Fish bone imitating concept and zero poisson ratio lattice structure-based driving torque-rotation angle curve analysis and prediction model for variable-camber structure of wing
By establishing a driving torque-angle curve analysis and prediction model of the wing variable curvature structure based on the concept of imitation fish bones and zero-Poisson's ratio dot matrix structure, the eccentric lever rotates to drive the wing variable curvature structure, the problem of difficult to quickly and with high accuracy in the prior art is solved, and simple matching of driving system parameters and energy consumption optimization are achieved.
Patent Information
- Application Number
- CN202510585972.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-08
- Publication Date
- 2025-08-19
AI Technical Summary
The prior art is difficult to quickly and with high accuracy to predict the dynamic relationship between the driving torque and rotation angle of the wing variable camber structure, affecting the parameter matching of the driving system and the energy consumption optimization.
A driving torque-angle curve analysis and prediction model of the wing variable curvature structure based on the concept of imitation fish bones and zero Poisson's ratio dot matrix structure is established. The wing variable curvature structure is driven by the symmetrically installed eccentric lever, and the relationship between torque and angle is calculated using the energy method.
The rapid and high-precision prediction of the drive torque-angle curve of the wing variable curvature structure is realized, and the parameter matching and energy consumption optimization of the drive system are simplified.
Smart Images
Figure CN120509110A_ABST
Abstract
Description
Technical Field
[0001] The invention provides a wing variable camber structure driving torque-angle curve analytical prediction model based on a fishbone-like concept and a zero Poisson's ratio lattice structure, belonging to the field of aviation. Background Art
[0002] As a core component of a morphing aircraft, a variable-camber wing structure can optimize aerodynamic performance by adjusting wing camber. However, the design and control of its drive system relies on characterizing the dynamic relationship between drive torque and rotation angle. Therefore, it is urgent to establish an analytical prediction model for the drive torque-angle curve of a variable-camber wing structure based on the fishbone concept and a zero-Poisson's ratio lattice structure. This model can achieve rapid and high-precision prediction of the drive torque-angle curve for the variable-camber wing structure, providing a theoretical tool for drive system parameter matching and energy optimization. Summary of the Invention
[0003] The present invention establishes an analytical prediction model for the driving torque-angle curve of a wing variable camber structure based on the fishbone concept and a zero Poisson's ratio lattice structure. The method has the advantages of simple calculation and high accuracy. The technical solution is as follows:
[0004] The up / down deflection of the wing camber structure is achieved by the rotation drive of the symmetrically installed eccentric lever. Figure 1 This is a schematic diagram of the wing's variable camber structure. Each time the eccentric lever rotates a certain angle, the wing's variable camber structure assumes a corresponding geometric configuration. To establish a theoretical model for predicting the driving torque-rotation angle relationship during the deflection process of the wing's variable camber structure, the following assumptions are made:
[0005] (1) During the deflection process, the deformation of the upper and lower wing surface corrugated units of the wing variable camber structure is in the form of tension or compression;
[0006] (2) In the defined a-xyz coordinate system, the y-axis coordinate of the intersection of the centerline of the eccentric lever and the centerline of the web of the variant structure remains unchanged;
[0007] (3) In the yz plane, through the intersection of the projection curve of the eccentric lever centerline and the projection line of the centerline of the web of the variant structure, draw a tangent to the projection curve of the eccentric lever centerline. The angle between the tangent and the projection line of the centerline of the web remains unchanged.
[0008] (4) Ignore the friction between the eccentric lever and the web of the variant structure.
[0009] The energy method was used to calculate the relationship between the torque of the eccentric lever and the rotation angle of the eccentric lever during the deflection of the wing's variable-camber structure. The work performed by the eccentric lever during the deflection of the wing's variable-camber structure is equal to the strain energy stored during the extension and compression of the corrugated unit.
