Multi-aircraft cluster combination method

Abstract

The invention provides a multi-aircraft cluster combination method, and belongs to the field of multi-aircraft cluster combination flight control. According to the multi-aircraft gathering combination method, a first limiting block is aligned with a second limiting groove, and is inserted from right to left until the first limiting block penetrates through the second limiting groove; then the second connecting piece is rotated by 180 degrees to enable the first limiting protrusion to be aligned with the second limiting groove, insertion continues to enable the first limiting protrusion to penetrate through the second limiting groove, then the second connecting piece is rotated by 180 degrees to enable the first limiting block to be aligned with the first limiting groove, insertion continues to enable the first limiting block to completely penetrate through the first limiting groove, and then the second connecting piece is rotated by 180 degrees; and the first limiting protrusion is aligned with the first limiting groove and then continues to be inserted till the second limiting block abuts against the bottom face of the third limiting groove, the abutting block is inserted between the first limiting block and the first supporting leg, and the abutting block is fixedly connected to the first supporting leg. According to the method, the dismounting efficiency can be improved, and the problem of dismounting difficulty is solved.

Description

Technical Field

[0001] The present invention belongs to the field of multi-aircraft cluster combination flight control, and in particular relates to a multi-aircraft cluster combination method. Background Art

[0002] Based on the body design and flight characteristics, drones can be divided into fixed-wing, multi-rotor and flapping-wing drones. Multi-rotor drones are particularly good at low-altitude and low-speed flights because of their simple structure and good maneuverability, and can easily achieve vertical take-off and landing, hovering, and multi-directional changes. Among them, quad-rotor drones, as the most common type of multi-rotor drones, control the six degrees of freedom of the drone by adjusting the rotation speed of the four rotors. Although they have the advantages of high maneuverability, small size, and easy operation, their load capacity is limited due to their limitations in energy efficiency and thrust-to-weight ratio, making it difficult to transport large mass objects for a long time.

[0003] To overcome this limitation, multiple quad-rotor drones can be integrated into a collaborative flight platform to significantly enhance their carrying capacity, thereby achieving stable transportation of large mass objects and making up for the shortcomings of a single quad-rotor drone in load capacity and drive. Among them, the design of the connection components that connect multiple quad-rotor drones into a collective operating system is particularly critical. However, the connection components of the multi-aircraft collective structure in the prior art are mostly connected to the drones through multiple bolts, which are difficult to disassemble and assemble during the process of disassembling and assembling the bolts due to limited disassembly and assembly space. Summary of the invention

[0004] In view of this, in order to solve the problem that the connection components of the multi-aircraft assembly structure in the prior art are mostly connected to the drones through multiple bolts, and the disassembly and assembly process of the bolts will be difficult due to limited disassembly and assembly space. The present invention proposes a multi-aircraft assembly method.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] A method for assembling a multi-aircraft assembly structure is used to assemble a multi-aircraft assembly structure, wherein the multi-aircraft assembly comprises a flight platform and multiple branches, wherein the branches comprise a first connecting member, a second connecting member, a tightening block, a ball joint connecting member and an extension plate, wherein the first connecting member comprises a connecting seat for connecting to the aircraft and a first leg and a second leg both fixedly connected to the connecting seat, wherein the first leg is provided with a first connecting hole and a first limiting groove that are connected in communication, the second leg is provided with a second connecting hole and a second limiting groove that are connected in communication, and a third limiting groove is provided on a side of the second leg away from the first leg; the second connecting member comprises a connecting bridge and a first connecting portion and a second connecting portion both fixedly connected to the connecting bridge, and a first limiting block is fixedly provided on the circumferential side surface of the first connecting portion and a first limiting protrusion, the first limiting block is away from the second connecting part relative to the first limiting protrusion, and a second limiting block and a second limiting protrusion are fixedly provided on the circumferential side of the second connecting part, the first limiting protrusion is inserted in the first limiting groove, the second limiting protrusion is inserted in the second limiting groove, the second limiting block is inserted in the third limiting groove, and the first connecting part and the second connecting part are respectively penetrated through the first connecting hole and the second connecting hole; one end of the clamping block is clamped against the first limiting protrusion, and the other end is clamped against the first leg, and the clamping block is detachably connected to the first connecting part; one end of the extension plate is connected to the connecting bridge through the ball joint connector, and the other end is connected to the flying platform.

