Folding wing and rudder design method and unfolding locking mechanism thereof

Abstract

The invention discloses a folding wing and rudder design method and an unfolding locking mechanism thereof. The locking mechanism comprises a connecting handle, an elastic torsional spring and a rotating shaft. A locking head and a connector are arranged on the two sides of the bottom of the folding wing or the folding rudder respectively; the design method comprises the steps of obtaining performance parameters, and determining specific indexes such as folding sizes and unfolding time of the folding wing and the rudder. And designing a structural model according to principles of generalization, reliability and the like, and determining geometric parameters of the wing and the rudder. Verifying the strength of parts of the locking mechanism, calculating a plurality of parameters of an elastic torsion spring, and analyzing the unfolding time and synchronism. Finally, consistency checking is conducted based on finite element simulation analysis, torque and bending moment are applied in ABAQUS software according to parameters, the structural strength of the folded rudder is analyzed, and it is ensured that the design meets the requirement. According to the folding wing and rudder design method, through the scientific design process and multi-principle comprehensive application, the high-performance requirement is met, meanwhile, the cost is effectively reduced, the reliability and maintainability of products are improved, and the remarkable beneficial effects are achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft structural design, and specifically relates to a design method for folding wings and rudders and their deployment locking mechanisms. Background Art

[0002] In modern aerospace and military fields, the performance optimization of aircraft has always been a key concern. As key components of an aircraft, folding wings and rudders play a crucial role in enhancing the maneuverability of the aircraft and facilitating storage and transportation.

[0003] Early designs of folding wings and rudders often focused on achieving basic folding and deployment functions, with relatively simple and crude structures. With the increasingly diverse and complex mission requirements of aircraft, higher demands are placed on folding wings and rudders. On the one hand, in terms of performance, it is necessary to precisely control their folding dimensions to adapt to different carrying platforms and storage spaces, and at the same time, the requirements for deployment time and deployment synchronization are becoming more stringent to ensure that the aircraft can quickly and stably enter the working state at critical moments. However, traditional design methods are difficult to accurately meet the requirements of these refined performance parameters, and problems such as too long deployment time or poor synchronization often occur, affecting the overall control performance of the aircraft.

[0004] In the patent with the application number CN202410767575.X, a design method and structure for the deployment and locking mechanism of a small-sized high-temperature-resistant and high-rigidity folding rudder are disclosed. This design scheme determines the design parameters according to the overall design requirements, deduces the heat protection scheme, and iteratively calculates the dimensions of the folding mechanism to obtain the mechanism dimensions that meet the aerodynamic performance and stiffness requirements. The overall stiffness of the folding rudder manufactured using this design scheme is increased by more than 20%, and the load-bearing performance is increased by more than 30%; however, the folding rudder designed using this design scheme has the problem of low adaptability and is only suitable for individual manufacturing. Summary of the Invention

[0005] The purpose of the present invention is to provide a design method for folding wings and rudders and their deployment locking mechanisms to solve the following technical problems raised in the background art:

[0006] Traditional design methods are difficult to meet the requirements of refined performance parameters, and problems such as too long deployment time often occur.

[0007] To solve the above technical problems, the technical solution adopted by the present invention is:

[0008] A folding wing and rudder deployment and locking mechanism, comprising a connecting handle, a torsion spring and a rotating shaft; locking heads and connecting heads are respectively arranged on both sides of the bottom of the folding wing or folding rudder; both ends of the rotating shaft are movably connected to the connecting head and the locking head respectively, the connecting handle is connected to the rotating shaft, an installation groove is arranged on the connecting handle, an upper locking groove is arranged on one side of the connecting handle, a locking protrusion is arranged on the locking head, and the locking protrusion cooperates with the upper locking groove; the torsion spring is arranged in the installation groove, and both ends of the torsion spring are connected to the connecting handle and the connecting head respectively, and the torsion spring is used to drive the folding wing or folding rudder to rotate and reset and make the folding wing or folding rudder move axially along the rotating shaft to reset.

[0009] Further, a lower locking groove is arranged on one side of the connecting handle close to the connecting head, a locking block is arranged on the connecting head, and the lower locking groove cooperates with the locking block.

[0010] Further, ventilation holes are arranged on the locking head.

[0011] Further, a limiting stop is arranged on one side of the rotating shaft close to the connecting head, a limiting hole is arranged on one side of the connecting handle, and a limiting pin is arranged in the limiting hole.

