Self-locking buckle, folding wing and cylindrical folding wing unmanned aerial vehicle
By adopting self-locking snaps, thin plate extended trailing edges and semi-buried hinges on the cylinder folding wing drone, the problem of limited chord length during storage is solved, achieving higher load-bearing capacity and flight performance, while simplifying the folding mechanism and reducing weight and cost.
Patent Information
- Application Number
- CN202411913653.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-24
- Publication Date
- 2025-03-25
AI Technical Summary
The existing cylinder folding wing drones face problems such as limited chord length, poor aerodynamic characteristics, and low load-bearing capacity when stored. The common trailing edge folding method has poor storage effect and low complexity and reliability of the folding mechanism.
The folding wing design adopts a self-locking snap, a thin plate extended trailing edge and a semi-buried hinge. The trailing edge is expanded by a spring torque, and locking is achieved using a self-locking snap, simplifying the folding mechanism and saving storage space.
It effectively increases the chord length and main wing volume, improves the load-bearing capacity and cruising aerodynamic efficiency of the drone, significantly enhances flight performance, and reduces weight and cost.
Smart Images
Figure CN119683041A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a self-locking buckle, folding wing, and barrel-type folding wing unmanned aerial vehicle. Background Art
[0002] The cylinder-type folding-wing UAV has wings that can be folded and unfolded. In the folded state, it can be stored in a storage tube for easy transportation and can be used for single-person missions. At present, cylinder-type folding-wing UAVs are usually folded in the span direction, and they are bound to face the problem that the chord-wise size of the wing is limited by the storage tube: on the one hand, the wing chord length is small and the Reynolds number is limited, resulting in poor aerodynamic characteristics of the UAV and reduced aerodynamic efficiency; on the other hand, the main wing area is limited and the lifting space is limited, resulting in limited carrying capacity of the UAV. Although some folding-wing UAVs choose to fold the trailing edge to obtain a larger wing size when stored, they still face the following problems: First, after the wings are folded, more space will be consumed in the height direction, and the storage effect is poor; second, the wings of this type of aircraft usually use an active folding mechanism, which has a complex folding mechanism, low reliability, and will bring additional weight, see Fig. 9 In summary, whether it is folding only in the span direction or using the common trailing edge folding method, it is not conducive to improving the comprehensive performance of the UAV. Therefore, seeking a trailing edge folding mechanism with small storage space, simple folding mechanism, and effective improvement of the aerodynamic characteristics of the wing has become a key and difficult content in the current design of barrel-type folding wing UAVs. Summary of the invention
[0003] The purpose of the present invention is to provide a self-locking buckle, folding wing, barrel-type folding wing drone. The present invention has the characteristics of small storage space, simple folding mechanism, and can effectively improve the aerodynamic characteristics of the wing.
[0004] The technical solution of the present invention is: a self-locking buckle, comprising an elastic hook and a landslide, wherein a groove is provided on the bottom surface of the elastic hook, the depth of the groove increases along the length direction of the elastic hook, the head end of the bottom surface of the groove is connected to the bottom surface of the elastic hook, and the tail end of the bottom surface of the groove is connected to the bottom surface of the elastic hook via a vertical surface A; the landslide is in the form of a right-angled triangle block as a whole, the top surface of the landslide is the inclined surface of the right-angled triangle block, the tail end is the vertical surface B of the right-angled triangle block, and the bottom surface is the flat surface of the right-angled triangle block; when the self-locking buckle is buckled, the bottom surface of the groove is matched with the top surface of the landslide, and the vertical surface A is matched with the vertical surface B.
[0005] In the aforementioned self-locking buckle, the top surface of the elastic hook is streamlined.
[0006] A folding wing equipped with the aforementioned self-locking buckle comprises a main wing, wherein the bottom surface of the tail end of the main wing is connected to the extended trailing edge via a semi-buried hinge; the elastic hook of the self-locking buckle is installed on the top surface of the tail end of the main wing, and the slide is installed on the top surface of the head end of the extended trailing edge via a flat surface; the head end of the bottom surface of the slot is aligned with the end surface of the tail end of the main wing, and the head end of the slide is aligned with the end surface of the head end of the extended trailing edge.
[0007] In the aforementioned folding wing, the ratio of the extended trailing edge width to the airfoil chord length is 30%±10%.