[0007] The multi-aircraft collective combination method comprises:

[0008] S1: Align the first connecting portion with the second connecting hole, align the first limiting block with the second limiting groove, and insert the second connecting member from right to left until the first limiting block just passes through the second limiting groove;

[0009] S2: Rotate the second connecting member 180° so that the first limiting protrusion is aligned with the second limiting groove, and then continue to insert the second connecting member from right to left so that the first limiting protrusion completely passes through the second limiting groove;

[0010] S3: Rotate the second connecting member 180° so that the first limiting block is aligned with the first limiting groove, and then continue to insert the second connecting member from right to left so that the first limiting block completely passes through the first limiting groove;

[0011] S4: Rotate the second connecting member 180° so that the first limiting protrusion is aligned with the first limiting groove, and then continue to insert the second connecting member from right to left until the second limiting block is tightly pressed against the bottom surface of the third limiting groove;

[0012] S5: inserting the abutting block between the first limiting block and the first supporting leg, and fixing the abutting block to the first supporting leg.

[0013] As a preferred solution for the connection component of the above-mentioned multi-aircraft collective structure, the ball joint connection includes an outer shell and a ball head, the ball head can rotate in any direction relative to the outer shell, the ball head is fixedly connected to the connecting bridge, and the outer shell is fixedly connected to the extension plate.

[0014] As a preferred solution for the connection component of the above-mentioned multi-aircraft collective structure, the ball head is provided with a bolt hole, and the connecting bridge is provided with a ball head connecting hole. The ball head is fixedly connected to the connecting bridge by bolts passing through the ball head connecting holes and being screwed to the bolt holes.

[0015] As a preferred solution of the connection assembly of the above-mentioned multi-aircraft collective structure, the ball joint connection also includes an adjusting nut, and the adjusting nut can adjust the tightness between the ball head and the shell.

[0016] As a preferred solution of the connection assembly of the above-mentioned multi-aircraft collective structure, the flight platform is provided with a plurality of arc-shaped connecting long holes, and the arc-shaped connecting long holes are used to be connected to the extension plate.

[0017] As a preferred solution of the connection component of the above-mentioned multi-aircraft collective structure, the flight platform is provided with a load connection hole group, and the load connection hole group includes a first load connection hole, a second load connection hole and a third load connection hole, all of which are used to connect the load or the actuator.

[0018] As a preferred solution of the connection assembly of the above-mentioned multi-aircraft collective structure, both long sides of the extension plate are provided with folded edges.

[0019] As a preferred solution of the connection assembly of the above-mentioned multi-aircraft collective structure, the extension plate is provided with a plurality of fourth load connection holes at intervals, and the fourth load connection holes are used to connect the load.

[0020] As a preferred solution for the connection assembly of the above-mentioned multi-aircraft collective structure, the extension plate is provided with a plurality of weight-reducing holes, and the plurality of weight-reducing holes are arranged at intervals.

[0021] As a preferred solution of the connection component of the above-mentioned multi-aircraft collective structure, the connection seat is provided with a plurality of aircraft connection holes, the plurality of aircraft connection holes are arranged at intervals, and the aircraft connection holes are used to connect with the aircraft.

[0022] Compared with the prior art, the multi-aircraft cluster combination method provided by the present invention has the following beneficial effects:

[0023] 1. The present invention provides a method for assembling a plurality of aircrafts. In the method for assembling a plurality of aircrafts, the installation process of the first connecting member and the second connecting member is as follows: first align the first connecting portion with the second connecting hole, and align the first limiting block with the second limiting groove, so that the second connecting member is inserted into the second connecting hole from right to left until the first limiting block just passes through the second limiting groove; then the second connecting member is rotated 180° so that the first limiting protrusion is aligned with the second limiting groove, and then the second connecting member is further inserted from right to left so that the first limiting protrusion completely passes through the second limiting groove, at which time the first connecting portion is located between the first leg and the second leg; then the second connecting member is rotated 180° so that the first limiting block is aligned with the first limiting groove , and then continue to insert the second connecting piece from right to left, so that the first limit block completely passes through the first limit groove; then rotate the second connecting piece 180° to align the first limit protrusion with the first limit groove, and then continue to insert the second connecting piece from right to left until the second limit block is tightly pressed against the bottom surface of the third limit groove, that is, the second limit block is inserted into the third limit groove. At this time, the first connecting part and the second connecting part are respectively inserted into the first connecting hole and the second connecting hole, the first limit protrusion is inserted into the first limit groove, and the second limit protrusion is inserted into the second limit groove; finally, insert the tightening block into the middle of the first limit block and the first leg, and fix the tightening block to the first leg, so that the first limit block can no longer move to the right.