[0012] Further, a limiting platform is fixedly connected to one side of the connecting handle close to the connecting head.

[0013] A folding wing and rudder design method for designing a folding wing and rudder in the previous aspect, comprising the following steps:

[0014] A. Obtain the performance parameters required for the folding wing and rudder; the performance parameters include folding size, deployment time, deployment synchronism, mass, maximum torque load and maximum bending moment load;

[0015] B. Design the structural model of the folding wing and rudder based on the principles of generalization development, reliability design, low cost, standardization and rationality; including designing the geometric parameters of the folding wing and rudder, and the geometric parameters include wing and rudder root chord length, tip chord length, middle chord length, span, trailing edge sweep angle, rudder rotating shaft position, rudder root thickness, rudder tip thickness, leading edge radius, trailing edge radius;

[0016] C. Verify the strength of the locking mechanism components; including calculating and checking the working limit bending moment torque, torsion spring stiffness, working limit torsion angle, minimum working torque of the torsion spring, maximum working torque of the torsion spring, spring stiffness, working limit load, spring working limit deformation, minimum working elastic force of the spring and maximum working elastic force of the spring; establish a three-dimensional model of the folding wing and rudder based on the geometric parameters and conduct envelope analysis and deployment time and deployment synchronism analysis;

[0017] D. Conduct consistency verification on the folding wing and rudder based on finite element simulation analysis, including determining material parameters according to the mass and geometric parameter requirements of the folding wing and rudder, constraining the end face of the rudder root in the ABAQUS software, applying corresponding torque and bending moment according to the maximum torque load and maximum bending moment load, and conducting finite element analysis on the structural strength of the folding rudder under the combined action of bending moment and torque.

[0018] Furthermore, in step B, it also includes considering the manufacturing process of the folding wing and rudder, and selecting the manufacturing process according to the selected material and geometric parameters.

[0019] Furthermore, in step D, it also includes conducting finite element analysis on the connecting handle.

[0020] Furthermore, in step D, after completing the consistency verification in step D, it also includes step E:

[0021] Optimize and adjust the structural model of the folding wing and rudder according to the results of the finite element simulation analysis. If the simulation results show that the stress in some parts is too large or the deformation exceeds the allowable range, then adjust the corresponding geometric parameters or materials, and then conduct finite element analysis again until the design requirements are met.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] Through the design of the torsion spring in the locking mechanism of the present invention, by accurately calculating key parameters such as the working limit bending moment and torque of the torsion spring, the torsional spring stiffness, the working limit torsional angle, the minimum working torque of the torsion spring, the maximum working torque of the torsion spring, the spring stiffness, the working limit load, the spring working limit deformation, the minimum working elastic force of the spring, and the maximum working elastic force of the spring, the folding wing and rudder can complete the unfolding action at a faster speed, thereby effectively reducing the unfolding time and ensuring that the aircraft can enter the ideal control state in a timely manner during flight missions that require rapid response.

[0024] Through the systematic design process of the present invention, the designed folding wing and rudder can meet strict performance parameter requirements. During the design process, the principle of low cost is always followed. By optimizing the structural design, selecting conventional materials, and reducing the number of structural parts and other measures, the manufacturing cost of the product is effectively reduced. At the same time, the application of the generalization principle also helps to reduce the later use and maintenance costs. The implementation of the reliability design principle and the rationality principle makes the structure of the folding wing and rudder more concise, and the operation and maintenance more convenient. The concise mechanism layout reduces the probability of failure, and the design that is easy to operate and maintain can be quickly repaired when problems occur, improving the reliability and maintainability of the product.

[0025] The present invention also comprehensively verifies the strength of the components of the locking mechanism, involving the calculation and verification of multiple key parameters of the torsion spring. At the same time, envelope analysis, deployment time and synchronization analysis are also carried out. This meticulous analysis can ensure that the locking mechanism can work reliably under various working conditions, avoiding failures caused by insufficient strength or unqualified performance of the components.

