A folding mechanism
By designing a locking structure to control the wing folding mechanism, the problems of aerodynamic shape damage and poor maintainability of existing folding mechanisms are solved, realizing stable wing folding and convenient maintenance, and improving flight performance and safety.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- JIFEI ZHIHANG TECHNOLOGY (XIAN) CO LTD
- Filing Date
- 2025-07-28
- Publication Date
- 2026-07-14
Smart Images
Figure CN224491475U_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of folding technology, and more particularly to a folding mechanism. Background Technology
[0002] Fixed-wing aircraft, especially carrier-based aircraft and large unmanned aerial vehicles, often adopt folding wing designs to reduce the footprint required for storage, parking and transportation.
[0003] Existing folding mechanism designs generally suffer from problems such as aerodynamic deformation and poor maintainability. Therefore, there is an urgent need to develop a new type of wing folding mechanism to effectively solve these problems. Utility Model Content
[0004] The main purpose of this application is to provide a folding mechanism that addresses the problems of aerodynamic shape damage and poor maintainability that are common in existing folding mechanism designs.
[0005] To achieve the above objectives, this application provides a folding mechanism connected between an inner wing structure simulator and an outer wing structure simulator disposed opposite to each other in a first direction. The folding mechanism includes a first connector, a second connector, and a locking structure. The first connector is disposed on the side of the inner wing structure simulator facing the outer wing structure simulator. The second connector is disposed on the side of the outer wing structure simulator facing the inner wing structure simulator and is rotatably connected to the first connector. The second connector has a degree of freedom of rotation about a second direction to fold the outer wing structure simulator. The locking structure is disposed between the inner wing structure simulator and the outer wing structure simulator and is connected to either the inner wing structure simulator or the outer wing structure simulator. The locking structure cooperates with the first connector and the second connector to lock or release the rotational degree of freedom of the second connector.
[0006] Optionally, the first connector is provided with a first limiting hole whose axial direction is the same as the second direction, and the second connector is provided with a first mating hole coaxial with the first limiting hole; the locking structure includes a pin and a driving part, the pin is inserted into the first limiting hole and the first mating hole, and has the freedom to move along the second direction; the driving part is connected to the inner section wing structure simulation component or the outer section wing structure simulation component, and the driving part is connected to the pin and provides the pin with a moving driving force.
[0007] Optionally, both the first connector and the second connector have a main body connected to the corresponding simulation component and an ear piece connected to the corresponding main body. The ear piece on the first connector is a first ear piece, and the ear piece on the second connector is a second ear piece. The second ear piece and the first ear piece are rotatably connected by a rotating shaft. The axial direction of the rotating shaft is the same as the second direction. The first limiting hole is provided on the first ear piece, and the first mating hole is provided on the second ear piece.
[0008] Optionally, when the driving unit is connected to the inner wing structure simulation component, the driving unit is located on the side of the first lug away from the second lug; when the driving unit is connected to the outer wing structure simulation component, the driving unit is located on the side of the second lug away from the first lug; wherein, a sliding sleeve coaxial with the first limiting hole is provided on the corresponding lug near the driving unit, and the pin passes through the sliding sleeve to slide in the second direction.
[0009] Optionally, the drive unit is connected to the inner wing structure simulation component, and the first connector has two first lugs facing each other in the second direction, with the second lug located between the two first lugs.
[0010] Optionally, the first connector, the second connector, and the pin constitute a folding portion, and there are two folding portions arranged opposite each other in the second direction; wherein, the driving portion is located between the two folding portions and connected to the two pins, and the driving portion provides the moving driving force to the two pins to synchronously lock or release the rotational degrees of freedom of the two second connectors.
[0011] Optionally, the drive unit includes a fixed support, a rocker arm shaft, a central rocker arm, and a connecting rocker arm. The fixed support is connected to the inner section wing structure simulator or the outer section wing structure simulator. The rocker arm shaft passes through the fixed support and is rotatably connected to the fixed support. The rocker arm shaft has a degree of freedom to rotate about its own axis, and the axis is the same as a third direction. The center part of the central rocker arm is fixed to the end of the rocker arm shaft. The connecting rocker arm corresponds to the pin, with one end rotatably connected to the corresponding pin and the other end rotatably connected to the end of the central rocker arm. The connecting rocker arm has a degree of freedom to rotate about the third direction.
