Parameterization method for structural design of telescopic deformation wing in high-speed flight environment

Abstract

The invention discloses a parameterization method for design of a telescopic deformation wing structure in a high-speed flight environment, and the method comprises the steps: building an initial parameterization model of a wing according to basic parameters of a complete stretching state of the wing; each wing is divided into a fixed section and a telescopic section; a group of spanwise telescopic mechanisms and a main beam are arranged at the wing root of the fixed section, and three groups of thin beams at the root parts of the fixed section and the telescopic section are parameterized and positioned by taking the spanwise telescopic mechanisms and the main beam as reference, so that the groups of thin beams surround the corresponding telescopic mechanisms or main beams; three wide beams are arranged at the tip of the telescopic section; a self-defined supplementary spar needs to be arranged at the leading edge; determining the positions of the wing ribs according to the elongation of each section and the preset number of the wing ribs; and in combination with the positions of the telescopic mechanism and the main beam and wing root wing parameters of the telescopic section, through stretching and cutting operation, holes are formed in the positions of corresponding wing ribs, and a space for accommodating the telescopic section is reserved in the fixed section, so that parametric modeling of the wing structure is completed. According to the method, flexible parameter adjustment, optimization and verification can be carried out to meet the requirements of various flight mission profiles.

Description

Technical Field

[0001] The present invention relates to the technical field of wing structure design, and in particular to a parameterized method for designing a telescopic deformation wing structure in a high-speed flight environment. Background Art

[0002] With the rapid development of aerospace technology, research on morphable wings for high-speed flight has become increasingly popular. Extreme flight environments place higher demands on wing structural design, requiring both reliability and stability under extreme aerodynamic conditions while also improving maneuverability.

[0003] Traditional high-speed aircraft often use fixed wing structures. Although this type of wing simplifies the design and manufacturing process, it will be severely affected by thermo-aeroelastic effects and structural loads in extreme environments, making it difficult to maintain the optimal lift-to-drag ratio and stability at different flight speeds. In addition, fixed wings have poor adaptability in the high-speed domain and cannot flexibly adjust the wing shape for different mission profiles (such as cruising, acceleration, and hovering). In recent years, in order to improve the performance of wings under high-speed flight conditions, some studies have attempted to use deformable wing structures, including changing the wing span, sweep angle, or chord length distribution through servo mechanisms to optimize aerodynamic characteristics in different speed ranges. However, these methods mostly rely on empirical models and repeated experiments, and lack systematic and parameterized design methods, resulting in long design cycles, high costs, and difficulty in rapid iterative optimization.

[0004] With the advancement of computing power, parametric design and simulation-based optimization techniques have become widely used in aerospace structures. However, mature parametric methods are still lacking for the design of morphing wing structures in high-speed flight environments. Most current design processes still rely heavily on manual parameter adjustment and trial-and-error, lacking a fast-converging, scalable parametric construction and optimization framework.

[0005] In summary, existing wing design methods for high-speed aircraft lack efficient parametric modeling and optimization methods for telescopic morphing wings. Therefore, a systematic approach is urgently needed to rapidly establish a parametric model for telescopic morphing wings and flexibly adjust, optimize, and validate it to meet the requirements of various flight mission profiles. Summary of the Invention

[0006] In view of this, the purpose of the present invention is to provide a parametric method for the structural design of telescopic deformable wings in a high-speed flight environment, so as to solve the problem of lack of efficient parametric modeling and optimization means for telescopic deformable wings raised in the background art.

[0007] The present invention solves the technical problem by adopting the following technical solutions:

[0008] A parameterized method for designing a telescopic and deformable wing structure in a high-speed flight environment comprises the following steps:

[0009] Step S1: establishing an initial parameterized model of the wing based on the basic parameters of the wing in a fully extended state;

[0010] Step S2: The wing is divided into a fixed section and a telescopic section. The telescopic section is divided into a root portion that is completely retracted into the fixed section and a tip portion that cannot be retracted.

[0011] Step S3: A spanwise telescopic mechanism and a main beam are arranged at the root of the fixed section. Based on this, three sets of thin beams with a thickness of t1 are parametrically positioned at the root of the fixed section and the telescopic section, so that each set of thin beams surrounds the corresponding telescopic mechanism or main beam. Three wide beams with a thickness of t1 are arranged at the tip of the telescopic section to enhance spanwise stiffness.