[0008] In the aforementioned folding wing, in the unfolded state, the end surface of the main wing tail end coincides with the end surface of the extended trailing edge head end, and the main wing tail end profile and the extended trailing edge head end profile transition smoothly.
[0009] In the aforementioned folding wing, the semi-embedded hinge is a sheet hinge, including a hinge piece A, a hinge piece B, a rotating shaft and a torsion spring; wherein the hinge piece A and the hinge piece B can realize 180° rotation around the rotating shaft, and the elasticity of the torsion spring can make the two hinge pieces be in an unfolded state in a free state; the hinge piece A is semi-embedded in the bottom surface of the tail end of the main wing, and the hinge piece B is semi-embedded in the bottom surface of the head end of the extended trailing edge.
[0010] In the aforementioned folding wing, the main wing and the extended trailing edge are connected via more than one semi-buried hinge.
[0011] In the aforementioned folding wing, the main wing and the extended trailing edge are locked together via more than one self-locking buckle.
[0012] A barrel-type folding-wing UAV is equipped with the aforementioned folding wings.
[0013] The advantages of the present invention are: the trailing edge of the airfoil is extended in the form of a thin plate, the deployment is completed by using a spring torque, and the locking is achieved by a self-locking buckle, which effectively saves storage space on the one hand, simplifies the folding mechanism on the other hand, and effectively increases the chord length and main wing area of the wing. Specifically, it has the following beneficial effects:
[0014] 1. Compared with the folding-wing UAV without trailing edge folding, the trailing edge extended folding locking mechanism can increase the wing chord length of the folding-wing UAV by more than 30%, thereby increasing the main wing area and cruise Reynolds number of the folding-wing UAV by more than 30%, and then increase the carrying capacity of the folding-wing UAV by more than 20%, and improve the cruise lift-to-drag ratio by more than 10%, and the flight performance is significantly enhanced.
[0015] Taking a barrel-type folding-wing UAV with a cruising speed of 15m / s, a cruising lift coefficient of 0.86, a wingspan of 2m, and a barrel size of 0.25m as an example, due to the barrel size limitation, when there is no folding trailing edge, the maximum chord length of the aircraft wing does not exceed 0.25m. After adopting the trailing edge folding solution, the chord length of the aircraft wing can be increased to more than 0.325m, and the main wing area of the aircraft can be increased from 0.5m2 Increased to 0.65m 2 , the cruise Reynolds number of the aircraft airfoil can be increased from 250,000 to 330,000, and the aircraft cruise lift-to-drag ratio is improved by 20%. Therefore, the aircraft takeoff weight can be increased from 6.04kg to 7.86kg, but the required thrust only needs to be increased from 0.357kg to 0.393kg, see Figure 8 .
[0016] 2. The extended trailing edge is in the shape of a thin plate, which smoothly transitions to the tail of the airfoil. After folding, it can effectively reduce the storage space in the height direction.
[0017] 3. The extended trailing edge is connected to the main wing through a semi-buried hinge, and the trailing edge is unfolded by the elastic force provided by the hinge torsion spring. It is simple and reliable, and the semi-buried design can reduce resistance during the flight phase.
[0018] 4. After the trailing edge is unfolded, it can be further folded upward with the help of aerodynamic force until the main wing contacts the separation surface of the extended trailing edge (the end surface of the main wing tail and the head end surface of the extended trailing edge), eliminating the need for a complex folding device.
[0019] 5. A self-locking buckle structure is set above the main wing and the extended trailing edge, which can achieve self-locking when the separation surfaces of the two are in contact. The structure is simple and reliable. When unlocking, you only need to pry the hook by hand, which is easy to operate.
[0020] 6. The starting positions of the self-locking buckles are chamfered, and the overall shape is streamlined, which can effectively reduce the wing resistance during flight.
[0021] 7. Compared with the conventional trailing edge folding mechanism, the overall weight of the simple trailing edge extended folding locking mechanism consisting of a thin plate trailing edge, a hinge with a torsion spring, and a self-locking buckle structure can be reduced by more than 60%, and the cost can be reduced by more than 80%. It has the significant advantages of light weight, high reliability, and low cost, and its practicality is greatly improved. BRIEF DESCRIPTION OF THE DRAWINGS
[0022] Figure 1 It is a schematic diagram of the self-locking buckle locking method;
[0023] Figure 2 This is a schematic diagram of the unlocking method of the self-locking buckle;
[0024] Figure 3 Schematic diagram of the folding wing structure.
