Flying wing structure and ornithopter

Abstract

The present disclosure relates to a flying wing structure and an ornithopter. The flying wing structure comprises a wing skeleton, a wing surface support, a first fixed beam, a second fixed beam and a receiving rod. One end of the first fixed beam is rotatably connected to the wing surface support, and the first fixed beam is clamped to the wing surface support when the first fixed beam is rotated to a first preset position. One end of the second fixed beam is rotatably connected to the wing surface support, and the second fixed beam is clamped to the wing surface support when the second fixed beam is rotated to a second preset position. The receiving rod is connected to the wing surface support and located between the first fixed beam and the second fixed beam. When the first fixed beam is unclamped from the wing surface support, the first fixed beam moves towards the receiving rod. When the second fixed beam is unclamped from the wing surface support, the second fixed beam moves towards the receiving rod. The wing surface is laid on the wing skeleton. The overall projection area of the folded flying wing structure is small, which is convenient for storage, packaging and carrying.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft design technology, and more specifically, to a flying wing structure and a flapping-wing aircraft. Background Technology

[0002] In the field of aircraft design technology, biomimetic flapping-wing aircraft all incorporate a flapping-wing structure. However, existing flapping-wing structures have a large overall projected area when stored, making them inconvenient to pack, store, and carry.

[0003] It should be noted that the information disclosed in the background section above is only used to enhance the understanding of the background of this disclosure, and therefore may include information that does not constitute prior art known to those skilled in the art. Utility Model Content

[0004] This disclosure provides a flying wing structure and a flapping-wing aircraft, which can reduce the overall projected area after folding, making it easier to store, pack and carry.

[0005] One aspect of this disclosure provides a flying wing structure, including:

[0006] The wing frame includes wing surface support, a first fixed beam, a second fixed beam, and a storage rod;

[0007] One end of the first fixed beam is rotatably connected to the wing support, and when the first fixed beam rotates to the first preset position, the first fixed beam is engaged with the wing support;

[0008] One end of the second fixed beam is rotatably connected to the wing support, and when the second fixed beam rotates to the second preset position, the second fixed beam engages with the wing support;

[0009] The storage rod is connected to the wing support, and the storage rod is located between the first fixed beam and the second fixed beam;

[0010] When the first fixed beam is disengaged from the wing support, the first fixed beam moves toward the storage rod.

[0011] When the second fixed beam is disengaged from the wing support, the second fixed beam moves toward the storage rod.

[0012] The wing surface is laid on the wing frame.

[0013] In some embodiments of this disclosure, the two ends of the wing support are respectively provided with a first snap-fit ​​groove and a second snap-fit ​​groove;

[0014] The first fixed beam has a first snap-fit ​​part at the end near the wing support. When the first fixed beam is rotated to the first preset position, the first snap-fit ​​part snaps into the first snap-fit ​​groove.

[0015] The second fixed beam has a second locking part at the end near the wing support. When the second fixed beam rotates to the second preset position, the second locking part engages with the second locking groove.

[0016] In some embodiments of this disclosure, a first boss is provided at the end of the first fixed beam near the wing support;

[0017] The first locking part includes a first positioning pin and a first spring. The first spring is sleeved on the outer periphery of the first fixed beam and located on the side of the first boss close to the wing support. The first positioning pin is located on the side of the first spring away from the boss and can compress the first spring. When the first fixed beam rotates to the first preset position, the first positioning pin can be locked in the first locking groove under the elastic force of the first spring.

[0018] The second fixed beam has a second protrusion at the end near the wing support; the second locking part includes a second positioning pin and a second spring, the second spring is sleeved on the outer periphery of the second fixed beam and located on the side of the second protrusion near the wing support; the second positioning pin is located on the side of the second spring away from the protrusion and can compress the second spring; when the second fixed beam rotates to the second preset position, the second positioning pin can be locked in the second locking groove under the elastic force of the second spring.

[0019] In some embodiments of this disclosure, the wing frame further includes a support rod, which is rotatably connected to the wing surface support and is located between the storage rod and the second fixed beam;

[0020] The wing surface includes a first edge line, a second edge line, and a third edge line connecting the first edge line and the second edge line;

[0021] The storage rod and the support rod are connected to the area of ​​the wing surface enclosed by the first edge line, the second edge line and the third edge line.

