A method for determining the load of a plane double fork beam type equal rigidity wing under torque load

Abstract

The application belongs to the technical field of planar double fork beam type equal rigidity wing design, and particularly relates to a load determination method for a planar double fork beam type equal rigidity wing under a torque load, wherein a calculation formula for wing load of the planar double fork beam type equal rigidity wing under the torque load is given, the wing load of the planar double fork beam type equal rigidity wing under the torque load can be quickly calculated, and the requirement of rapid iteration of wing structure strength and airplane overall layout parameter design can be well met.

Description

Technical Field

[0001] This application belongs to the field of planar double-forked beam constant stiffness wing design technology, specifically relating to a method for determining the load of a planar double-forked beam constant stiffness wing subjected to torque load. Background Technology

[0002] Compared to conventional wing layouts, planar double-spar wings can better adapt to the special requirements of aircraft loading and shape, but compared to traditional wing box structures, their load transfer and deformation are more complex.

[0003] A planar double-spar wing includes a front spar and a rear spar, which are located in the same plane. A wing with the same stiffness for both the front and rear spars is called an equal-stiffness wing.

[0004] Analyzing the internal force distribution of a planar double-spar constant stiffness wing under torque load is of great significance for the design of its structural strength parameters and the overall aircraft layout parameters. Currently, this is mostly determined by the finite element analysis method, which is time-consuming, laborious, and has a long iterative calculation cycle, making it difficult to meet the needs of rapid iteration in the design of wing structural strength and overall aircraft layout parameters.

[0005] This application is made in view of the aforementioned technical deficiencies.

[0006] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0007] The purpose of this application is to provide a method for determining the load on a planar double-forked beam wing with equal stiffness under torque load, so as to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] A method for determining the load on a planar double-forked beam airfoil subjected to torque loads, comprising:

[0010] Step 1: Establish a planar double-forked beam type constant stiffness wing subjected to torsional load analysis model:

[0011] The front inclined beam OA and the rear inclined beam OB are designed to be located in the horizontal plane of the aircraft and fixed at point O. Points A and B are located in the plane of symmetry of the aircraft and are fixedly supported at points A and B.

[0012] Establish an Oxy coordinate system within the aircraft's horizontal plane, with the origin at point O; design the z-axis to be perpendicular to the aircraft's horizontal plane and positive upwards; the x-axis to be perpendicular to the yz plane and positive to the right; and the y-axis to be positive in the opposite direction of the aircraft's heading.

[0013] A concentrated torque T is applied at point O. o A torsional load analysis model of a planar double-forked beam is established along the negative x-axis, where:

[0014] The length of the front inclined beam OA is l1;

[0015] The length of the rear inclined beam OB is l2;

[0016] The angle between the front inclined beam OA and the rear inclined beam OB is α;

[0017] The angle between the front inclined beam OA and the x-axis is β;

[0018] Step 2: Establish the analysis model of the front inclined beam OA:

[0019] Decompose the front inclined beam OA and the rear inclined beam OB at point O, making the front inclined beam OA and the rear inclined beam OB independent;

[0020] Rotate the Oxy coordinate system counterclockwise by an angle β around point O to establish a coordinate system Ox1y1, and make the beam axis of the front inclined beam OA coincide with Ox1;

[0021] A shear force F is applied to the front inclined beam OA at point O. oA Perpendicular to the Ox1y1 plane, pointing inwards is considered positive, conforming to the right-hand coordinate system rule; apply bending moment M oA The direction is parallel to y1, causing the front inclined beam OA to bend upwards as positive; the applied torque is T. oA The direction is parallel to x1, so that the counterclockwise torsion of the front inclined beam OA is positive, and the analysis model of the front inclined beam OA is established.

