CN210942221U - Structure for aerial combination of aircraft and aircraft adopting structure - Google Patents

Abstract

A structure for aerial assembly of an aircraft and an aircraft employing the same, the structure comprising: winglets, power supply and control devices, actuators and connecting rods; wherein: winglets connected to the wings of the aircraft by links, the aircraft being dockable together by the winglets; and the power supply and control device is positioned inside the aircraft and used for supplying power to electric equipment on the aircraft and controlling and maintaining the position of the winglet in the space by controlling the actuator. The utility model discloses a flight control problem of avoiding leading to because of the mechanism trouble for the structure of aircraft combination in air possesses the simple nimble characteristics of butt joint mode.

Description

Structure for aerial combination of aircraft and aircraft using the same

technical field

The present disclosure relates to the technical field of aircraft, and in particular, to structures for aerial assembly of aircraft.

Background technique

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 of the wing is limited, so the high-pressure airflow on the lower wing surface will bypass the wingtips at both ends, trying to reach the low-pressure area on the upper wing surface. flow away, forming a wingtip vortex at the wingtip portion, which in turn forms a downwash, resulting in induced drag. Induced drag affects the aerodynamic performance of the aircraft and reduces range and flight time. An innovative idea is that multiple aircraft are connected together by wing tips to form a combined aircraft. The combined aircraft eliminates the wingtip vortex and induced drag of a single aircraft, and increases the aspect ratio of the aircraft. Therefore, the combined aircraft has a higher lift-to-drag ratio than a single aircraft, and can achieve longer range and greater loading weight. In terms of performing tasks, the combined aircraft can flexibly change its form according to the type and requirements of the task: a single aircraft is suitable for performing small-scale and small-scale tasks; when combined, it can use the advantages of long range and heavy load to perform large-scale and complex tasks. The aerial combined docking technology is the key technology of combined aircraft, but the existing technology has some problems: the docking method mostly adopts mechanical connection, the docking process lacks flexibility, and the control accuracy is high; the mechanical docking structure is complex, the mechanism is heavy, and the reliability is low. Once the connecting mechanism is stuck, it will cause the aircraft to lose control.

Utility model content

In view of this, the main purpose of the present invention is to provide a structure for aerial combination of aircraft, in order to at least partially solve at least one of the above technical problems.

In order to achieve the above purpose, the utility model provides a structure for aerial combination of aircraft, including: winglet, power supply and control device, actuator and connecting rod; wherein:

Winglets are connected to the wings of the aircraft through connecting rods, and the aircraft can be docked together through the winglets;

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

Wherein, one side of the skin of the winglet is a plane, so as to be used for butt joint.

Wherein, the skin on the other side of the winglet is streamlined, and the two winglets are butted together to form a streamlined airfoil.

Wherein, a winglet rotating shaft is arranged between the winglet and the wing, and the winglet can rotate around the winglet rotating shaft and is fixed in one position.

Wherein, the winglet reduces the wing length through the winglet rotating shaft.

Preferably, after the combined aircraft is formed, the aircraft has the ability to flexibly adjust its attitude through the winglet rotation axis.

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

Wherein, when the winglets are erected, the heading stability can be increased and the induced drag of the wingtips can be reduced.

Wherein, an electromagnetic device is installed in the winglet, and the magnetic attraction force generated by the electromagnetic device makes the winglets of the two airplanes butt together.

Wherein, a near field communication device is also installed in the winglet, and the two aircraft transmit and exchange data through the close near field communication device.

Preferably, the structure is not limited to two aircrafts, and multiple aircrafts can also be combined through this structure.

An aircraft adopting the above-mentioned structure for aerial combination of aircraft;

Preferably, the aircraft is a fixed-wing aircraft.

Based on the above technical solutions, it can be seen that the structure for aerial combination of aircraft of the present invention has at least one of the following beneficial effects relative to the prior art:

(1) The utility model has the advantages of easy control of the docking mode, flexible adjustment mode, simple docking structure and the like.

(2) The structure of the utility model for aerial combination of aircraft has the characteristics of simple and flexible docking mode, and avoids flight control problems caused by mechanism failures.

Description of drawings

Fig. 1 is the schematic diagram of the utility model on the plane;

Fig. 2 is the vertical state schematic diagram of the utility model;

3 is a schematic diagram of the horizontal state of the utility model;

4 is a schematic diagram of the working state of two aircrafts according to an embodiment of the present utility model;

FIG. 5 is a schematic diagram of the docking of three aircraft through winglets according to an embodiment of the present invention.

In the above drawings, the meanings of the reference signs are as follows:

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

Detailed ways

In order to make the purpose, technical solutions and advantages of the present utility model clearer, the present utility model will be further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings.

The utility model discloses a structure for aerial combination of an aircraft, which comprises a power supply and a 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 through the shaft, link and actuator, and can maintain the winglet in a horizontal, vertical and a certain position in between. Electromagnetic equipment is installed inside the winglet, and adjacent aircraft are docked and attached to each other through the magnetic attraction generated by the electromagnetic equipment installed on the winglet. By controlling the power supply, the close-fitting winglets can be separated due to the lack of magnetic attraction, so that the combined aircraft can be disintegrated into a single aircraft. The inside of the winglet is equipped with near-field communication equipment, and the successfully docked aircraft can transmit data through near-field communication. The utility model has the advantages of easy control of the docking mode, simple docking structure and the like.

Specifically, the present utility model provides a structure for aerial combination of aircraft, including: winglet, power supply and control device, actuator and connecting rod; wherein:

Winglets are connected to the wings of the aircraft through connecting rods, and the aircraft can be docked together through the winglets;

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

Wherein, one side of the skin of the winglet is a plane, so as to be used for butt joint.

