LU500704B1

LU500704B1 - Aircraft Docking Assembly, Aircraft with Docking Assembly and Grid-Form Connected Aircraft Group

Info

Publication number: LU500704B1
Application number: LU500704A
Authority: LU
Inventors: Tong Zou; Siyu Liu; Ming Zhu; Kangwen Sun; Chenxuan Zhao
Original assignee: Univ Beihang
Priority date: 2021-09-29
Filing date: 2021-09-29
Publication date: 2022-03-29

Abstract

The aircraft docking assembly comprises a left wing tip joint, a right wing tip joint and a nose joint which are connected with each other through wing plates and all provided with magnetic connectors, mortise and tenon structures and electrical connectors; two or three aircraft docking assemblies are docked through magnetic connectors, mortise and tenon structures and electrical connectors. The aircraft docking assembly can use magnetic force as an air docking medium, and the mortise and tenon structure and the electrical connector are used for positioning, transmitting force and electrifying between the two aircraft docking assemblies; specifically, within a certain distance range, the mutual magnetic force between the magnetic connectors enables the two aircraft docking assemblies to be automatically attracted, the two aircraft docking assemblies are docked in place with the mortise and tenon structure, and then signals are transmitted and/or electric energy is distributed through the electrical connectors.

Description

DESCRIPTION 7500708 Aircraft Docking Assembly, Aircraft with Docking Assembly and Grid-Form Connected Aircraft Group

TECHNICAL FIELD The invention relates to the technical field of aircraft, in particular to aircraft docking assembly, aircraft with docking assembly and grid-form connected aircraft group.

BACKGROUND This part only provides background information related to this disclosure, which is not necessarily prior art. With the development of solar photovoltaic material technology and the reduction of its production cost, aircraft with solar energy as the auxiliary energy or even the main energy has gradually become an important research target with directionality and frontier in aviation field. With the long time flight conditions of solar aircraft gradually maturing, solar aircraft have the potential to fly continuously for a long time without consuming fuel, and to perform long-time flying missions in near space, which has great application potential in military and civil fields.

Because of the limitation of solar power area density and considering the efficiency of solar panels, a single solar aircraft with a single wing needs a larger wing area to lay solar panels to provide sufficient energy for solar aircraft.

However, increasing the size of single solar aircraft will bring a series of problems, such as poor environmental adaptability and high requirements for landing and landing sites. If people want to improve the environmental adaptability of single solar power aircraft during take-off and landing and reduce the requirements of single solar power aircraft for take-off site, people need to reduce the size of single solar power aircraft during take-off and landing, but this will not meet the load requirements of single solar power aircraft.

SUMMARY The purpose of the present invention is to propose an aircraft docking assembly aiming at the shortcomings of the above-mentioned prior art. The aircraft docking assembly of the present invention can utilize magnetic force as an air docking 7500704 medium, and utilize mortise and tenon structure and electrical connectors to carry out positioning force transmission and electrification between two aircraft docking assemblies. Specifically, within a certain distance range, the mutual magnetic force between the magnetic connectors enables the two aircraft docking assemblies to self-attract, and the two aircraft docking assemblies are docked in place with mortise and tenon structure, and then signals are transmitted and/or electrical energy is distributed through the electrical connectors. The purpose is achieved by the following technical scheme.

In the first aspect, the invention provides an aircraft docking assembly, the aircraft docking assembly comprises a left wing tip Joint, a right wing tip Joint and a nose joint which are connected with each other through wing plates and all provided with magnetic connectors, mortise and tenon structures and electrical connectors; two or three aircraft docking assemblies are docked through magnetic connectors, mortise and tenon structures and electrical connectors.

Preferably, the magnetic connector comprises iron blocks respectively arranged on the left side and the top of the left wing tip joint, and loss-of-electricity electromagnets respectively arranged on the right side of the right wing tip Joint and the bottom of the nose joint.