[0022] Step 3: Establish the analysis model of the rear inclined beam OB:

[0023] The rear inclined beam OB is fixedly constrained at point O;

[0024] Rotate the Oxy coordinate system counterclockwise by 180 degrees around point O. ° -α+β angle, translate to point B so that point O coincides with point B, establish coordinate system Bx2y2, and make the beam axis of the rear inclined beam OB coincide with Bx2;

[0025] A shear force F is applied to the rear inclined beam OB at point B. B Perpendicular to the Bx2y2 plane, pointing outwards is positive, conforming to the right-hand coordinate system rule; apply bending moment M B The direction is parallel to y2, causing the rear inclined beam OB to bend downwards as positive; the applied torque is T.B The direction is parallel to x2, so that the counterclockwise torsion of the rear inclined beam OB is positive, and an analytical model of the rear inclined beam OB is established.

[0026] Step 4: Calculate the bending stiffness and torsional stiffness of the front inclined beam OA and the rear inclined beam OB:

[0027] Establish a section perpendicular to the Ox1y1 plane and the Ox1 axis, cut the front inclined beam OA with this section to obtain the cross-sectional shape of the front inclined beam OA, and calculate the bending moment of inertia I0 of the front inclined beam OA section relative to the oy1 axis and the torsional moment of inertia J0 relative to the Ox1 axis.

[0028] Based on the material of the front inclined beam OA, the elastic modulus E0 of the front inclined beam OA is obtained;

[0029] Calculate the bending stiffness E0I0=E0×I0 and the torsional stiffness G0J0=G0×J0 of the front inclined beam OA;

[0030] The bending stiffness of the rear inclined beam OB is assigned as E0I0, and the torsional stiffness is assigned as G0J0.

[0031] Step 5: Establish a computational model of a planar double-forked beam type airfoil with equal stiffness after removing the constraint at point B:

[0032] The fixed support constraint at point B is removed from the analysis model of the planar double-forked beam isobaric wing under torque load;

[0033] A load F is applied at point B. B T B M B , of which F B The vertical shear force is perpendicular to the Oxy plane and positive along the z-axis; T B The torque along the OB axis is positive, pointing from point O to point B; M B To determine the torque perpendicular to the rear inclined beam OB section, and taking the downward bending at point B as positive, a calculation model of a planar double-forked beam type constant stiffness wing with the constraint at point B removed is established.

[0034] Step 6: Calculate the displacement of point B:

[0035] Based on the computational model of a planar double-forked beam isothermal wing with the constraint at point B removed, calculate the vertical displacement ω at point B. B :

[0036]

[0037] Calculate the twist angle φ at point B. B :

[0038]

[0039] Calculate the bending angle θ at point B. B :

[0040]

[0041] Step 7: Calculate the load at point B:

[0042] Let ω B =0, θ B =0, solving the system of equations simultaneously yields:

[0043]

[0044]

[0045]

[0046] in,

[0047]

[0048]

[0049] Step 8: Calculate the load at point A:

[0050] Calculate the load at point A in the Oxy coordinate system based on the force balance relationship:

[0051] Shear force F A =-F B ;

[0052] Bending moment M A =(M B -F B l2)cos(α-β)-T B sin(α-β)+F B l1cosβ;

[0053] Torque T A =-(M B -F B l2)sin(α-β)-T B cos(α-β)+F B l1sinβ+T o .

[0054] According to at least one embodiment of this application, the above-described method for determining the load of a torsional-loaded planar double-forked beam type equal stiffness wing further includes:

[0055] Step 9: Calculate the load at any point OB of the rear inclined beam:

[0056] Select any point on the rear inclined beam OB. The x2 coordinate of this point in the Bx2y2 coordinate system is x. 2i Calculate the load at this point in the Bx2y2 coordinate system:

[0057] Shear force F oBi =-F B ;

[0058] Bending moment M oBi =-M B +F B x 2i ;

[0059] Torque T oBi =T B .

[0060] According to at least one embodiment of this application, the above-described method for determining the load of a torsional-loaded planar double-forked beam type equal stiffness wing further includes:

[0061] Step 10: Calculate the load on the front inclined beam OA at end point O:

[0062] According to the formula in step nine and the load T at point O. o The load at end point O of the front inclined beam OA in the Bx2y2 coordinate system:

[0063] Shear force F oB =-F B ;

[0064] Bending moment M oB =-M B +F B l2+T o sin(α-β);

[0065] Torque T oB =T B -T o cos(α-β);

[0066] Based on the coordinate transformation, the load at point O, the endpoint of the front inclined beam OA, in the Ox1y1 coordinate system is obtained as follows:

[0067] Shear force F oA =F oB ;

[0068] Bending moment M oA =-M oB cosα-T oB sinα;

[0069] Torque T oA =M oB sinα-T oB cosα.