[0010] According to the energy principle, the work done by a single eccentric lever is
[0011]
[0012] Where M(θ) is the torque of the eccentric lever, and θ1 and θ2 are the rotation angles of the eccentric lever.
[0013] The strain energy stored in the corrugated element during the stretching and compression process is
[0014]
[0015] Where P(δ) is the load during the stretching or compression of the corrugated unit, and δ1 and δ2 are the displacements during the stretching or compression of the corrugated unit.
[0016] When the eccentric lever rotates 0 degrees, select any three non-coincident points on its axis to establish the xy plane, and construct the three-dimensional rectangular coordinate system a-xyz through point a, as shown in Figure 2 As shown in Figure 1. Point a serves as the coordinate origin. The eccentric lever's segment ab' is a straight line, while the remainder is a circular arc. Point b' is the point of tangency between the arc and the straight line, and the straight line ab' coincides with the y-axis. The eccentric lever rotates about the straight line ab'. The calculations in this section are based on the established a-xyz three-dimensional rectangular coordinate system.
[0017] The variant structure and the af section of the eccentric lever have a uniform cross-section, and the cross-sectional diameter of the af section of the eccentric lever is consistent with the width of the slot in the middle of the web. During the rotation of the eccentric lever, it always fits tightly against the web, and the small cross-sectional end always maintains contact with the rear wall, ensuring that the y-axis coordinate of the intersection of the web centerline and the eccentric lever centerline remains constant. To simplify the calculation process, the projection of the central axis of the variant structure and the eccentric lever on the yaz plane is selected for study, as shown in the figure below: Figure 3 As shown in Figure 1. Points B, C, D, E, and F are the coordinates of the intersection of the web centerline and the upper wing surface centerline, respectively. Points B', C', D', E', and F' are the coordinates of the intersection of the web centerline and the lower wing surface centerline. Points b, c, d, e, and f are the coordinates of the intersection of the web centerline and the projection curve of the eccentric lever centerline on the yaz plane.
[0018] When calculating the strain energy of a zero-Poisson's-ratio lattice structure, the tensile / compressive deformation of the corrugated element must be used as an input parameter. Therefore, before calculating the strain energy, the coordinates of the upper surface points A to F and the lower surface points A' to F' of the variant structure under different deflection states must be determined. Based on the assumptions of this section, the relative positions and distances between the six intersection points on the eccentric lever and the intersection points of the upper and lower airfoils remain unchanged. Therefore, the coordinates of the intersection of the projection curve of the eccentric lever's central axis on the yaz plane and the centerline of the web under different deflection states must first be determined. The coordinates of the intersection of the upper and lower airfoils can then be derived using geometric relationships.
[0019] When the eccentric lever rotates 0 degrees, the expression of the center axis of the arc part of the eccentric lever is
[0020]
[0021] where x0=172.063, y0=34.070, r=171.455, x el-min =0,x el-max =12.544,y el-min =34.065,
[0022] y el-max =98.428.
[0023] Evenly select 60 points on the arc, the coordinates of each point are
[0024]
[0025] The eccentric lever drives the variant structure to deflect by a certain angle. In order to obtain the center of the arc segment of the eccentric lever and the coordinates of each point on the arc segment after the rotation of a certain angle, a rotation matrix needs to be introduced. The rotation matrix of the eccentric lever is
[0026]
[0027] Where θ is the rotation angle of the eccentric lever.
[0028] The coordinate matrix of the center of the eccentric lever arc after rotating a certain angle is:
[0029]
[0030] The coordinate matrix of 60 points on the arc of the eccentric lever after rotating a certain angle is
[0031]
[0032] After rotating a certain angle, the coordinates of 60 points on the eccentric lever arc projected onto the yz plane are
[0033]
[0034] The 60 points projected onto the yz plane are fitted using the least squares method to obtain the fitting curve:
[0035]
[0036] Where a, b, and c are determined by the rotation angle θ of the eccentric lever, z f and y f are the two variables of the fitting curve, y f-min =0,yf-max =98.428.
