the established finite element model of the aircraft wing-rudder structure, structural nodes are selected on the surfaces of the wing surface structure and the tail wing surface structure to perform aerodynamic structure interpolation.

[0006] Preferably, in step 1.1, when extracting the initial modeling parameters, For the fuselage compartment structure, the extracted initial modeling parameters include fuselage length, fuselage section radius, number of longitudinal beams, rectangular longitudinal beam section parameters, and number of bulkheads; The initial modeling parameters extracted for the wing-rudder structure include wing root chord length, wing tip chord length, span and grid size.

[0007] Preferably, in step 1.2, the fuselage compartment structure is modeled as follows: 1) Extract characteristic parameters of the fuselage geometry; 2) Perform 2D fuselage section geometry parametric modeling based on the extracted characteristic parameters; 3) Call the modular subroutine function of surface stretching to stretch the two-dimensional geometric shape into a three-dimensional geometric shape according to the set stretching parameters; 4) Based on the three-dimensional shape, the modular subroutine function of curve stretching and the subroutine function of flat unit generation are called to freely set the number of bulkheads and the relative position of the bulkheads along the longitudinal direction of the fuselage to complete the geometric shape modeling of the fuselage.

[0008] Preferably, in step 1.3, the wing-rudder structure is modeled as follows: 1) Describe the three-dimensional geometric shape of the wing or control surface; 2) Perform two-dimensional plane meshing in the forward projection direction of the wing or rudder plane geometry; 3) Extract typical parameters of 2D plane meshing, set the number of transverse components and the relative positions of longitudinal and transverse components; 4) Using the outer shape of the skin as the boundary, unfold the internal components three-dimensionally in the thickness direction.

[0009] Preferably, when performing two-dimensional plane meshing in step 2), the positions of the internal components need to be considered.

[0010] Preferably, in step 1.4, the steps of generating and dividing the flat aerodynamic grid of the airfoil structure are as follows: 1) Extract the geometric parameters of the wing plane; 2) Based on the parameterization of the plane geometric shape, the corresponding flat panel mesh is generated to parameterize the wing aerodynamic mesh.

[0011] Preferably, the implementation method of step 1.5 is as follows: 1) For the established finite element model of the aircraft wing and rudder structure, the structural grid nodes on one side of the wing surface are selected as interpolation points; 2) Generate a SET card text file of structural interpolation points through a script program to perform aerodynamic structure interpolation.

[0012] Preferably, the selection principle of the structural grid nodes is as follows: Distribute as evenly as possible; Select the intersection of the main load-bearing structure, supporting structure and skin; Cover with aerodynamic grid.

[0013] Preferably, using the constructed aircraft wing-rudder structure model, within a predetermined Mach number and nominal state range, the wing-rudder wingtip root ratio is changed to perform flutter analysis, and a flutter safety margin analysis curve graph corresponding to the wing-rudder wingtip root ratio is obtained; Using the aircraft wing-rudder structure model, the flutter analysis is carried out by changing the size of the wing-rudder rocker arm within the predetermined Mach number and nominal state range, and the flutter safety margin analysis curve corresponding to the size of the wing-rudder rocker arm is obtained.

[0014] The beneficial effects of the present invention compared with the prior art are: In the prior art, during the development of aircraft, structural strength tests, vibration tests, flutter tests, etc. are required after the structural design is finalized. Flutter testing is a very important part and is carried out after the structural scheme is finalized. Due to the large workload of modeling and analysis, the development cycle of the aircraft is often extended. At the same time, if the structure does not meet certain flutter speed and flutter frequency requirements, design improvements are required, which undoubtedly repeats the previous work, increases the workload of flutter analysis, and reduces the efficiency of structural design.