[0025] Figure 4 It is a schematic diagram of the connection structure of the self-locking buckle on the folding wing;
[0026] Figure 5 It is a schematic diagram of the connection structure of the semi-embedded hinge on the folding wing;
[0027] Figure 6This is a schematic diagram of a semi-embedded hinge;
[0028] Figure 7 It is a schematic diagram of the unfolding process on the folded wing;
[0029] Figure 8 This is the influence curve of Reynolds number on the lift-to-drag ratio of folding-wing UAV;
[0030] Fig. 9 Schematic diagram of Boeing's conventional trailing edge folding mechanism.
[0031] Among them: 1-main wing, 101-tail end face of the main wing, 2-extended trailing edge, 201-head end face of the extended trailing edge, 3-semi-embedded hinge, 301-hinge plate, 302-hinge plate, 303-rotating shaft, 304-torsion spring, 4-self-locking buckle, 401-hook, 402-slide, 403-slot, 404-vertical surface A, 405-vertical surface B, 406-flat surface. DETAILED DESCRIPTION
[0032] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.
[0033] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is by no means limited to any specific settings and methods proposed below, but covers any improvements, replacements and modifications of structures, methods, devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, known structures and technologies are not shown to avoid unnecessary ambiguity in the present invention.
[0034] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.
[0035] Example 1. A self-locking buckle, see Figure 1-Figure 7, including an elastic hook 401 and a landslide 402. The bottom surface of the elastic hook 401 is provided with a slot 403, the depth of the slot 403 increases along the length direction of the elastic hook 401, the head end of the bottom surface of the slot 403 is connected to the bottom surface of the elastic hook 401, and the tail end of the bottom surface of the slot 403 is connected to the bottom surface of the elastic hook 401 through a vertical surface A404; the landslide 402 is a right-angled triangle block as a whole, the top surface of the landslide 402 is the inclined surface of the right-angled triangle block, the tail end is the vertical surface B405 of the right-angled triangle block, and the bottom surface is the flat surface 406 of the right-angled triangle block; when the self-locking buckle is buckled, the bottom surface of the slot 403 is aligned with the top surface of the landslide 402, and the vertical surface A404 is aligned with the vertical surface B405.
[0036] The top surface of the elastic hook 401 is streamlined, so that in the cruising state, the airflow on the hook will not be obviously separated, effectively reducing the flight resistance.
[0037] A folding wing equipped with the aforementioned self-locking buckle comprises a main wing 1, wherein the bottom surface of the tail end of the main wing 1 is connected to the extended trailing edge 2 via a semi-buried hinge 3; an elastic hook 401 of the self-locking buckle 4 is installed on the top surface of the tail end of the main wing 1, and a slide 402 is installed on the top surface of the head end of the extended trailing edge 2 via a flat surface 406; the head end of the bottom surface of the slot 403 is aligned with the end surface 101 of the tail end of the main wing, and the head end of the slide 402 is aligned with the end surface 201 of the head end of the extended trailing edge.
[0038] The ratio of the width of the aforementioned extended trailing edge 2 to the chord length of the airfoil is 30%±10%.
[0039] In the unfolded state, the tail end surface 101 of the main wing is aligned with the head end surface 201 of the extended trailing edge, and the tail end profile of the main wing 1 and the head end profile of the extended trailing edge 2 are smoothly transitioned.
[0040] The aforementioned semi-embedded hinge 3 is a sheet hinge, including a hinge piece A301, a hinge piece B302, a rotating shaft 303 and a torsion spring 304; wherein the hinge piece A301 and the hinge piece B302 can realize 180° rotation around the rotating shaft 303, and the elasticity of the torsion spring 304 can make the two hinge pieces unfolded in a free state; the hinge piece A301 is semi-embedded in the bottom surface of the tail end of the main wing 1, and the hinge piece B302 is semi-embedded in the bottom surface of the head end of the extended trailing edge 2. Thereby reducing the windward area and reducing the flight resistance.
[0041] The aforementioned main wing 1 and the extended trailing edge 2 are connected via one or more semi-embedded hinges 3 .
[0042] The main wing 1 and the extended trailing edge 2 are locked together via one or more self-locking buckles 4 .