[0022] In some embodiments of this disclosure, the lengths of the first fixed beam, the second fixed beam, and the support rod are all less than the length of the storage rod.

[0023] In some embodiments of this disclosure, the first fixed beam, the second fixed beam, the storage rod, and the support rod are all bonded to the wing surface or connected by snap rings.

[0024] In some embodiments of this disclosure, the wing support includes a recess located between the first snap-fit ​​groove and the second snap-fit ​​groove, and the first fixing beam, the second fixing beam, and the support rod all pass through the recess.

[0025] In some embodiments of this disclosure, the recess includes a first sidewall and a second sidewall that are oppositely distributed, and the first sidewall is provided with a first mounting hole, a second mounting hole and a third mounting hole that are arranged side by side.

[0026] The second sidewall is provided with a fourth mounting hole, a fifth mounting hole and a sixth mounting hole arranged side by side;

[0027] The flying wing structure also includes a first rotating shaft, a second rotating shaft and a third rotating shaft, wherein the first rotating shaft passes through the first mounting hole, the first fixing beam and the fourth mounting hole in sequence;

[0028] The second rotating shaft passes through the second mounting hole, the support rod, and the fifth mounting hole in sequence; the third rotating shaft passes through the third mounting hole, the second fixing beam, and the sixth mounting hole in sequence.

[0029] In some embodiments of this disclosure, the number of support rods is 2 to 6, and at least some of the support rods have different lengths.

[0030] Another aspect of this disclosure provides a flapping-wing aircraft, including a fuselage and a flying wing structure, the flying wing structure being the flying wing structure described above, and the flying wing structure being detachably connected to the fuselage.

[0031] The technical solution provided in this disclosure can achieve the following beneficial effects:

[0032] The flying wing structure disclosed herein includes a wing frame and a wing surface. The wing surface is laid on the wing frame, which includes a wing surface support, a first fixed beam, a second fixed beam, and a retractable rod. One end of the first fixed beam is rotatably connected to the wing surface support, and when the first fixed beam rotates to a first preset position, it engages with the wing surface support to secure it. One end of the second fixed beam is rotatably connected to the wing surface support, and when the second fixed beam rotates to a second preset position, it engages with the wing surface support to secure it. When both the first and second fixed beams are in their preset positions and are fixed, the flying wing structure can be deployed.

[0033] When the first fixed beam and the second fixed beam are disengaged from the wing support, both beams can move towards the storage rod. Therefore, the entire wing frame can fold towards the storage rod when the first and second fixed beams are disengaged, causing the wing surface to fold synchronously towards the storage rod. This reduces the projected area of ​​the folded wing structure, facilitating its storage, packaging, and transport.

[0034] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit this disclosure. Attached Figure Description

[0035] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure. It is obvious that the drawings described below are merely some embodiments of this disclosure, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort.

[0036] Figure 1 A schematic diagram of the structure of a flying wing structure in the deployed state according to an exemplary embodiment of the present disclosure is shown;

[0037] Figure 2 A schematic diagram of the structure of a flying wing structure according to an exemplary embodiment of the present disclosure is shown when it is in an unfolded state and in a folded state;

[0038] Figure 3 A schematic diagram of a flying wing structure in a folded state according to an exemplary embodiment of the present disclosure is shown;

[0039] Figure 4 An exemplary embodiment according to this disclosure is shown. Figure 1 Schematic diagram of the exploded structure of part of the structure;

[0040] Figure 5 An exemplary embodiment according to this disclosure is shown. Figure 1 Enlarged structural diagram of part of the structure.

[0041] Explanation of reference numerals in the attached figures:

[0042] 1. Wing frame; 11. Wing surface support; 111. First snap-fit ​​groove; 112. Second snap-fit ​​groove; 113. Recess; 1131. First sidewall; 1131a. First mounting hole; 1131b. Second mounting hole; 1131c. Third mounting hole; 1132. Second sidewall; 12. First fixing beam; 121. First boss; 13. Second fixing beam; 131. Second boss; 14. Storage rod; 15. Support rod; 21. First snap-fit ​​part; 211. First positioning pin; 212. First spring; 22. Second snap-fit ​​part; 221. Second positioning pin; 222. Second spring; 31. First pivot; 32. Second pivot; 33. Third pivot; 41. First disassembly / assembly component; 42. Second disassembly / assembly component; 10. Wing surface; 101. First edge line; 102. Second edge line; 103. Third edge line. Detailed Implementation

[0043] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that the present invention will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and therefore their detailed description will be omitted.

