Model airplane folding wing with high strength

Abstract

The utility model relates to the technical field of folding wings, and discloses a model airplane folding wing with high strength, which comprises a folding frame and a locking mechanism, a rotating shaft is rotatably connected onto an upper frame plate and a lower frame plate of the folding frame, the rotating shaft is driven to rotate by a servo motor matched with a gear, and a connector connected onto the rotating shaft is connected with a wing. The rotating joints at the ends of the wings are driven to rotate through the motors and the gears arranged in the connectors, and the wings in the horizontal state are rotated to be in the vertical state; the locking mechanism locks the wings on the folding frame after the wings are folded, the locking mechanism comprises a horizontal pushing cylinder and a U-shaped clamping head, and the U-shaped clamping head is pushed by the horizontal pushing cylinder to move so as to be clamped on the outer side face of a clamping rod connected between the upper frame plate and the lower frame plate. Due to the design of the folding wings, the safety and the control performance of flight are improved, the model airplane is more convenient to transport and store, the size is reduced, the cost is reduced, and the use flexibility is enhanced.

Description

Technical Field

[0001] The utility model belongs to the technical field of folding wings, and in particular relates to a high-strength folding wing for an airplane model. Background Art

[0002] In the field of aviation models, the design and application of folding wings are increasingly valued because they can significantly reduce the size and weight of aircraft models without sacrificing flight performance, making them easier to carry and transport.

[0003] Many folding wings currently on the market use ordinary materials, such as aluminum alloy or other plastic materials. The strength and durability of these materials are relatively low, and they are easily deformed or damaged by external forces during flight. The folding and unfolding mechanisms of some folding wings rely on manual operation, or use simple mechanical devices. These devices are insufficient in operational complexity and reliability, and are prone to failure during the folding or unfolding process. The locking mechanism of some folding wings is simply designed and lacks effective limiting and guiding mechanisms, which may cause the wings to shift during flight, affecting flight stability. In terms of design, the component layout of some folding wings may not be reasonable, resulting in interference between mechanical components during the folding or unfolding process, affecting the smooth operation of the mechanism.

[0004] Due to the above defects, the existing folding wings are insufficient in terms of flight safety, and are prone to flight accidents due to wing deformation or accidental deployment. In view of this, we propose a high-strength folding wing for a model aircraft. Utility Model Content

[0005] The present invention addresses the technical issues mentioned above: the prior art folding wings rarely utilize high-strength materials such as carbon fiber or alloys, resulting in insufficient structural strength and durability. This lack of efficient power drive and precise guidance mechanisms leads to poor stability in folding and unfolding the wings, complex operation, and low reliability.

[0006] To achieve the above objectives, the present invention provides the following technical solutions:

[0007] A high-strength model airplane folding wing comprises a folding frame and a locking mechanism. The folding frame comprises an upper frame plate and a lower frame plate. A rotating shaft is rotatably connected at the center position of the left end of the upper frame plate and the lower frame plate. The rotating shaft is fixedly sleeved with a servo motor and gears located between the upper frame plate and the lower frame plate. The rotating shaft is fixedly connected to a connector, which is connected to the wing. The motor and gears provided in the connector drive the rotating joint at the end of the wing to rotate, thereby rotating the wing from a horizontal state to a vertical state.

[0008] The locking mechanism locks the wings on the folding frame after the wings are folded. The locking mechanism includes a push cylinder and a U-shaped clamp. The push cylinder pushes the U-shaped clamp to move and then clamps the U-shaped clamp on the outer side of the clamp rod connecting the upper frame plate and the lower frame plate.

[0009] The high-strength model airplane folding wing has the following steps: first, when folding the wing, the motor and gear drive the rotating joint at the end of the wing to rotate, so that the wing in a horizontal state is rotated to a vertical state; then, the servo motor cooperates with the gear to drive the rotation, and then the connector extended on the front side of the folding frame is driven to rotate to the left side of the folding frame, thus completing the folding of the wing; finally, after the wing is folded, the push cylinder on the locking mechanism pushes the U-shaped clamping head to move, clamps the U-shaped clamping head on the outer side of the clamping rod, and then locks the folded wing and the connector on the folding frame; the folding function makes the model airplane more convenient to transport and store, reduces the volume, and is easy to carry.

[0010] Preferably, the upper frame plate and the lower frame plate are further connected by a plurality of vertical poles.

[0011] Preferably, a protrusion protruding outward is provided at a corner of the front end of the upper frame plate and the lower frame plate. When the connecting head and the wing are unfolded, the locking rod connected to the end of the vertical cylinder piston rod is pushed by the vertical cylinder installed on the protrusion, and the locking rod is inserted into the positioning hole provided in the connecting head, and then used to lock the wing after the wing is unfolded.