[0043] A barrel-type folding-wing UAV is equipped with the aforementioned folding wings.
[0044] When the extended trailing edge 2 is unfolded, the elastic force provided by the torsion spring 304 built into the semi-embedded hinge 3 is first released, and then the folding is achieved with the help of the upward aerodynamic force on the rudder surface. When the tail end face 101 of the main wing and the head end face 201 of the extended trailing edge are in contact with each other, the inclined surface of the landslide 402 moves along the bottom surface of the slot 403. When they are in contact, the inclined surface of the landslide 402 is in contact with the bottom surface of the slot 403, and at the same time, the vertical surface A404 and the vertical surface B405 are in contact, so that the entire landslide 402 is wedged into the slot 403 to achieve self-locking. When the extended trailing edge 2 is folded, the elastic hook 401 is first opened upwards, and after the landslide 402 exits the slot 403 and is unlocked, the extended trailing edge 2 is folded downward by about 180°, and the cylindrical folding-wing UAV is stored in the storage cylinder.
[0045] Different from the traditional barrel-type folding wing UAV without folding trailing edge, on the one hand, the folding trailing edge can effectively reduce the storage space of the UAV in the height direction when folded, thereby significantly reducing the size of the launch tube or storage tube; on the other hand, the folding trailing edge can effectively increase the main wing area and chord length of the folding wing UAV when unfolded, and improve the flight Reynolds number of the UAV, thereby effectively improving the effective carrying capacity and cruising aerodynamic efficiency of the barrel-type folding wing UAV, so that it has stronger flight performance. After the UAV leaves the launch tube or storage tube, the extended trailing edge is jointly driven by the torsion spring and aerodynamic force to unfold, and is locked by the self-locking buckle, with a simple structure and high reliability; when the wing is folded, it can be quickly unlocked and stored by bending the hook, which is easy to operate; the hinge with torsion spring is a semi-embedded design, and the self-locking buckle is a streamlined design, which can effectively reduce the resistance during the flight stage, and is integrated with the main wing and the extended trailing edge, with low processing difficulty.
[0046] Example 2. Figure 3-5 As shown, a folding wing for a barrel-type folding-wing UAV includes a main wing 1, an extended trailing edge 2, a semi-embedded hinge 3, and a self-locking buckle 4.
[0047] like Figure 6 As shown, the semi-embedded hinge 3 is a sheet hinge, which is composed of a hinge sheet A301, a hinge sheet B302, a rotating shaft 303, and a torsion spring 304, wherein the hinge sheet A301 and the hinge sheet B302 can realize 180° rotation around the rotating shaft 303, and the elasticity of the torsion spring 304 can make the two hinge sheets unfolded in a free state. The semi-embedded hinge 3 is distributed along the span direction on the lower surface of the main wing 1, wherein half of the hinge sheet A301 is buried in the skin surface of the main wing 1 along the thickness direction, and half of the hinge sheet B302 is buried in the extended trailing edge 2 along the thickness direction, thereby reducing the windward area and reducing the flight resistance.
[0048] like Figure 1 , 2As shown, the self-locking buckle 4 is composed of an elastic hook 401 and a slide 402, and the material is carbon fiber composite material or aluminum alloy. The elastic hook 401 is integrally formed with the outer skin of the main wing 1, and the slide 402 is integrally formed with the extended trailing edge 2. The integrally formed areas are chamfered to reduce flight resistance. When the extended trailing edge is in the unfolded state, the elastic hook and the slide can fit completely without a gap, and can effectively prevent the extended trailing edge from being separated from the main wing.
[0049] A folding wing for a barrel-type folding-wing UAV, the specific working principle of which is:
[0050] When the UAV is in the launch tube, the extended trailing edge 2 is folded and hidden under the main wing 1. Since the extended trailing edge 2 itself is relatively thin, the storage volume can be effectively reduced; the semi-buried hinge 3 is in a compressed state, relying on the outer wall of the launch tube to resist the elastic force of the torsion spring 304;
[0051] 2 After the drone is out of the tube, under the elastic force of the torsion spring 304, the hinge piece A301 and the hinge piece B302 unfold, driving the extended trailing edge 2 to unfold backward around the rotation axis 304. The unfolding process is shown in FIG. Figure 7 ;
[0052] After the extended trailing edge 2 rotates about the rotation axis 304 by about 180°, the elastic hook 401 contacts and slides with the slide 402. When the extended trailing edge 2 is completely in close contact with the main wing 1, the hook-shaped structure of the elastic hook 401 is just stuck on the rear wall surface of the slide 402, and the self-locking buckle 4 is in a locked state. In the flight state, the relative positions of the extended trailing edge 2 and the main wing 1 are relatively locked and will not be disengaged.