[0024] The first limiting protrusion is inserted into the first limiting groove, the second limiting protrusion is inserted into the second limiting groove, and the second limiting block is inserted into the third limiting groove, so that the first connecting member and the second connecting member can be limited in the circumferential direction; the second limiting block is inserted into the third limiting groove, the second limiting block abuts against the bottom surface of the third limiting groove, the pressing block is fixed between the first limiting block and the first leg, and the first leg and the second leg are both located between the second limiting block and the first limiting block, so that the first connecting member and the second connecting member can be limited in the axial direction. And only one bolt is needed to fix the pressing block to the first leg to fix the first connecting member and the second connecting member, which greatly reduces the difficulties caused by limited space during disassembly and assembly, and installation and disassembly are very convenient, fast and efficient.

[0025] 2. The present invention provides a method for collectively combining multiple aircraft. In the method, each branch can be connected to one aircraft, and multiple branches are connected to a flight platform. Multiple aircraft can be collectively operated, which can greatly improve the load limit and endurance, and has great practical application value.

[0026] 3. The present invention provides a method for assembling multiple aircrafts. In the method, the second connecting member is connected to the flight platform via a ball joint connecting member and an extension plate, so that the aircraft can swing in all directions and stop at will without interfering with the rotation of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0028] Figure 1 is an assembly diagram of a multi-aircraft assembly structure after being assembled using the multi-aircraft assembly method provided by a specific embodiment of the present invention;

[0029] Figure 2 is a structural schematic diagram of a first connecting member in a multi-aircraft assembly method provided by a specific embodiment of the present invention;

[0030] Figure 3 is a structural schematic diagram of a second connecting member in a multi-aircraft assembly method provided by a specific embodiment of the present invention;

[0031] Figure 4 is a schematic diagram of S1 in the multi-aircraft collective combination method provided by a specific embodiment of the present invention;

[0032] Figure 5 is a schematic diagram of S2 in the multi-aircraft collective combination method provided by a specific embodiment of the present invention;

[0033] Figure 6 is a schematic diagram of S3 in the multi-aircraft collective combination method provided by a specific embodiment of the present invention;

[0034] Figure 7 is a schematic diagram of S4 in the multi-aircraft collective combination method provided by a specific embodiment of the present invention;

[0035] Figure 8 It is a structural schematic diagram of a ball joint connection member in a multi-aircraft assembly method provided by a specific embodiment of the present invention along a first viewing angle;

[0036] Fig. 9 is a schematic structural diagram of a ball joint connection member in a multi-aircraft assembly method provided by a specific embodiment of the present invention along a second viewing angle;

[0037] Fig.10 It is a structural schematic diagram of an extension plate in a multi-aircraft assembly method provided by a specific embodiment of the present invention;

[0038] Fig.11 It is a schematic diagram of the structure of the flight platform in the multi-aircraft collective combination method provided by a specific embodiment of the present invention.

