Structure for aircraft aerial assembly and aircraft using the same

Abstract

A structure for aerial assembly of an aircraft, the structure comprising: a winglet, a power supply and control device, an actuator and a connecting rod; wherein: the winglet is connected to the wing of the aircraft through the connecting rod, and the aircraft can be docked together through the winglet; the power supply and control device is located inside the aircraft, and is used to supply power to electrical equipment on the aircraft, and to control and maintain the position of the winglet in space by controlling the actuator. The structure for aerial assembly of an aircraft of the present invention has the characteristics of simple and flexible docking mode, and avoids flight control problems caused by mechanism failure.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft, and in particular to a structure for aerial assembly of an aircraft. Background Art

[0002] When the aircraft wing generates lift, the pressure on the lower surface of the wing is greater than that on the upper surface, and the wingspan length of the wing is limited, so the high-pressure airflow on the lower wing surface will bypass the wingtips at both ends and try to flow to the low-pressure area on the upper wing surface, forming wingtip vortices at the wingtips, and then forming downwash, resulting in induced drag. Induced drag affects the aerodynamic performance of the aircraft and reduces the range and flight time. An innovative idea is to connect multiple aircraft together through the wingtips to form a combined aircraft. The combined aircraft eliminates the wingtip vortices and induced drag of a single aircraft and increases the aircraft aspect ratio. Therefore, the combined aircraft has a higher lift-to-drag ratio than a single aircraft, and can achieve a longer range and a larger load weight. In terms of mission execution, the combined aircraft can flexibly change its form according to the mission type and requirements: a single aircraft is suitable for performing small-scale tasks in a small range; when combined, it uses the advantages of long range and heavy load to perform large and complex tasks. Aerial combination docking technology is the key technology for combining aircraft, but the existing technology has some problems: the docking method mostly uses mechanical connection, the docking process lacks flexibility and requires high control accuracy; the mechanical docking structure is complex, the mechanism is heavy and the reliability is low. Once the connection mechanism is stuck, the aircraft will lose control. Summary of the invention

[0003] In view of this, the main purpose of the present invention is to provide a structure for aerial assembly of an aircraft, so as to at least partially solve at least one of the above-mentioned technical problems.

[0004] In order to achieve the above-mentioned object, the present invention provides a structure for aerial assembly of an aircraft, comprising: a winglet, a power supply and control device, an actuator and a connecting rod; wherein:

[0005] A winglet connected to the wing of the aircraft through a connecting rod, and the aircraft can be docked together through the winglet;

[0006] The power supply and control device is located inside the aircraft and is used to supply power to electrical equipment on the aircraft and to control and maintain the position of the winglet in space by controlling the actuator.

[0007] Wherein, one side skin of the winglet is a plane for fitting and docking.

[0008] The skin on the other side of the winglet is streamlined, and the two winglets form a streamlined airfoil after being butted together.

[0009] Wherein, a winglet rotating shaft is provided between the winglet and the wing, and the winglet can rotate around the winglet rotating shaft and be fixed in one position.

[0010] Wherein, the winglet reduces the wing length through the winglet rotating shaft.

[0011] Preferably, after the combined aircraft is formed, the aircraft has the ability to flexibly adjust its attitude through the winglet shaft.

[0012] Wherein, the angle α between the winglet and the wing is in the range of 0° to 90°.

[0013] When the winglet is erected, the heading stability can be increased and the induced drag of the wing tip can be reduced.

[0014] Among them, an electromagnetic device is installed in the winglet, and the magnetic attraction generated by the electromagnetic device enables the winglets of the two aircraft to be docked together.

[0015] Among them, a near-field communication device is also installed in the winglet, and the two aircraft transmit and exchange data through the near-field communication device in close proximity.

[0016] Preferably, the structure is not limited to two aircraft, and multiple aircraft can also be combined through the structure.

[0017] An aircraft using the structure for aerial assembly of the aircraft as described above;

[0018] Preferably, the aircraft is a fixed-wing aircraft.

[0019] Based on the above technical solutions, it can be seen that the structure for aircraft aerial assembly of the present invention has at least one of the following beneficial effects compared with the prior art:

[0020] (1) The present invention has the advantages of easy control of docking mode, flexible adjustment mode and simple docking structure.

[0021] (2) The structure for aerial assembly of an aircraft of the present invention has the characteristics of simple and flexible docking method, thus avoiding flight control problems caused by mechanism failure. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a schematic diagram of the present invention on an aircraft;

[0023] Figure 2 It is a schematic diagram of the vertical state of the present invention;

[0024] Figure 3 It is a schematic diagram of the horizontal state of the present invention;

[0025] Figure 4 This is a schematic diagram of the working status of two aircrafts according to an embodiment of the present invention;

[0026] Figure 5 This is a schematic diagram of three aircraft docking through winglets according to an embodiment of the present invention.

