阅读说明：本技术 用于飞行器空中组合的结构及采用其的飞行器 (The structure combined in the air for aircraft and the aircraft using it ) 是由 应培 杨延平 毕莹 张子健 王波 于 2019-10-10 设计创作，主要内容包括：一种用于飞行器空中组合的结构,该结构包括：小翼、电源与控制装置、作动器和连杆；其中：小翼,通过连杆连接于所述飞行器的机翼上,所述飞行器能够通过小翼对接在一起；电源与控制装置,位于所述飞行器内部,用于为飞行器上的用电设备供电,以及通过控制作动器从而控制与维持小翼在空间中的位置。本发明的用于飞行器空中组合的结构,具备对接方式简单灵活的特点,避免因机构故障导致的飞行控制问题。(A kind of structure combined in the air for aircraft, the structure include: winglet, power supply and control device, actuator and connecting rod；Wherein: winglet is connected on the wing of the aircraft by connecting rod, and the aircraft can be docking together by winglet；Power supply and control device are located at the aircraft interior, are used to be carry-on power supply for electrical equipment, and to control and maintain the position of winglet in space by control actuator.The structure combined in the air for aircraft of the invention, has the characteristics of docking mode simple and flexible, flight control problem caused by avoiding because of mechanism-trouble.)

1. a kind of structure combined in the air for aircraft characterized by comprising winglet, power supply and control device, actuator And connecting rod；Wherein:

Winglet is connected on the wing of the aircraft by connecting rod, and the aircraft can be docking together by winglet；

Power supply and control device are located at the aircraft interior, are used to be carry-on power supply for electrical equipment, and pass through control Position of the actuator processed to control with maintenance winglet in space.

2. structure according to claim 1, which is characterized in that a side skin of the winglet is plane, for being bonded Docking.

3. structure according to claim 1, which is characterized in that another side skin of the winglet be it is streamlined, it is two small A streamline aerofoil profile is formed after wing docking.

4. structure according to claim 1, which is characterized in that be equipped with winglet shaft, winglet between the winglet and wing It can be rotated around winglet shaft, and be fixed on a position.

5. structure according to claim 4, which is characterized in that the winglet reduces wing length by winglet shaft.

Preferably, aircraft has the ability that posture is adjusted flexibly by winglet shaft after forming combination aircraft.

6. structure according to claim 1, which is characterized in that angle α is in 0 °~90 ° models between the winglet and wing It encloses.

7. structure according to claim 1, which is characterized in that when the winglet is holded up, can increase shipping-direction stability and Reduce the induced drag of wing tip.

8. structure according to claim 1, which is characterized in that be equipped with electromagnetic equipment in the winglet, electromagnetic equipment produces Raw magnetic attraction makes the winglet of two airplanes be docking together.

9. structure according to claim 1, which is characterized in that be also equipped near field communication means, two framves in the winglet Aircraft by close near field communication means transmit and exchange data.

Preferably, the structure is not limited to two airplanes, multi-aircraft can be also combined with this configuration.

10. a kind of aircraft using such as the described in any item structures combined in the air for aircraft of claim 1~10；

Preferably, the aircraft is fixed wing aircraft.

Technical field

This disclosure relates to the structure that vehicle technology field, more particularly, to aircraft are combined in the air.

Background technique

When aircraft wing generates lift, the pressure ratio upper surface of wing lower surface it is big, and wing span length is that have Limit, so the high pressure draught of lower aerofoil can bypass both ends wing tip, try hard to flow away to the low-pressure area of top airfoil, in tip station shape At tip vortex, and then purling is formed, leads to induced drag.Induced drag affects the aeroperformance of aircraft, reduces boat Journey endurance.A kind of thinking of innovation is that multiple aircrafts are linked together by wing tip, forms combined type aircraft.Combined type Aircraft eliminates the tip vortex and induced drag of single aircraft, increases aircraft aspect ratio, therefore combines aircraft than single A aircraft has higher lift resistance ratio, can reach farther voyage and bigger Weight Loaded.In terms of execution task, combined type Aircraft can be according to task type and requiring flexible transformation form: single aircraft is suitably executed small range small tasks；Combination When, it is remote using voyage, load-carrying is big etc., and advantages execute large complicated task.Aerial combination docking technique is the key that combination aircraft Technology, but there are some problems for the prior art: docking mode mostly uses mechanical connection, and docking operation lacks flexibility, control Required precision is high；Structure is complicated for mechanical splice, and mechanism weight is big, reliability is low, once bindiny mechanism is stuck will to will lead to aircraft It is out of control.