Preferably, the mortise and tenon structure comprises mortise and tenon blocks respectively arranged on the left side of the left wing tip joint and the right side of the right wing tip joint, wedge-shaped protrusions arranged on the top of the left wing tip joint and the right wing tip joint and wedge-shaped grooves arranged on the bottom of the nose joint.

Preferably, the wedge-shaped groove at the bottom of the nose joint covers the wedge-shaped protrusions on the left wing tip joint and the right wing tip joint, and the nose joint is simultaneously butted with the wedge-shaped protrusions on the left wing tip joint and the right wing tip joint through the wedge-shaped groove.

Preferably, the electrical connector comprises an electrifying element and a communication element which are arranged on the left side and the top of the left wing tip joint, the right side and the top of the right wing tip joint and the bottom of 500704 the nose Joint.

Preferably, the left-wing tip joint comprises a left-wing tip plate and a left-wing tip joint cartridge receiver which is arranged on the left-wing tip plate and flush with the left side of the left-wing tip plate, and the magnetic connector, mortise and tenon structure and electrical connector on the left-wing tip joint are all arranged in the left-wing tip joint cartridge receiver.

Preferably, the right-wing tip joint comprises a right-wing tip plate and a right-wing tip joint cartridge receiver which is arranged on the right-wing tip plate and flush with the right side of the right-wing tip plate, and the magnetic connectors, mortise and tenon structures and electrical connectors on the right-wing tip joint are all arranged in the right-wing tip joint cartridge receiver.

Preferably, the aircraft docking assembly comprises a triangular structure consisting of three wing plates, and the left wing tip joint, the right wing tip joint and the nose joint are respectively arranged at two side corners and one bottom corner of the triangular structure.

In the second aspect, the invention provides an aircraft, the aircraft comprises the aircraft docking assembly according to the first aspect of the invention, and two or three adjacent aircraft are docked in the air through the aircraft docking assembly.

In the third aspect, the invention provides a grid-form connected aircraft group, which comprises a plurality of aircraft according to the second aspect, and the plurality of aircraft form a triangular array, and two aircrafts distributed adjacently up and down in the triangular array are butted with the left wing tip joint or the right wing tip joint through the nose joint, two aircrafts distributed left and right adjacently in the triangle array are butted with the right wing tip joint through the left wing tip joint.

The grid-form connected aircraft group provided in the third aspect of the present invention is based on the aircraft docking assembly provided in the first aspect of the present invention and the aircraft provided in the second aspect of the present invention. Each aircraft is provided with a nose joint at the nose and a left wing tip joint and a right wing tip joint at the left and right wings, magnetic connectors, 7500704 mortise and tenon structures and electrical connectors are arranged on the nose joint, the left wing tip joint and the right wing tip joint; a plurality of aircrafts form triangular grid distribution through joints, which solves the technical problems that mechanical connection requires high precision, complex structure and is not suitable for docking multiple aircrafts in the air.

BRIEF DESCRIPTION OF THE FIGURES Through reading the detailed description of the preferred embodiments below, various other advantages and benefits will become clear to those of ordinary skill in the art. The drawings are only used for the purpose of illustrating the preferred embodiments, and are not considered as a limitation to the present invention. Also, throughout the drawings, the same reference symbols are used to denote the same components. In the figure: Fig. 1 is the schematic diagram of the assembly structure of the adapter assembly on a single aircraft according to an embodiment of the present invention; Fig. 2 is the schematic diagram of the docking structure of the adapter assembly on the grid-form connected aircraft group according to the embodiment of the present invention; Fig. 3 is the schematic structural diagram of the left wing tip joint according to the embodiment of the present invention; Fig. 4 is the schematic structural diagram of the right wing tip joint according to the embodiment of the present invention; Fig. 5 is the schematic structural diagram of the nose joint of the embodiment of the present invention; Fig. 6 is the schematic diagram of the split structure of the left wing tip joint, the right wing tip joint and the nose joint according to the embodiment of the present invention; Fig. 7 is the schematic diagram of the docking structure of the left wing tip joint and the right wing tip joint according to the embodiment of the present invention; Fig. 8 is the schematic diagram of the docking structure of the left wing tip joint and the nose joint according to the embodiment of the present invention; 500704 Fig. 9 is the schematic diagram of the docking structure of the left wing tip Joint, the right wing tip Joint and the nose joint according to the embodiment of the present invention.