[0044] Although relative terms such as "up" and "down" are used in this specification to describe the relative relationship of one component of an icon to another, these terms are used only for convenience, such as according to the orientation of the examples shown in the accompanying drawings. It is understood that if the device of the icon is flipped upside down, the component described as "up" will become the component described as "down." When a structure is "up" of another structure, it may mean that the structure is integrally formed on the other structure, or that the structure is "directly" mounted on the other structure, or that the structure is "indirectly" mounted on the other structure through another structure.

[0045] The terms “a,” “one,” “the,” and “the” are used to indicate the existence of one or more elements / components / etc.; the terms “including” and “having” are used to indicate an open-ended inclusion and that other elements / components / etc. may exist in addition to those listed. The terms “first,” “second,” “third,” and “fourth” are used only as markers and are not a limitation on the number of objects.

[0046] This disclosure provides a flapping-wing aircraft, which can be a biomimetic bird, but is not limited thereto. The flapping-wing aircraft may include a fuselage and a flying wing structure. The flying wing structure can be detachably connected to the fuselage. The fuselage can provide a power source for the flapping-wing aircraft, and the flying wing structure can provide a lift source for the flapping-wing aircraft. The flight direction and altitude of the flapping-wing aircraft can be controlled through the flying wing structure.

[0047] like Figures 1 to 3 As shown, the flying wing structure may include: a wing frame 1 and a wing surface 10. The wing surface 10 can be laid on the wing frame 1. For example, the wing surface 10 can be laid on the wing frame 1 by adhesive or snap-fit, but it is not limited to this. The wing surface 10 can also be laid on the wing frame 1 in other ways. This disclosure does not specifically limit the way the wing surface 10 is laid on the wing frame 1; it can be selected and set according to the actual situation, and all of this is within the protection scope of this disclosure.

[0048] like Figure 1 As shown, the wing frame 1 may include a wing surface support 11, a first fixed beam 12, and a second fixed beam 13. One end of the first fixed beam 12 is rotatably connected to the wing surface support 11, and when the first fixed beam 12 rotates to a first preset position, the first fixed beam 12 and the wing surface support 11 can be engaged, so that the wing surface support 11 can fix the first fixed beam 12, and the first fixed beam 12 can be held at the first preset position.

[0049] One end of the second fixed beam 13 can be rotatably connected to the wing support 11, and when the second fixed beam 13 is rotated to the second preset position, the second fixed beam 13 and the wing support 11 can be engaged, so that the wing support 11 can fix the second fixed beam 13, and the second fixed beam 13 can be kept at the second preset position.

[0050] In this embodiment, when the first fixed beam 12 is located at the first preset position and the second fixed beam 13 is located at the second preset position and both are fixed by the wing support 11, the deployment of the flying wing structure can be realized.

[0051] like Figure 2 and Figure 3 As shown, the wing frame 1 may further include a retractable rod 14, which can be connected to the wing support 11 and is located between the first fixed beam 12 and the second fixed beam 13. When the first fixed beam 12 is disengaged from the wing support 11, the first fixed beam 12 can move toward the retractable rod 14; when the second fixed beam 13 is disengaged from the wing support 11, the second fixed beam 13 can move toward the retractable rod 14.

[0052] Therefore, when the first fixed beam 12 and the second fixed beam 13 are disengaged, the entire wing frame 1 can fold towards the storage rod 14, thereby causing the wing surface 10 to fold towards the storage rod 14 simultaneously. In other words, the storage rod 14 can be understood as the central reference rod for folding the wing frame 1, with the entire wing frame 1 folding and storing around this storage rod 14 as its center. Consequently, this arrangement allows all the components of the wing frame 1 and the wing surface 10 to fold near the location of the storage rod 14, significantly reducing the projected area of ​​the folded wing structure and facilitating its storage, packaging, and transport.