Summary of the invention

In view of this, the main purpose of the present invention is to provide a kind of structures combined in the air for aircraft, to extremely Partially solve at least one of above-mentioned technical problem.

To achieve the goals above, the present invention provides a kind of structures combined in the air for aircraft, comprising: winglet, Power supply and control device, actuator and connecting rod；Wherein:

Winglet is connected on the wing of the aircraft by connecting rod, and the aircraft can be docked at one by winglet It rises；

Power supply and control device are located at the aircraft interior, for being carry-on power supply for electrical equipment, Yi Jitong Cross position of the control actuator to control with maintenance winglet in space.

Wherein, a side skin of the winglet is plane, for being bonded docking.

Wherein, another side skin of the winglet is streamlined, forms a streamline aerofoil profile after two winglet docking.

Wherein, winglet shaft is equipped between the winglet and wing, winglet can be rotated around winglet shaft, and be fixed on one A position.

Wherein, the winglet reduces wing length by winglet shaft.

Preferably, aircraft has the ability that posture is adjusted flexibly by winglet shaft after forming combination aircraft.

Wherein, between the winglet and wing angle α in 0 °~90 ° ranges.

Wherein, when the winglet is holded up, shipping-direction stability can be increased and reduce the induced drag of wing tip.

Wherein, electromagnetic equipment is installed, the magnetic attraction that electromagnetic equipment generates makes the winglet pair of two airplanes in the winglet It is connected together.

Wherein, be also equipped near field communication means in the winglet, two airplanes by close near field communication means pass Defeated and exchange data.

Preferably, the structure is not limited to two airplanes, multi-aircraft can be also combined with this configuration.

A kind of aircraft using the structure combined in the air for aircraft as described above；

Preferably, the aircraft is fixed wing aircraft.

Based on the above-mentioned technical proposal it is found that the structure combined in the air for aircraft of the invention compared with the existing technology extremely One of have the advantages that less:

(1) present invention has many advantages, such as that docking mode is easily controllable, adjustment mode is flexible, docking structure is simple.

(2) structure combined in the air for aircraft of the invention, has the characteristics of docking mode simple and flexible, avoid because Flight control problem caused by mechanism-trouble.

Detailed description of the invention

Fig. 1 is the schematic diagram of the present invention aboard；

Fig. 2 is vertical state schematic diagram of the present invention；

Fig. 3 is horizontality schematic diagram of the present invention；

Fig. 4 is two airplane working state schematic representations of the embodiment of the present invention；

Fig. 5 is that three airplanes of the embodiment of the present invention dock schematic diagram by winglet.

In above-mentioned attached drawing, appended drawing reference meaning is as follows:

1, winglet；2, power supply and control device；3, wing；4, upper covering；5, lower covering；6, electromagnetic equipment；7, near field is logical Believe equipment；8, winglet shaft；9, actuator；10, connecting rod.

Specific embodiment

To make the objectives, technical solutions, and advantages of the present invention clearer, below in conjunction with specific embodiment, and reference Attached drawing, the present invention is described in further detail.

The invention discloses a kind of structure combined in the air for aircraft, including power supply and control device, electromagnetic equipment, Near-field communication equipment, shaft, actuator etc..Winglet is located on the outside of wing, rotates winglet by shaft, connecting rod and actuator, And can maintain winglet it is horizontal, vertical and between some position.Electromagnetic equipment is housed, adjacent aircraft passes through inside winglet The magnetic attraction that the electromagnetic equipment being respectively mounted on winglet generates is docked and is close together.It can be with by control power supply Separate the winglet being close to because no magnetic attraction acts on, making to combine aircraft to disintegrate is single aircraft.Equipped with close inside winglet Field communication equipment, data can be transmitted by near-field communication modes by docking successful aircraft.The present invention is easy to docking mode Control, the advantages that docking structure is simple.

Specifically, the present invention provides a kind of structures combined in the air for aircraft, comprising: winglet, power supply and control Device, actuator and connecting rod；Wherein:

Winglet is connected on the wing of the aircraft by connecting rod, and the aircraft can be docked at one by winglet It rises；

Power supply and control device are located at the aircraft interior, for being carry-on power supply for electrical equipment, Yi Jitong Cross position of the control actuator to control with maintenance winglet in space.

Wherein, a side skin of the winglet is plane, for being bonded docking.

Wherein, another side skin of the winglet is streamlined, forms a streamline aerofoil profile after two winglet docking.

Wherein, winglet shaft is equipped between the winglet and wing, winglet can be rotated around winglet shaft, and be fixed on one A position.

Wherein, the winglet reduces wing length by winglet shaft.

Preferably, aircraft has the ability that posture is adjusted flexibly by winglet shaft after forming combination aircraft.