Explanation of labels in the figure: 1000: Grid-form connected aircraft group; 100: Aircraft; 10: Left wing tip joint; 20: Right wing tip joint; 30: Nose joint; 40: Wing tip Joint cartridge receiver; 50: Iron block; 60: Loss-of-electricity electromagnet; 70: Conductive contacts; 80: Wing tip plate; 90: Nose joint cartridge receiver; 101: Tenon block; 110: Mortise; 120: Wedge-shaped protrusions; 130: Wedge-shaped grooves.

DESCRIPTION OF THE INVENTION Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the disclosure are shown in the drawings, it should be understood that the disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to enable a more thorough understanding of the disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that the aircraft docking assembly of the present invention is illustrated by connecting aircraft groups in a grid manner, which is only a preferred embodiment and does not limit the technical scheme of the present invention. For example, the aircraft docking assembly of the present invention can also be applied to other aircraft groups with similar layout, and this adjustment does not deviate from the protection scope of the technical scheme of the present invention.

It should be understood that the terminology used herein is for the purpose of describing specific example embodiments only, and is not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms "a", "an" and "the" as used herein may also be meant to include the plural. The terms "including", "comprising" and "having" are inclusive and thus indicate the presence of stated features, elements and/or components, but do not exclude the presence or addition of one or more other features, elements, components, and/or combinations thereof. HU500704 Although the terms first, second, third, fourth, fifth and sixth, etc. may be used herein to describe a plurality of elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be limited by these terms. These terms can only be used to distinguish one element, component, region, layer or section from another. Unless the context clearly indicates otherwise, terms such as "first", "second" and other numerical terms are used herein without implying order. In addition, in the description of the present invention, unless otherwise specified and limited, the terms "set" and "connected" should be broadly understood, for example, they can be fixed connection, detachable connection or integrated connection; they can be connected directly or indirectly through an intermediate medium. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific conditions.

For convenience of description, spatial relative relation terms can be used to describe the relation of one element or feature with respect to another as shown in the figure, such as "bottom", "top", "side", "upper", "lower", "inner", "outer", etc. This spatial relative term is intended to encompass different orientations of the device in use or operation in addition to the orientations depicted in the figures. For example, if the device in the figure is turned upside down, elements described as "below" other elements or features will then be oriented as "above" other elements or features. Therefore, the example term "below" can include both upper and lower orientations. The device can be oriented additionally (rotated 90 degrees or in other directions) and the spatial relative relationship descriptors used herein are interpreted accordingly.

As shown in figs. 1 and 2, in the first aspect, the invention provides an aircraft docking assembly, the aircraft docking assembly comprises a left wing tip joint 10, a right wing tip joint 20 and a nose joint 30 which are connected with each other through wing plates and all provided with magnetic connectors, mortise and tenon structures and electrical connectors; two or three aircraft docking assemblies are docked through magnetic connectors, mortise and tenon structures and electrical connectors.

The aircraft docking assembly of the invention can use magnetic force as an air 500704 docking medium, and use mortise and tenon structures and electrical connectors to carry out positioning force transmission and electrification between two aircraft docking assemblies, specifically, within a certain distance range, the mutual magnetic force between the magnetic connectors enables the two aircraft docking assemblies to be automatically attracted, and the two aircraft docking assemblies are docked in place with the mortise and tenon structure, and then signals are transmitted and/or electric energy is distributed through the electrical connectors.

As shown in figs. 3 to 6, according to one embodiment of the present invention, the magnetic connector comprises iron blocks 50 respectively arranged on the left side and the top of the left wing tip joint 10, and loss-of-electricity electromagnets 60 respectively arranged on the right side of the right wing tip joint 20 and the bottom of the nose joint 30.