[0070] According to at least one embodiment of this application, the above-described method for determining the load of a torsional-loaded planar double-forked beam type equal stiffness wing further includes:

[0071] Step 11: Calculate the load at any point OA of the front inclined beam:

[0072] Select any point on the front inclined beam OA. The x1 coordinate of this point in the Ox1y1 coordinate system is x. 1i Calculate the load at this point in the Ox1y1 coordinate system:

[0073] Shear force F oAi =F oA ;

[0074] Bending moment M oAi =M oA -F oA x 1i ;

[0075] Torque T oAi =T oA .

[0076] This application has at least the following beneficial technical effects:

[0077] This paper provides a method for determining the load of a planar double-spar constant stiffness wing under torque load, and gives a calculation formula for the wing load of the planar double-spar constant stiffness wing under torque load. The wing load of the planar double-spar constant stiffness wing under torque load can be calculated quickly, which can well meet the needs of rapid iteration in the design of wing structural strength and overall aircraft layout parameters. Attached Figure Description

[0078] Figure 1 This is a schematic diagram of the torsional load analysis model of the planar double-forked beam type constant stiffness airfoil provided in the embodiments of this application;

[0079] Figure 2 This is a schematic diagram of the analysis model of the front inclined beam OA provided in the embodiments of this application;

[0080] Figure 3 This is a schematic diagram of the analysis model of the rear inclined beam OB provided in the embodiments of this application;

[0081] Figure 4 This is a schematic diagram of the calculation model of a planar double-forked beam type constant stiffness wing with the constraint at point B removed, provided in an embodiment of this application.

[0082] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0083] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0084] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0085] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0086] The following is in conjunction with the appendix Figures 1 to 4 This application provides a further detailed description of the method for determining the load on a plane double-forked beam type constant stiffness wing subjected to torque load.

[0087] Step 1: Establish a planar double-forked beam type constant stiffness wing subjected to torsional load analysis model:

[0088] The front inclined beam OA and the rear inclined beam OB are designed to be located in the horizontal plane of the aircraft and fixed at point O. Points A and B are located in the plane of symmetry of the aircraft and are fixedly supported at points A and B.

[0089] Establish an Oxy coordinate system within the aircraft's horizontal plane, with the origin at point O; design the z-axis to be perpendicular to the aircraft's horizontal plane and positive upwards; the x-axis to be perpendicular to the yz plane and positive to the right; and the y-axis to be positive in the opposite direction of the aircraft's heading.

[0090] A concentrated torque T is applied at point O. o A torsional load analysis model of a planar double-forked beam is established along the negative x-axis, such as... Figure 1 As shown, where:

[0091] The length of the front inclined beam OA is l1;

[0092] The length of the rear inclined beam OB is l2;

[0093] The angle between the front inclined beam OA and the rear inclined beam OB is α;

[0094] The angle between the front inclined beam OA and the x-axis is β.

[0095] Step 2: Establish the analysis model of the front inclined beam OA:

[0096] Decompose the front inclined beam OA and the rear inclined beam OB at point O, making the front inclined beam OA and the rear inclined beam OB independent;

[0097] Rotate the Oxy coordinate system counterclockwise by an angle β around point O to establish a coordinate system Ox1y1, and make the beam axis of the front inclined beam OA coincide with Ox1;

[0098] A shear force F is applied to the front inclined beam OA at point O. oA Perpendicular to the Ox1y1 plane, pointing inwards is considered positive, conforming to the right-hand coordinate system rule; apply bending moment M oA The direction is parallel to y1, causing the front inclined beam OA to bend upwards as positive; the applied torque is T. oA The direction is parallel to x1, making the counterclockwise torsion of the front inclined beam OA positive. An analytical model of the front inclined beam OA is established, as follows: Figure 2 As shown.