[0039] In the figure:

[0040] 1. first connecting member; 11. connecting seat; 12. first supporting leg; 13. second supporting leg; 121. first connecting hole; 122. first limiting groove; 131. second connecting hole; 132. second limiting groove; 133. third limiting groove;

[0041] 2. second connecting member; 21. connecting bridge; 22. first connecting portion; 23. second connecting portion; 221. first limiting block; 222. first limiting protrusion; 231. second limiting block; 232. second limiting protrusion;

[0042] 3. Ball joint connector; 31. Ball head; 32. Housing; 33. Adjusting nut;

[0043] 4. Extension plate; 41. Weight reduction hole; 42. Fourth load connection hole; 43. Folding edge;

[0044] 5. Flying platform; 51. Arc-shaped connecting long hole; 52. Load connecting hole group; 521. First load connecting hole; 522. Second load connecting hole; 523. Third load connecting hole;

[0045] 100. Aircraft. DETAILED DESCRIPTION

[0046] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely explain the technical solutions in the embodiments of the present invention. It should be noted that the embodiments of the present invention and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0047] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0048] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0049] In the description of this embodiment, the terms "upper", "lower", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplified operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0050] See also Figure 1-11 To illustrate this embodiment, the present invention provides a method for assembling a multi-aircraft assembly, which is used to assemble a multi-aircraft assembly structure, wherein the multi-aircraft assembly structure includes a flight platform 5 and multiple branches, wherein the branches include a first connecting member 1, a second connecting member 2, a tightening block, a ball joint connecting member 3 and an extension plate 4, wherein the first connecting member 1 includes a connecting seat 11 for connecting to an aircraft 100 and a first leg 12 and a second leg 13 both fixedly connected to the connecting seat 11, wherein the first leg 12 is provided with a first connecting hole 121 and a first limiting groove 122 that are connected, the second leg 13 is provided with a second connecting hole 131 and a second limiting groove 132 that are connected, and a third limiting groove 133 is provided on a side of the second leg 13 away from the first leg 12; the second connecting member 2 includes a connecting bridge 21 and a first connecting portion 22 and a second connecting portion 23 both fixedly connected to the connecting bridge 21, and the first connecting portion 12 and the second connecting portion 13 are fixedly connected to the connecting bridge 21. A first limit block 231 and a first limit protrusion 222 are fixedly provided on the circumferential side surface of the connecting part 22, the first limit block 221 is away from the second connecting part 23 relative to the first limit protrusion 222, and a second limit block 231 and a second limit block 232 are fixedly provided on the circumferential side surface of the second connecting part 23, the first limit protrusion 222 is inserted into the first limit groove 122, the second limit block 232 is inserted into the second limit groove 132, the second limit block 231 is inserted into the third limit groove 133, and the first connecting part 22 and the second connecting part 23 are respectively penetrated into the first connecting hole 121 and the second connecting hole 131; one end of the clamping block is clamped against the first limit protrusion 222, and the other end is clamped against the first leg 12, and the clamping block is detachably connected to the first connecting part 22; one end of the extension plate 4 is connected to the connecting bridge 21 through the ball joint connector 3, and the other end is connected to the flying platform 5.

[0051] The multi-aircraft integration method includes:

[0052] like Figure 4 As shown, S1: align the first connection portion 22 with the second connection hole 131, align the first limiting block 221 with the second limiting groove 132, and insert the second connection member 2 from right to left until the first limiting block 221 just passes through the second limiting groove 132;

[0053] like Figure 5 As shown, S2: rotate the second connecting member 2 by 180° so that the first limiting protrusion 222 is aligned with the second limiting groove 132, and then continue to insert the second connecting member 2 from right to left so that the first limiting protrusion 222 completely passes through the second limiting groove 132;

[0054] like Figure 6 As shown, S3: rotate the second connecting member 2 by 180° so that the first limiting block 221 is aligned with the first limiting groove 122, and then continue to insert the second connecting member 2 from right to left so that the first limiting block 221 completely passes through the first limiting groove 122;

[0055] like Figure 7 As shown, S4: rotate the second connecting member 2 by 180° so that the first limiting protrusion 222 is aligned with the first limiting groove 122, and then continue to insert the second connecting member 2 from right to left until the second limiting block 231 is tightly pressed against the bottom surface of the third limiting groove 133;

[0056] S5: insert the abutting block between the first limiting block 221 and the first supporting leg 12 , and fix the abutting block to the first supporting leg 12 .

[0057] It can be understood that the multi-aircraft assembly method also includes: the extension plate 4 is connected to the flight platform 5 by bolts, the extension plate 4 and the outer shell 32 of the ball joint connector 3 are connected by bolts, the ball head 31 of the ball joint connector 3 is connected to the second connector 2 by bolts, and the first connector 1 is connected to the aircraft 100.