In this embodiment, the loss-of-electricity electromagnets 60 used in the magnetic connector is an electromagnet with power-off magnetization and power-on demagnetization. In the normal connection process of the multiple aircraft docking assemblies, the multiple loss-of-electricity electromagnets 60 connected with the multiple aircraft docking assemblies are kept in a magnetic state, and the electromagnets are energized and demagnetized only during the separation operation between the multiple aircraft docking assemblies. Compared with the common electromagnet, the loss-of-electricity electromagnet 60 does not need to be energized for most of the time, so as to reduce the energy consumption required to maintain the magnetic force of the electromagnet.

As shown in figs. 3 to 9, according to one embodiment of the present invention, the mortise and tenon structure comprises mortise 110 and tenon blocks 101 respectively arranged on the left side of the left wing tip joint 10 and the right side of the right wing tip joint 20, wedge-shaped protrusions 120 arranged on the top of the left wing tip joint 10 and the right wing tip joint 20 and wedge-shaped grooves 130 arranged on the bottom of the nose joint 30.

In this embodiment, the left end face of the left wing tip joint 10 is provided with a mortise left turned and a left tenon block for butting the right wing tip joint 20, and 500704 the upper end face of the left wing tip Joint 10 is provided with a wedge-shaped protrusion 120 for butting the nose joint 30. The right end face of the right-wing tip joint 20 is provided with a right tenon block and a mortise right turned for butting the left-wing tip joint 10, and the upper end face of the right-wing tip joint 20 is provided with a wedge-shaped protrusion 120 for butting the nose joint 30. The lower end face of the nose joint 30 is provided with wedge-shaped grooves 130 which are matched with the wedge-shaped protrusions 120 of the upper end faces of the left and right wing tip joints and positioned.

According to the embodiment of the invention, magnetic force can be used as an air docking medium among a plurality of aircraft docking assemblies, and a mortise and tenon structure is used for positioning and transmitting force among the aircraft docking assemblies, so that the purpose that a plurality of aircraft 100 can be docked in the air through a plurality of aircraft docking assemblies is achieved.

With continued reference to figs. 3-9, according to one embodiment of the present invention, the electrical connector comprises an electrifying element and a communication element which are arranged on the left side and the top of the left wing tip joint 10, the right side and the top of the right wing tip joint 20 and the bottom of the nose joint 30.

In this embodiment, the electrical connector includes two conductive contacts 70 with spring contact pins, and the two conductive contacts 70 include an electrifying element and a communication element. Within a certain distance range, the mutual magnetic force between the loss-of-electricity electromagnet 60 and the iron block 50 on the aircraft docking assembly enables the two aircraft 100 to automatically attract, and the two aircrafts 100 are docked in place through the cooperation of the mortise 110 and the tenon block 101, so as to improve the feasibility of docking the two aircrafts 100 in the air. After the two aircrafts 100 are joined, the signals are transmitted through the communication elements and the electric energy is distributed through the electrifying elements.

With continued reference to figs. 3-9, according to one embodiment of the present invention, the right-wing tip joint 10 comprises a right-wing tip plate 80 and a 7500704 right-wing tip Joint cartridge receiver (wing tip Joint cartridge receiver 40) which is arranged on the right-wing tip plate 80 and flush with the right side of the right-wing tip plate 80, and the magnetic connectors, mortise and tenon structures and electrical connectors on the right-wing tip joint 10 are all arranged in the right-wing tip joint cartridge receiver (wing tip joint cartridge receiver 40). Further, the left-wing tip joint comprises a left-wing tip plate 80 and a left-wing tip joint cartridge receiver (wing tip joint cartridge receiver 40) which is arranged on the left-wing tip plate 80 and flush with the left side of the left-wing tip plate 80, and the magnetic connector, mortise and tenon structure and electrical connector on the left-wing tip joint 20 are all arranged in the left-wing tip joint cartridge receiver (wing tip joint cartridge receiver 40).