[0012] Step S4: A customized supplementary spar needs to be arranged at the leading edge to enhance the structural strength and rigidity of the wing leading edge;

[0013] Step S5: Determine the rib positions according to the spans of each section and the preset number of ribs, with the rib thickness being t2;

[0014] Step S6: Based on the telescopic mechanism, the position of the main beam, and the wing root airfoil parameters of the telescopic section, holes are formed at the corresponding rib positions through stretching and cutting operations, and space is reserved in the fixed section to accommodate the telescopic section, thereby completing the parametric modeling of the wing structure.

[0015] Furthermore, in the initial parametric model of the wing, the leading edge of the wing root is the origin, the chord length direction is the X direction, and the span direction is the Y direction. The basic parameters of the wing in the fully extended state include the half span l, the root chord length c0, the tip chord length c1, and the sweep angle Λ.

[0016] Furthermore, the method of establishing the initial parametric model of the wing in step 1 is as follows: multiplying the normalized airfoil coordinates with the corresponding chord length to obtain the wing root and wingtip sections; drawing the leading and trailing edge guide lines based on the sweep angle Λ and the half span l; and finally generating the overall initial wing model based on the guide lines and sections.

[0017] Furthermore, in step S2, the ratio of the length of the fixed section to the length in the fully extended state is k0, and the ratio of the length of the overlapping part of the fixed section and the telescopic section in the fully extended state is k1. Based on this, the length of the fixed section is calculated to be l0=k0*l, the length of the overlapping part is l'=k1*l, the length of the root of the telescopic section is l1=l0, and the length of the tip of the telescopic section is l2=(1+k1)*l-l0-l1.

[0018] Furthermore, in step 3, the main beam position coordinates are x0 and the diameter is d0; the leading edge telescopic mechanism coordinates are x11 and the diameter is d11; the trailing edge telescopic mechanism position coordinates x12 are determined as x12=2*x0-x11 according to the mirror relationship, and the diameters d12 and d11 are equal; the lengths of the three are all equal to the fixed section extension length.

[0019] Furthermore, in step 3, the three groups of thin beams in the fixed section and the telescopic section are offset by a distance x' along the X direction relative to the main beam or telescopic mechanism they surround, and the X coordinates of the thin beams are defined as x11±x', x0±x' and x12±x'.

[0020] Furthermore, the number of supplementary spars customized in step 4 is n0, and the spacing is x2'.

[0021] Furthermore, in step 5, the number of ribs in the fixed section is n1, the number of ribs at the root of the telescopic section is n2, and the number of ribs at the tip of the telescopic section is n3, and the coordinates are initially set to be evenly distributed along the span direction.

[0022] Furthermore, the stretching and cutting operation in step 6 should be performed along the movement direction of the telescopic mechanism; wherein, for the fixed section wing, the cutting range does not exceed the wing root plane; for the telescopic section wing, only the root ribs are cut.

[0023] Furthermore, all parameters can be modified and adjusted based on simulation or testing after modeling to meet the strength, stiffness and stability requirements of the structural design.

[0024] The present invention discloses a parameterized method for designing a telescopic and deformable wing structure in a high-speed flight environment, which has the following beneficial effects:

[0025] 1. Efficiency: By defining a series of key parameters, this invention can quickly construct a parametric model of the wing. This reduces reliance on manual trial and error, making the design process more efficient.

[0026] 2. Flexibility: Parametric methods allow designers to quickly adjust various parameters, enabling agile design iterations based on mission requirements and performance targets. This flexibility enables the wing to achieve the optimal configuration under varying loads and flight conditions.

[0027] 3. Overall Scalability: Once a high-speed wing design is obtained, new designs can be quickly generated for other aircraft or different demand scenarios (such as different flight altitudes and speed ranges) by simply adjusting some parameters. This scalability facilitates the promotion and application of this method in a wider range of aviation and spacecraft designs. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 is a flow chart of the method of the present invention;

[0029] Figure 2 This is a schematic diagram of the initial wing model;

[0030] Figure 3 It is a schematic diagram of the structure of the fixed section of the wing;

[0031] Figure 4 It is a schematic diagram of the structure of the telescopic section of the wing;

[0032] Figure 5 It is a schematic diagram of the overall structure of the telescopic deformable wing;

[0033] Figure 6 It is the parameter definition and distribution diagram.