[0026] The present invention uses ABAQUS software for finite element simulation analysis. According to the mass and geometric parameter requirements of the folding wing and rudder, the material parameters are determined, and the corresponding torque and bending moment are applied to evaluate the structural strength under their combined action. This method can accurately predict the mechanical properties of the product in actual use, timely discover potential problems in the design, and thus optimize and improve, improving the accuracy and reliability of the design. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the overall structure when the unfolding locking mechanism of the present invention is in use;

[0028] Figure 2 It is a schematic diagram of the partial structure when the unfolding locking mechanism of the present invention is in use;

[0029] Figure 3 It is a schematic diagram of the overall structure of the unfolding locking mechanism of the present invention;

[0030] Figure 4 It is a schematic sectional view when the unfolding locking mechanism of the present invention is in use;

[0031] Figure 5 It is a schematic diagram of the overall structure of the folding wing of the present invention;

[0032] Figure 6 It is a schematic diagram of the overall structure of the folding rudder of the present invention;

[0033] Figure 7 It is a model diagram of the folding wing of the present invention;

[0034] Figure 8 It is a model diagram of the folding rudder of the present invention;

[0035] Figure 9 It is one of the cloud maps of the present invention;

[0036] Figure 10 It is another cloud map of the present invention;

[0037] Figure 11 It is the third cloud map of the present invention

[0038] Figure 12 It is the fourth cloud map of the present invention

[0039] Figure 13 It is the fifth cloud map of the present invention

[0040] Figure 14 This is the sixth cloud chart of the present invention

[0041] Figure 15 This is the seventh cloud chart of the present invention

[0042] Figure 16 This is the eighth cloud chart of the present invention

[0043] Figure 17 This is the ninth cloud chart of the present invention

[0044] Figure 18 This is the tenth cloud chart of the present invention

[0045] Markings in the figure: 1 - connecting handle, 2 - locking projection, 3 - ventilation hole, 4 - locking head, 5 - torsion spring, 6 - connecting head, 7 - rotating shaft, 8 - limiting stop, 9 - upper locking groove, 10 - limiting platform, 11 - lower locking groove, 12 - installation groove, 13 - limiting hole Specific embodiments

[0046] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention

[0047] Embodiment

[0048] A folding wing and rudder deployment locking mechanism includes a connecting handle 1, a torsion spring 5, and a rotating shaft 7; locking heads 4 and connecting heads 6 are respectively arranged on both sides of the bottom of the folding wing or folding rudder; both ends of the rotating shaft 7 are movably connected to the connecting head 6 and the locking head 4 respectively, the connecting handle 1 is connected to the rotating shaft 7, an installation groove 12 is arranged on the connecting handle 1, an upper locking groove 9 is arranged on one side of the connecting handle 1, a locking projection 2 is arranged on the locking head 4, and the locking projection 2 cooperates with the upper locking groove; the torsion spring 5 is arranged in the installation groove 12, and both ends of the torsion spring 5 are connected to the connecting handle 1 and the connecting head 6 respectively, and the torsion spring 5 is used to drive the folding wing or folding rudder to rotate and reset and make the folding wing or folding rudder move axially along the rotating shaft 7 to reset

[0049] The connecting handle 1 is connected to the locking head 4 and the connecting head 6 through the rotating shaft 7, that is, it is connected to the bottom of the folding wing or the folding rudder. The torsion spring 5 is used to drive the folding wing or the folding rudder to rotate and reset and to make the folding wing or the folding rudder move and reset along the axial direction of the rotating shaft 7. Specifically, when the folding rudder or the folding wing is folded, the folding rudder or the folding wing first moves forward, so that the locking protrusion 2 is separated from the upper locking groove 9, and at the same time, the torsion spring generates a locking elastic force and a torsion force; the folding rudder or the folding wing is in the envelope surface after being folded. When unfolding, the folding rudder or the folding wing is separated from the envelope surface, and the folding rudder or the folding wing is automatically unfolded under the action of the torsion spring. At the same time, the torsion spring 5 pushes the folding rudder or the folding wing to move and reset and makes the upper locking groove and the locking protrusion 2 stuck. The matching part of the locking groove and the locking protrusion 2 bears the load during flight. Since the mechanism is provided with the torsion spring 5, the two ends of the torsion spring 5 are respectively connected to the connecting handle 1 and the connecting head 6, which can not only drive the folding wing or the folding rudder to rotate and reset, but also make it move and reset along the axial direction of the rotating shaft 7. During the unfolding process, even if it is subject to external interference such as vibration and impact, the elastic force and torsional force provided by the torsion spring 5 can continue to act, pushing the folding wing or folding rudder to overcome the interference force and move toward the correct unfolding position, so as to make it unfold as completely as possible and reduce the occurrence of incomplete unfolding due to interference. Secondly, a locking groove 9 is provided on the connecting handle 1, and a locking protrusion 2 is provided on the locking head 4. The two cooperate with each other, and when unfolding, the torsion spring 5 pushes the folding wing or folding rudder to move and reset, so that the upper locking groove and the locking protrusion 2 are stuck. This way of matching the slot and the protrusion is equivalent to providing a stable locking mechanism for the unfolding state of the folding wing or folding rudder. When facing vibration and impact, as long as the external interference force does not exceed the limit that the slot and the protrusion can withstand, it can ensure that the folding wing or folding rudder is maintained in the unfolded state, avoiding loosening and displacement due to interference, which leads to incomplete unfolding.