[0027] In the above drawings, the meanings of the reference numerals are as follows:

[0028] 1. Winglet; 2. Power supply and control device; 3. Wing; 4. Upper skin; 5. Lower skin; 6. Electromagnetic device; 7. Near field communication device; 8. Winglet shaft; 9. Actuator; 10. Connecting rod. DETAILED DESCRIPTION

[0029] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings.

[0030] The present invention discloses a structure for aerial assembly of aircraft, including a power supply and control device, an electromagnetic device, a near-field communication device, a rotating shaft, an actuator, and the like. The winglet is located on the outside of the wing, and the winglet is rotated by a rotating shaft, a connecting rod, and an actuator, and the winglet can be maintained in a horizontal, vertical, or somewhere in between position. An electromagnetic device is installed inside the winglet, and adjacent aircraft are docked and pressed together by the magnetic attraction generated by the electromagnetic devices installed on the winglets. By controlling the power supply, the tightly pressed winglets can be separated due to the lack of magnetic attraction, so that the combined aircraft is disintegrated into a single aircraft. A near-field communication device is installed inside the winglet, and the successfully docked aircraft can transmit data through the near-field communication method. The present invention has the advantages of easy control of the docking method and a simple docking structure.

[0031] Specifically, the present invention provides a structure for aerial assembly of an aircraft, comprising: a winglet, a power supply and control device, an actuator and a connecting rod; wherein:

[0032] A winglet connected to the wing of the aircraft through a connecting rod, and the aircraft can be docked together through the winglet;

[0033] The power supply and control device is located inside the aircraft and is used to supply power to electrical equipment on the aircraft and to control and maintain the position of the winglet in space by controlling the actuator.

[0034] Wherein, one side skin of the winglet is a plane for fitting and docking.

[0035] The skin on the other side of the winglet is streamlined, and the two winglets form a streamlined airfoil after being butted together.

[0036] Wherein, a winglet rotating shaft is provided between the winglet and the wing, and the winglet can rotate around the winglet rotating shaft and be fixed in one position.

[0037] Wherein, the winglet reduces the wing length through the winglet rotating shaft.

[0038] Preferably, after the combined aircraft is formed, the aircraft has the ability to flexibly adjust its attitude through the winglet shaft.

[0039] Wherein, the angle α between the winglet and the wing is in the range of 0° to 90°.

[0040] When the winglet is erected, the heading stability can be increased and the induced drag of the wing tip can be reduced.

[0041] Among them, an electromagnetic device is installed in the winglet, and the magnetic attraction generated by the electromagnetic device enables the winglets of the two aircraft to be docked together.

[0042] Among them, a near-field communication device is also installed in the winglet, and the two aircraft transmit and exchange data through the near-field communication device in close proximity.

[0043] Preferably, the structure is not limited to two aircraft, and multiple aircraft can also be combined through the structure.

[0044] An aircraft using the structure for aerial assembly of the aircraft as described above;

[0045] Preferably, the aircraft is a fixed-wing aircraft.

[0046] The specific implementation of the present invention will be further described below in conjunction with the accompanying drawings.

[0047] A structure for aerial assembly of an aircraft, comprising a winglet 1, a power supply and control device 2, an electromagnetic device 6, a near field communication device 7, a winglet shaft 8, an actuator 9, a connecting rod 10 and the like.

[0048] like Figure 1 As shown, the aircraft is equipped with winglets 1 at both ends of a wing 3. A power supply and control device 2 is installed inside the aircraft, which can supply power to an electromagnetic device 6 inside the winglet 1, a near field communication device 7 and an actuator 9 inside the wing. The power supply can be, but is not limited to, a battery, a generator, etc.

[0049] like Figure 2 As shown, the winglet 1 forms a linkage mechanism with the actuator 9 through the rotating shaft 8 and the connecting rod 10, and the power supply and the controller 2 adjust the state of the winglet 1 by controlling the actuator 9. When flying, the erected winglet 1 can reduce the wingtip induced drag and increase the heading stability of the aircraft. When the aircraft is on the ground, the erected winglet 1 can reduce the area occupied by the aircraft and facilitate dispatching.

[0050] like Figure 2 As shown, the lower skin 5 of the winglet 1 is a plane, and the upper skin 4 has a streamlined airfoil. When the winglet 2 is in the upright position, the lower skin 5 is used to fit and dock with the lower skin of the winglet of the adjacent aircraft. The upper skin 4 maintains a streamlined airfoil to reduce air resistance.