[0034] Among them, in the figure:

[0035] 1- telescopic mechanism, 2- main beam, 3- thin beam, 4- supplementary wing beam, 5- wing rib, 6- fixed section wing, 7- wide beam, 8- telescopic section wing. DETAILED DESCRIPTION

[0036] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0037] refer to Figure 1 The present invention discloses a parameterized method for designing a telescopic deformable wing structure in a high-speed flight environment, comprising the following steps:

[0038] Step S1: establishing an initial parameterized model of the wing based on the basic parameters of the wing in a fully extended state;

[0039] Step S2: The wing is divided into a fixed section and a telescopic section. The telescopic section is divided into a root portion that is completely retracted into the fixed section and a tip portion that cannot be retracted.

[0040] Step S3: A spanwise telescopic mechanism and a main beam are arranged at the root of the fixed section. Based on this, three sets of thin beams with a thickness of t1 are parametrically positioned at the root of the fixed section and the telescopic section, so that each set of thin beams surrounds the corresponding telescopic mechanism or main beam. Three wide beams with a thickness of t1 are arranged at the tip of the telescopic section to enhance spanwise stiffness.

[0041] Step S4: Since a high-speed flight environment requires a large sweep angle, the chord length of the fixed section may be significantly longer than that of the telescopic section. Therefore, a customized supplementary spar is arranged at the leading edge to enhance the structural strength and stiffness of the wing leading edge.

[0042] Step S5: Determine the rib positions according to the spans of each section and the preset number of ribs, with the rib thickness being t2;

[0043] Step S6: Based on the telescopic mechanism, the position of the main beam, and the wing root airfoil parameters of the telescopic section, holes are formed at the corresponding rib positions through stretching and cutting operations, and space is reserved in the fixed section to accommodate the telescopic section, thereby completing the parametric modeling of the wing structure.

[0044] The method of the present invention can effectively reduce the complexity of the design of telescopic deformable wing structures under high-speed flight conditions, is applicable to diverse flight requirements, and provides an efficient and simple parameterization method for the rapid design and research of high-speed flight wing structures.

[0045] To further optimize the technical solution, in the initial parametric model of the wing, the leading edge of the wing root is the origin, the chord length direction is the X direction, and the span direction is the Y direction. The basic parameters of the wing in the fully extended state include half span l, root chord length c0, tip chord length c1, and sweep angle Λ.

[0046] To further optimize the technical solution, the method for establishing the initial parametric model of the wing in step 1 is as follows: multiply the normalized airfoil coordinates by the corresponding chord length to obtain the wing root and wingtip sections; draw the leading and trailing edge guide lines based on the sweep angle Λ and the half span l; and finally generate the overall initial wing model based on the guide lines and sections.

[0047] To further optimize the technical solution, in step S2, the ratio of the length of the fixed segment to the length in the fully extended state is k0, and the ratio of the length of the overlapping part of the fixed segment and the telescopic segment in the fully extended state is k1. Based on this, the length of the fixed segment is calculated to be l0=k0*l, the length of the overlapping part is l'=k1*l, the length of the root of the telescopic segment is l1=l0, and the length of the tip of the telescopic segment is l2=(1+k1)*l-l0-l1.

[0048] To further optimize the technical solution, in step 3, the main beam position coordinates are x0 and the diameter is d0; the leading edge telescopic mechanism coordinates are x11 and the diameter is d11; the trailing edge telescopic mechanism position coordinates x12 are determined as x12=2*x0-x11 according to the mirror relationship, and the diameters d12 and d11 are equal; the lengths of the three are all equal to the fixed section extension length.

[0049] To further optimize the technical solution, in step 3, the three groups of thin beams in the fixed section and the telescopic section are offset by a distance x' along the X direction relative to the main beam or telescopic mechanism they surround, and the X coordinates of the thin beams are defined as x11±x', x0±x' and x12±x'.

[0050] To further optimize the technical solution, the number of customized supplementary wing beams in step 4 is n0, and the spacing is x2'.

[0051] To further optimize the technical solution, in step 5, the number of ribs in the fixed section is n1, the number of ribs at the root of the telescopic section is n2, and the number of ribs at the tip of the telescopic section is n3. The coordinates are initially set to be evenly distributed along the span direction.

[0052] To further optimize the technical solution, the stretching and cutting operation in step 6 should be performed along the movement direction of the telescopic mechanism; wherein, for the fixed section wing, the cutting range does not exceed the wing root plane; for the telescopic section wing, only the root ribs are cut.

[0053] To further optimize the technical solution, all parameters can be modified and adjusted based on simulation or testing after modeling to meet the strength, stiffness and stability requirements of the structural design.