[0012] Optionally, the drive unit further includes a limiting part and a limiting pin. The limiting part is connected to the fixed support and sleeved on the outer periphery of the rocker arm shaft. The limiting part has an arc-shaped notch in the axial direction. The limiting pin is fixed to the outer periphery of the rocker arm shaft and passes through the arc-shaped notch. When the locking structure locks the rotational degree of freedom of the second joint, the limiting pin abuts against the first end of the arc-shaped notch. When the locking structure releases the rotational degree of freedom of the second joint, the limiting pin abuts against the second end of the arc-shaped notch.
[0013] Optionally, the central rocker arm has a limiting insertion hole; the drive unit further includes a locking pin, which passes through the fixed support and is threadedly connected to the fixed support; wherein, when the locking structure locks the rotational degree of freedom of the second joint, the limiting insertion hole is located on the axial direction of the locking pin, and the end of the locking pin passes through the limiting insertion hole to lock the rotational degree of freedom of the rocker arm shaft.
[0014] Optionally, the folding mechanism further includes a spring pin, and the first connector is also provided with a second limiting hole with the same axial direction as the second direction, and the second connector is also provided with a second mating hole; wherein, when the outer wing structure simulation component is folded, the second limiting hole and the second mating hole are coaxial, and the spring pin is inserted into the second limiting hole and the second mating hole.
[0015] The folding mechanism proposed in this application releases the rotational freedom of the second connector through a locking structure during use. Rotating the second connector causes the outer wing structure simulation component to fold relative to the inner wing structure simulation component. During unfolding, rotating the second connector unfolds the outer wing structure simulation component relative to the inner wing structure simulation component, and locking the rotational freedom of the second connector through the locking structure completes the wing unfolding. The folding mechanism is installed between the inner and outer wing structure simulation components, effectively preventing damage to the aerodynamic shape of the aircraft wing. Furthermore, during maintenance, only the first connector, the second connector, and the locking structure need to be disassembled for component repair or replacement, making it more convenient and faster. Attached Figure Description
[0016] To more clearly illustrate the prior art and the present invention, the accompanying drawings used in the description of the prior art and the embodiments of the present invention will be briefly introduced below. Obviously, the drawings described below are merely exemplary, and those skilled in the art can derive other drawings from the provided drawings without any creative effort.
[0017] The structures, proportions, sizes, etc. illustrated in this specification are only for the purpose of assisting those skilled in the art in understanding and reading the content disclosed herein, and are not intended to limit the conditions under which this utility model can be implemented. Any modifications to the structure, changes in the proportions, or adjustments to the size, without affecting the effects and purposes that this utility model can produce, should still fall within the scope of the technical content disclosed in this utility model.
[0018] Figure 1 This is a schematic diagram of the overall structure of a folding mechanism proposed in an embodiment of this application;
[0019] Figure 2 for Figure 1 A structural breakdown diagram of the Chinese embodiment;
[0020] Figure 3 This is a schematic diagram of the locking structure in an embodiment of this application;
[0021] Figure 4 for Figure 3 Another perspective structural diagram of the embodiment;
[0022] Figure 5 for Figure 4 A structural breakdown diagram of the Chinese embodiment;
[0023] Figure 6 This is a schematic diagram of the folding mechanism according to an embodiment of this application during folding.
[0024] Figure 7 for Figure 6 A schematic diagram showing the structural breakdown of the Chinese embodiment.
[0025] In the diagram: 1. Simulated inner wing structure; 2. Simulated outer wing structure; 3. First connector; 31. First limiting hole; 32. Second limiting hole; 4. Second connector; 41. First mating hole; 42. Second mating hole; 5. Locking structure; 51. Pin; 52. Drive unit; 521. Fixed support; 522. Rocker arm shaft; 523. Center rocker arm; 5231. Limiting insertion hole; 524. Connecting rocker arm; 525. Limiting part; 526. Limiting pin; 527. Locking pin; 6. Sliding sleeve.
[0026] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation
[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.
[0028] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in this utility model embodiment are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.
[0029] In this utility model, unless otherwise explicitly specified and limited, the terms "connection" and "fixation" should be interpreted broadly. For example, "fixation" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.
[0030] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.
[0031] The present application will now be described in detail with reference to the accompanying drawings and embodiments.
[0032] Figure 1 This is a schematic diagram of the overall structure of a folding mechanism proposed in an embodiment of this application; Figure 2 for Figure 1 A structural breakdown diagram of the Chinese embodiment; Figure 3 This is a schematic diagram of the locking structure in an embodiment of this application; Figure 4 for Figure 3 Another perspective structural diagram of the embodiment; Figure 5 for Figure 4 A structural breakdown diagram of the Chinese embodiment; Figure 6 This is a schematic diagram of the folding mechanism according to an embodiment of this application during folding. Figure 7 for Figure 6 A schematic diagram showing the structural breakdown of the Chinese embodiment.