[0012] The use of raised sections and vertical cylinders allows the wings to be locked after deployment by inserting locking rods into positioning holes. This design improves wing stability during flight and prevents wing displacement due to vibration and other factors. When the wings are deployed, the upper and lower raised sections hold the connector in place, ensuring greater stability and strength after deployment, allowing the wings to withstand greater loads.

[0013] Preferably, the end of the connector away from the wing is provided with two connecting plates symmetrically arranged in an upper and lower direction, and the connecting plates are fixedly sleeved on the outer side surface of the rotating shaft.

[0014] Preferably, two connecting plates are provided above and below to cooperate with the connecting head to form a 匚-shaped groove, a support block is installed in the 匚-shaped groove, and the push cylinder is embedded in the support block.

[0015] Preferably, the U-shaped clamp is fixedly connected to the rectangular guide frame, the piston rod end of the push cylinder is fixedly connected to the front inner wall of the rectangular guide frame through a convex plate, and the outer side surface of the support block is provided with a guide frame that cooperates with the rectangular guide frame to limit and guide sliding.

[0016] The design of the support block and the guide frame ensures that the piston rod of the flat push cylinder can slide along the inner wall surface of the rectangular guide frame accurately, reduces deviation and vibration during movement, improves the guiding accuracy of the mechanism, improves the reliability of the U-shaped clamp during locking, and ensures the stable locking of the wing after folding.

[0017] Compared with the prior art, the technical effects and advantages of the model aircraft folding wing are:

[0018] The motor and gear drive rotating joint at the wing end drive the wing to rotate from a horizontal state to a vertical state. Then, the servo motor drives the rotating shaft through the gear, and the connecting head is driven to rotate to the left side of the folding frame while being stretched out, completing the folding of the wing. In this process, the vertical rod provides support for the overall structure, ensuring smooth folding. After folding, the flat push cylinder is activated to move the U-shaped clamp, which is then clamped outside the connecting rod between the upper and lower frame plates. This action is realized through the precise guidance of the guide frame and the support block, ensuring the accuracy and reliability of the locking.

[0019] When the wing needs to be unfolded, the vertical cylinder pushes the locking rod into the positioning hole of the connecting head to lock the wing. The protrusions limit the upper and lower ends of the connecting head, ensuring the stability of the wing during flight.

[0020] The high-strength material and the precise locking mechanism design ensure that the wing will not deform or be damaged due to external forces during flight, improving the safety of flight. At the same time, the stable wing helps to maintain the balance of the model aircraft, improving the control performance. By using multiple vertical rods and precise guide mechanisms, the stability of the overall structure is enhanced, dispersing various forces such as aerodynamic load and gravity during flight, reducing the possibility of mechanical interference, and ensuring smooth operation of the mechanism.

[0021] The folding function makes the model aircraft more convenient to transport and store, reducing the volume and facilitating portability. This not only improves the flexibility of the model aircraft, but also reduces the cost of transportation and storage. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 is a structural schematic diagram of the utility model;

[0023] Figure 2 is a structural schematic diagram of the utility model wing rotating from a horizontal state to a vertical state;

[0024] Figure 3 is a state diagram of the utility model wing after folding.

[0025] Figure 4 is a state diagram of the utility model connecting head in use;

[0026] Figure 5 Figure 6 is a state diagram of the connection head being folded to the left side of the folding frame according to the utility model.

[0027] In the figure: 1, folding frame; 11, upper frame plate; 12, lower frame plate; 13, rotating shaft; 14, connection head; 15, clamping rod; 16, vertical rod; 17, protruding part; 18, vertical cylinder; 19, positioning hole; 110, connecting plate; 111, U-shaped groove; 112, supporting block; 113, guide frame; 2, locking mechanism; 21, flat push cylinder; 22, U-shaped clamp; 23, rectangular guide frame; 24, protruding plate; 3, wing; 4, rotating joint. DETAILED DESCRIPTION

[0028] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the utility model.

[0029] The following will be combined with the drawings in the embodiments of the utility model Figure 1-5 The application will be further described in detail,

[0030] The embodiment of the application discloses a model folding wing with high strength, which comprises a folding frame 1 and a locking mechanism 2. The folding frame 1 is made of high-strength materials such as carbon fiber, alloy, etc., thereby increasing the strength and durability of the overall structure. The folding frame 1 comprises an upper frame plate 11 and a lower frame plate 12. The upper frame plate 11 and the lower frame plate 12 are rotationally connected with a rotating shaft 13 at the center position of the left end. The rotating shaft 13 is fixedly sleeved with a gear driven by a servo motor, and is located between the upper frame plate 11 and the lower frame plate 12. The rotating shaft 13 is fixedly connected with a connection head 14. The connection head 14 is connected with a wing 3. The wing 3 is rotated by a motor and a gear drive rotating joint 4 at the end of the wing 3, so as to rotate the wing 3 from a horizontal state to a vertical state.