[0058] The installation process of the first connecting member 1 and the second connecting member 2 of the multi-aircraft assembly structure is as follows: Figure 4 As shown, first align the first connecting portion 22 with the second connecting hole 131, and align the first limiting block 221 with the second limiting groove 132, so that the second connecting member 2 is inserted into the second connecting hole 131 from right to left until the first limiting block 221 just passes through the second limiting groove 132; then rotate the second connecting member 2 180°, align the first limiting protrusion 222 with the second limiting groove 132, and then continue to insert the second connecting member 2 from right to left, so that the first limiting protrusion 222 completely passes through the second limiting groove 132, as shown in FIG. Figure 5As shown, at this time, the first connecting portion 22 is located between the first leg 12 and the second leg 13; Figure 6 As shown, the second connecting member 2 is rotated 180° to align the first limiting block 221 with the first limiting groove 122, and then the second connecting member 2 is inserted from right to left to completely pass through the first limiting groove 122; Figure 7 As shown, the second connecting member 2 is then rotated 180° to align the first limiting protrusion 222 with the first limiting groove 122, and the second connecting member 2 is further inserted from right to left until the second limiting block 231 is pressed against the bottom surface of the third limiting groove 133, that is, the second limiting block 231 is inserted into the third limiting groove 133, so that the second limiting block 231 can no longer move to the left. At this time, the first connecting portion 22 and the second connecting portion 23 are respectively inserted into the first connecting hole 121 and the second connecting hole 131, the first limiting protrusion 222 is inserted into the first limiting groove 122, and the second limiting block 232 is inserted into the second limiting groove 132, so that circumferential limiting can be achieved; finally, the tightening block is inserted between the first limiting block 221 and the first leg 12, and the tightening block is fixedly connected to the first leg 12, so that the first limiting block 221 can no longer move to the right, thereby achieving axial limiting. Only one bolt is needed to fix the abutting block to the first leg 12 so that the first connecting member 1 and the second connecting member 2 can be fixedly connected.

[0059] It can be understood that, by inserting the first limiting protrusion 222 into the first limiting groove 122, the second limiting protrusion 232 into the second limiting groove 132, and the second limiting block 231 into the third limiting groove 133, the first connecting member 1 and the second connecting member 2 can be limited in the circumferential direction; the second limiting block 231 is inserted into the third limiting groove 133, the second limiting block 231 abuts against the bottom surface of the third limiting groove 133, the pressing block is fixed between the first limiting block 221 and the first leg 12, and the first leg 12 and the second leg 13 are both located between the second limiting block 231 and the first limiting block 221, so that the first connecting member 1 and the second connecting member 2 can be limited in the axial direction. And only one bolt is needed to fix the pressing block to the first leg 12, so that the first connecting member 1 and the second connecting member 2 can be fixedly connected, which greatly reduces the difficulties caused by the limited space for disassembly and assembly during the disassembly and assembly process, and the installation and disassembly are very convenient, fast and efficient.

[0060] In this multi-aircraft assembly method, each branch can be connected to an aircraft 100, and multiple branches are connected to the flight platform 5. Multiple aircraft 100 can be operated in a connected manner, which can greatly improve the load limit and endurance, and has great practical application value. Only one bolt is required to connect the first connecting member 1 and the second connecting member 2, which greatly reduces the difficulties caused by limited disassembly and assembly space during disassembly and assembly. The second connecting member 2 is connected to the flight platform 5 through a ball joint connector 3 and an extension plate 4, which enables the aircraft 100 to swing in all directions and stop at will without interfering with the rotation of the aircraft 100.

[0061] In this embodiment, the number of the aircraft 100 is three, and the aircraft 100 is a quad-rotor drone.

[0062] Alternatively, if Figure 8 As shown, the ball joint connector 3 includes a housing 32 and a ball head 31. The ball head 31 can rotate in any direction relative to the housing 32. The ball head 31 is fixedly connected to the connecting bridge 21, and the housing 32 is fixedly connected to the extension plate 4. It can be understood that a portion of the ball head 31 is exposed from the housing 32, and the other portion is wrapped by the housing 32. The portion wrapping the ball head 31 fits the shape of the ball head 31, and can keep the ball head 31 rotating in any direction. Bolt holes are provided on the ball head 31, and the ball head 31 can be connected to the connecting bridge 21 by bolts.