[0015] The present invention provides a method for rapid flutter analysis of spacecraft suitable for cabin wing surface combination configurations through the study of typical wing-rudder structures and mechanism parametric modeling. By using this method, users can conveniently and quickly model and flutter analyze the aircraft, and can also quickly generate new analysis models for analysis and calculation after changing the key parameters of the structure, thereby reducing the workload and cost of flutter analysis work, and greatly improving the efficiency of aircraft structure design. When the initial structural design plan is not formed, a rapid parametric modeling and flutter analysis method can also be provided to the designer to help the designer complete the structural design more efficiently. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 Schematic diagram of parameter extraction for finite element modeling of wing-rudder structure; Figure 2 Finite element modeling for skin structures; Figure 3 Finite element modeling of the wing spar structure; Figure 4 Finite element modeling of wing ribs; Figure 5 It is a schematic diagram of the variable parameters of the flat panel mesh; Figure 6 Grid division for the wing, rudder and plate surface elements; Figure 7 Grid division for the tail wing and rudder plate; Figure 8 It is the aerodynamic grid of the whole aircraft flat panel structure of the wing-rudder combined cabin; Fig. 9 This is a schematic diagram of the optimization design of the shoot-root ratio; Fig.10 Schematic diagram of rocker arm size optimization design; DETAILED DESCRIPTION The present invention will be further described below in conjunction with the accompanying drawings.

[0017] The present invention studies the parametric modeling and flutter analysis methods of the aircraft wing-rudder structure and mechanism, and can realize rapid parametric modeling and modal simulation of finite element models of typical components such as wing-rudder skin and skeleton, while efficiently realizing flutter analysis of the wing-rudder structure and mechanism, so as to solve the problems in the prior art of frequent structural design adjustments during the aircraft development process, resulting in repeated flutter analysis work, delays, and extended cycles.

[0018] On this basis, the present invention can also provide analysis results of the influence of key parameters such as wing-rudder external dimensions, skin thickness, rocker arm stiffness, etc. on its flutter characteristics, so as to solve technical problems such as the influence of key parameters on the flutter boundary of the wing-rudder structure and the optimization adjustment of the wing-rudder structure and mechanism in the development process of prior art aircraft.

[0019] The analysis method of the present invention is as follows: 1. Parametric modeling method Considering that flutter analysis not only involves structural dynamics finite element modeling, but also includes aerodynamic-structural interpolation, aerodynamic meshing and the like, in order to better realize the parameterization of each link of flutter analysis, the present invention performs modeling through a programming language to realize parameterization; and adopts a programming method to realize the parameterization of the finite element model.

[0020] The flutter analysis modeling of the pneumatic rudder on a macro scale includes two aspects: structural modeling and aerodynamic mesh division. Parametric flutter analysis is to achieve parameterization of the structure and parameterization of the aerodynamic mesh. The establishment of the structural dynamics model mainly includes the division of the unit mesh and the assignment of unit attributes. In order to make the parametric modeling method more universal, it is convenient for modular operation and implementation.

[0021] 1.1 Initial modeling parameter extraction For the fuselage cabin structure, the main parameters extracted by finite element modeling include fuselage length L, fuselage section radius R, number of longitudinal beams N1 (by default, the longitudinal beams are evenly distributed along the circumference of the fuselage, and the circumferential position can also be specified), rectangular longitudinal beam section H1*B1 parameters, and number of bulkheads N2 (by default, the bulkheads are evenly distributed along the longitudinal direction of the fuselage, and the longitudinal position can also be specified).

[0022] The main parameters that can be extracted from the finite element modeling of the wing-rudder structure are as follows: Figure 1 As shown, it includes the wing root chord length b1, the wing tip chord length b2, the span l and the grid size j*k, etc.

[0023] 1.2 Modeling of fuselage structure The research objects of fuselage structure modeling mainly include skin, bulkhead and longitudinal beam. The specific modeling steps are as follows: 1) Extract characteristic parameters of the fuselage geometric shape, including fuselage length, space radius reserved for equipment loading in the bulkhead, wing root thickness, fuselage cross-sectional geometric parameters, number and location of bulkheads, and number and location of beams, etc.; 2) Perform 2D fuselage section geometry parametric modeling based on the extracted feature parameters 3) Call the modular subroutine function of surface stretching to stretch the two-dimensional geometric shape into a three-dimensional geometric shape according to the set stretching parameters; 4) Based on the three-dimensional shape, the modular subroutine function of curve stretching and the subroutine function of flat unit generation are called to freely set the number of bulkheads and the relative position of the bulkheads along the longitudinal direction of the fuselage to complete the geometric shape modeling of the fuselage.