[0031] The upper frame plate 11 and the lower frame plate 12 are rotationally connected through the rotating shaft 13. This structure design provides good mechanical strength and stability. The rotating connection of the rotating shaft 13 ensures the stability and reliability in the folding process. The fixing of the connection head 14 and the wing 3 is realized through the rotating joint 4 driven by the motor and the gear. This design enables the wing 3 to maintain high structural strength during folding.

[0032] The upper frame plate 11 and the lower frame plate 12 are provided with a protruding part 17 at one corner of the front end, and the connecting head 14 and the wing 3 are expanded by the vertical cylinder 18 installed on the protruding part 17 to push the locking rod connected to the piston rod end of the vertical cylinder 18, and the locking rod is inserted into the positioning hole 19 opened on the connecting head 14, and then used to lock the wing 3 after the wing 3 is expanded. The setting of the protruding part 17 and the use of the vertical cylinder 18 make the wing 3 be locked by inserting the locking rod into the positioning hole 19 after the wing 3 is expanded. This design improves the stability of the wing 3 during flight, prevents displacement of the wing 3 due to vibration and other reasons, and the upper and lower protruding parts 17 can limit the upper and lower ends of the connecting head 14 after the wing 3 is expanded, so that the stability of the expanded wing 3 is better and the strength is higher, and can bear greater load.

[0033] The locking mechanism 2 locks the wing 3 on the folding frame 1 after the wing 3 is folded, and the locking mechanism 2 includes a horizontal push cylinder 21 and a U-shaped clamp 22, and the U-shaped clamp 22 is moved by the horizontal push cylinder 21 to clamp the outer side of the clamping rod 15 connected between the upper frame plate 11 and the lower frame plate 12.

[0034] The upper and lower two connecting plates 110 cooperate with the connecting head 14 to form a U-shaped groove 111, and the U-shaped groove 111 is provided with a support block 112, and the horizontal push cylinder 21 is embedded and installed in the support block 112. The U-shaped clamp 22 is fixedly connected with a rectangular guide frame 23, the piston rod end of the horizontal push cylinder 21 is fixedly connected with the front end inner wall surface of the rectangular guide frame 23 through a protruding plate 24, and the outer side of the support block 112 is provided with a guide frame 113 for limiting and guiding sliding of the rectangular guide frame 23.

[0035] The design of the U-shaped groove 111 in combination with the connecting head 14 provides a firm support structure for the wing 3, increases the stability and strength of the overall structure. The design of the support block 112 and the guide frame 113 ensures that the piston rod of the horizontal push cylinder 21 can slide along the inner wall surface of the rectangular guide frame 23 accurately, reduces the deviation and vibration during movement, and improves the guiding accuracy of the mechanism. The fixed connection of the U-shaped clamp 22 with the rectangular guide frame 23 and the fixed connection of the piston rod end with the front end inner wall surface of the rectangular guide frame 23 simplify the design of the locking mechanism, making the locking and unlocking operation of the wing 3 more direct and efficient. The outer side of the support block 112 is provided with a guide frame 113 for limiting and guiding sliding of the rectangular guide frame 23, which improves the reliability of the U-shaped clamp 22 during locking and ensures the stable locking of the wing 3 after folding.

[0036] A protruding portion 17 is provided at a corner of the front end of the upper and lower frame plates 11, 12. When the connector 14 and wing 3 are deployed, a vertical cylinder 18 mounted on the protruding portion 17 pushes a locking rod connected to the end of the piston rod of the vertical cylinder 18, inserting the locking rod into a positioning hole 19 defined in the connector 14. This locks the wing 3 after deployment. The provision of the protruding portion 17 and the use of the vertical cylinder 18 allow the locking rod to be inserted into the positioning hole 19 to lock the wing 3 after deployment. This design improves the stability of the wing 3 during flight and prevents displacement of the wing 3 due to vibration and other factors. After deployment, the upper and lower protruding portions 17 restrain the upper and lower ends of the connector 14, ensuring greater stability and strength for the deployed wing 3, allowing it to withstand greater loads.

[0037] The upper frame plate 11 and the lower frame plate 12 are also connected by a plurality of vertical rods 16. The plurality of vertical rods 16 connecting the upper frame plate 11 and the lower frame plate 12 enhances the stability of the overall structure. The arrangement of the vertical rods 16 provides additional support points for the overall structure, helping to disperse and withstand various forces during flight, such as aerodynamic loads and gravity. The plurality of vertical rods 16 are installed within the range of space through which the connector 14 and the locking mechanism 2 rotate without affecting the rotation. In other words, the layout of the vertical rods 16 connecting the upper frame plate 11 and the lower frame plate 12 should leave sufficient clearance for the connector 14 and the locking mechanism 2 to move, reducing the possibility of mechanical interference and ensuring the smooth operation of the mechanism.