[0033] It should be understood that, Figures 1-2 The images shown are of the structural state when the folding mechanism is unfolded; Figures 3-5 The diagrams shown are partial structural illustrations of the locking structure 5 when the folding mechanism is unfolded. Figure 6 and Figure 7 The images shown all depict the structural state of the folding mechanism when it is folded. In the relevant descriptions of this application, unless otherwise specified, it is assumed that the folding mechanism is in a folded state. Figures 1-2 The unfolded state shown.
[0034] refer to Figures 1 to 7 It should be understood that Figure 2 The connections between the various components should be like Figure 1 As compact as in the middle, Figure 7 The connections between the various components should be like Figure 6 As compact as in the middle, this is only for illustrative purposes and will Figure 2 and Figure 7 To facilitate understanding, some components are shown disassembled. This application embodiment provides a folding mechanism connected between an inner wing structure simulation 1 and an outer wing structure simulation 2 arranged opposite each other in a first direction. The folding mechanism may further include a first connector 3, a second connector 4, and a locking structure 5. The first connector 3 is located on the side of the inner wing structure simulation 1 facing the outer wing structure simulation 2. The second connector 4 is located on the side of the outer wing structure simulation 2 facing the inner wing structure simulation 1 and is rotatably connected to the first connector 3. The second connector 4 has a degree of freedom to rotate about a second direction to fold the outer wing structure simulation 2. The locking structure 5 is located between the inner wing structure simulation 1 and the outer wing structure simulation 2 and is connected to either the inner wing structure simulation 1 or the outer wing structure simulation 2. The locking structure 5 cooperates with the first connector 3 and the second connector 4 to lock or release the rotational degree of freedom of the second connector 4.
[0035] The folding mechanism proposed in this application releases the rotational freedom of the second connector 4 through the locking structure 5 during use, thereby rotating the second connector 4 to fold the outer wing structure simulation 2 relative to the inner wing structure simulation 1. During unfolding, rotating the second connector 4 unfolds the outer wing structure simulation 2 relative to the inner wing structure simulation 1, and locking the rotational freedom of the second connector 4 through the locking structure 5 completes the wing unfolding. The folding mechanism is installed between the inner wing structure simulation 1 and the outer wing structure simulation 2, effectively preventing damage to the aerodynamic shape of the aircraft wing. At the same time, during maintenance, only the first connector 3, the second connector 4, and the locking structure 5 need to be disassembled for component repair or replacement, which is more convenient and faster.
[0036] The folding mechanism is completely concealed within the skin, eliminating the need for additional protrusions on the aerodynamic surface. This significantly reduces flight drag and improves lift-to-drag ratio and cruise efficiency. The concealed design also effectively protects core components, reduces the risk of failure caused by environmental factors, and enhances the safety of the outer wing structure simulator 2 in the deployed state.
[0037] It should be noted that a foldable wing typically consists of two parts. The first part is the inner wing section connected to the fuselage, which is usually fixed in place. The second part is the outer wing section connected to the end of the inner wing section away from the fuselage. When the outer wing section and the inner wing section form a certain angle, it indicates that the outer wing section is folded. When the outer wing section and the inner wing section are parallel, it indicates that the outer wing section is unfolded.
[0038] In the embodiments of this application, such as Figure 1 As shown, the inner wing structure simulator 1 represents the inner wing of the aircraft, and the outer wing structure simulator 2 represents the outer wing of the aircraft.
[0039] Among them, such as Figure 1 As shown, the first direction is the X direction and the second direction is the Y direction. The end face of the inner wing structure simulation component 1 away from the fuselage can be regarded as the reference plane. When the outer wing structure simulation component 2 is unfolded, the end face of the outer wing structure simulation component 2 and the end face of the inner wing structure simulation component 1 are parallel to the reference plane. At this time, the direction perpendicular to the reference plane is the first direction. The second direction is parallel to the horizontal plane and perpendicular to the first direction. In this way, the outer wing structure simulation component 2 can be folded or unfolded around the second direction, i.e., the horizontal direction.
[0040] It should be understood that the parallelism of the second direction with the horizontal plane is only a preferred embodiment. Even if the second direction is at a certain angle to the horizontal plane, the outer wing structure simulator 2 can be rotated around the second direction to fold or unfold the outer wing structure simulator 2.