[0024] In the above modeling process, the modeling objects are described as follows: The skin is the dimensional component of the fuselage, and its main function is to maintain the aerodynamic shape of the structure. Therefore, the unit division of the skin is basically consistent with the geometric shape of the fuselage. When dividing the skin unit grid, it is necessary to pay attention to the coordination with the unit boundaries of the internal skeleton structure. For example, the boundaries of components such as longitudinal beams and bulkheads. The coordination of unit boundaries is closely related to the parametric description of the internal structure, such as the position and relative inclination of longitudinal beams and bulkheads in the fuselage. In this way, the unit division of the skin also reflects the parametric implementation of the model.

[0025] The bulkhead structure is the main force transmission and load bearing structure of the aircraft. The structural finite element modeling of the bulkhead is similar to the skin modeling, and both use surface units for modeling. The parameterization of the unit is mainly described by position parameters and quantity parameters. The percentage of the bulkhead in the longitudinal length of the fuselage and the number of bulkheads are determined when the geometric model is created. In the modeling process, it is also necessary to pay attention to the coordination of the bulkhead unit and the skin unit, otherwise it will cause calculation errors.

[0026] The longitudinal beam is the longitudinal member of the fuselage that mainly bears bending moment and shear force. It is often simulated by beam elements in the dynamic finite element model. The wing beam unit can be described by quantity parameters, position parameters and section parameters. The quantity parameters of the beam are specified manually. Considering the coordination with the skin unit and the bulkhead unit nodes, the position parameters of the beam should be described with reference to the skin and bulkhead nodes. The section parameters of the beam are rectangular by default, and can also be parametrically modified to I-shaped, circular, L-shaped, etc.

[0027] 1.3 Modeling of wing-rudder structure The research objects of wing-rudder structure modeling mainly include skin, wing spar and wing rib. The specific modeling steps are as follows: 1) Describe the three-dimensional geometric shape of the wing (or control surface); 2) Perform two-dimensional plane meshing in the forward projection direction of the wing (or rudder) plane geometry; 3) Extract typical parameters of 2D plane meshing (such as the position of wing beams and ribs; the percentage of longitudinal and transverse components, etc.); call the modular subroutine function of curve stretching and the subroutine function of plate unit generation, set the number of transverse components and the relative positions of longitudinal and transverse components, 4) Using the skin shape as the boundary, the internal components are three-dimensionally unfolded in the thickness direction (implemented through the three-dimensional unfolding subroutine code).

[0028] There are two prerequisites for extending the structural model to the internal structural space and generating the internal structural unit grid: (1) the position of the internal components is considered when dividing the two-dimensional plane grid; (2) the three-dimensional shape of the wing surface (or rudder surface) has been unfolded. With the above two conditions, the typical components inside the rudder can be modeled smoothly. As conventional aerodynamic rudder components, typical structural components mainly include skin, wing beam and wing rib. Among them: The skin is a dimensional component of the aerodynamic rudder, and its main function is to maintain the aerodynamic shape of the structure. Therefore, the unit division of the skin is basically consistent with the aerodynamic shape of the rudder surface. When dividing the skin unit grid, it is necessary to pay attention to the coordination with the boundaries of the internal skeleton structure units, such as the boundaries of components such as spars and ribs. The coordination of unit boundaries is closely related to the parametric description of the internal structure, such as the position and relative inclination of spars and ribs on the rudder surface. In this way, the unit division of the skin also reflects the parametric implementation of the model. The generated skin structure unit is as follows: Figure 2 shown.