[0053] like Figure 1 As shown, when the first fixed beam 12 is in the first preset position and the second fixed beam 13 is in the second preset position, the included angle between the first fixed beam 12 and the second fixed beam 13 can be 0 degrees or 180 degrees, that is, the first fixed beam 12 and the second fixed beam 13 are parallel or coincident. However, it is not limited to this. When the first fixed beam 12 is in the first preset position and the second fixed beam 13 is in the second preset position, the included angle between the first fixed beam 12 and the second fixed beam 13 can also be an acute angle or an obtuse angle, which can be selected and set according to the actual situation. This is all within the protection scope of this disclosure, and this disclosure does not impose specific limitations on it.

[0054] In some embodiments, such as Figure 4 As shown, the wing support 11 may be provided with a first engaging groove 111, and the end of the first fixed beam 12 near the wing support 11 is provided with a first engaging part 21. When the first fixed beam 12 rotates to the first preset position, the first engaging part 21 can engage with the first engaging groove 111. Thus, by providing the first engaging groove 111, this embodiment can limit the first fixed beam 12 when it rotates, so as to ensure that the first fixed beam 12 can move accurately and smoothly to the first preset position.

[0055] Furthermore, when the first fixed beam 12 rotates to the first preset position, the first engaging part 21 engages with the first engaging groove 111, which increases the connection area between the first fixed beam 12 and the wing support 11, thereby enhancing the stability of the first fixed beam 12 after engagement. Simultaneously, when the first engaging part 21 and the first engaging groove 111 engage, the side wall of the first engaging groove 111 can stop and limit the first engaging part 21, further improving the engagement strength between the first engaging part 21 and the first engaging groove 111, and further enhancing the stability of the first fixed beam 12 after engagement.

[0056] The wing support 11 may be provided with a second locking groove 112, and the end of the second fixed beam 13 near the wing support 11 may be provided with a second locking part 22. When the second fixed beam 13 rotates to the second preset position, the second locking part 22 can engage with the second locking groove 112. Thus, by providing the second locking groove 112, this embodiment can limit the second fixed beam 13 when it rotates, so as to ensure that the second fixed beam 13 can move accurately and smoothly to the second preset position.

[0057] Furthermore, when the second fixed beam 13 rotates to the second preset position, the second engaging portion 22 engages with the second engaging groove 112, which increases the connection area between the second fixed beam 13 and the wing support 11, thereby enhancing the stability of the second fixed beam 13 after engagement. Simultaneously, when the second engaging portion 22 engages with the second engaging groove 112, the side wall of the second engaging groove 112 can stop and limit the second engaging portion 22, further improving the engagement strength between the second engaging portion 22 and the second engaging groove 112, and further enhancing the stability of the second fixed beam 13 after engagement.

[0058] In some embodiments, such as Figures 1 to 5 As shown, the first fixed beam 12 and the second fixed beam 13 can be located at both ends of the wing support 11, so as to maximize the area of ​​the flying wing structure when the first fixed beam 12 and the second fixed beam 13 are in the preset position, thereby improving the aerodynamic performance of the flying wing structure and improving the flight performance of the flapping wing aircraft.

[0059] like Figure 4 As shown, the first snap-fit ​​groove 111 and the second snap-fit ​​groove 112 can be located at both ends of the wing support 11, so as to snap-fit ​​with the first fixed beam 12 and the second fixed beam 13 located at both ends of the wing support 11.

[0060] In some embodiments, such as Figure 4 and Figure 5 As shown, a first boss 121 may be provided at the end of the first fixed beam 12 near the wing support 11. The first engaging portion 21 may include a first positioning pin 211 and a first spring 212. The first spring 212 may be sleeved on the outer periphery of the first fixed beam 12 and may be located on the side of the first boss 121 near the wing support 11. The first positioning pin 211 may be located on the side of the first spring 212 away from the boss, and the first positioning pin 211 can compress the first spring 212.

[0061] When the first fixed beam 12 rotates to the first preset position, the first positioning pin 211 can be engaged in the first engaging groove 111 under the elastic force of the first spring 212, so that the first positioning pin 211 can automatically engage with the first engaging groove 111 by utilizing the elastic force of the first spring 212. Furthermore, the first spring 212 can still apply elastic force to the first positioning pin 211 after the first positioning pin 211 is engaged with the first engaging groove 111, so as to keep the first positioning pin 211 pressed against the first engaging groove 111, thereby ensuring that the first positioning pin 211 will not disengage from the first engaging groove 111, further ensuring the engagement strength between the first fixed beam 12 and the wing support 11.