[0041] refer to Figure 1 and Figure 2 In an exemplary embodiment, the first connector 3 is provided with a first limiting hole 31 whose axial direction is the same as the second direction, and the second connector 4 is provided with a first mating hole 41 coaxial with the first limiting hole 31; the locking structure 5 may include a pin 51 and a driving part 52, the pin 51 is inserted into the first limiting hole 31 and the first mating hole 41, and has a degree of freedom to move along the second direction; the driving part 52 is connected to the inner section wing structure simulation component 1 or the outer section wing structure simulation component 2, and the driving part 52 is connected to the pin 51 and provides a driving force for the pin 51 to move.
[0042] Specifically, the drive unit 52 drives the pin 51 to move along the second direction, causing the pin 51 to be pulled out of the first limiting hole 31 and the first mating hole 41. At this time, the rotational degree of freedom of the second connector 4 is released, thereby causing the outer wing structure simulation part 2 to rotate around the second direction and fold. When the outer wing structure simulation part 2 unfolds, the first limiting hole 31 and the first mating hole 41 are coaxial. The drive unit 52 drives the pin 51 to move along the second direction, causing the pin 51 to be inserted into the first limiting hole 31 and the first mating hole 41, thereby locking the rotational degree of freedom of the second connector 4 to prevent the outer wing structure simulation part 2 from rotating.
[0043] refer to Figure 1 and Figure 2 In an exemplary embodiment, both the first connector 3 and the second connector 4 have a main body connected to the corresponding simulation component and an ear piece connected to the corresponding main body. The ear piece on the first connector 3 is the first ear piece, and the ear piece on the second connector 4 is the second ear piece. The second ear piece and the first ear piece are rotatably connected by a rotating shaft. The axial direction of the rotating shaft is the same as the second direction. The first limiting hole 31 is provided on the first ear piece, and the first mating hole 41 is provided on the second ear piece.
[0044] Specifically, such as Figure 1 and Figure 2 As shown, the main body of the first connector 3 can also be in the form of a sheet, and is connected to the inner section wing structure simulation part 1 by tensile bolts, so as to facilitate the disassembly of the first connector 3. The first lug on the first connector 3 is perpendicular to the second direction, so as to facilitate the rotation of the first connector 3 around the second direction. The first limiting hole 31 is provided on the first lug.
[0045] Similarly, the main body of the second connector 4 can also be plate-shaped and connected to the outer wing structure simulation part 2 by tensile bolts to facilitate the disassembly of the second connector 4. The second lug on the second connector 4 is perpendicular to the second direction so that the second connector 4 can rotate around the second direction. The first mating hole 41 is provided on the second lug.
[0046] The second ear piece is rotatably connected to the first ear piece via a rotating shaft. The axis of the rotating shaft is the same as the second direction, so the second ear piece can rotate relative to the first ear piece around the axis of the rotating shaft. That is, the second connector 4 can rotate relative to the first connector 3 around the second direction.
[0047] For example, the shaft can be fixed on the first ear piece, and a hole is made on the second ear piece and a bearing is installed in the hole. The bearing is sleeved on the outer circumference of the shaft, so that the second ear piece can rotate about the axis of the shaft relative to the first ear piece.
[0048] refer to Figure 2 In an exemplary embodiment, when the drive unit 52 is connected to the inner wing structure simulation component 1, the drive unit 52 is located on the side of the first lug that is away from the second lug; when the drive unit 52 is connected to the outer wing structure simulation component 2, the drive unit 52 is located on the side of the second lug that is away from the first lug; wherein, a sliding sleeve 6 coaxial with the first limiting hole 31 is provided on the corresponding lug near the drive unit 52, and the pin 51 passes through the sliding sleeve 6 to slide in the second direction.
[0049] Specifically, in this embodiment, the drive unit 52 is connected to the inner section wing structure simulation component 1. At this time, the drive unit 52 is located on the side of the first ear piece away from the second ear piece, and a sliding sleeve 6 coaxial with the first limiting hole 31 is also provided on the side of the first ear piece away from the second ear piece. The pin 51 is inserted into the sliding sleeve 6 and slides with the sliding sleeve 6.
[0050] When the drive unit 52 drives the pin 51 to pull out the first limiting hole 31 and the first mating hole 41, the end of the pin 51 away from the drive unit 52 is located in the sliding sleeve 6.
[0051] It should be understood that if the drive unit 52 is connected to the outer wing structure simulation part 2, the sliding sleeve 6 can be set on the side of the second lug away from the first lug and coaxially set with the first mating hole 41.
[0052] Furthermore, self-lubricating bushings can be installed in the first limiting hole 31 and the first mating hole 41 to reduce the friction between the pin 51 and the first connector 3 and the second connector 4.
[0053] refer to Figure 1 In an exemplary embodiment, the drive unit 52 is connected to the inner section wing structure simulation component 1, and the first connector 3 has two first lugs opposite each other in a second direction, with the second lug located between the two first lugs.