[0099] Step 3: Establish the analysis model of the rear inclined beam OB:

[0100] The rear inclined beam OB is fixedly constrained at point O;

[0101] Rotate the Oxy coordinate system counterclockwise by 180 degrees around point O. ° -α+β angle, translate to point B so that point O coincides with point B, establish coordinate system Bx2y2, and make the beam axis of the rear inclined beam OB coincide with Bx2;

[0102] A shear force F is applied to the rear inclined beam OB at point B. B Perpendicular to the Bx2y2 plane, pointing outwards is positive, conforming to the right-hand coordinate system rule; apply bending moment M B The direction is parallel to y2, causing the rear inclined beam OB to bend downwards as positive; the applied torque is T. B The direction is parallel to x2, making the counterclockwise torsion of the rear inclined beam OB positive. An analytical model for the rear inclined beam OB is established, as follows: Figure 3 As shown.

[0103] Step 4: Calculate the bending stiffness and torsional stiffness of the front inclined beam OA and the rear inclined beam OB:

[0104] Establish a section perpendicular to the Ox1y1 plane and the Ox1 axis, cut the front inclined beam OA with this section to obtain the cross-sectional shape of the front inclined beam OA, and calculate the bending moment of inertia I0 of the front inclined beam OA section relative to the oy1 axis and the torsional moment of inertia J0 relative to the Ox1 axis according to the calculation method of mechanics of materials.

[0105] Based on the material of the front inclined beam OA, the elastic modulus E0 of the front inclined beam OA is obtained;

[0106] The bending stiffness of the front inclined beam OA is calculated to be E0I0=E0×I0, and the torsional stiffness is G0J0=G0×J0;

[0107] The bending stiffness of the rear inclined beam OB is assigned as E0I0, and the torsional stiffness as G0J0.

[0108] Step 5: Establish a computational model of a planar double-forked beam type airfoil with equal stiffness after removing the constraint at point B:

[0109] The fixed support constraint at point B is removed from the analysis model of the planar double-forked beam isobaric wing under torque load;

[0110] A load F is applied at point B. B T B M B , of which F B The vertical shear force is perpendicular to the Oxy plane and positive along the z-axis; T B The torque along the OB axis is positive, pointing from point O to point B; M B To represent the torque perpendicular to the rear inclined beam section OB, and taking the downward bending at point B as positive, a calculation model of a planar double-forked beam type with equal stiffness is established, freeing the constraint at point B. Figure 4 As shown.

[0111] Step 6: Calculate the displacement of point B:

[0112] Based on a computational model of a planar double-forked beam isothermal wing with the constraint at point B removed, the vertical displacement ω at point B is calculated using structural mechanics methods. B:

[0113]

[0114] The angle of twist at point B was calculated.

[0115]

[0116] The bending angle θ at point B is calculated. B :

[0117]

[0118] Step 7: Calculate the load at point B:

[0119] Let ω B =0, θ B =0, solve the three equations simultaneously, and we get:

[0120]

[0121]

[0122]

[0123] in,

[0124]

[0125]

[0126] Step 8: Calculate the load at point A:

[0127] Calculate the load at point A in the Oxy coordinate system based on the force balance relationship:

[0128] Shear force F A =-F B ;

[0129] Bending moment M A =(M B -F B l2)cos(α-β)-T B sin(α-β)+F B l1cosβ;

[0130] Torque T A =-(M B -F B l2)sin(α-β)-T B cos(α-β)+F Bl1sinβ+T o .

[0131] Step 9: Calculate the load at any point OB of the rear inclined beam:

[0132] Select any point on the rear inclined beam OB. The x2 coordinate of this point in the Bx2y2 coordinate system is x. 2i ;

[0133] according to Figure 3 The calculation model shown is used to calculate the load at this point in the Bx2y2 coordinate system according to the calculation methods of structural mechanics:

[0134] Shear force F oBi =-F B ;

[0135] Bending moment M oBi =-M B +F B x 2i ;

[0136] Torque T oBi =T B .