[0037] Draw a straight line perpendicular to the tangent line of the overfitting curve at any point (such as Figure 3 The expression is shown as
[0038]
[0039] A straight line coinciding with the centerline of the web (e.g. Figure 3 The expression is shown as
[0040]
[0041] Among them, θ j It is the angle between the line perpendicular to the tangent and the centerline of the web.
[0042] Draw a circle with the intersection of the web centerline and the eccentric lever centerline projected onto the yaz plane curve as the center and the distance from the intersection to the upper / lower wing surface as the radius (e.g. Figure 3 As shown), we can get
[0043] (yy f ) 2 +(zz f ) 2 =r web 2 (12) Among them, r web It is the distance from the intersection of the web centerline and the projection of the eccentric lever centerline to the upper / lower wing surface along the web centerline.
[0044] By combining equations (11) and (12), we can get the coordinates of point A to point F and point A' to point F' (e.g. Figure 3 As shown), as follows
[0045]
[0046] When the eccentric lever is deflected, the period length of the corrugated unit on the upper and lower airfoils is
[0047]
[0048] Where α and β are points A, B, C, D, E, F, A', B', C', D', E', and F' on the upper and lower wing surfaces, respectively, and θ is the angle of rotation of the eccentric lever.
[0049] The tensile / compressive displacement of the corrugated element is
[0050] δ αβ-θ-θ' =|T αβ-θ -T αβ-θ' | (15)
[0051] Among them, δ αβ-θ-θ'It represents the change in the distance between the two points of the corrugated unit αβ during the process of the eccentric lever moving from θ to θ'.
[0052] Substituting Equation (14) into Equation (2) yields the strain energy stored in the corrugated unit:
[0053]
[0054] Among them, V εαβ-θ-θ' K represents the strain energy stored in the corrugated unit αβ during the eccentric lever's transition from θ to θ'. αβ represents the tensile / compressive stiffness of the corrugated element αβ.
[0055] The total strain energy stored in the upper and lower wing surface corrugations during the downward deflection of the wing variable camber structure and the rotation of the eccentric lever from θ to θ' is:
[0056]
[0057] Where R represents the number of corrugated units along the span.
[0058] When the wing variable camber structure deflects downward, the strain energy stored in the upper and lower wing surface corrugated units is equal to the work done by the eccentric lever. The two eccentric levers are symmetrically installed inside the variant structure. The rotation angles are equal and opposite, and the torque is also equal. Half of the strain energy stored in the upper and lower wing surface corrugated units is equal to the work done by a single eccentric lever. The expression of the torque when the eccentric lever rotates from θ degrees to θ' degrees is
[0059]
[0060] Among them, M θ' (θ) is the torque when the eccentric lever rotates from θ degrees to θ' degrees, θ=5i,θ'=5i+5, i=0,1,2,…,14. BRIEF DESCRIPTION OF THE DRAWINGS
[0061] Figure 1 It is an overall schematic diagram of the wing variable camber structure based on the fishbone concept and zero Poisson's ratio lattice structure.
[0062] Figure 2 Schematic diagram of the a-xyz rectangular coordinate system.
[0063] Figure 3 Schematic diagram of the projection and geometric relationship of the wing variable camber structure in the yz plane.