Wherein, between the winglet and wing angle α in 0 °~90 ° ranges.

Wherein, when the winglet is holded up, shipping-direction stability can be increased and reduce the induced drag of wing tip.

Wherein, electromagnetic equipment is installed, the magnetic attraction that electromagnetic equipment generates makes the winglet pair of two airplanes in the winglet It is connected together.

Wherein, be also equipped near field communication means in the winglet, two airplanes by close near field communication means pass Defeated and exchange data.

Preferably, the structure is not limited to two airplanes, multi-aircraft can be also combined with this configuration.

A kind of aircraft using the structure combined in the air for aircraft as described above；

Preferably, the aircraft is fixed wing aircraft.

The following further describes the specific embodiments of the present invention with reference to the drawings.

A kind of structure combined in the air for aircraft, by winglet 1, power supply and control device 2, electromagnetic equipment 6, near field leads to Believe the compositions such as equipment 7, winglet shaft 8, actuator 9, connecting rod 10.

As shown in Figure 1, aircraft installs winglet 1 at the both ends of wing 3.Interior of aircraft is equipped with power supply and control device 2, can be Electromagnetic equipment 6 inside winglet 1, the actuator 9 in near-field communication equipment 7 and wing are powered, and power supply can be but not limited to electricity Pond, generator etc..

As shown in Fig. 2, winglet 1 forms linkage mechanism by shaft 8 and connecting rod 10 and actuator 9, power supply and controller 2 are logical Control 9 actuation of actuator realization is crossed to adjust the state of winglet 1.When flight, wing tip induced drag can be reduced by holding up winglet 1, And it can increase vector stability.When aircraft is at ground, aircraft occupied area can be reduced by holding up winglet 1, facilitate scheduling.

As shown in Fig. 2, the lower covering 5 of winglet 1 is plane, upper covering 4 has streamline aerofoil profile.Winglet 2 is in cocked position When, lower covering 5 is used to be bonded docking with the lower covering of adjacent aircraft winglet.Upper covering 4 keeps streamline aerofoil profile that can reduce air Resistance generates.

As shown in Fig. 2, being equipped with electromagnetic equipment 6, power supply and control device 2 inside winglet 1 as the power supply of electromagnetic equipment 6, make electricity Magnetic machine 6 generates magnetic force.When adjacent aircraft is closely combined in the air, acted on by magnetic attraction, the winglet 1 of two airplanes The lower fitting of covering 5 is together.The magnetic attraction persistently generated can make two winglets 1 be kept fixed magnetic connection status, make two airplanes at For a combination aircraft.Cutting power supply can be such that two winglets 1 separate because no magnetic attraction acts on, and make to combine aircraft disintegration For multiple monomer aircrafts.

As shown in figure 3, power supply and control device 2 control 9 actuation of actuator, by connecting rod 10 and shaft 8, winglet 1 is adjusted To horizontal position.

As shown in Figure 2,3, the mechanism that power supply and control device 2, actuator 9, connecting rod 8 and shaft 10 form can make winglet 1 maintain it is horizontal, vertical and between some position, the angle α that winglet 1 and horizontal position are formed is by power supply and control device 2 It sets and controls implementation.

As shown in figure 3, being equipped with near-field communication equipment 7, power supply and control device 2 inside winglet 1 as the confession of near-field communication equipment 7 Electricity, near-field communication equipment 7 have information data transmission exchange capacity.After two aircrafts are docked by winglet 1, aircraft can be by small Near-field communication equipment 6 on the wing 1 carries out data transmission and exchanges.Near-field communication equipment 6 can be but not limited to near-field communication skill The modes such as art, bluetooth, optics.

As shown in figure 4, every airplane can be independently around respective after adjacent aircraft is combined with each other together by winglet 1 Shaft 8 rotate, the new aircraft for adjusting respective posture, therefore being composed have certain structural flexibility.Two winglets 1 simultaneously It is combined into a complete streamline aerofoil profile, it is possible to reduce resistance generates, and increases the shipping-direction stability of combination aircraft.

As shown in figure 5, to be carried out by the structure for combining aircraft of the present invention in the air applied to three airplanes The schematic diagram combined in the air.The present invention is not limited to two framves or the combination of three airplanes.By this method, multi-aircraft can be real Now combine.

Particular embodiments described above has carried out further in detail the purpose of the present invention, technical scheme and beneficial effects Describe in detail bright, it should be understood that the above is only a specific embodiment of the present invention, is not intended to restrict the invention, it is all Within the spirit and principles in the present invention, any modification, equivalent substitution, improvement and etc. done should be included in protection of the invention Within the scope of.