[0054] Specifically, in this embodiment of the application, the drive unit 52 is connected to the inner section wing structure simulation component 1. In this case, there can be two first lugs, and the second lug is disposed between the two first lugs. In this way, the rotating shaft can be fixed on the two first lugs, which can increase the stability of the connection between the rotating shaft and the first lugs, and make the second connector 4 rotate around the rotating shaft more stably.
[0055] Of course, if the drive unit 52 is connected to the outer wing structure simulation part 2, then two second lugs can be provided on the second connector 4 so that the first lug can be inserted between the two second lugs.
[0056] refer to Figure 1 In an exemplary embodiment, the first connector 3, the second connector 4, and the pin 51 constitute a folding part, and there are two folding parts arranged opposite to each other in a second direction; wherein, the driving part 52 is located between the two folding parts and connected to the two pins 51, and the driving part 52 provides the two pins 51 with a moving driving force to synchronously lock or release the rotational degrees of freedom of the two second connectors 4.
[0057] like Figure 1 As shown, the stability of the outer wing structure simulator 2 during rotation can be further improved by the cooperation of the two folding parts.
[0058] In addition, the two folding parts are arranged opposite each other in the second direction, so that the rotating shafts in the two folding parts coincide axially. In this way, when the outer section wing structure simulation part 2 rotates and drives the two second joints 4 to rotate, the rotation process of the two second joints 4 does not interfere with each other.
[0059] refer to Figures 3-6 In an exemplary embodiment, the drive unit 52 may include a fixed support 521, a rocker arm shaft 522, a central rocker arm 523, and a connecting rocker arm 524. The fixed support 521 is connected to the inner section wing structure simulator 1 or the outer section wing structure simulator 2. The rocker arm shaft 522 passes through the fixed support 521 and is rotatably connected to the fixed support 521. The rocker arm shaft 522 has a degree of freedom to rotate about its own axis and the axis is the same as a third direction. The central part of the central rocker arm 523 is fixed to the end of the rocker arm shaft 522. The connecting rocker arm 524 corresponds to the pin 51 and one end is rotatably connected to the corresponding pin 51, and the other end is rotatably connected to the end of the central rocker arm 523. The connecting rocker arm 524 has a degree of freedom to rotate about a third direction.
[0060] Among them, such as Figure 3 As shown, the third direction is the Z direction. In the preferred embodiment, the first direction and the second direction are mutually perpendicular horizontal directions, and the third direction is the direction of gravity.
[0061] In this embodiment, the fixed support 521 is connected to the inner wing structure simulation component 1. The fixed support 521 may also include a main body and a third lug perpendicular to the main body. The main body of the fixed support 521 may be plate-shaped and connected to the inner wing structure simulation component 1 by tensile bolts to facilitate disassembly of the fixed support 521. The third lug may be perpendicular to the first lug.
[0062] Furthermore, the rocker arm shaft 522 can pass through and be rotatably connected to the third lug. When the rocker arm shaft 522 is rotated, the central rocker arm 523 can be driven to rotate around the axial direction of the rocker arm shaft 522, thereby causing both ends of the central rocker arm 523 to rotate around the axial direction of the rocker arm shaft 522, i.e., in the third direction. For example, if the drive unit 52 simultaneously drives two pins 51 to move synchronously, then the connecting rocker arms 524 are rotatably connected to both ends of the central rocker arm 523, and the ends of each connecting rocker arm 524 furthest from the central rocker arm 523 are rotatably connected to the pins 51. Figure 1 As shown, the pin 51 is slidably engaged with the sliding sleeve 6. Thus, when the two ends of the central rocker arm 523 rotate, the corresponding pin 51 will be driven to move synchronously closer to or farther away from the central rocker arm 523 in the second direction through the corresponding connecting rocker arm 524.
[0063] When the two pins 51 approach the central rocker arm 523 simultaneously, each pin 51 is pulled out of the corresponding first limiting hole 31 and the corresponding first mating hole 41 to release the rotational degree of freedom of the corresponding second connector 4. When the two pins 51 move away from the central rocker arm 523 simultaneously, each pin 51 is inserted into the corresponding first limiting hole 31 and the corresponding first mating hole 41 to lock the rotational degree of freedom of the corresponding second connector 4. That is, the rotational degree of freedom of the second connector 4 can be locked or released simply by rotating the rocker arm shaft 522, without the need for special tools or external power supply and other additional equipment, which greatly improves the operation speed.