[0137] Step 10: Calculate the load on the front inclined beam OA at point O:

[0138] According to F oBi M oBi and T oBi The calculation formula is used to calculate the load at point OAO of the front inclined beam in the Bx2y2 coordinate system:

[0139] Shear force F oB =-F B ;

[0140] Bending moment M oB =-M B +F B l2+T o sin(α-β);

[0141] Torque T oB =T B -T o cos(α-β);

[0142] Based on the coordinate transformation, the load of the front inclined beam OA at point O in the ox1y1 coordinate system is obtained as follows:

[0143] Shear force F oA =F oB ;

[0144] Bending moment M oA =-M oB cosα-ToB sinα;

[0145] Torque T oA =M oB sinα-T oB cosα.

[0146] Step 11: Calculate the load at any point OA of the front inclined beam:

[0147] Select any point on the front inclined beam OA. The x1 coordinate of this point in the ox1y1 coordinate system is x. 1i ;

[0148] according to Figure 2 The calculation model shown can be used to calculate the load at this point in the ox1y1 coordinate system according to the calculation methods of structural mechanics:

[0149] Shear force F oAi =F oA ;

[0150] Bending moment M oAi =M oA -F oA x 1i ;

[0151] Torque T oAi =T oA .

[0152] The method for determining the load of a planar double-spar constant stiffness wing under torque load provided in the above embodiments gives a calculation formula for the wing load of a planar double-spar constant stiffness wing under torque load. It can quickly calculate the wing load of a planar double-spar constant stiffness wing under torque load, which can well meet the needs of rapid iteration in the design of wing structural strength and overall aircraft layout parameters.

[0153] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for determining the load on a planar double-forked beam type airfoil subjected to torque load, characterized in that, include: Step 1: Design the front inclined beam OA and rear inclined beam OB to be located in the horizontal plane of the aircraft and fixed at point O. Points A and B are located in the plane of symmetry of the aircraft and are fixedly supported. Establish an Oxy coordinate system in the horizontal plane of the aircraft, with the origin at point O. Apply a concentrated torque at point O. A torsional load analysis model of a planar double-forked beam is established with the direction along the negative x-axis. Step 2: Decompose the front inclined beam OA and the rear inclined beam OB at point O, making them independent; rotate the Oxy coordinate system counterclockwise around point O so that the beam axis of the front inclined beam OA is aligned with... Overlap, establish a coordinate system ;exist Shear force is applied to the front inclined beam OA. Bending moment Torque is An analytical model of the front inclined beam OA is established; Step 3: Fix the rear inclined beam OB at point O; rotate the Oxy coordinate system counterclockwise around point O and translate it to point B, so that point O coincides with point B, and the beam axis of the rear inclined beam OB is aligned with... Overlap, establish a coordinate system ;exist Shear force is applied to the rear inclined beam OB at the point. Bending moment Torque is An analytical model for the rear inclined beam OB is established. Step 4: Calculate the bending stiffness of the front inclined beam OA and the rear inclined beam OB. Torsional stiffness ; Step 5: Remove the fixed support constraint at point B in the torque load analysis model of the planar double-forked beam isobaric wing; apply shear force at point B. Torque Bending moment Establish a computational model of a planar double-forked beam iso-stiffness wing with the constraint at point B removed; Step 6: Based on the calculation model of the planar double-forked beam isostiff wing with the constraint at point B removed, calculate the vertical displacement at point B. Twist angle Bending angle ; Step 7, Order , , Solve the simultaneous equations to calculate the load at point B; Step 8: Based on the force balance relationship, calculate the load at point A in the Oxy coordinate system, including shear force. Bending moment Torque .