[0050] In a preferred embodiment, a lower locking groove 11 is provided on one side of the connecting handle 1 close to the connecting head 6, and a locking block is provided on the connecting head 6, and the lower locking groove 11 cooperates with the locking block. During the process of resetting the folding rudder or folding wing, the lower locking groove 11 can also cooperate with the locking block. This design further enhances the stability of the connection between the folding wing or folding rudder and the connecting handle 1, and can better prevent unnecessary shaking or displacement during the process of unfolding the folding wing or rudder and subsequent flight, and assists the cooperation of the locking protrusion 2 and the upper locking groove 9 to jointly bear the load during flight, thereby ensuring the reliable operation of the entire structure.

[0051] In a preferred embodiment, the upper locking groove 9 and the lower locking groove 11 are arranged in a cross pattern. This cross arrangement limits and fixes the folding wing or folding rudder from two mutually perpendicular directions, greatly enhancing the stability of the overall structure, enabling the folding wing or folding rudder to be firmly fixed in the accurate position under different stress conditions, more reliably withstanding the multi-directional loads during flight, and further ensuring the stability and reliability of the deployment locking mechanism.

[0052] In a preferred embodiment, ventilation holes 3 are provided on the locking head 4. The ventilation holes 3 are connected to the shaft holes 7 on the locking head 4 for installing the rotating shaft 7, so as to balance the pressure between the shaft holes 7 and the outside world, and facilitate preventing obstacles when the folding rudder or folding wing moves axially.

[0053] In a preferred embodiment, a limiting stop 8 is provided on one side of the rotating shaft 7 close to the connecting head 6, a limiting hole 13 is provided on one side of the connecting handle 1, and a limiting pin is arranged in the limiting hole 13. Through the design of the limiting stop 8, the rotating shaft 7 can be connected to the connecting handle 1 through a pin.

[0054] In a preferred embodiment, a limiting platform 10 is also fixedly connected to one side of the connecting handle 1 close to the connecting head 6. The limiting platform 10 can contact the connecting head 6, and the limiting platform 10 is used to limit the axial movement range of the folding wing or folding rudder. By contacting the connecting head 6, the limiting platform 10 clearly limits the movement range of the folding wing or folding rudder in the axial direction of the rotating shaft 7, avoiding excessive axial movement during the processes of deployment, folding, and flight, ensuring that its movement is always within a reasonable and controllable range, thereby ensuring the stable and reliable operation of the entire mechanism and enhancing the safety and stability of the overall structure.

[0055] In a preferred embodiment, a connecting protrusion is provided on one side of the connecting handle 1 close to the lower locking groove 11. The connecting protrusion is used for limiting, specifically to ensure the one-way folding of the rudder surface or wing surface, and can effectively prevent excessive radial rotation when the locking fails after the rudder surface or wing surface is deployed, thereby effectively ensuring reliability.

[0056] Design method 1:

[0057] A design method for a folding wing and rudder, used for designing a folding wing and rudder as described in the previous aspect, includes the following steps:

[0058] A. Obtain the performance parameters required for the folding wing and rudder; the performance parameters include folding dimensions, deployment time, deployment synchronization, mass, maximum torque load, and maximum bending moment load;

[0059] Among them, the performance parameters for the folding wing include:

[0060] Folding dimensions: The projectile diameter is 127 mm, and the outer contour of the wing after folding does not exceed

[0061] Deployment time: not greater than 500 ms;

[0062] Deployment synchronization: not greater than 20% of the deployment time;

[0063] Mass: for a single control surface, not greater than 160 g

[0064] Center of mass: not required;

[0065] Maximum torque load: for a fixed wing surface, this index is not mentioned;

[0066] Maximum bending moment load: 10.0 Nm.