[0062] A second boss 131 may be provided at the end of the second fixed beam 13 near the wing support 11. The second locking part 22 may include a second positioning pin 221 and a second spring 222. The second spring 222 may be sleeved on the outer periphery of the second fixed beam 13 and may be located on the side of the second boss 131 near the wing support 11. The second positioning pin 221 may be located on the side of the second spring 222 away from the boss and may compress the second spring 222.

[0063] When the second fixed beam 13 rotates to the second preset position, the second positioning pin 221 can be engaged in the second locking groove 112 under the elastic force of the second spring 222, so that the second positioning pin 221 can automatically engage with the second locking groove 112 by utilizing the elastic force of the second spring 222. Furthermore, the second spring 222 can still apply elastic force to the second positioning pin 221 after it is engaged with the second locking groove 112, so as to keep the second positioning pin 221 pressed against the second locking groove 112, thereby ensuring that the second positioning pin 221 will not disengage from the second locking groove 112, further ensuring the engagement strength between the second fixed beam 13 and the wing support 11.

[0064] In some embodiments, such as Figure 1 and Figure 2 As shown, the wing frame 1 may also include a support rod 15, which is rotatably connected to the wing surface support 11. The support rod 15 can be located between the storage rod 14 and the second fixed beam 13. By setting the support rod 15, the structural strength of the wing frame 1 can be improved, and the support points of the wing frame 1 on the wing surface 10 can be increased, thereby improving the flatness of the wing surface 10 after being supported by the wing frame 1.

[0065] The wing frame 1 may include multiple support rods 15. For example, the number of support rods 15 in the wing frame 1 may be 2 to 6, that is, the number of support rods 15 may be 2, 3, 4, 5, or 6, but it is not limited to this. The wing frame 1 may also include other numbers of support rods 15, all of which are within the protection scope of this disclosure.

[0066] Multiple support rods 15 can be spaced apart to further improve the structural strength of the wing frame 1 and increase the support points of the wing frame 1 on the wing surface 10, thereby further improving the flatness of the wing surface 10 after being supported by the wing frame 1.

[0067] like Figure 1 and Figure 2 As shown, at least some of the support rods 15 can have different lengths. Since the shape of the wing 10 is irregular, by setting support rods 15 of different lengths, it can be ensured that the end of each support rod 15 away from the wing support 11 can be supported at the edge of the wing 10, so as to ensure that each support rod 15 has a good support capacity for the wing 10.

[0068] The wing surface 10 may include a first edge line 101, a second edge line 102, and a third edge line 103 connecting the first edge line 101 and the second edge line 102. The storage rod 14 and the support rod 15 may be connected to the area of ​​the wing surface 10 enclosed by the first edge line 101, the second edge line 102, and the third edge line 103.

[0069] Furthermore, such as Figure 1 and Figure 2 As shown, the first fixed beam 12 and the second fixed beam 13 can also be connected to the area of ​​the wing surface 10 enclosed by the first edge line 101, the second edge line 102, and the third edge line 103. The first fixed beam 12, the second fixed beam 13, the storage rod 14, and the support rod 15 can all be bonded to the wing surface 10 or connected by snap rings to ensure the connection strength between the wing surface 10 and the first fixed beam 12, the second fixed beam 13, the storage rod 14, and the support rod 15. However, this is not the only possibility. The first fixed beam 12, the second fixed beam 13, the storage rod 14, and the support rod 15 can also be connected to the wing surface 10 by other connection methods. These can be selected and set according to the actual situation, and all of this is within the protection scope of this disclosure.

[0070] The first edge line 101 can be parallel to the first fixed beam 12, and the second edge line 102 can be parallel to the second fixed beam 13, to ensure the supporting effect of the first fixed beam 12 and the second fixed beam 13 on the wing surface 10 and improve the flatness of the wing surface 10. However, this is not a limitation; the first edge line 101 and the first fixed beam 12 may not be parallel, that is, the first edge line 101 and the first fixed beam 12 may have a non-zero angle. Similarly, the second edge line 102 and the second fixed beam 13 may not be parallel, that is, the second edge line 102 and the second fixed beam 13 may have a non-zero angle.