[0063] Optionally, the connection bridge 21 is provided with a ball head connection hole, and a bolt is passed through the ball head connection hole and screwed to the bolt hole to fix the ball head 31 to the connection bridge 21 .

[0064] Alternatively, if Fig. 9 As shown, the ball joint connector 3 further includes an adjusting nut 33, which can adjust the tightness between the ball head 31 and the housing 32. Tightening the adjusting nut 33 can make the squeezing between the ball head 31 and the housing 32 tighter; loosening the adjusting nut 33 can relax the squeezing between the ball head 31 and the housing 32, so that the adjusting nut 33 can adjust the tightness between the ball head 31 and the housing 32.

[0065] like Fig.11 As shown, optionally, the flight platform 5 is provided with a plurality of arc-shaped connecting long holes 51, and the arc-shaped connecting long holes 51 are used to connect with the extension plate 4. In this embodiment, four arc-shaped connecting long holes 51 are provided, and two are in the inner circle and two are in the outer circle. The arc-shaped connecting long holes 51 in the inner circle and the arc-shaped connecting long holes 51 in the outer circle are arranged alternately, and the number of aircraft 100 can be flexibly adjusted to meet the configuration requirements of different numbers of aircraft 100, and the distribution distance of the aircraft 100 can be elastically adjusted. It can be understood that the flight platform 5 and the extension plate 4 are connected by four bolts.

[0066] Optionally, the flying platform 5 is provided with a load connection hole group 52, which includes a first load connection hole 521, a second load connection hole 522, and a third load connection hole 523, and the first load connection hole 521, the second load connection hole 522, and the third load connection hole 523 are all used to connect a load or an actuator. The first load connection hole 521 is a round hole for fixing. The second load connection hole 522 and the third load connection hole 523 are designed in consideration of the fact that the load or actuator may pass through the upper and lower sides of the flying platform 5, and can meet the requirements of carrying different types of loads or actuators.

[0067] like Fig.10 As shown, optionally, both long sides of the extension plate 4 are provided with folded edges 43. That is, the two long sides of the extension plate 4 are bent, thereby increasing the rigidity of the extension plate 4.

[0068] Optionally, the extension plate 4 is provided with a plurality of fourth load connection holes 42 at intervals, and the fourth load connection holes 42 are used to connect the load, so as to meet the carrying requirements of different types of loads.

[0069] Optionally, the extension plate 4 is provided with a plurality of weight-reducing holes 41, and the plurality of weight-reducing holes 41 are arranged at intervals, so as to reduce the deadweight of the connection assembly.

[0070] Optionally, the connection seat 11 is provided with a plurality of aircraft connection holes, the plurality of aircraft connection holes are arranged at intervals, and the aircraft connection holes are used to connect with the aircraft 100 .

[0071] Obviously, the embodiments of the present invention disclosed above are only used to help illustrate the present invention. The embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. According to the content of this specification, many modifications and changes can be made. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that technicians in the relevant technical field can understand and use the present invention well. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the claims of the present invention.