[0067] For the performance parameters of the folding rudder, they include:

[0068] Folding dimensions: projectile diameter 127 mm, the outer contour of the rudder after folding does not exceed φ164 mm;

[0069] Deployment time: not greater than 500 ms;

[0070] Deployment synchronization: not greater than 20% of the deployment time;

[0071] Mass: for a single control surface, not greater than 150 g;

[0072] Center of mass: not required;

[0073] Maximum torque load: 1.5 Nm;

[0074] Maximum bending moment load: 6.0 Nm.

[0075] B. Design the structural models of the folding wing and rudder based on the principles of generalization development, reliability design, low cost, standardization, and rationality; including designing the geometric parameters of the folding wing and rudder, and the geometric parameters include the root chord length, tip chord length, middle chord length, span, trailing edge sweep angle, rudder rotation axis position, root thickness of the rudder, tip thickness of the rudder, leading edge radius, and trailing edge radius;

[0076] Among them, the principle of generalization development refers to reducing the manufacturing, usage, and later maintenance costs. The principle of reliability design refers to streamlining the mechanism layout on the premise of meeting the functional indicators. The principle of low-cost design refers to following the low-cost design principle during the scheme design process on the premise of meeting the functional indicators, minimizing the number of structural parts as much as possible, making components multi-functional, and selecting conventional materials as much as possible while reducing the variety of selected materials. The standardization principle means that the design scheme meets the provisions of relevant national standards and industry standards; the rationality principle means ensuring easy operation and reliable maintenance.

[0077] The wing surface model after design is as Figure 5 shown, the wing surface model after design is as Figure 6As shown in the figure, the geometric parameters of the folding wing are designed as follows:

[0078] The chord length at the wing root is 95 mm, the tip chord length is 50 mm, the span is 75 mm, the trailing edge sweep angle is 0°, and the wing is fixed to the projectile body. The thickness at the wing root is tentatively set at 7 mm - 10 mm, and the thickness at the tip of the tail wing is tentatively set at 3 mm. The leading edge radius is 1.5 mm, and the trailing edge radius is 1.5 mm.

[0079] The geometric parameters of the folding rudder are designed as follows:

[0080] The chord length at the rudder root is 54 mm, the tip chord length is 17 mm, the middle chord length is 24 mm, the span is 50 mm, the trailing edge sweep angle is 0°, and the rudder rotation axis is located 24.5 mm behind the tip. The thickness at the rudder root is tentatively set at 7 mm - 10 mm, the thickness at the rudder tip is tentatively set at 3 mm, and the thickness at the middle position is evenly transitioned. The leading edge radius is 1.5 mm, and the trailing edge radius is 1.5 mm.

[0081] C. Verify the strength of the components of the locking mechanism; including calculating and checking the working limit bending moment torque, torsion spring stiffness, working limit torsion angle, minimum working torque of the torsion spring, maximum working torque of the torsion spring, spring stiffness, working limit load, spring working limit deformation, minimum working elastic force of the spring, and maximum working elastic force of the spring; establish three-dimensional models of the folding wing and rudder based on geometric parameters and conduct envelope analysis, deployment time, and deployment synchronization analysis;

[0082] Calculate the moment of inertia of the folding wing and rudder and estimate the resistance moment; establish a mathematical model of the projectile torsion spring, and the mathematical model includes deployment time, torsion spring stiffness, and torque; set constraint conditions, including deployment time less than or equal to 500 ms, working stress less than or equal to the allowable stress of the material, and spring size less than or equal to the installation space; iteratively output the spring size parameters.

[0083] In this design method, for the folding wing, the pitch diameter D of the projectile torsion spring is 9.5 mm, the wire diameter d is 2 mm, the folding torsion angle of the wing surface is 110°, the initial working torsion angle of the torsion spring is 75°, the maximum working torsion angle of the torsion spring is 185°, the number of active coils n is 17, the free height H0 is 44.5 mm, the maximum compressed height H n = 37 mm, and the spring height after the wing and rudder surfaces are locked is 42 mm. From this, calculate and check the satisfaction of the design parameters of the projectile torsion spring.