[0064] The symbols in the figure are explained as follows:
[0065] Figure 3 Middle θ j It is the angle between the straight line perpendicular to the tangent line of a point on the curve of the projection of the central axis of the eccentric lever on the yz plane and the center line of the web. webIt is the distance from the intersection of the web centerline and the projection of the eccentric lever centerline to the upper / lower wing surface along the web centerline. DETAILED DESCRIPTION
[0066] The present invention establishes an analytical prediction model for the driving torque-angle curve of a wing variable camber structure based on the fishbone concept and a zero Poisson's ratio lattice structure. The method has the advantages of simple calculation and high accuracy. The technical solution is as follows:
[0067] The up / down deflection of the wing camber structure is achieved by the rotation drive of the symmetrically installed eccentric lever. Figure 1 This is a schematic diagram of the wing's variable camber structure. Each time the eccentric lever rotates a certain angle, the wing's variable camber structure assumes a corresponding geometric configuration. To establish a theoretical model for predicting the driving torque-rotation angle relationship during the deflection process of the wing's variable camber structure, the following assumptions are made:
[0068] (1) During the deflection process, the deformation of the upper and lower wing surface corrugated units of the wing variable camber structure is in the form of tension or compression;
[0069] (2) In the defined a-xyz coordinate system, the y-axis coordinate of the intersection of the centerline of the eccentric lever and the centerline of the web of the variant structure remains unchanged;
[0070] (3) In the yz plane, through the intersection of the projection curve of the eccentric lever centerline and the projection line of the centerline of the web of the variant structure, draw a tangent to the projection curve of the eccentric lever centerline. The angle between the tangent and the projection line of the centerline of the web remains unchanged.
[0071] (4) Ignore the friction between the eccentric lever and the web of the variant structure.
[0072] The energy method was used to calculate the relationship between the torque of the eccentric lever and the rotation angle of the eccentric lever during the deflection of the wing's variable-camber structure. The work performed by the eccentric lever during the deflection of the wing's variable-camber structure is equal to the strain energy stored during the extension and compression of the corrugated unit.
[0073] According to the energy principle, the work done by a single eccentric lever is
[0074]
[0075] Where M(θ) is the torque of the eccentric lever, and θ1 and θ2 are the rotation angles of the eccentric lever.
[0076] The strain energy stored in the corrugated element during the stretching and compression process is
[0077]
[0078] Where P(δ) is the load during the stretching or compression of the corrugated unit, and δ1 and δ2 are the displacements during the stretching or compression of the corrugated unit.
[0079] When the eccentric lever rotates 0 degrees, select any three non-coincident points on its axis to establish the xy plane, and construct the three-dimensional rectangular coordinate system a-xyz through point a, as shown in Figure 2 As shown in Figure 1. Point a serves as the coordinate origin. The eccentric lever's segment ab' is a straight line, while the remainder is a circular arc. Point b' is the point of tangency between the arc and the straight line, and the straight line ab' coincides with the y-axis. The eccentric lever rotates about the straight line ab'. The calculations in this section are based on the established a-xyz three-dimensional rectangular coordinate system.
[0080] The variant structure and the af section of the eccentric lever have a uniform cross-section, and the cross-sectional diameter of the af section of the eccentric lever is consistent with the width of the slot in the middle of the web. During the rotation of the eccentric lever, it always fits tightly against the web, and the small cross-sectional end always maintains contact with the rear wall, ensuring that the y-axis coordinate of the intersection of the web centerline and the eccentric lever centerline remains constant. To simplify the calculation process, the projection of the central axis of the variant structure and the eccentric lever on the yaz plane is selected for study, as shown in the figure below: Figure 3 As shown in Figure 1. Points B, C, D, E, and F are the coordinates of the intersection of the web centerline and the upper wing surface centerline, respectively. Points B', C', D', E', and F' are the coordinates of the intersection of the web centerline and the lower wing surface centerline. Points b, c, d, e, and f are the coordinates of the intersection of the web centerline and the projection curve of the eccentric lever centerline on the yaz plane.
[0081] When calculating the strain energy of a zero-Poisson's-ratio lattice structure, the tensile / compressive deformation of the corrugated element must be used as an input parameter. Therefore, before calculating the strain energy, the coordinates of the upper surface points A to F and the lower surface points A' to F' of the variant structure under different deflection states must be determined. Based on the assumptions of this section, the relative positions and distances between the six intersection points on the eccentric lever and the intersection points of the upper and lower airfoils remain unchanged. Therefore, the coordinates of the intersection of the projection curve of the eccentric lever's central axis on the yaz plane and the centerline of the web under different deflection states must first be determined. The coordinates of the intersection of the upper and lower airfoils can then be derived using geometric relationships.