[0064] In addition, in the locking structure 5, the fixed support 521 is connected to the inner wing structure simulation part 1, and the other components are all connected to the fixed support 521. Thus, the locking structure 5 can be disassembled and repaired or replaced simply by removing the fixed support 521 from the inner wing structure simulation part 1, which is more convenient and faster.
[0065] It should be noted that when disassembling the locking structure 5, the rocker arm shaft 522 can be rotated first to slide the pin 51 out of the sliding sleeve 6 before disassembly, so as to prevent the pin 51 from interfering with the sliding sleeve 6; or the first connector 3 and the second connector 4 can be disassembled first, and the first connector 3 and the second connector 4 can be moved away along the second direction before disassembling the locking structure 5.
[0066] In a preferred embodiment, taking the third direction as the same as the direction of gravity as an example, the central rocker arm 523 is fixed to the top of the rocker arm pivot 522. Thus, even if the outer wing structure simulation part 2 is rotated upward and folded, it is still easy to rotate the rocker arm pivot 522 at the bottom of the rocker arm pivot 522.
[0067] refer to Figure 4 In an exemplary embodiment, the drive unit 52 may further include a limiting part 525 and a limiting pin 526. The limiting part 525 is connected to the fixed support 521 and sleeved on the outer periphery of the rocker arm shaft 522. The limiting part 525 has an arc-shaped notch in the axial direction. The limiting pin 526 is fixed to the outer periphery of the rocker arm shaft 522 and passes through the arc-shaped notch. When the locking structure 5 locks the rotational degree of freedom of the second connector 4, the limiting pin 526 abuts against the first end of the arc-shaped notch. When the locking structure 5 releases the rotational degree of freedom of the second connector 4, the limiting pin 526 abuts against the second end of the arc-shaped notch.
[0068] Specifically, when the limiting pin 526 passes through the arc-shaped notch, the rocker arm shaft 522 rotates around its own axis, which will cause the limiting pin 526 to rotate around the axis of the rocker arm shaft 522 within the arc-shaped notch. In this way, the arc-shaped notch and the limiting pin 526 can limit the rotation angle of the rocker arm shaft 522.
[0069] Furthermore, when the locking structure 5 locks the rotational degree of freedom of the second connector 4, the limiting pin 526 abuts against the first end of the arc-shaped notch; when the locking structure 5 releases the rotational degree of freedom of the second connector 4, the limiting pin 526 abuts against the second end of the arc-shaped notch; in other words, when the rocker arm shaft 522 is rotated and the two pins 51 are inserted into the corresponding first limiting hole 31 and first mating hole 41, the rotational degree of freedom of the second connector 4 is locked, and the limiting pin 526 abuts against the first end of the arc-shaped notch; when the rocker arm shaft 522 is rotated and the two pins 51 are pulled out of the corresponding first limiting hole 31 and first mating hole 41, the rotational degree of freedom of the second connector 4 is released, and the limiting pin 526 abuts against the second end of the arc-shaped notch; thus, the rotational amplitude of the rocker arm shaft 522 can be controlled by the abutting of the limiting pin 526 against the end wall of the arc-shaped notch, which is more convenient and faster.
[0070] refer to Figures 3-6 In an exemplary embodiment, the central rocker arm 523 has a limiting insertion hole 5231; the drive unit 52 may also include a locking pin 527, which passes through the fixed support 521 and is threadedly connected to the fixed support 521; wherein, when the locking structure 5 locks the rotational degree of freedom of the second connector 4, the limiting insertion hole 5231 is located on the axial direction of the locking pin 527, and the end of the locking pin 527 passes through the limiting insertion hole 5231 to lock the rotational degree of freedom of the rocker arm shaft 522.
[0071] Specifically, when the locking structure 5 locks the rotational degree of freedom of the second connector 4, that is, when the outer wing structure simulation part 2 is in the deployed state, the pin 51 is inserted into the first limiting hole 31 and the first mating hole 41 to lock the rotational degree of freedom of the second connector 4; at the same time, by rotating the locking pin 527, the locking pin 527 is inserted into the limiting insertion hole 5231, which locks the rotational degree of freedom of the central rocker arm 523, and further locks the rotational degree of freedom of the rocker arm shaft 522. In this way, the position of the pin 51 can be locked, effectively preventing the pin 51 from being pulled out of the first limiting hole 31 and the first mating hole 41 due to shaking or other factors.
[0072] It should be noted that when the outer wing structure simulation part 2 needs to be folded, the locking pin 527 needs to be rotated first to separate the locking pin 527 from the central rocker arm 523, and then the rocker arm shaft 522 needs to be rotated to drive the pin 51 to pull out the first limiting hole 31 and the first mating hole 41. After that, the outer wing structure simulation part 2 can be rotated to fold.