In this embodiment, the left wing tip plate 80 is arranged at the left wing tip of the aircraft docking assembly, and the left wing tip joint cartridge receiver is installed on the left wing tip plate 80. The left wing tip plate 80 can increase the docking area during the docking process of two aircraft docking assemblies, thereby improving the docking stability between the two aircraft docking assemblies, relieving the docking stress between the left wing tip joint cartridge receiver and the right wing tip joint cartridge receiver, and reducing the dislocation phenomenon of the two aircraft docking assemblies after docking.

With continued reference to figs. 7-9, further, the body joint 30 includes a head joint cartridge receiver 90, which can increase the butt joint area between the airframe joint 30 and the left and right wing tip joints, relieve the butt joint stress between the left and right wing tip joint cartridge receivers and the nose joint cartridge receiver 90, and reduce the dislocation phenomenon of two or three aircraft butt joints after butt joint.

According to one embodiment of the present invention, the aircraft docking assembly comprises a triangular structure consisting of three wing plates, and the left wing tip joint 10, the right wing tip joint 20 and the nose joint 30 are respectively arranged at two side corners and one bottom corner of the triangular structure.

In this embodiment, the structural stability of the aircraft docking assembly can 500704 be improved by setting the aircraft docking assembly into a triangular structure, meanwhile, by arranging the left wing tip joint 10, the right wing tip joint 20 and the nose joint 30 at two side corners and one bottom corner of the triangular structure respectively, the force balance of the aircraft docking assembly can be improved, and the tilting phenomenon of the aircraft docking assembly in the docking process can be reduced. Further, the three wing plates can be respectively butted with the left wing tip joint 10, the right wing tip joint 20 and the nose joint 30 through magnetic elements, so as to improve the disassembly and assembly convenience of the aircraft docking assembly.

The embodiment of the invention provides an aircraft docking assembly between aircraft 100 which uses magnetic force as a medium and uses a loss-of-electricity electromagnet 60 for connection, aiming at realizing single-point and multi-point connection of grid connection of aircraft groups to aircraft groups 100, meanwhile, the aircraft docking assembly also has the advantages of simple and reliable structure and low power consumption. Because there is no exposed mechanism, the aircraft docking assembly bears less interference resistance during use. In addition, the aircraft docking assembly provided by the embodiment of the present invention uses magnetic force as a medium for connecting the aircraft groups 100 in a grid manner in the air, and can allow docking operations within a larger precision range.

In the second aspect, the invention provides an aircraft 100, the aircraft 100 comprises the aircraft docking assembly according to the first aspect of the invention, and two or three adjacent aircraft 100 are docked in the air through the aircraft docking assembly.

According to an embodiment of the present invention, the overall composition of a single aircraft 100 includes a left wing tip joint 10, a right wing tip joint 20 and a nose joint 30. The left and right wing tip joints 20 are located at both ends of the left and right wings, and the outer end faces of the left and right wing tip joints 20 are flush with the outer end faces of the end plates of the left and right wing tips.

The assembly structure of a single aircraft 100 is shown in fig. 1, and the aircraft group after assembling a plurality of aircraft 100 is connected with the aircraft group 7500704 in a grid-form as shown in fig. 2. The aircraft 100 in fig. 1 and fig. 2 is a structural schematic diagram, which reflects the overall layout structure of the triangular united wing aircraft 100, but does not include the specific details of the aircraft 100. The embodiment of the invention adopts the triangular united wing aircraft 100 and the grid-connected aircraft group 100 as the preferred embodiment of the application layout of the invention; the present invention can also be used only in one docking mode of wing tip docking or nose docking, or aircraft 100 with other layout forms and air docking modes, and will not be described here.

As shown in picture 2, in the third aspect, the invention provides a grid-form connected aircraft group 100, which comprises a plurality of aircraft 100 according to the second aspect, and the plurality of aircraft 100 form a triangular array, and two aircrafts 100 distributed adjacently up and down in the triangular array are butted with the left wing tip Joint 10 or the right wing tip Joint 20 through the nose joint 30, two aircrafts 100 distributed left and right adjacently in the triangle array are butted with the right wing tip joint 20 through the left wing tip Joint 10.