[0082] When the eccentric lever rotates 0 degrees, the expression of the center axis of the arc part of the eccentric lever is
[0083]
[0084] where x0=172.063, y0=34.070, r=171.455, x el-min =0,x el-max =12.544,y el-min =34.065,y el-max=98.428.
[0085] Evenly select 60 points on the arc, the coordinates of each point are
[0086]
[0087] The eccentric lever drives the variant structure to deflect by a certain angle. In order to obtain the center of the arc segment of the eccentric lever and the coordinates of each point on the arc segment after the rotation of a certain angle, a rotation matrix needs to be introduced. The rotation matrix of the eccentric lever is
[0088]
[0089] Where θ is the rotation angle of the eccentric lever.
[0090] The coordinate matrix of the center of the eccentric lever arc after rotating a certain angle is:
[0091]
[0092] The coordinate matrix of 60 points on the arc of the eccentric lever after rotating a certain angle is
[0093]
[0094] After rotating a certain angle, the coordinates of 60 points on the eccentric lever arc projected onto the yz plane are
[0095]
[0096] The 60 points projected onto the yz plane are fitted using the least squares method to obtain the fitting curve:
[0097]
[0098] Where a, b, and c are determined by the rotation angle θ of the eccentric lever, z f and y f are the two variables of the fitting curve, y f-min =0,y f-max =98.428.
[0099] Draw a straight line perpendicular to the tangent line of the overfitting curve at any point (such as Figure 3 The expression is shown as
[0100]
[0101] A straight line coinciding with the centerline of the web (e.g. Figure 3 The expression is shown as
[0102]
[0103] Among them, θj It is the angle between the line perpendicular to the tangent and the centerline of the web.
[0104] Draw a circle with the intersection of the web centerline and the eccentric lever centerline projected onto the yaz plane curve as the center and the distance from the intersection to the upper / lower wing surface as the radius (e.g. Figure 3 As shown), we can get
[0105] (yy f ) 2 +(zz f ) 2 =r web 2 (12) Among them, r web It is the distance from the intersection of the web centerline and the projection of the eccentric lever centerline to the upper / lower wing surface along the web centerline.
[0106] By combining equations (11) and (12), we can get the coordinates of point A to point F and point A' to point F' (e.g. Figure 3 As shown), as follows
[0107]
[0108] When the eccentric lever is deflected, the period length of the corrugated unit on the upper and lower airfoils is
[0109]
[0110] Where α and β are points A, B, C, D, E, F, A', B', C', D', E', and F' on the upper and lower wing surfaces, respectively, and θ is the angle of rotation of the eccentric lever.
[0111] The tensile / compressive displacement of the corrugated element is
[0112] δ αβ-θ-θ' =|T αβ-θ -T αβ-θ' | (15)
[0113] Among them, δ αβ-θ-θ' It represents the change in the distance between the two points of the corrugated unit αβ during the process of the eccentric lever moving from θ to θ'.
[0114] Substituting Equation (14) into Equation (2) yields the strain energy stored in the corrugated unit:
[0115]
[0116] Among them, V εαβ-θ-θ' K represents the strain energy stored in the corrugated unit αβ during the eccentric lever's transition from θ to θ'. αβ represents the tensile / compressive stiffness of the corrugated element αβ.
[0117] The total strain energy stored in the upper and lower wing surface corrugations during the downward deflection of the wing variable camber structure and the rotation of the eccentric lever from θ to θ' is:
[0118]
[0119] Where R represents the number of corrugated units along the span.