[0054] The present invention discloses a parametric method for the structural design of telescopic and deformable wings in a high-speed flight environment, which has the following beneficial effects: High efficiency: The present invention can quickly construct a parametric model of the wing by defining a series of key parameters. This reduces the reliance on manual trial and error, making the design process more efficient. Flexibility: Through the parametric method, the designer can quickly adjust various parameters, thereby performing agile design iterations based on mission requirements and performance indicators. This flexibility enables the wing to achieve the optimal form under different loads and flight conditions. Overall scalability: After obtaining a certain high-speed flight wing solution, new solutions can be quickly generated for other aircraft or different demand scenarios (such as different flight altitudes, speed ranges) by adjusting only some parameters. This scalability helps the method to be promoted and applied in a wider range of aviation or spacecraft designs.

[0055] Example

[0056] Figure 1 This is a flow chart of the design method of the present invention. Step 1 is to generate an initial model based on the basic parameters of the wing. The normalized airfoil coordinates are multiplied by the corresponding chord length to obtain the cross-sections of the wing root and wingtip. The leading and trailing edge guide lines of the wing are drawn according to the sweep angle Λ and the half span l. Finally, the guide lines and cross-sections are combined to generate the Figure 2 The overall initial wing model is shown.

[0057] Step 2 is to divide the wing into a fixed section and a telescopic section according to a preset ratio. The telescopic section is further divided into a root portion that is completely retracted into the fixed section and a tip portion that cannot be retracted. Figure 3 and Figure 4 As shown. Define the ratio of the fixed segment length to the fully extended state length as k0, and the ratio of the length of the overlapping part of the fixed segment and the telescopic segment in the fully extended state as k1. Based on these ratios, we can calculate:

[0058] Fixed segment length l0=l*k0

[0059] The length of the overlapping part l'=k1*l

[0060] Extension length of the telescopic section root l1 = l0

[0061] Extension length of telescopic section tip l2=(1+k1)*l-l0-l1

[0062] Step 3 is to set up a set of span-wise telescopic mechanisms 1 and a main beam 2 at the root of the fixed section wing, such as Figure 3 As shown. The main beam position coordinate is x0, and the diameter is d0; the leading edge telescopic mechanism coordinate is x11, and the diameter is d11; the trailing edge telescopic mechanism position coordinate x12 is determined by the symmetry relationship as x12 = 2*x0 - x11, and the diameter d12 = d11; the lengths of all three are equal to the length of the fixed section. Based on this, the three sets of thin beams 3 with a thickness of t1 at the root of the fixed section and the telescopic section are parametrically positioned, as shown in the figure. Figure 3 and Figure 4 As shown, each group of thin beams surrounds the corresponding telescopic mechanism or main beam. Three wide beams 7 with a thickness of t1 are arranged at the end of the telescopic section, as shown in FIG. Figure 4 As shown, to enhance the spanwise stiffness.

[0063] Step 4 is to arrange the customized supplementary spar 4 in the fixed section. Figure 3 As shown, the number of supplementary spars is n0 and the spacing is x2'. These supplementary spars are used to enhance the structural strength and aerodynamic performance of the wing leading edge area, especially at large sweep angles.

[0064] Step 5 is to position the spar according to the span and number parameters. The number of ribs in the fixed section is n1, the number of ribs in the root of the telescopic section is n2, and the number of ribs in the tip of the telescopic section is n3. The ribs are initially evenly distributed along the span. If n1 = n2 = 1 and n3 = 2, the distribution of rib 5 is as follows: Figure 3 and Figure 4 shown.

[0065] In step 6, based on the telescopic mechanism, the position of the main beam and the wing root airfoil parameters of the telescopic section, holes are formed at the corresponding wing rib positions through stretching and cutting operations, and space is reserved in the fixed section to accommodate the telescopic section.

[0066] The specific operations are as follows:

[0067] 1. Stretch cutting direction: along the movement direction of the telescopic mechanism, in this case the Y direction;

[0068] 2. Extent of resection:

[0069] a) For the fixed section wing 6, the cut-off range does not exceed the wing root plane, such as Figure 3 As shown;

[0070] b) For the telescopic wing 8, only the root ribs are cut off, such as Figure 4 shown.

[0071] At this point, the parametric modeling of the wing is complete, and the overall structure of the telescopic deformable wing is as follows: Figure 5 As shown, the overall parameter definition and distribution are as follows Figure 6 The parameter definition table is shown in Table 1.