[0038] The high-strength folding wing of the aircraft model has a structure that, when folding the wing 3, first, the motor and the gear drive the rotating joint 4 at the end of the wing 3 to rotate, so that the wing 3 in the horizontal state is rotated to the vertical state. Figure 2 As shown, the servo motor cooperates with the gear to drive the rotation, thereby driving the connector 14 on the front side of the folding frame 1 to rotate to the left side of the folding frame 1, thus completing the folding of the wing 3; finally, after the wing 3 is folded, the push cylinder 21 on the locking mechanism 2 pushes the U-shaped clamp 22 to move, and the U-shaped clamp 22 is clamped on the outer side of the clamping rod 15, thereby locking the folded wing 3 and locking the connector 14 to the folding frame 1; Figure 3 As shown,

[0039] The locking mechanism 2, comprised of a push cylinder 21 and a U-shaped clamp 22, securely locks the wings 3 to the folding frame 1, preventing them from accidentally unfolding during flight or transport. This ensures that the wings 3 will not be deformed or damaged by external forces during flight, enhancing flight safety. The stability and strength of the folding wings help maintain the model aircraft's balance during flight and improve its maneuverability. The folding function also makes the model aircraft more convenient to transport and store, reducing its size and making it easier to carry.

[0040] Finally, it should be noted that: the above only for the preferred embodiments of the present application, and is not intended to limit the present application, although the foregoing embodiments of the present application has been described in detail, for the skilled in the art, it still can be modified, or for part of the technical features of the equivalent replacement, the spirit and principles of the present application, made any modification, equivalent replacement, improvement, etc., should be included within the scope of the present application.

Claims

1. A high-strength folding wing for a model airplane, characterized in that: Comprising: A folding frame (1), the folding frame (1) includes an upper frame plate (11) and a lower frame plate (12). At the center position of the left ends of the upper frame plate (11) and the lower frame plate (12), a rotating shaft (13) is rotatably connected. A connection head (14) is fixedly sleeved on the rotating shaft (13) and is located between the upper frame plate (11) and the lower frame plate (12). The rotating shaft (13) is driven to rotate by a servo motor in cooperation with gears. The rotating shaft (13) is fixedly connected to a connection head (14), and the connection head (14) is connected to the wing (3). By means of a motor and gears arranged inside the connection head (14), the rotating joint (4) at the end of the wing (3) is driven to rotate, and the wing (3) in a horizontal state is rotated into a vertical state; A locking mechanism (2), which locks the wing (3) on the folding frame (1) after the wing (3) is folded. The locking mechanism (2) includes a flat push cylinder (21) and a U-shaped chuck (22). By pushing the U-shaped chuck (22) to move through the flat push cylinder (21), the U-shaped chuck (22) is clamped on the outer side surface of a clamping rod (15) connected between the upper frame plate (11) and the lower frame plate (12).

2. The high-strength folding wing of a model aircraft according to claim 1, characterized in that: The upper frame plate (11) and the lower frame plate (12) are also connected by a plurality of vertical rods (16).

3. The high-strength folding wing of a model aircraft according to claim 1, characterized in that: At one corner of the front end of the upper frame plate (11) and the lower frame plate (12), a convex portion (17) protruding outward is provided. When the connection head (14) and the wing (3) are unfolded, a vertical cylinder (18) installed on the convex portion (17) is used to push a locking rod connected to the end of the piston rod of the vertical cylinder (18), and the locking rod is inserted into a positioning hole (19) opened on the connection head (14), so as to lock the wing (3) after the wing (3) is unfolded.

4. The high-strength folding wing of a model aircraft according to claim 1, characterized in that: At one end of the connection head (14) far from the wing (3), two connecting plates (110) arranged symmetrically up and down are provided, and the connecting plates (110) are fixedly sleeved on the outer side surface of the rotating shaft (13).

5. The high-strength folding wing of a model aircraft according to claim 4, characterized in that: The two connecting plates (110) arranged up and down cooperate with the connection head (14) to enclose a U-shaped groove (111), and a support block (112) is installed in the U-shaped groove (111). The flat push cylinder (21) is embedded and installed in the support block (112).

6. The high-strength folding wing of a model aircraft according to claim 5, characterized in that: The U-shaped chuck (22) is fixedly connected to a rectangular guide frame (23). The end of the piston rod of the flat push cylinder (21) is fixedly connected to the front inner wall surface of the rectangular guide frame (23) through a convex plate (24). A guide frame (113) for limiting and guiding the sliding of the rectangular guide frame (23) is provided on the outer side surface of the support block (112).

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