CN210942221U - Structure for aerial combination of aircraft and aircraft adopting structure - Google Patents
Structure for aerial combination of aircraft and aircraft adopting structure Download PDFInfo
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- CN210942221U CN210942221U CN201921694210.XU CN201921694210U CN210942221U CN 210942221 U CN210942221 U CN 210942221U CN 201921694210 U CN201921694210 U CN 201921694210U CN 210942221 U CN210942221 U CN 210942221U
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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
Technical Field
The present disclosure relates to the field of aircraft technology, and more particularly to structures for aerial assembly of aircraft.
Background
When the aircraft wing generates lift force, the pressure of the lower surface of the wing is larger than that of the upper surface, the span length of the wing is limited, so that high-pressure airflow of the lower wing surface bypasses wing tips at two ends and tries to flow to a low-pressure area of the upper wing surface, a wing tip vortex is formed at the wing tip part, and then downwash is formed, and induced resistance is caused. The induced resistance affects the aerodynamic performance of the aircraft and reduces the voyage time. One innovative approach is to connect multiple aircraft together via wing tips to form a combined aircraft. The combined aircraft eliminates the tip vortex and the induced resistance of a single aircraft, increases the aspect ratio of the aircraft, has higher lift-drag ratio than the single aircraft, and can reach longer range and larger loading weight. In the aspect of task execution, the combined aircraft can flexibly change the form according to the type and the requirement of the task: a single aircraft is suitable for performing a small-scale mission; when the device is combined, large-scale complex tasks are executed by utilizing the advantages of long voyage, large load and the like. The air combination docking technology is a key technology of a combination aircraft, but the prior art has some problems: the butt joint mode adopts mechanical connection, the butt joint process is lack of flexibility, and the requirement on control precision is high; the mechanical butt joint structure is complex, the mechanism has heavy weight and low reliability, and once the connecting mechanism is blocked, the airplane can be out of control.
SUMMERY OF THE UTILITY MODEL
In view of the above, a primary object of the present invention is to provide a structure for aerial assembly of an aircraft intended to at least partially solve at least one of the above technical problems.
In order to achieve the above object, the present invention provides a structure for an 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.
And one side skin of the winglet is a plane for fitting and butt joint.
The skin on the other side of each winglet is streamline, and the two winglets are butted to form a streamline airfoil.
And 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 at one position.
Wherein the winglet reduces wing length by way of a winglet pivot.
Preferably, after the combined aircraft is formed, the aircraft has the capability of flexibly adjusting the posture through the winglet rotating shaft.
Wherein the included angle α between the winglet and the wing is in the range of 0-90 degrees.
Wherein, when the winglet is erected, the course stability can be increased and the induced resistance of a wingtip can be reduced.
Wherein, install electromagnetic equipment in the winglet, the magnetic attraction that electromagnetic equipment produced makes the winglet butt joint of two airplanes together.
And the two airplanes transmit and exchange data through the close near field communication device.
Preferably, the structure is not limited to two airplanes, and a plurality of airplanes can be combined by the structure.
An aircraft employing a structure for aircraft airborne compounding as described above;
preferably, the aircraft is a fixed wing aircraft.
Based on the technical solution provided by the utility model, the structure for aerial combination of aircraft has one of following beneficial effect at least for prior art:
(1) the utility model has the advantages of easy control of the butt joint mode, flexible adjustment mode, simple butt joint structure and the like.
(2) 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.
Drawings
FIG. 1 is a schematic view of the present invention on an aircraft;
FIG. 2 is a schematic view of the vertical state of the present invention;
FIG. 3 is a schematic view of the horizontal state of the present invention;
fig. 4 is a schematic view of the working states of two airplanes according to the embodiment of the present invention;
fig. 5 is a schematic diagram of three airplanes according to an embodiment of the present invention docked together via winglets.
In the above drawings, the reference numerals have the following meanings:
1. a winglet; 2. a power supply and control device; 3. an airfoil; 4. covering the skin; 5. a lower skin; 6. an electromagnetic device; 7. a near field communication device; 8. a winglet shaft; 9. an actuator; 10. a connecting rod.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings.
The utility model discloses a structure for aerial combination of aircraft, including power and controlling means, electromagnetic equipment, near field communication equipment, pivot, actuator etc. The winglet is positioned on the outer side of the wing, and the winglet can rotate through the rotating shaft, the connecting rod and the actuator and can be maintained at a certain position in the horizontal direction, the vertical direction and the middle direction. Electromagnetic equipment is arranged in the winglets, and adjacent airplanes are butted and tightly attached together through magnetic attraction force generated by the electromagnetic equipment respectively arranged on the winglets. The close winglets can be separated due to the fact that no magnetic attraction force exists through controlling power supply, and the combined aircraft is disassembled into a single aircraft. Near field communication equipment is arranged in the winglet, and the airplane which is successfully docked can transmit data in a near field communication mode. The utility model has the advantages of the butt joint mode is easily controlled, the butt joint structure is simple, etc.
Specifically, the utility model provides a structure for aircraft is combination in air, include: 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.
And one side skin of the winglet is a plane for fitting and butt joint.