[0084] Working limit bending moment torque T j

[0085] T j = Ed 3 σ j / (32K1) = 1052.433 N·mm

[0086] Torsion spring stiffness

[0087]

[0088] Working limit torsional angle

[0089]

[0090] Minimum working torque of torsion spring

[0091] T1 = T'ψ1 = 417.4120957 N·mm

[0092] Maximum working torque of torsion spring

[0093] T n = T'ψ n = 1029.616503 N·mm

[0094] Spring stiffness

[0095]

[0096] Working limit load

[0097]

[0098] Spring working limit deformation

[0099]

[0100] Minimum working elastic force of spring

[0101] P1 = pF1 = 27.1 N

[0102] Maximum working elastic force of spring

[0103] P n = pF n = 81.3 N

[0104] In this design method, for the folding rudder, the mean diameter of the spring D = 7 mm, the wire diameter d = 1.4 mm, the folding torsional angle of the wing surface is 95°, the initial working torsional angle of the torsion spring is 53°, the maximum working torsional angle of the torsion spring is 148°, the number of active turns n = 13, the free height H0 = 26 mm, the maximum compressed height Hn = 21 mm, and the spring height after the rudder surface is locked is 23.5 mm. Thus, the satisfaction of the design parameters of the torsion spring is calculated and checked.

[0105] Working limit bending moment torque Tj

[0106] T j = Ed 3 σ j / (32K1) = 391.6442936 N·mm

[0107] Torsion spring stiffness

[0108]

[0109] Working limit torsional angle

[0110]

[0111] Minimum working torque of torsion spring

[0112] T1 = T'ψ1 = 125.6906379 N·mm

[0113] Maximum working torque of torsion spring

[0114] T n = T'ψ n = 350.9851776 N·mm

[0115] Spring stiffness

[0116]

[0117] Working limit load

[0118]

[0119] Spring working limit deformation

[0120]

[0121] Minimum working elastic force of spring

[0122] P1 = pF1 = 21.27 N

[0123] Maximum working elastic force of spring

[0124] P n = pF n = 42.53846154 N

[0125] Calculate the deployment time of the folding wing and the synchronization of the folding wing deployment;

[0126] The moment of inertia J of the wing surface of the folding wing = 65167.54 g·mm 2 , Initial torsional angle Wing surface working angle Torque T at maximum working angle n = 1029.62 N·mm, Resistance torque T z = P n μl = 81.3×0.3×9 N·mm = 219.5 N·mm,

[0127] Thus, calculate the theoretical deployment time t of the wing surface:

[0128] Rotational circular frequency

[0129]

[0130] Wing surface theoretical deployment time t

[0131]

[0132] Here, a is a coefficient, and here a takes 1.

[0133] Wing surface deployment synchronization time:

[0134] Since the folding wings have the same structure, the deployment synchronization time is determined by the consistency of manufacturing accuracy and the consistency of folding angles. Theoretically, the deployment synchronization time of the folding wings is 0.

[0135] Calculate the deployment time of the folding wings and the deployment synchronization of the folding wings;

[0136] The moment of inertia J of the wing surface of the folding wing = 6418.5 g·mm 2 , initial torsion angle Control surface working angle Torque T at the maximum working angle n = 351 N·mm, resistance torque T z = P n μl = 42.5385×0.3×6 N·mm = 76.57 N·mm,

[0137] From this, calculate the theoretical deployment time t of the wing surface:

[0138] Rotational circular frequency

[0139]

[0140] Control surface theoretical deployment time t

[0141]

[0142] Here, a is a coefficient, and here a takes 1.

[0143] Control surface deployment synchronization time

[0144] Since the folding rudders have the same structure, the deployment synchronization time is determined by the consistency of manufacturing accuracy and the consistency of folding angles. Theoretically, the deployment synchronization time of the folding rudders is 0.

[0145] D. Based on the finite element simulation analysis, conduct consistency verification on the folding wings and rudders, including determining material parameters according to the mass and geometric parameter requirements of the folding wings and rudders, establishing models of the folding wings and rudders, in the ABAQUS software, constraining the root end face of the rudder, applying corresponding torques and bending moments according to the maximum torque load and maximum bending moment load, and conducting finite element analysis on the structural strength of the folding rudders under the combined action of bending moment and torque.

[0146] The primary materials used for the folding rudder and wing are 7075 aluminum alloy and 0Cr17Ni4Cu4Nb stainless steel alloy, and their main mechanical property parameters are shown in Table 1.