The grid-form connected aircraft group 100 provided in the third aspect of the present invention is based on the aircraft docking assembly provided in the first aspect of the present invention and the aircraft 100 provided in the second aspect of the present invention. Each aircraft is provided with a nose Joint 30 at the nose and a left wing tip joint 10 and a right wing tip Joint 20 at the left and right wings; magnetic connectors, mortise and tenon structures and electrical connectors are arranged on the nose joint 30, the left wing tip joint 10 and the right wing tip joint 20; a plurality of aircrafts 100 form triangular grid distribution through joints, which solves the technical problems that mechanical connection requires high precision, complex structure and is not suitable for docking multiple aircrafts in the air.

The docking scheme adopted by the aircraft group grid connection with the aircraft group 100 provided by the embodiment of the present invention has the advantages of simplicity, reliability and low resistance without moving parts driven by machinery. In addition, the grid-form connected aircraft group 100 adopts the connection mode of magnetic docking, which allows a wide range of docking 500704 accuracy, and the conversion process between combination and separation state is flexible and convenient. The connection scheme of the loss-of-electricity electromagnet 60 can also reduce the overall power consumption. In addition, the embodiment of the invention adopts the combination of the nose joint 30 and the left and right wing tip joints 20, which causes a small increase in aerodynamic resistance.

According to the embodiment of the present invention, the connection mode of the grid connection of the aircraft group to the aircraft group 100 is as follows: 1) General connection mode: each joint is attracted by magnetic force. When it is necessary to separate, the power supply of the corresponding loss-of-electricity electromagnet 60 is turned on to make the electromagnet lose its magnetism, thus achieving the purpose of separating the joint. Among the two abutted joints, one side is a loss-of-electricity electromagnet 60 and the other side is an iron block 50, so as to reduce the risk that the two abutted joints cannot be separated. If both sides are electromagnets, the electromagnets of either side can't complete the circuit, which will cause the two butt joints to be unable to separate.

When connecting, the two joints to be butted are brought close to a certain range, and the two joints are automatically attracted under the action of magnetic force, and are positioned through the mortise 110 and the tenon block 101 on the cartridge receiver. If the primary butt joint fails, control the corresponding electromagnets to be electrified and separated, and then butt joint again until the two joints to be butt joint successfully.

After the two joints to be docked are positioned and docked, the conductive contact 70 between the two joints is turned on for transmitting control signals or distributing electric energy between two adjacent aircraft 100, or transmitting signals and distributing electric energy at the same time, depending on the connection requirements of specific aircraft 100.

2) Butting the left and right wing tip joints 20: the left end face of left wing tip joint 10 is left iron block 50, and the right end face of right wing tip joint corresponding to left iron block 50 is set as a loss-of-electricity electromagnet 60. The two joints are provided with tenons 101 and mortise 110 for positioning and 7500704 transmitting force at the butt joint position. After the docking is completed, the tenon block 101 corresponds to the mortise 110, and then the docking position is determined, so as to transfer the load between the adjacent end faces during flight.

When the left wing tip joint 10 and the right wing tip joint 20 are attracted and positioned, the contacts on the left and right end faces of the joint transmit signals and/or distribute electric energy.

When the left wing tip joint 10 and the right wing tip joint 20 are attracted, the wing tip plates 80 are combined together and continue to play the role of rectifying and vertical stabilizer.

3) The wing tip joint is connected with the nose joint 30: the upper end face of the wingtip joint is an iron block 50, and the lower end face of the nose joint 30 is a loss-of-electricity electromagnet 60. The joint is provided with tenons 101 and mortise 110 for positioning and transmitting force at corresponding positions. As an example, the connection mode between the left wing tip joint 10 and the nose joint 30 is shown in fig. 8.