Claims

1. A method for combining multiple aircraft, characterized in that: The invention is used for assembling a multi-aircraft assembly structure, the multi-aircraft assembly structure comprising a flight platform (5) and a plurality of branches, the branches comprising a first connecting member (1), a second connecting member (2), a tightening block, a ball joint connecting member (3) and an extension plate (4), the first connecting member (1) comprising a connecting seat (11) for connecting with an aircraft (100) and a first leg (12) and a second leg (13) both fixedly connected to the connecting seat (11), the first leg (12) being provided with a first connecting hole (13) communicating with the first connecting hole (13) The second leg (13) is provided with a second connecting hole (131) and a second limiting groove (122) in communication with each other, and a third limiting groove (133) is provided on a side of the second leg (13) away from the first leg (12); the second connecting member (2) comprises a connecting bridge (21) and a first connecting portion (22) and a second connecting portion (23) both fixedly connected to the connecting bridge (21), and a first limiting block (221) and a first limiting block (222) are fixedly provided on a circumferential side surface of the first connecting portion (22). The first limiting block (221) is relatively far away from the second connecting portion (23) from the first limiting block (222); the second limiting block (231) and the second limiting block (232) are fixedly provided on the circumferential side surface of the second connecting portion (23); the first limiting block (222) is inserted into the first limiting groove (122); the second limiting groove (232) is inserted into the second limiting groove (132); and the second limiting block (231) is inserted into the third limiting groove (133). , the first connecting portion (22) and the second connecting portion (23) are respectively inserted into the first connecting hole (121) and the second connecting hole (131); one end of the pressing block is pressed against the first limiting protrusion (222), and the other end is pressed against the first leg (12), and the pressing block is detachably connected to the first connecting portion (22); one end of the extension plate (4) is connected to the connecting bridge (21) through the ball joint connector (3), and the other end is connected to the flying platform (5); The multi-aircraft collective combination method comprises: S1: Align the first connection portion (22) with the second connection hole (131), align the first limiting block (221) with the second limiting groove (132), and insert the second connection member (2) from right to left until the first limiting block (221) just passes through the second limiting groove (132); S2: Rotate the second connecting member (2) 180° so that the first limiting protrusion (222) is aligned with the second limiting groove (132), and then continue to insert the second connecting member (2) from right to left so that the first limiting protrusion (222) completely passes through the second limiting groove (132); S3: Rotate the second connecting member (2) 180° so that the first limiting block (221) is aligned with the first limiting groove (122), and then continue to insert the second connecting member (2) from right to left so that the first limiting block (221) completely passes through the first limiting groove (122); S4: Rotate the second connecting member (2) 180° so that the first limiting protrusion (222) is aligned with the first limiting groove (122), and then continue to insert the second connecting member (2) from right to left until the second limiting block (231) is tightly pressed against the bottom surface of the third limiting groove (133); S5: inserting the abutting block between the first limiting block (221) and the first supporting leg (12), and fixing the abutting block to the first supporting leg (12).

2. The multi-aircraft assembly method according to claim 1, characterized in that: The ball joint connection (3) comprises an outer shell (32) and a ball head (31); the ball head (31) can rotate in any direction relative to the outer shell (32); the ball head (31) is fixedly connected to the connection bridge (21); and the outer shell (32) is fixedly connected to the extension plate (4).

3. The multi-aircraft assembly method according to claim 2, characterized in that: The ball head (31) is provided with a bolt hole, and the connecting bridge (21) is provided with a ball head connecting hole. Bolts are passed through the ball head connecting holes and are screwed to the bolt holes to fix the ball head (31) and the connecting bridge (21).

4. The multi-aircraft assembly method according to claim 2, characterized in that: The ball joint connection (3) further comprises an adjusting nut (33), wherein the adjusting nut (33) can adjust the tightness between the ball head (31) and the housing (32).

5. The multi-aircraft assembly method according to claim 1, characterized in that: The flying platform (5) is provided with a plurality of arc-shaped connecting long holes (51), and the arc-shaped connecting long holes (51) are used to be connected to the extension plate (4).

6. The multi-aircraft assembly method according to claim 1, characterized in that: The flying platform (5) is provided with a load connection hole group (52), wherein the load connection hole group (52) comprises a first load connection hole (521), a second load connection hole (522) and a third load connection hole (523), all of which are used to connect a load or an actuator.

7. The multi-aircraft assembly method according to claim 1, characterized in that: Both long sides of the extension plate (4) are provided with folded edges (43).

8. The multi-aircraft assembly method according to claim 1, characterized in that: The extension plate (4) is provided with a plurality of fourth load connection holes (42) at intervals, and the fourth load connection holes (42) are used to connect a load.

9. The multi-aircraft assembly method according to claim 1, characterized in that: The extension plate (4) is provided with a plurality of weight-reducing holes (41), and the plurality of weight-reducing holes (41) are arranged at intervals.

10. The multi-aircraft assembly method according to claim 1, characterized in that: The connection seat (11) is provided with a plurality of aircraft connection holes, the plurality of aircraft connection holes are arranged at intervals, and the aircraft connection holes are used to connect to the aircraft (100).

Images