[0029] Since the division of skin units takes into account the internal skeleton structure of the rudder, such as wing beams, wing ribs, etc., the grid units will be sparse and dense when dividing the two-dimensional grid. In the leading edge of the skin, considering the large change in the curvature of its aerodynamic shape, the length of the grid unit is adjusted to be smaller to obtain a more accurate aerodynamic force distribution. In the triangular area of ​​the wing root part, the grid unit needs to be coordinated with the leading edge part, so the grid in the triangular area of ​​the wing root is also dense. At the wing tip of the rudder, the grid of the wing tip part is sparse because of the layout of the internal rib structure of the rudder and the coordination of the leading edge grid units.

[0030] The spar is the longitudinal component of the rudder surface, usually composed of a rib and a web. Its main function is to bear the shear force and bending moment of the wing surface and the shear force transmitted from each rib. The longitudinal wall cannot bear and transmit the bending moment of the wing surface. In a multi-web wing surface, the wall plays a major supporting role for the skin and bears the aerodynamic load directly transmitted from the skin.

[0031] The plate unit is often used in the finite element model of the dynamics of the wing beam structure. The wing beam unit can be described by position parameters and section parameters. The position parameters are mainly described in the form of two-dimensional plane units, such as the percentage position of the root chord point and the sweep angle of the wing beam. When describing the two-dimensional plane unit, the wing beam part has been considered. Therefore, the generation of the wing beam mesh can obtain the coordinate value of the wing beam three-dimensional mesh unit through the interpolation algorithm based on the position of the two-dimensional plane unit and the three-dimensional shape of the rudder surface. This also solves the problem of coordination between the skin unit mesh and the wing beam mesh unit.

[0032] The section parameters include beam height and flange width (thickness parameter is reflected in the unit properties), as shown in the schematic diagram. The beam height depends on the plane position and the height of the three-dimensional shape, which has been reflected in the position parameter description and three-dimensional shape expansion.

[0033] After the wing beam unit is parametrically described, the expansion from the three-dimensional shape to the internal structure can be achieved by defining the number of units in the height direction. The generated wing beam structure finite element model is as follows: Figure 3 shown.

[0034] The rib is a transverse member of the rudder surface, and sometimes the rib has a flange. Ordinary ribs do not participate in the overall force of the wing surface. Their main function is to bear local aerodynamic loads and maintain the shape of the wing surface.

[0035] The structural dynamics finite element model of the rib is similar to that of the wing beam. The parameterization of its unit can also be described by position parameters and section parameters. The rib unit can also be described by position parameters and section parameters. The position parameters are mainly described in the form of two-dimensional plane units, such as the percentage position of the rib on the front beam, and the rib inclination angle. When describing the two-dimensional plane unit, the rib part is also considered. Therefore, the generation of the rib mesh can obtain the coordinate value of the rib three-dimensional mesh unit through the interpolation algorithm based on the position of the two-dimensional plane unit and the three-dimensional shape of the rudder surface. This also solves the problem of coordination between the skin unit mesh and the rib mesh unit.

[0036] The parametric description of the wing rib unit and the generated wing rib finite element unit are shown in Figure 2. Figure 4 shown.

[0037] 1.4 Flat plate aerodynamic mesh generation and division of wing structure Since flutter is a self-excited vibration caused by aerodynamics, flutter analysis also requires aerodynamic data, and generalized unsteady aerodynamics are generally used. In engineering, the flat panel method is often used for calculation, which requires the division of the flat panel grid. The variable parameters of the flat panel grid are implemented as follows: Figure 5 The steps for aerodynamic meshing of flat surface elements of the wing structure are as follows: 1) Combined with the two-dimensional parametric segmentation of the wing model, the geometric shape parameters of the wing plane are extracted; 2) Based on the parameterization of the plane geometry, the script program for geometry processing automatically generates the corresponding flat panel mesh, so that the wing aerodynamic mesh can be parameterized.