Further, the two iron blocks 50 on the left and right wing tip joints 20 are different in front and back positions to prevent reverse connection. Specifically, the left joint iron block 50 is arranged behind the tenon block 101 and the right joint iron block 50 is arranged in front of the tenon block 101.

After the wing tip joint and the nose joint 30 are attracted and positioned, the conductive contacts 70 on the inclined surfaces of the tenon block 101 or the mortise 110 transmit signals and/or distribute electric energy.

4) Connection of three connectors: after any two connectors are sucked, the third connector can still be connected and the contacts can be connected. As shown in fig. 9, the left and right wing tip joints 20 are butted with the nose joint 30 to form a three-joint combined structure.

The above is only a preferred embodiment of the present invention, but the protection scope of the present invention is not limited to this. Any person familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be covered within 500704 the protection scope of the present invention.

Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

CLAIMS LU500704

1. An aircraft docking assembly, characterized in that the aircraft docking assembly comprises a left wing tip joint, a right wing tip joint and a nose joint which are connected with each other through wing plates and all provided with magnetic connectors, mortise and tenon structures and electrical connectors, two or three aircraft docking assemblies are docked through magnetic connectors, mortise and tenon structures and electrical connectors.

2. The aircraft docking assembly according to claim 1, characterized in that the magnetic connector comprises iron blocks respectively arranged on the left side and the top of the left wing tip joint, and loss-of-electricity electromagnets respectively arranged on the right side of the right wing tip joint and the bottom of the nose joint.

3. The aircraft docking assembly according to claim 1, characterized in that the mortise and tenon structure comprises mortise and tenon blocks respectively arranged on the left side of the left wing tip joint and the right side of the right wing tip joint, wedge-shaped protrusions arranged on the top of the left wing tip joint and the right wing tip joint and wedge-shaped grooves arranged on the bottom of the nose joint.

4. The aircraft docking assembly according to claim 3, characterized in that the wedge-shaped groove at the bottom of the nose joint covers the wedge-shaped protrusions on the left wing tip joint and the right wing tip joint, and the nose joint is simultaneously butted with the wedge-shaped protrusions on the left wing tip joint and the right wing tip joint through the wedge-shaped groove.

5. The aircraft docking assembly according to claim 1, characterized in that the electrical connector comprises an electrifying element and a communication element which are arranged on the left side and the top of the left wing tip joint, the right side and the top of the right wing tip joint and the bottom of the nose joint.

6. The aircraft docking assembly according to claim 1, characterized in that the left-wing tip joint comprises a left-wing tip plate and a left-wing tip joint cartridge receiver which is arranged on the left-wing tip plate and flush with the left side of the left-wing tip plate, and the magnetic connector, mortise and tenon structure and electrical connector on the left-wing tip joint are all arranged in the left-wing tip joint cartridge receiver. 7500708

7. The aircraft docking assembly according to claim 1, characterized in that the right-wing tip joint comprises a right-wing tip plate and a right-wing tip joint cartridge receiver which is arranged on the right-wing tip plate and flush with the right side of the right-wing tip plate, and the magnetic connectors, mortise and tenon structures and electrical connectors on the right-wing tip joint are all arranged in the right-wing tip joint cartridge receiver.

8. The aircraft docking assembly according to claim 1, characterized in that the aircraft docking assembly comprises a triangular structure consisting of three wing plates, and the left wing tip joint, the right wing tip joint and the nose joint are respectively arranged at two side corners and one bottom corner of the triangular structure.

9. An aircraft, characterized in that the aircraft comprises the aircraft docking assembly according to any one of claims 1 to 8, and two or three adjacent aircraft are docked in the air through the aircraft docking assembly.

10. A grid-form connected aircraft group, characterized in that the grid-form connected aircraft group comprises a plurality of aircraft according to claim 9, and the plurality of aircraft form a triangular array, and two aircrafts distributed adjacently up and down in the triangular array are butted with the left wing tip joint or the right wing tip joint through the nose joint, two aircrafts distributed left and right adjacently in the triangle array are butted with the right wing tip joint through the left wing tip joint.