[0147] Table 1 Structural Material Properties

[0148]

[0149] Perform a finite element analysis on the structural strength of the folding wing under bending moment load. Use the ABAQUS analysis software. The number of elements in the finite element model is 318369, and the number of nodes is 79962. The analysis model is shown in Figure 7 .

[0150] Perform a finite element analysis on the structural strength of the folding rudder under the combined action of bending moment and torque. Use the ABAQUS analysis software. The number of elements in the finite element model is 1061432, and the number of nodes is 210580. The analysis model is shown in Figure 8 .

[0151] The strength analysis structures of the folding wing and rudder are shown in Table 2:

[0152] Table 2 Strength Analysis Results of Folding Wing and Rudder

[0153]

[0154]

[0155] The summary of the satisfaction of the design indicators for the folding wing and folding rudder is shown in Table 3:

[0156] Table 3 Satisfaction of Indicators for Folding Wing and Rudder

[0157]

[0158]

[0159]

[0160]

[0161]

[0162] Through this design method, folding wings and rudders that meet the design indicators can be obtained quickly.

[0163] Design Method 2:

[0164] Different from Design Method 1, in Step B, it also includes considering the manufacturing processes of the folding wings and rudders, and selecting the manufacturing processes according to the selected materials and geometric parameters. Through the precise matching of process - material - geometry, it ensures that the theoretical design performance is transformed into physical performance, and the early process intervention can reduce the later rework.

[0165] Design Method 3:

[0166] Different from Design Method 1, in Step D, it also includes performing a finite element analysis on the connecting handle. In the structural design of the folding wing / rudder, the connecting handle is the core force - transmitting component for transmitting the unfolding driving torque and bearing the aerodynamic load, and its strength, stiffness, and fatigue performance directly affect the overall reliability.

[0167] Specifically, a refined model of the connecting handle is established in ABAQUS, and the meshes are encrypted in areas such as the rotating shaft hole, threaded hole, and transition fillet. The following boundary conditions of the actual working conditions are applied:

[0168] The torque load is based on the maximum unfolding resistance torque:

[0169] T max = k·θ max (K is the stiffness of the torsion spring, θ max is the maximum rotation angle);

[0170] The bending moment load is to simulate the aerodynamic load:

[0171] M = 0.5ρv 2 ·C L ·S·c (ρ is the air density, S is the area of the wing or rudder, c is the chord length)

[0172] The unfolding impact load is simulated through explicit dynamic analysis. Define the pre - tightening force of the torsion spring as the initial condition, set the contact pair, and the friction coefficient μ between the connecting handle and the rotating shaft is 0.1□0.15. Output the time - history curve.

[0173] Perform fatigue analysis based on FE - Safe or nCode:

[0174] Input the material S - N curve, load the mission profile spectrum, apply the Miner cumulative damage theory to calculate the damage factor D = ∑(ni / Ni), and identify the fatigue critical points. Shot peening treatment is performed on the identified fatigue critical points.

[0175] Design Method 4:

[0176] In Step D, after completing the consistency check of Step D, it also includes Step E:

[0177] Optimize and adjust the structural models of the folding wings and rudders according to the results of finite element simulation analysis. If the simulation results show that the stress in some parts is too high or the deformation exceeds the allowable range, adjust the corresponding geometric parameters or materials, and then conduct finite element analysis again until the design requirements are met.

[0178] Specifically, for example, use variable-radius fillets to optimize the stress concentration area, reducing the peak stress by 30% - 50%. Or adjust the thickness distribution through parametric modeling. For example, increase the thickness of the wing and rudder root areas from 5 mm to 7 mm, and reduce the thickness of the tip areas from 3 mm to 2.5 mm. If the local stress of the aluminum alloy reaches 280 MPa, it can be replaced with TC4 titanium alloy. The topology optimization module of ABAQUS can also be used, such as TOSCA, to automatically generate a weight reduction hole scheme to ensure that the stress of the new configuration is lower than the allowable value.