[0053] 4 In the flight state, the semi-buried hinge 3 has a smaller windward area, and the self-locking buckle 4 is streamlined, which can effectively reduce the flight resistance;
[0054] After the flight is completed, when the wings are stored, the elastic hook 401 is lifted upward by hand, and the hook-shaped structure is separated from the rear wall of the slide 402, and the self-locking buckle 4 is unlocked. Then, the extended trailing edge 2 is pressed downward to rotate 180 degrees around the rotation axis 304, folded and hidden under the main wing 1, and the aircraft is stored in the launch tube. Then, let go and use the wall of the launch tube to restrain the trailing edge from unfolding.
[0055] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the field can easily think of various equivalent modifications or substitutions within the technical scope disclosed by the present invention, and these modifications or substitutions should all be covered within the protection scope of the present invention.
Claims
1. A self-locking buckle, characterized in that: The invention comprises an elastic hook (401) and a slide (402). The bottom surface of the elastic hook (401) is provided with a slot (403). The depth of the slot (403) increases along the length direction of the elastic hook (401). The head end of the bottom surface of the slot (403) is connected to the bottom surface of the elastic hook (401). The tail end of the bottom surface of the slot (403) is connected to the bottom surface of the elastic hook (401) via a vertical surface A (404). The slide (402) is a right-angled triangle block as a whole. The top surface of the slide (402) is the inclined surface of the right-angled triangle block, the tail end is the vertical surface B (405) of the right-angled triangle block, and the bottom surface is the flat surface (406) of the right-angled triangle block. When the self-locking buckle is buckled, the bottom surface of the slot (403) is matched with the top surface of the slide (402), and the vertical surface A (404) is matched with the vertical surface B (405).
2. The self-locking buckle according to claim 1, characterized in that: The top surface of the elastic hook (401) is streamlined.
3. A folding wing equipped with the self-locking buckle according to claim 1 or 2, characterized in that: The invention comprises a main wing (1), wherein the bottom surface of the tail end of the main wing (1) is connected to the extended trailing edge (2) via a semi-buried hinge (3); the elastic hook (401) of the self-locking buckle (4) is installed on the top surface of the tail end of the main wing (1), and the slide (402) is installed on the top surface of the head end of the extended trailing edge (2) via a straight surface (406); the head end of the bottom surface of the slot (403) is aligned with the end surface (101) of the tail end of the main wing, and the head end of the slide (402) is aligned with the end surface (201) of the head end of the extended trailing edge.
4. The folding wing according to claim 3, characterized in that: The ratio of the width of the extended trailing edge (2) to the chord length of the airfoil is 30%±10%.
5. The folding wing according to claim 3, characterized in that: In the unfolded state, the end surface (101) of the tail end of the main wing is aligned with the end surface (201) of the head end of the extended trailing edge, and the tail end profile of the main wing (1) and the head end profile of the extended trailing edge (2) are smoothly transitioned.
6. The folding wing according to claim 3, characterized in that: The semi-embedded hinge (3) is a sheet hinge, comprising a hinge sheet A (301), a hinge sheet B (302), a rotating shaft (303) and a torsion spring (304); wherein the hinge sheet A (301) and the hinge sheet B (302) can realize 180° rotation around the rotating shaft (303), and the elasticity of the torsion spring (304) can make the two hinge sheets be in an unfolded state in a free state; the hinge sheet A (301) is semi-embedded in the bottom surface of the tail end of the main wing (1), and the hinge sheet B (302) is semi-embedded in the bottom surface of the head end of the extended trailing edge (2).
7. The folding wing according to claim 3, characterized in that: The main wing (1) and the extended trailing edge (2) are connected via one or more semi-buried hinges (3).
8. The folding wing according to claim 3, characterized in that: The main wing (1) and the extended trailing edge (2) are locked together via one or more self-locking buckles (4).
9. A cylindrical folding-wing UAV, characterized in that: The folding wing according to any one of claims 3 to 8 is installed.