[0051] like Figure 2 As shown, an electromagnetic device 6 is installed inside the winglet 1, and the power supply and control device 2 supplies power to the electromagnetic device 6, so that the electromagnetic device 6 generates magnetic force. When adjacent aircraft are combined in the air at a close distance, the lower skins 5 of the winglets 1 of the two aircraft are attached together by the magnetic attraction. The continuously generated magnetic attraction can keep the two winglets 1 in a fixed magnetic connection state, so that the two aircraft become a combined aircraft. Cutting off the power supply can cause the two winglets 1 to separate due to the lack of magnetic attraction, so that the combined aircraft disintegrates into multiple single aircraft.

[0052] like Figure 3 As shown, the power supply and control device 2 controls the actuator 9 to operate, and adjusts the winglet 1 to a horizontal position through the connecting rod 10 and the rotating shaft 8.

[0053] like Figure 2 , 3 As shown, the mechanism composed of the power supply and control device 2, the actuator 9, the connecting rod 8 and the rotating shaft 10 can maintain the winglet 1 at a horizontal, vertical or a position therebetween. The angle α formed by the winglet 1 and the horizontal position is set and controlled by the power supply and control device 2.

[0054] like Figure 3 As shown, a near field communication device 7 is installed inside the winglet 1, and the power supply and control device 2 supplies power to the near field communication device 7, which has the ability to transmit and exchange information data. After the two aircraft are docked through the winglet 1, the aircraft can perform data transmission and exchange through the near field communication device 6 on the winglet 1. The near field communication device 6 can be, but is not limited to, near field communication technology, Bluetooth, optics, etc.

[0055] like Figure 4 As shown, after the adjacent aircraft are combined with each other through the winglets 1, each aircraft can independently rotate around its own rotation axis 8 to adjust its own attitude, so the combined new aircraft has a certain structural flexibility. At the same time, the two winglets 1 are combined into a complete streamlined airfoil, which can reduce the generation of drag and increase the heading stability of the combined aircraft.

[0056] like Figure 5 FIG. 1 is a schematic diagram of applying the structure of the aircraft aerial combination of the present invention to three aircraft for aerial combination. The present invention is not limited to the combination of two or three aircraft. In this way, multiple aircraft can be combined.

[0057] The specific embodiments described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A structure for aerial assembly of an aircraft, characterized in that: include: Winglets, power and control units, actuators and linkages; including: A winglet connected to the wing of the aircraft through a connecting rod, and the aircraft can be docked together through the winglet; A power supply and control device, located inside the aircraft, for supplying power to electrical equipment on the aircraft and controlling and maintaining the position of the winglet in space by controlling the actuator; A winglet rotating shaft is provided between the winglet and the wing, and the winglet can rotate around the winglet rotating shaft and be fixed in one position; An arc-shaped protrusion is provided at one end of the winglet close to the wing, and an arc-shaped groove is provided at one end of the wing close to the winglet, and the arc-shaped protrusion matches the arc-shaped groove; An electromagnetic device is installed in the winglet. The magnetic attraction generated by the electromagnetic device makes the winglets of the two aircraft dock together. The continuously generated magnetic attraction keeps the two winglets in a fixed magnetic connection state; cutting off the power supply causes the two winglets to separate due to the lack of magnetic attraction.

2. The structure according to claim 1, characterized in that: One side skin of the winglet is flat so as to be fitted and docked.

3. The structure according to claim 1, characterized in that: The skin on the other side of the winglet is streamlined, and the two winglets form a streamlined airfoil after being butted together.

4. The structure according to claim 1, characterized in that The winglet reduces the wing length via the winglet rotation axis.

5. The structure according to claim 4, characterized in that: After the combined aircraft is formed, the aircraft has the ability to flexibly adjust its attitude through the winglet rotation axis.

6. The structure according to claim 1, characterized in that The angle α between the winglet and the wing is in the range of 0° to 90°.

7. The structure according to claim 1, characterized in that When the winglet is erected, the heading stability can be increased and the induced drag of the wing tip can be reduced.

8. The structure according to claim 1, characterized in that A near field communication device is also installed in the winglet, and the two aircraft transmit and exchange data through the near field communication device in close proximity.

9. The structure according to claim 1, characterized in that The structure is not limited to two aircraft, and multiple aircraft can also be combined through the structure.

10. An aircraft using the structure for aerial assembly of an aircraft as claimed in any one of claims 1 to 9.

11. The aircraft according to claim 10, characterized in that The aircraft is a fixed-wing aircraft.

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