[0073] It should be understood that if the rocker arm pivot 522 is connected to the center part of the central rocker arm 523, then the limiting socket 5231 is an eccentric hole on the central rocker arm 523.
[0074] In addition, such as Figure 4 As shown, the limiting part 525 can be an irregular structure, so that the locking pin 527 can pass through both the limiting part 525 and the fixed support 521. The locking pin 527 is threadedly connected to both the limiting part 525 and the fixed support 521, making it more convenient to rotate the locking pin 527 without interference from the limiting part 525.
[0075] In addition, such as Figure 4 As shown, both the rocker arm shaft 522 and the locking pin 527 have hexagonal heads at their bottom, so that a corresponding socket or wrench can be used to fit onto the hexagonal heads to rotate the rocker arm shaft 522 and the locking pin 527.
[0076] Of course, the limiting part 525 and the fixed support 521 can be an integral structure, so as to make the threaded hole for the locking pin 527 to be connected in one go.
[0077] refer to Figure 6 and Figure 7 In an exemplary embodiment, the folding mechanism may further include a spring pin, and the first connector 3 is also provided with a second limiting hole 32 with the same axial direction as the second direction, and the second connector 4 is also provided with a second mating hole 42; wherein, when the outer section wing structure simulation part 2 is folded, the second limiting hole 32 and the second mating hole 42 are coaxial, and the spring pin is inserted into the second limiting hole 32 and the second mating hole 42.
[0078] Specifically, when the outer wing structure simulation part 2 is folded, a spring pin (not shown) can be inserted into the second limiting hole 32 and the second mating hole 42 to lock the rotational degree of freedom of the second joint 4, and further lock the rotational degree of freedom of the outer wing structure simulation part 2, so that the outer wing structure simulation part 2 can maintain the folded state.
[0079] The spring pins should correspond one-to-one with the folding parts so that the spring pins can be inserted into the second limiting hole 32 and the second mating hole 42 of the corresponding folding parts.
[0080] Of course, the rotatable angle of the outer wing structure simulator 2 from the unfolded state to the folded state can be changed by changing the position of the second limiting hole 32 on the first ear and the position of the second mating hole 42 on the second ear.
[0081] Furthermore, such as Figure 6 As shown, in this embodiment, the outer wing structure simulator 2 can rotate from the unfolded state to the folded state by an angle of 133°. At this time, the second lug on the second connector 4 abuts against the main body of the first connector 3, allowing the outer wing structure simulator 2 to reach its maximum rotation angle. At this time, the center of gravity of the outer wing structure simulator 2 and the second connector 4 as a whole is located on the side of the pivot at the rotatable connection between the first lug and the second lug, closer to the inner wing structure simulator 1. Therefore, even without inserting the spring pin, the outer wing structure simulator 2 can maintain its folded state.
[0082] It should be noted that there are three ways to keep the outer wing structure simulation component 2 in a folded state. The first is that the second lug abuts against the main body of the first connector 3, and the rotation angle needs to be such that the outer wing structure simulation component 2 will not rotate due to its own weight. The second is that the second limiting hole 32 and the second mating hole 42 are coaxial and a spring pin is inserted. The third is as shown in the embodiment of this application, where the second limiting hole 32 and the second mating hole 42 are coaxial and a spring pin is inserted. At the same time, the rotation angle is larger, and the second lug abuts against the main body of the first connector 3. This makes the outer wing structure simulation component 2 more stable when it is in a folded state.
[0083] Furthermore, self-lubricating bushings can be installed in the second limiting hole 32 and the second mating hole 42 to reduce the friction between the spring pin and the first connector 3 and the second connector 4.
[0084] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.
Claims
1. A folding mechanism, characterized in that, The folding mechanism, connecting the inner wing structure simulator (1) and the outer wing structure simulator (2) which are arranged opposite to each other in a first direction, includes: The first connector (3) is located on the side of the inner wing structure simulation component (1) facing the outer wing structure simulation component (2); The second connector (4) is located on the side of the outer wing structure simulation piece (2) facing the inner wing structure simulation piece (1) and is rotatably connected to the first connector (3). The second connector (4) has a degree of freedom to rotate about a second direction to fold the outer wing structure simulation piece (2). A locking structure (5) is disposed between the inner wing structure simulation component (1) and the outer wing structure simulation component (2) and connected to the inner wing structure simulation component (1) or the outer wing structure simulation component (2). The locking structure (5) cooperates with the first connector (3) and the second connector (4) to lock or release the rotational degree of freedom of the second connector (4).