[0120] When the wing variable camber structure deflects downward, the strain energy stored in the upper and lower wing surface corrugated units is equal to the work done by the eccentric lever. The two eccentric levers are symmetrically installed inside the variant structure. The rotation angles are equal and opposite, and the torque is also equal. Half of the strain energy stored in the upper and lower wing surface corrugated units is equal to the work done by a single eccentric lever. The expression of the torque when the eccentric lever rotates from θ degrees to θ' degrees is
[0121]
[0122] Among them, M θ' (θ) is the torque when the eccentric lever rotates from θ degrees to θ' degrees, θ=5i,θ'=5i+5, i=0,1,2,…,14.
Claims
1. An analytical prediction model for the torque-angle curve of a wing variable camber structure based on the fishbone concept and a zero Poisson's ratio lattice structure, characterized by: The up / down deflection of the wing's variable camber structure is achieved by the rotation of a symmetrically mounted eccentric lever. Each time the eccentric lever rotates a certain angle, the wing's variable camber structure assumes a corresponding geometric configuration. To establish a theoretical model for predicting the driving torque-rotation angle relationship during the deflection process, the following assumptions are made: (1) During the deflection process, the deformation of the upper and lower wing surface corrugated units of the wing variable camber structure is in the form of tension or compression; (2) In the defined a-xyz coordinate system, the y-axis coordinate of the intersection of the centerline of the eccentric lever and the centerline of the web of the variant structure remains unchanged; (3) In the yz plane, the intersection of the projected curve through the center axis of the eccentric lever and the projected straight line through the center line of the web of the variant structure, Draw a tangent to the projected curve of the center axis of the eccentric lever, and the angle between the tangent and the projected straight line of the web centerline remains constant; (4) Ignore the friction between the eccentric lever and the web of the variant structure; The energy method is used to calculate the relationship between the torque of the eccentric lever and the rotation angle of the eccentric lever during the deflection process of the wing variable camber structure; The work done by the eccentric lever during the deflection of the wing variable camber structure is equal to the strain energy stored in the process of stretching and compressing the corrugated unit; According to the energy principle, the work done by a single eccentric lever is Where M(θ) is the torque of the eccentric lever, θ1 and θ2 are the rotation angles of the eccentric lever; The strain energy stored in the corrugated element during the stretching and compression process is Where P(δ) is the load during the stretching or compression of the corrugated unit, δ1 and δ2 are the displacements during the stretching or compression of the corrugated unit; When the eccentric lever is rotated 0 degrees, select any three non-coincident points on its axis to establish the xy plane, and construct the three-dimensional rectangular coordinate system a-xyz through point a. Point a is the coordinate origin, the ab' segment of the eccentric lever is the straight line, and the rest is the arc. Point b' is the tangent point between the arc and the straight line, and the straight line ab' coincides with the y-axis. The eccentric lever rotates around the straight line ab'. The calculations in this section are all based on the established a-xyz three-dimensional rectangular coordinate system. The variant structure and the af portion of the eccentric lever have equal cross-sectional characteristics, and the cross-sectional diameter of the af section of the eccentric lever is consistent with the width of the slot in the middle of the web. During the rotation of the eccentric lever, it always fits tightly against the web, and the small-section end always maintains contact with the rear wall plate, ensuring that the y-axis coordinate of the intersection of the web centerline and the eccentric lever centerline remains constant. To simplify the calculation process, the projection of the central axis of the variant structure and the eccentric lever on the yaz plane is selected for study. Among them, points B, C, D, E, and F are the coordinates of the intersection of the web centerline and the upper wing centerline, respectively, and points B', C', D', E', and F' are the coordinates of the intersection of the web centerline and the lower wing centerline. Points b, c, d, e, and f are the coordinates of the intersection of the web centerline and the projection curve of the central axis of the eccentric lever on the yaz plane. When calculating the strain energy of a zero-Poisson's-ratio lattice structure, the tensile / compressive deformation of the corrugated element must be used as an input parameter. Therefore, before calculating the strain energy, the coordinates of points A to F on the upper surface and A' to F' on the lower surface of the variant structure must be determined under different deflection states. Based on the assumptions of this section, the relative positions and distances between the six intersection points on the eccentric lever and the intersection points of the upper and lower airfoils remain unchanged. Therefore, the coordinates of the intersection of the projection curve of the eccentric lever's central axis on the yaz plane and the web centerline under different deflection states must be determined first. The coordinates of the intersection points of the upper and lower airfoils can then be derived using geometric relationships. When the eccentric lever rotates 0 degrees, the expression of the center axis of the arc part of the eccentric lever is where x0=172.063,y0=34.070,r=171.455,x el-min =0,x el-max =12.544,y el-min =34.065, y el-max ＝98.