[0038] At the current stage, the aerodynamic modeling will temporarily treat the wing-rudder structure as a whole. The aerodynamic flat panel mesh of the wing-rudder is as follows Figure 6 As shown, the tail fin rudder aerodynamic flat panel mesh is as follows Figure 7 shown.

[0039] The current aerodynamic grid is divided into 10 grids along the span direction of the wing surface and 50 grids along the span direction, which can meet the needs of flutter analysis of the research object. Based on the aerodynamic grid of the components, the aerodynamic grid of the whole aircraft is established in the current stage according to the spatial geometric position relationship of the wing surface and the structural model. Figure 8 shown.

[0040] 1.5 Aerodynamic structure interpolation After establishing the aerodynamic mesh of the flat plate surface, the next step is to select aerodynamic structure interpolation points on the structural surface.

[0041] The steps of aerodynamic structure interpolation are as follows: 1) Select the structural grid nodes on one side of the airfoil as interpolation points; 2) Generate a SET card text file of structural interpolation points through a script program.

[0042] In the above process, the principle for selecting structural interpolation points is usually to select structural nodes on the surface of one side of the wing; the distribution of structural interpolation nodes is as uniform as possible to reflect the overall structural modal vibration shape; the interpolation nodes are selected at the intersection of the main load-bearing structure, supporting structure and skin as much as possible to avoid the influence of local modal interpolation; the aerodynamic grid is covered as much as possible to avoid extrapolation during the aerodynamic structure interpolation process.

[0043] According to the established finite element model of the wing-rudder combined compartment structure, structural nodes for aerodynamic structure interpolation are selected on the surfaces of the wing surface structure and the tail surface structure.

[0044] 2. Structural optimization design method based on rudder flutter safety margin during the entire flight process The aforementioned parametric modeling method is used to reconstruct the model and extract key parameters for flutter analysis and calculation.

[0045] 3. Based on the flutter analysis of the aircraft wing-rudder structure and mechanism and the flutter sensitivity analysis results of typical key parameters, an optimization design method for the wing-rudder structure and mechanism is proposed with the flutter margin of the entire flight process as a constraint.

[0046] Example 1: Optimization design of wing tip root ratio Take the reference Mach number Ma = 3, change the wing tip root ratio of the rudder by 20% before and after the nominal state, and perform flutter analysis. Based on the calculated data, establish the following Fig. 9 The flutter safety margin analysis graph is shown.

[0047] On the premise that a 15% margin has been reserved, Fig. 9 It can be seen that when the tip-to-root ratio is 0.4, the flutter speed boundary has intersected the flight envelope, and the aircraft will flutter in this intersection area. In the case of a nominal tip-to-root ratio of 0.33, there is still a certain safety margin. In the case of a tip-to-root ratio of 0.25, the safety margin is larger.

[0048] Example 2: Optimal design of rocker arm size Take the reference Mach number Ma = 3, change the rudder rocker arm size by 20% before and after the nominal state, and perform flutter analysis. Based on the calculated data, the following is established: Fig.10 The flutter safety margin analysis graph is shown.

[0049] On the premise that a 15% margin has been reserved, Fig.10 It can be seen that when the rocker arm size is 19mm, the flutter velocity boundary intersects with the flight envelope. The aircraft is unsafe in this intersection area and should be avoided as much as possible. In the case of the nominal rocker arm size of 24mm, there is still a certain safety margin. In the case of the rocker arm size of 29mm, the safety margin is larger.

[0050] From the analysis of the above curves, it can be seen that when designing the key parameters of the wing-rudder structure and mechanism, under the premise of ensuring a certain margin, it is necessary to avoid the flutter speed boundary from intersecting the flight envelope. Designers can use the above optimization design method to select the key parameters of the wing-rudder structure and wing-rudder mechanism with a large safety margin during design to ensure the safety of the aircraft.

[0051] The present invention combines the parametric modeling, simulation, flutter analysis and optimization design of aircraft wing-rudder structures and mechanisms, provides a typical structural optimization design platform for wing-rudder structures and mechanisms, realizes rapid optimization of typical parameters and flutter boundary simulation, and provides a technical basis for the optimization of aircraft wing-rudder structures and mechanisms.