The skin on the other side of each winglet is streamline, and the two winglets are butted to form a streamline airfoil.
And 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 at one position.
Wherein the winglet reduces wing length by way of a winglet pivot.
Preferably, after the combined aircraft is formed, the aircraft has the capability of flexibly adjusting the posture through the winglet rotating shaft.
Wherein the included angle α between the winglet and the wing is in the range of 0-90 degrees.
Wherein, when the winglet is erected, the course stability can be increased and the induced resistance of a wingtip can be reduced.
Wherein, install electromagnetic equipment in the winglet, the magnetic attraction that electromagnetic equipment produced makes the winglet butt joint of two airplanes together.
And the two airplanes transmit and exchange data through the close near field communication device.
Preferably, the structure is not limited to two airplanes, and a plurality of airplanes can be combined by the structure.
An aircraft employing a structure for aircraft airborne compounding as described above;
preferably, the aircraft is a fixed wing aircraft.
The following describes the embodiments of the present invention with reference to the accompanying drawings.
A structure for aerial combination of an aircraft comprises a winglet (1), a power supply and control device (2), an electromagnetic device (6), a near field communication device (7), a winglet rotating shaft (8), an actuator (9), a connecting rod (10) and the like.
As shown in fig. 1, an aircraft is fitted with winglets 1 at both ends of the wing 3. The aircraft is internally provided with a power supply and control device 2 which can supply power to the electromagnetic device 6, the near field communication device 7 and the actuator 9 in the wing inside the winglet 1, and the power supply can be, but is not limited to, a battery, a generator and the like.
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 through controlling the actuator 9 to actuate. When flying, the winglet 1 can be erected to reduce the wing tip induced resistance and increase the course stability of the airplane. When the airplane is on the ground, the vertical winglets 1 can reduce the occupied area of the airplane and facilitate the dispatching.
As shown in fig. 2, the lower skin 5 of the winglet 1 is planar and the upper skin 4 has a streamlined aerofoil shape. The lower skin 5 is intended to be in abutting abutment with the lower skin of an adjacent aircraft winglet when the winglet 2 is in the erected position. The upper skin 4 maintains a streamline airfoil shape to reduce the generation of air resistance.
As shown in fig. 2, the winglet 1 is internally provided with an electromagnetic device 6, 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 airplanes are combined in the air at a short distance, the lower skins 5 of the winglets 1 of the two airplanes are attached together under the action of magnetic attraction. The continuously generated magnetic attraction can ensure that the two winglets 1 keep a fixed magnetic connection state, so that the two airplanes become a combined aircraft. The two winglets 1 can be separated due to the fact that power supply is cut off, and the combined aircraft is disassembled into a plurality of single aircrafts.
As shown in fig. 3, the power supply and control device 2 controls the actuator 9 to actuate, via the connecting rod 10 and the rotating shaft 8, to adjust the winglet 1 to a horizontal position.
As shown in fig. 2 and 3, the power and control device 2, the actuator 9, the link 8 and the shaft 10 form a mechanism that allows the winglet 1 to be maintained in a position that is horizontal, vertical and in between, the angle α that the winglet 1 makes with the horizontal position being set and controlled by the power and control device 2.
As shown in fig. 3, the winglet 1 is internally provided with a near field communication device 7, the power supply and control device 2 supplies power to the near field communication device 7, and the near field communication device 7 has information data transmission and exchange capability. After two aircraft are docked via the winglet 1, the aircraft can transmit and exchange data via the near field communication device 6 on the winglet 1. The near field communication device 6 may be, but is not limited to, near field communication technology, bluetooth, optical, etc.
As shown in fig. 4, after adjacent airplanes are combined with each other through the winglets 1, each airplane can independently rotate around the respective rotating shaft 8 to adjust the respective posture, so that the combined new aircraft has certain structural flexibility. Meanwhile, the two winglets 1 are combined into a complete streamline airfoil shape, so that the generation of resistance can be reduced, and the course stability of the combined aircraft is improved.
As shown in fig. 5, the structure of the aircraft combination in the air according to the present invention is applied to three airplanes to perform combination in the air. The utility model discloses do not limit to two or three aircraft combinations. In this way, multiple aircraft may be combined.
The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921694210.XU CN210942221U (en) | 2019-10-10 | 2019-10-10 | Structure for aerial combination of aircraft and aircraft adopting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921694210.XU CN210942221U (en) | 2019-10-10 | 2019-10-10 | Structure for aerial combination of aircraft and aircraft adopting structure |
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| Publication Number | Publication Date |
|---|---|
| CN210942221U true CN210942221U (en) | 2020-07-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921694210.XU Active CN210942221U (en) | 2019-10-10 | 2019-10-10 | Structure for aerial combination of aircraft and aircraft adopting structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525632A (en) * | 2019-10-10 | 2019-12-03 | 中国科学院工程热物理研究所 | The structure combined in the air for aircraft and the aircraft using it |
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2019
- 2019-10-10 CN CN201921694210.XU patent/CN210942221U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525632A (en) * | 2019-10-10 | 2019-12-03 | 中国科学院工程热物理研究所 | The structure combined in the air for aircraft and the aircraft using it |
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