428. Evenly select 60 points on the arc, the coordinates of each point are where z0=0, …,2π. The eccentric lever drives the variant structure to deflect by a certain angle. In order to obtain the center of the arc segment of the eccentric lever and the coordinates of each point on the arc segment after the rotation of a certain angle, a rotation matrix needs to be introduced. The rotation matrix of the eccentric lever is Where θ is the rotation angle of the eccentric lever; The coordinate matrix of the center of the eccentric lever arc after rotating a certain angle is: The coordinate matrix of 60 points on the arc of the eccentric lever after rotating a certain angle is After rotating a certain angle, the coordinates of 60 points on the eccentric lever arc projected onto the yz plane are The 60 points projected onto the yz plane are fitted using the least squares method to obtain the fitting curve: Where a, b, and c are determined by the rotation angle θ of the eccentric lever, z f and y f are the two variables of the fitting curve, y f-min =0,y f-max =98.428; The expression of a straight line perpendicular to the tangent line of the overfitting curve at any point is: The expression of the straight line coinciding with the center line of the web is Among them, θ j is the angle between the line perpendicular to the tangent and the centerline of the web; With the intersection of the web centerline and the eccentric lever centerline projected onto the yaz plane curve as the center of the circle and the distance from the intersection to the upper / lower wing surface as the radius, we can get Among them, r web The distance from the intersection of the web center axis and the projection of the eccentric lever center axis to the upper / lower wing surface along the web center axis; Combining equations (11) and (12) we can get the coordinates of point A to point F and point A' to point F', as follows When the eccentric lever is deflected, the period length of the corrugated unit on the upper and lower airfoils is Where α and β are points A, B, C, D, E, F, A', B', C', D', E', and F' on the upper and lower wing surfaces, respectively, and θ is the angle of rotation of the eccentric lever; The tensile / compressive displacement of the corrugated element is δ αβ-θ-θ' =|T αβ-θ -T αβ-θ' | (15) Among them, δ αβ-θ-θ' It represents the change in the distance between the two points of the corrugated unit αβ during the process of the eccentric lever moving from θ to θ'; Substituting Equation (14) into Equation (2) yields the strain energy stored in the corrugated unit: Among them, V εαβ-θ-θ' K represents the strain energy stored in the corrugated unit αβ during the eccentric lever's transition from θ to θ'. αβ represents the tensile / compressive stiffness of the corrugated unit αβ; The total strain energy stored in the upper and lower wing surface corrugations during the downward deflection of the wing variable camber structure and the rotation of the eccentric lever from θ to θ' is: Where R represents the number of corrugated units along the span direction; When the wing variable camber structure deflects downward, the strain energy stored in the upper and lower wing surface corrugated units is equal to the work done by the eccentric lever. The two eccentric levers are symmetrically installed inside the variant structure. The rotation angles are equal and opposite, and the torque is also equal. Half of the strain energy stored in the upper and lower wing surface corrugated units is equal to the work done by a single eccentric lever. The expression of the torque when the eccentric lever rotates from θ degrees to θ' degrees is Among them, M θ' (θ) is the torque when the eccentric lever rotates from θ degrees to θ' degrees, θ=5i,θ'=5i+5, i=0,1,2,…,14.