[0052] The platform includes parameter interaction module, structural modeling module, and flutter analysis module. The design platform has good parameter input, file operation, GUI graphical interface interaction, flutter analysis and other functions, which are easy for users to learn and master. On the basis of basic function settings, the platform adopts modular programming, realizes the development of various functions and the integration of tool platforms, all of which are presented on the GUI graphical interface for user convenience.

[0053] The parameter interaction module mainly corresponds to the "parameter input" and "file operation" functions of the design platform. The GUI graphical interface function is used to create an interactive interface for the tool platform under the GUI; the input parameter definition of the GUI text box is written through the subroutine code, and all key parameters are read into the platform for platform retrieval and use; the parameters are integrated to form mutual conversion of text file formats.

[0054] The structural modeling module mainly uses programming to realize the parametric generation of structural finite element models. And generate standard model calculation files. Among them, the combination of modeling parameters and structural models is mainly realized by writing modular program codes, providing parameters to the model template, and generating finite element model files.

[0055] The flutter analysis module is mainly divided into two parts. First, it mainly sets parameters such as "air density" and "reference Mach number" to generate a flat surface aerodynamic grid for flutter analysis. The shape parameters are used as the basic parameters for aerodynamic grid division, and the flat surface aerodynamic grid is defined in the "two-point chord length" method. By inputting parameters to give the grid partition "1, 4 points" coordinates and "1-2 chord length, 3-4 chord length", an aerodynamic grid card for flutter analysis is generated. Then use the GUI graphical interface to call it. By clicking the corresponding button, the solver program interface is automatically called, and the calculation input file generated by the previous module is selected to perform calculations and solutions for structural dynamics and flutter. Finally, a result file is generated, which contains the flutter analysis results.

[0056] The present invention studies the parametric modeling and flutter analysis methods of the aircraft wing-rudder structure and mechanism, and can realize rapid parametric modeling and modal simulation of finite element models of typical components such as wing-rudder skin and skeleton, while efficiently realizing flutter analysis of the wing-rudder structure and mechanism, so as to solve the problems in the prior art of frequent structural design adjustments during the aircraft development process, resulting in repeated flutter analysis work, delays, and extended cycles.

[0057] On this basis, the present invention can also provide analysis results of the influence of key parameters such as the wing-rudder external dimensions, skin thickness, and rocker arm stiffness on its flutter characteristics, so as to solve technical problems in the prior art and during the development of aircraft, such as the influence of key parameters on the flutter boundaries of the wing-rudder structure, and the optimization and adjustment of the wing-rudder structure and mechanism.

[0058] Finally, the present invention combines the parametric modeling, simulation, flutter analysis and optimization design of aircraft wing-rudder structures and mechanisms, provides a typical structural optimization design platform for wing-rudder structures and mechanisms, realizes rapid optimization of typical parameters and flutter boundary simulation, and provides a technical basis for the optimization of aircraft wing-rudder structures and mechanisms.

[0059] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. A method for rapid analysis of spacecraft flutter applicable to cabin-wing surface combination configuration, characterized in that: include: Parametric modeling of aircraft wing and rudder structures; Using the aircraft wing-rudder structure model, key parameters are extracted for flutter analysis and calculation; Based on the flutter analysis results, the wing-rudder structure is optimized with the flutter margin of the entire flight process as a constraint.

2. A method for rapid analysis of spacecraft flutter applicable to a cabin-wing surface combination configuration according to claim 1, characterized in that: The process of parametric modeling of the aircraft wing and rudder structure is as follows: 1.1 Extract initial modeling parameters; 1.2 Modeling of the fuselage compartment structure; 1.3 Model the wing-rudder structure; 1.4 Generate and divide the flat aerodynamic grid of the wing structure to obtain the finite element model of the aircraft wing and rudder structure; 1.5 According to the established finite element model of the aircraft wing-rudder structure, structural nodes are selected on the surfaces of the wing surface structure and the tail wing surface structure to perform aerodynamic structure interpolation.