2. The method for determining the load on a plane double-forked beam type wing with equal stiffness under torque load according to claim 1, characterized in that, In step one, in the Oxy coordinate system, the z-axis is designed to be perpendicular to the horizontal plane of the aircraft, with upward as positive; the x-axis is perpendicular to the yz plane, pointing to the right as positive; and the y-axis is positive against the aircraft's heading. The length of the front inclined beam OA is ; The length of the rear inclined beam OB is ; The angle between the front inclined beam OA and the rear inclined beam OB is ; The angle between the front inclined beam OA and the x-axis is... .

3. The method for determining the load on a plane double-forked beam type wing with equal stiffness under torque load according to claim 2, characterized in that, In step two, Shear force is applied to the front inclined beam OA. perpendicular to A plane, pointing inwards is positive, conforming to the right-hand coordinate system rule; applying a bending moment , direction parallel to This causes the front inclined beam OA to bend upwards, which is positive; the applied torque is... , direction parallel to This causes the front inclined beam OA to rotate counterclockwise to positive.

4. The method for determining the load on a plane double-forked beam type wing with equal stiffness under torque load according to claim 3, characterized in that, In step three, Shear force is applied to the rear inclined beam OB at the point. perpendicular to A plane pointing outwards is considered positive, conforming to the right-hand coordinate system rule; applying a bending moment , direction parallel to This causes the rear inclined beam OB to bend downwards in a positive direction; the applied torque is... , direction parallel to This causes the rear inclined beam OB to rotate counterclockwise to positive.

5. The method for determining the load on a plane double-forked beam type wing with equal stiffness under torque load according to claim 4, characterized in that, Step four is as follows: Establish perpendicular to plane and The cross-section of the axis is used to cut the front inclined beam OA, obtaining the cross-sectional shape of the front inclined beam OA. The relative cross-section of the front inclined beam OA is calculated. Bending moment of inertia of the shaft Relative to Torsional moment of inertia of the shaft ; Based on the material of the front inclined beam OA, the elastic modulus of the front inclined beam OA is obtained. ; Calculate the bending stiffness of the front inclined beam OA Torsional stiffness ; The bending stiffness of the rear inclined beam OB is given as follows: Torsional stiffness is .

6. The method for determining the load on a plane double-forked beam type wing with equal stiffness under torque load according to claim 5, characterized in that, In step five, shear force is applied at point B. Torque Bending moment ,in, The vertical shear force is perpendicular to the Oxy plane and is positive along the z-axis; The torque along the OB axis is positive, pointing from point O to point B; The torque is perpendicular to the cross section OB of the rear inclined beam, with the downward bending at point B as positive.

7. The method for determining the load on a plane double-forked beam type wing with equal stiffness under torque load according to claim 6, characterized in that, In step six, calculate the vertical displacement of point B. Specifically: ； Calculate the twist angle at point B. Specifically: ； Calculate the bending angle at point B. ; 。 8. The method for determining the load on a plane double-forked beam type wing with equal stiffness under torque load according to claim 7, characterized in that, Step seven is as follows: make , , Solve the simultaneous equations to calculate the load at point B, including the shear force. Torque Bending moment : ； ； ； in, n ； q 。 9. The method for determining the load on a plane double-forked beam type wing with equal stiffness under torque load according to claim 8, characterized in that, Also includes: Step eight is as follows: Shear force ; Bending moment ; Torque .

10. The method for determining the load on a plane double-forked beam type wing with equal stiffness under torque load according to claim 9, characterized in that, Also includes: Step 9: Calculate the load at any point OB of the rear inclined beam: Select any point on the rear inclined beam OB. This point is located at... coordinate system Coordinates are Calculate the point at Loads in coordinate system: Shear force ; Bending moment ; Torque ; Step 10: Calculate the load on the front inclined beam OA at point O: Calculate the position of point OAO on the front inclined beam. Loads in coordinate system: Shear force ; Bending moment ; Torque ; Based on coordinate transformation, the coordinates at point OAO on the front inclined beam are obtained. Loads in coordinate system: Shear force ; Bending moment ; Torque ; Step 11: Calculate the load at any point OA of the front inclined beam: Select any point on the front inclined beam OA. This point is located at... coordinate system Coordinates are Calculate the point at Loads in coordinate system: Shear force ; Bending moment ; Torque .

Images