[0072]

[0073] Table 1

[0074] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A parameterized method for designing a telescopic wing structure for high-speed flight, characterized in that: The process includes the following steps: Step S1: establishing an initial parameterized model of the wing based on the basic parameters of the wing in a fully extended state; Step S2: The wing is divided into a fixed section and a telescopic section. The telescopic section is divided into a root portion that is completely retracted into the fixed section and a tip portion that cannot be retracted. Step S3: A spanwise telescopic mechanism and a main beam are arranged at the root of the fixed section. Based on this, three sets of thin beams with a thickness of t1 are parametrically positioned at the root of the fixed section and the telescopic section, so that each set of thin beams surrounds the corresponding telescopic mechanism or main beam. Three wide beams with a thickness of t1 are arranged at the tip of the telescopic section to enhance spanwise stiffness. Step S4: A customized supplementary spar needs to be arranged at the leading edge to enhance the structural strength and rigidity of the wing leading edge; Step S5: Determine the rib positions according to the spans of each section and the preset number of ribs, with the rib thickness being t2; Step S6: Based on the telescopic mechanism, the position of the main beam, and the wing root airfoil parameters of the telescopic section, holes are formed at the corresponding rib positions through stretching and cutting operations, and space is reserved in the fixed section to accommodate the telescopic section, thereby completing the parametric modeling of the wing structure.

2. The parameterized method for designing a telescopic wing structure in a high-speed flight environment according to claim 1, characterized in that: In the initial parametric model of the wing, the leading edge of the wing root is the origin, the chord length direction is the X direction, and the span direction is the Y direction. The basic parameters of the wing in the fully extended state include the half span l, the root chord length c0, the tip chord length c1, and the sweep angle Λ.

3. The parameterized method for designing a telescopic wing structure in a high-speed flight environment according to claim 2, characterized in that: The method for establishing the initial parametric model of the wing in step 1 is as follows: multiply the normalized airfoil coordinates by the corresponding chord length to obtain the wing root and wingtip sections; draw the leading and trailing edge guide lines based on the sweep angle Λ and the half span l; and finally generate the overall initial wing model based on the guide lines and sections.

4. The parameterized method for designing a telescopic wing structure in a high-speed flight environment according to claim 3, characterized in that: In step S2, the ratio of the length of the fixed section to the length in the fully extended state is k0, and the ratio of the length of the overlapping part of the fixed section and the telescopic section in the fully extended state is k1. Based on this, the length of the fixed section is calculated to be l0=k0*l, the length of the overlapping part is l'=k1*l, the length of the root of the telescopic section is l1=l0, and the length of the tip of the telescopic section is l2=(1+k1)*l-l0-l1.

5. The parameterized method for designing a telescopic wing structure in a high-speed flight environment according to claim 3, characterized in that: In step 3, the main beam position coordinates are x0 and the diameter is d0; the leading edge telescopic mechanism coordinates are x11 and the diameter is d11; the trailing edge telescopic mechanism position coordinates x12 are determined as x12=2*x0-x11 according to the mirror relationship, and the diameters d12 and d11 are equal; the lengths of the three are all equal to the fixed section extension length.

6. The parameterized method for designing a telescopic wing structure in a high-speed flight environment according to claim 5, characterized in that: In step 3, the three groups of thin beams in the fixed section and the telescopic section are offset by a distance x' along the X direction relative to the main beam or telescopic mechanism they surround, and the X coordinates of the thin beams are defined as x11±x', x0±x' and x12±x'.

7. A parameterized method for designing a telescopic wing structure in a high-speed flight environment according to claim 1 or 6, characterized in that: The number of supplementary spars customized in step 4 is n0, and the spacing is x2'.

8. The parameterized method for designing a telescopic wing structure for high-speed flight environment according to claim 1 or 6, characterized in that: In step 5, the number of ribs at the fixed section is n1, the number of ribs at the root of the telescopic section is n2, and the number of ribs at the tip of the telescopic section is n3. The coordinates are initially set to be evenly distributed along the span direction.

9. A parameterized method for designing a telescopic and deformable wing structure in a high-speed flight environment according to claim 1 or 6, characterized in that: The stretching and cutting operation in step 6 should be performed along the movement direction of the telescopic mechanism; wherein, for the fixed section wing, the cutting range does not exceed the wing root plane; for the telescopic section wing, only the root ribs are cut.

10. The parameterized method for designing a telescopic wing structure in a high-speed flight environment according to claim 9, characterized in that: All parameters can be modified and adjusted based on simulation or testing after modeling to meet the strength, stiffness and stability requirements of the structural design.

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