[0071] In some embodiments, such as Figure 1 and Figure 2As shown, the lengths of the first fixed beam 12, the second fixed beam 13, and the support rod 15 can all be less than the length of the storage rod 14, which facilitates storage and folding using the storage rod 14 as a reference rod. However, this is not a limitation; the lengths of the first fixed beam 12, the second fixed beam 13, and the support rod 15 can also be equal to or greater than the length of the storage rod 14.

[0072] In some embodiments, such as Figure 4 As shown, the wing support 11 may include a recess 113, which may be located between the first locking groove 111 and the second locking groove 112. The first fixed beam 12, the second fixed beam 13 and the support rod 15 may all pass through the recess 113, so as to limit the first fixed beam 12, the second fixed beam 13 and the support rod 15 by using the recess 113, and ensure the accuracy and stability of the first fixed beam 12, the second fixed beam 13 and the support rod 15 during the movement.

[0073] The recess 113 may include a first sidewall 1131 and a second sidewall 1132 that are opposite to each other. The first sidewall 1131 may be provided with a first mounting hole 1131a, a second mounting hole 1131b and a third mounting hole 1131c that are arranged side by side. The second sidewall 1132 may be provided with a fourth mounting hole, a fifth mounting hole and a sixth mounting hole that are arranged side by side.

[0074] like Figure 4 and Figure 5 As shown, the flying wing structure may further include a first rotating shaft 31, a second rotating shaft 32, and a third rotating shaft 33. The first rotating shaft 31 can sequentially pass through a first mounting hole 1131a, a first fixed beam 12, and a fourth mounting hole, allowing the first fixed beam 12 to be rotatably connected to the first sidewall 1131 and the second sidewall 1132 via the first rotating shaft 31. The second rotating shaft 32 can sequentially pass through a second mounting hole 1131b, a support rod 15, and a fifth mounting hole, allowing the support rod 15 to be rotatably connected to the first sidewall 1131 and the second sidewall 1132 via the second rotating shaft 32. The third rotating shaft 33 can sequentially pass through a third mounting hole 1131c, a second fixed beam 13, and a sixth mounting hole, allowing the second fixed beam 13 to be rotatably connected to the first sidewall 1131 and the second sidewall 1132 via the third rotating shaft 33.

[0075] When there are multiple support rods 15, there are also multiple second mounting holes 1131b, fifth mounting holes, and second rotating shafts 32. The multiple second rotating shafts 32 pass through each second mounting hole 1131b and each fifth mounting hole respectively, so that the multiple support rods 15 can be rotatably connected to the first side wall 1131 and the second side wall 1132 through the second rotating shafts 32.

[0076] In some embodiments of this disclosure, such as Figures 1 to 3As shown, the flapping-wing aircraft may further include a first disassembly component 41 and a second disassembly component 42. The first disassembly component 41 may be located at the end of the first fixed beam 12 away from the wing support 11, and the first disassembly component 41 may be used to connect with a first area of ​​the fuselage. The second disassembly component 42 may be located at the end of the storage rod 14 away from the wing support 11 for connection with a second area of ​​the fuselage. Thus, by providing the first disassembly component 41 and the second disassembly component 42, the connection points and connection strength between the flying wing structure and the fuselage can be improved.

[0077] Other embodiments of this disclosure will readily occur to those skilled in the art upon consideration of the specification and practice of the utility models disclosed herein. This application is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope and spirit of this disclosure are indicated by the appended claims.

Claims

1. A flying wing structure, characterized in that, include: The wing frame (1) includes a wing surface support (11), a first fixed beam (12), a second fixed beam (13), and a storage rod (14); One end of the first fixed beam (12) is rotatably connected to the wing support (11), and when the first fixed beam (12) rotates to the first preset position, the first fixed beam (12) is engaged with the wing support (11); One end of the second fixed beam (13) is rotatably connected to the wing support (11), and when the second fixed beam (13) rotates to the second preset position, the second fixed beam (13) is engaged with the wing support (11); The storage rod (14) is connected to the wing support (11), and the storage rod (14) is located between the first fixed beam (12) and the second fixed beam (13); When the first fixed beam (12) is released from the snap-fit ​​state with the wing support (11), the first fixed beam (12) moves toward the storage rod (14); When the second fixed beam (13) is released from the snap-fit ​​state with the wing support (11), the second fixed beam (13) moves toward the storage rod (14); The wing surface (10) is laid on the wing frame (1).