Wherein, the skin on the other side of the winglet is streamlined, and the two winglets are butted together to form a streamlined airfoil.

Wherein, a winglet rotating shaft is arranged between the winglet and the wing, and the winglet can rotate around the winglet rotating shaft and is fixed in one position.

Wherein, the winglet reduces the wing length through the winglet rotating shaft.

Preferably, after the combined aircraft is formed, the aircraft has the ability to flexibly adjust its attitude through the winglet rotation axis.

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

Wherein, when the winglets are erected, the heading stability can be increased and the induced drag of the wingtips can be reduced.

Wherein, an electromagnetic device is installed in the winglet, and the magnetic attraction force generated by the electromagnetic device makes the winglets of the two airplanes butt together.

Wherein, a near field communication device is also installed in the winglet, and the two aircraft transmit and exchange data through the close near field communication device.

Preferably, the structure is not limited to two aircrafts, and multiple aircrafts can also be combined through this structure.

An aircraft adopting the above-mentioned structure for aerial combination of aircraft;

Preferably, the aircraft is a fixed-wing aircraft.

The specific embodiments of the present utility model will be further described below with reference to the accompanying drawings.

A structure for aerial combination of aircraft, consisting of winglet 1, power supply and control device 2, electromagnetic device 6, near field communication device 7, winglet rotating shaft 8, actuator 9, connecting rod 10, etc.

As shown in FIG. 1 , the aircraft is provided with winglets 1 at both ends of the wing 3 . A power supply and control device 2 is installed inside the aircraft, which can supply power to the electromagnetic equipment 6 inside the winglet 1, the near field communication equipment 7 and the actuator 9 in the wing. The power supply can be but not limited to batteries, generators, etc.

As shown in FIG. 2 , 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 realize the state adjustment of the winglet 1 by controlling the actuator 9 to act. In flight, erecting the winglets 1 can reduce the wingtip induced drag and increase the aircraft heading stability. When the aircraft is on the ground, erecting the winglets 1 can reduce the footprint of the aircraft and facilitate scheduling.

As shown in FIG. 2 , 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 erected position, the lower skin 5 is used for butt joint with the lower skin of the adjacent aircraft winglet. The upper skin 4 maintains a streamlined airfoil to reduce the generation of air resistance.

As shown in FIG. 2 , 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 a magnetic force. When adjacent aircraft are combined in the air at close range, the lower skins 5 of the winglets 1 of the two aircraft are attached together through the action of magnetic attraction. The continuously generated magnetic attraction can keep the two winglets 1 in a fixed magnetic connection state, so that the two aircrafts become a combined aircraft. Cutting off the power supply can cause the two winglets 1 to be separated due to the lack of magnetic attraction, so that the combined aircraft can be disintegrated into a plurality of single aircraft.

As shown in FIG. 3 , the power supply and control device 2 controls the actuator 9 to act, and the small wing 1 is adjusted to the horizontal position through the connecting rod 10 and the rotating shaft 8 .

As shown in Figures 2 and 3, the mechanism composed of the power supply and the control device 2, the actuator 9, the connecting rod 8 and the rotating shaft 10 can make the winglet 1 maintain a certain position in the horizontal, vertical and in between. The included angle α formed by the horizontal position is set and controlled by the power supply and the control device 2 .

As shown in FIG. 3 , 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 , and the near field communication device 7 has the capability of information and data transmission and exchange. After the two aircraft are docked through the winglet 1, the aircraft can transmit and exchange data through the near field communication device 6 on the winglet 1. The near field communication device 6 may be, but not limited to, near field communication technology, bluetooth, optics, and the like.

As shown in FIG. 4 , after adjacent aircraft are combined with each other through the winglets 1 , each aircraft can independently rotate around its own axis of rotation 8 to adjust its own attitude. Therefore, the combined new aircraft has 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.

As shown in FIG. 5 , it is a schematic diagram of aerial combination by applying the structure of the aircraft aerial combination of the present invention to three aircraft. The utility model is not limited to the combination of two or three aircraft. In this way, multiple aircraft can be combined.

The specific embodiments described above further describe the purpose, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above are only specific embodiments of the present invention and are not intended to limit the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included within the protection scope of the present utility model.

Claims (9)

1. A structure for aerial assembly of an aircraft, comprising: winglets, power supply and control devices, actuators and connecting rods; wherein:

winglets connected to the wings of the aircraft by links, the aircraft being dockable together by the winglets;

and the power supply and control device is positioned inside the aircraft and used for supplying power to electric equipment on the aircraft and controlling and maintaining the position of the winglet in the space by controlling the actuator.

2. The structure of claim 1, wherein one side skin of the winglet is planar for snug-fit interfacing.

3. The structure of claim 1, wherein the other side skin of the winglet is streamlined, and the two winglets are butted to form a streamline airfoil.

4. The structure of claim 1, wherein a winglet pivot is provided between the winglet and the wing, the winglet being rotatable about the winglet pivot and being fixed in position.

5. The structure of claim 1 wherein the angle α between the winglet and the wing is in the range of 0 ° to 90 °.

6. The structure of claim 1, wherein the winglet, when erected, provides increased directional stability and reduced induced drag at the tip of the wing;

electromagnetic equipment is installed in the winglets, and magnetic attraction force generated by the electromagnetic equipment enables the winglets of the two airplanes to be butted together.

7. The structure of claim 1, wherein a near field communication device is further mounted in the winglet, and wherein two aircraft transmit and exchange data via the proximate near field communication device;

the structure is not limited to two airplanes, and a plurality of airplanes can be combined through the structure.

8. An aircraft employing a structure for aircraft airborne assembly as claimed in any one of claims 1 to 7.

9. The aircraft of claim 8, wherein the aircraft is a fixed-wing aircraft.

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