[0179] In the description of the present invention, it should be understood that the orientation or positional relationships indicated by the terms "coaxial", "bottom", "one end", "top", "middle", "the other end", "upper", "one side", "top", "inner", "front", "center", "both ends", etc. are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0180] In the present invention, unless otherwise clearly specified and defined, the terms "installed", "set", "connected", "fixed", "swivelly connected", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two elements or the interaction relationship between two elements. Unless otherwise clearly defined, for those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0181] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A folding wing and rudder deployment and locking mechanism, characterized in that: It includes a connecting handle (1), a torsion spring (5) and a rotating shaft (7); locking heads (4) and connecting heads (6) are respectively arranged on both sides of the bottom of the folding wing or folding rudder; Both ends of the rotating shaft (7) are movably connected to the connecting head (6) and the locking head (4) respectively. The connecting handle (1) is connected to the rotating shaft (7). An installation groove (12) is arranged on the connecting handle (1). An upper locking groove (9) is arranged on one side of the connecting handle (1). A locking protrusion (2) is arranged on the locking head (4), and the locking protrusion (2) cooperates with the upper locking groove; The torsion spring (5) is arranged in the installation groove (12). Both ends of the torsion spring (5) are connected to the connecting handle (1) and the connecting head (6) respectively. The torsion spring (5) is used to drive the folding wing or folding rudder to rotate and reset and make the folding wing or folding rudder move axially along the rotating shaft (7) to reset.

2. The folding wing and rudder deployment and locking mechanism according to claim 1, characterized in that: A lower locking groove (11) is arranged on one side of the connecting handle (1) close to the connecting head (6). A locking block is arranged on the connecting head (6), and the lower locking groove (11) cooperates with the locking block.

3. A folding wing and rudder deployment and locking mechanism according to claim 1, characterized in that: A ventilation hole (3) is arranged on the locking head (4).

4. A folding wing and rudder deployment and locking mechanism according to claim 1, characterized in that: A limiting stop (8) is arranged on one side of the rotating shaft (7) close to the connecting head (6). A limiting hole (13) is arranged on one side of the connecting handle (1), and a limiting pin is arranged in the limiting hole (13).

5. A folding wing and rudder deployment and locking mechanism according to claim 1, characterized in that: A limiting platform (10) is also fixedly connected to one side of the connecting handle (1) close to the connecting head (6).

6. A folding wing and rudder design method for designing a folding wing and rudder according to any one of claims 1-5, characterized in that, It includes the following steps: A. Obtain the performance parameters required for the folding wing and rudder; The performance parameters include folding size, deployment time, deployment synchronism, mass, maximum torque load and maximum bending moment load; B. Design the structural model of the folding wing and rudder based on the principles of generalization development, reliability design, low cost, standardization and rationality; It includes designing the geometric parameters of the folding wing and rudder. The geometric parameters include the root chord length, tip chord length, middle chord length, span length, trailing edge sweep angle, rudder rotating shaft position, rudder root thickness, rudder tip thickness, leading edge radius, trailing edge radius of the wing and rudder; C. Verify the strength of the components of the locking mechanism; including calculating and checking the working limit bending moment torque, torsion spring stiffness, working limit torsion angle, minimum working torque of the torsion spring, maximum working torque of the torsion spring, spring stiffness, working limit load, spring working limit deformation, minimum working elastic force of the spring and maximum working elastic force of the spring; establish a three-dimensional model of the folding wing and rudder based on the geometric parameters and conduct envelope analysis and deployment time and deployment synchronism analysis; D. Conduct consistency check on the folding wing and rudder based on finite element simulation analysis, including determining material parameters according to the mass and geometric parameter requirements of the folding wing and rudder, establishing models of the folding wing and rudder, in the ABAQUS software, constraining the rudder root end face, applying corresponding torque and bending moment according to the maximum torque load and maximum bending moment load, and conducting finite element analysis on the structural strength of the folding rudder under the combined action of bending moment and torque.

7. A folding wing and rudder design method according to claim 6, characterized in that: In step B, it also includes considering the manufacturing process of the folding wing and rudder and selecting the manufacturing process according to the selected material and geometric parameters.

8. A folding wing and rudder design method according to claim 6, characterized in that: In step D, it also includes conducting finite element analysis on the connecting handle.

9. A folding wing and rudder design method according to claim 6, characterized in that: In step D, after completing the consistency check in step D, it also includes step E: Optimize and adjust the structural models of the folding wings and rudders according to the results of finite element simulation analysis; if the simulation results show that the stress in some parts is too large or the deformation exceeds the allowable range, adjust the corresponding geometric parameters or materials, and then conduct finite element analysis again until the design requirements are met.

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