3. A method for rapid analysis of spacecraft flutter applicable to a cabin-wing surface combination configuration according to claim 2, characterized in that: In step 1.1, when extracting the initial modeling parameters, For the fuselage compartment structure, the extracted initial modeling parameters include fuselage length, fuselage section radius, number of longitudinal beams, rectangular longitudinal beam section parameters, and number of bulkheads; The initial modeling parameters extracted for the wing-rudder structure include wing root chord length, wing tip chord length, span and grid size.

4. A method for rapid analysis of spacecraft flutter applicable to a cabin-wing combination configuration according to claim 2, characterized in that: In step 1.2, the fuselage compartment structure is modeled as follows: 1) Extract characteristic parameters of the fuselage geometry; 2) Perform 2D fuselage section geometry parametric modeling based on the extracted characteristic parameters; 3) Call the modular subroutine function of surface stretching to stretch the two-dimensional geometric shape into a three-dimensional geometric shape according to the set stretching parameters; 4) Based on the three-dimensional shape, the modular subroutine function of curve stretching and the subroutine function of flat unit generation are called to freely set the number of bulkheads and the relative position of the bulkheads along the longitudinal direction of the fuselage to complete the geometric shape modeling of the fuselage.

5. The method for rapid analysis of spacecraft flutter applicable to a cabin-wing surface combination configuration according to claim 2, characterized in that: In step 1.3, the wing-rudder structure is modeled as follows: 1) Describe the three-dimensional geometric shape of the wing or control surface; 2) Perform two-dimensional plane meshing in the forward projection direction of the wing or rudder plane geometry; 3) Extract typical parameters of 2D plane meshing, set the number of transverse components and the relative positions of longitudinal and transverse components; 4) Using the outer shape of the skin as the boundary, unfold the internal components three-dimensionally in the thickness direction.

6. A method for rapid analysis of spacecraft flutter applicable to a cabin-wing combination configuration according to claim 5, characterized in that: When performing two-dimensional plane meshing in step 2), the position of internal components needs to be considered.

7. The method for rapid analysis of spacecraft flutter applicable to a cabin-wing surface combination configuration according to claim 2, characterized in that: In step 1.4, the flat aerodynamic grid of the wing structure is generated and divided as follows: 1) Extract the geometric parameters of the wing plane; 2) Based on the parameterization of the plane geometric shape, the corresponding flat panel mesh is generated to parameterize the wing aerodynamic mesh.

8. The method for rapid flutter analysis of spacecraft applicable to a cabin-wing surface combination configuration according to claim 2, characterized in that: The implementation method of step 1.5 is as follows: 1) For the established finite element model of the aircraft wing and rudder structure, the structural grid nodes on one side of the wing surface are selected as interpolation points; 2) Generate a SET card text file of structural interpolation points through a script program to perform aerodynamic structure interpolation.

9. A method for rapid analysis of spacecraft flutter applicable to a cabin-wing surface combination configuration according to claim 8, characterized in that: The selection principles of structural grid nodes are as follows: Distribute as evenly as possible; Select the intersection of the main load-bearing structure, supporting structure and skin; Cover with aerodynamic grid.

10. The method for rapid analysis of spacecraft flutter applicable to a cabin-wing surface combination configuration according to claim 1, characterized in that: By using the aircraft wing-rudder structure model, the flutter analysis is performed by changing the wing-rudder wingtip root ratio within the predetermined Mach number and nominal state range, and the flutter safety margin analysis curve corresponding to the wing-rudder wingtip root ratio is obtained; Using the aircraft wing-rudder structure model, the flutter analysis is carried out by changing the size of the wing-rudder rocker arm within the predetermined Mach number and nominal state range, and the flutter safety margin analysis curve corresponding to the size of the wing-rudder rocker arm is obtained.

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