2. The flying wing structure according to claim 1, characterized in that, The two ends of the wing support (11) are respectively provided with a first snap-fit ​​groove (111) and a second snap-fit ​​groove (112); The first fixed beam (12) has a first snap-fit ​​part (21) at the end near the wing support (11). When the first fixed beam (12) rotates to the first preset position, the first snap-fit ​​part (21) snaps into the first snap-fit ​​groove (111). The second fixed beam (13) has a second snap-fit ​​part (22) at the end near the wing support (11). When the second fixed beam (13) rotates to the second preset position, the second snap-fit ​​part (22) snaps into the second snap-fit ​​groove (112).

3. The flying wing structure according to claim 2, characterized in that, The first fixed beam (12) has a first boss (121) at the end near the wing support (11); The first snap-fit ​​part (21) includes a first positioning pin (211) and a first spring (212). The first spring (212) is sleeved on the outer periphery of the first fixed beam (12) and located on the side of the first boss (121) close to the wing support (11). The first positioning pin (211) is located on the side of the first spring (212) away from the boss and can compress the first spring (212). When the first fixed beam (12) rotates to the first preset position, the first positioning pin (211) can be snapped into the first snap-fit ​​groove (111) under the elastic force of the first spring (212). The second fixed beam (13) has a second boss (131) at the end near the wing support (11); the second snap-fit ​​part (22) includes a second positioning pin (221) and a second spring (222). The second spring (222) is sleeved on the outer periphery of the second fixed beam (13) and located on the side of the second boss (131) near the wing support (11); the second positioning pin (221) is located on the side of the second spring (222) away from the boss and can compress the second spring (222); when the second fixed beam (13) rotates to the second preset position, the second positioning pin (221) can be snapped into the second snap-fit ​​groove (112) under the elastic force of the second spring (222).

4. The flying wing structure according to claim 2, characterized in that, The wing frame (1) also includes a support rod (15), which is rotatably connected to the wing surface support (11) and is located between the storage rod (14) and the second fixed beam (13); The wing surface (10) includes a first edge line (101), a second edge line (102), and a third edge line (103) connecting the first edge line (101) and the second edge line (102); The storage rod (14) and the support rod (15) are connected to the area of ​​the wing surface (10) enclosed by the first edge line (101), the second edge line (102) and the third edge line (103).

5. The flying wing structure according to claim 4, characterized in that, The lengths of the first fixed beam (12), the second fixed beam (13), and the support rod (15) are all less than the length of the storage rod (14).

6. The flying wing structure according to claim 4, characterized in that, The first fixed beam (12), the second fixed beam (13), the storage rod (14), and the support rod (15) are all bonded to the wing surface (10) or connected by snap rings.

7. The flying wing structure according to claim 4, characterized in that, The wing support (11) includes a recess (113) located between the first snap-fit ​​groove (111) and the second snap-fit ​​groove (112). The first fixing beam (12), the second fixing beam (13) and the support rod (15) are all inserted into the recess (113).

8. The flying wing structure according to claim 7, characterized in that, The recess (113) includes a first sidewall (1131) and a second sidewall (1132) that are opposite to each other. The first sidewall (1131) is provided with a first mounting hole (1131a), a second mounting hole (1131b) and a third mounting hole (1131c) that are arranged side by side. The second sidewall (1132) is provided with a fourth mounting hole, a fifth mounting hole and a sixth mounting hole arranged side by side; The flying wing structure also includes a first rotating shaft (31), a second rotating shaft (32) and a third rotating shaft (33), wherein the first rotating shaft (31) passes through the first mounting hole (1131a), the first fixing beam (12) and the fourth mounting hole in sequence; The second rotating shaft (32) passes through the second mounting hole (1131b), the support rod (15) and the fifth mounting hole in sequence; the third rotating shaft (33) passes through the third mounting hole (1131c), the second fixed beam (13) and the sixth mounting hole in sequence.

9. The flying wing structure according to claim 8, characterized in that, The number of the support rods (15) is 2 to 6, and at least some of the support rods (15) have different lengths.

10. A flapping-wing aircraft, characterized in that, It includes a fuselage and a flying wing structure, wherein the flying wing structure is the flying wing structure according to any one of claims 1-9, and the flying wing structure is detachably connected to the fuselage.

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