2. The folding mechanism as described in claim 1, characterized in that, The first connector (3) is provided with a first limiting hole (31) axially aligned with the second direction, and the second connector (4) is provided with a first mating hole (41) coaxial with the first limiting hole (31); the locking structure (5) includes: The pin (51) is inserted into the first limiting hole (31) and the first mating hole (41) and has the freedom to move along the second direction; The drive unit (52) is connected to the inner wing structure simulation component (1) or the outer wing structure simulation component (2), and the drive unit (52) is connected to the pin (51) and provides the pin (51) with a moving driving force.
3. The folding mechanism as described in claim 2, characterized in that, Both the first connector (3) and the second connector (4) have a main body connected to the corresponding simulation part and an ear piece connected to the corresponding main body part. The ear piece on the first connector (3) is the first ear piece, and the ear piece on the second connector (4) is the second ear piece. The second ear piece and the first ear piece are rotatably connected by a rotating shaft. The axial direction of the rotating shaft is the same as the second direction. The first limiting hole (31) is provided on the first ear piece, and the first mating hole (41) is provided on the second ear piece.
4. The folding mechanism as described in claim 3, characterized in that, When the drive unit (52) is connected to the inner section wing structure simulation part (1), the drive unit (52) is located on the side of the first ear piece away from the second ear piece; When the drive unit (52) is connected to the outer section wing structure simulation part (2), the drive unit (52) is located on the side of the second ear piece away from the first ear piece; Among them, a sliding sleeve (6) coaxial with the first limiting hole (31) is provided on the corresponding ear piece near the driving part (52), and the pin (51) is inserted into the sliding sleeve (6) to slide in the second direction.
5. The folding mechanism as described in claim 3, characterized in that, The drive unit (52) is connected to the inner section wing structure simulation component (1), and the first connector (3) has two first lugs opposite each other in the second direction, with the second lug located between the two first lugs.
6. The folding mechanism as described in claim 3, characterized in that, The first connector (3), the second connector (4), and the pin (51) constitute a folding part, and there are two folding parts arranged opposite to each other in the second direction; The drive unit (52) is located between the two folded parts and connected to the two pins (51). The drive unit (52) provides the moving drive force to the two pins (51) to synchronously lock or release the rotational degrees of freedom of the two second joints (4).
7. The folding mechanism as described in claim 2, characterized in that, The drive unit (52) includes: A fixed support (521) is connected to the inner section wing structure simulation component (1) or the outer section wing structure simulation component (2); The rocker arm pivot (522) passes through the fixed support (521) and is rotatably connected to the fixed support (521). The rocker arm pivot (522) has a degree of freedom to rotate about its own axis and the axis is the same as the third direction. A central rocker arm (523) is fixed at its center to the end of the rocker arm pivot (522); A connecting rocker arm (524) is connected to the pin (51) with one end rotatably connected to the corresponding pin (51) and the other end rotatably connected to the end of the central rocker arm (523). The connecting rocker arm (524) has a degree of freedom to rotate about the third direction.
8. The folding mechanism as described in claim 7, characterized in that, The drive unit (52) further includes: The limiting part (525) is connected to the fixed support (521) and sleeved on the outer periphery of the rocker arm shaft (522). The limiting part (525) has an arc-shaped notch in the axial direction. The limiting pin (526) is fixed to the outer periphery of the rocker arm pivot (522) and passes through the arc-shaped notch; When the locking structure (5) locks the rotational degree of freedom of the second connector (4), the limiting pin (526) abuts against the first end of the arc-shaped notch; When the locking structure (5) releases the rotational degree of freedom of the second connector (4), the limiting pin (526) abuts against the second end of the arc-shaped notch.
9. The folding mechanism as described in claim 8, characterized in that, The central rocker arm (523) has a limiting socket (5231); the drive unit (52) further includes: A locking pin (527) passes through the fixed support (521) and is threadedly connected to the fixed support (521); When the locking structure (5) locks the rotational degree of freedom of the second connector (4), the limiting hole (5231) is located on the axial direction of the locking pin (527), and the end of the locking pin (527) is inserted into the limiting hole (5231) to lock the rotational degree of freedom of the rocker arm shaft (522).
10. The folding mechanism as described in claim 2, characterized in that, The folding mechanism also includes a spring pin, and the first connector (3) is also provided with a second limiting hole (32) with the same axial direction as the second direction, and the second connector (4) is also provided with a second mating hole (42). When the outer wing structure simulation part (2) is folded, the second limiting hole (32) and the second mating hole (42) are coaxial, and the spring pin is inserted into the second limiting hole (32) and the second mating hole (42).