WO2024060633A1 - Aircraft wing having integrated distributed ducted fan, and electric aircraft - Google Patents

Abstract

An aircraft wing (10) having an integrated distributed ducted fan, the aircraft wing (10) being attached to a fuselage (20) and being provided with a ducted fan power set (30), wherein the ducted fan power set (30) is provided on an inboard section (11) of the aircraft wing (10) and is arranged above the aircraft wing (10) so as to form an integral body with the aircraft wing (10), and wherein the inboard section (11) comprises an inboard flap (11a), the inboard flap (11a) being able to move between a first extended position and a first retracted position, and wherein, when in the first extended position, the inboard flap (11A) protrudes relative to the inboard section (11) and abuts against the trailing edge of the ducted fan power set (30), and when in the first retracted position, the inboard flap (11A) is retracted relative to the inboard section (11). The inboard flap (11A) is a movable component. In this way, when necessary, the inboard flap (11A) extends rearwards and deflects, and the jet of air outputted by the ducted fan, under the action of the Coanda effect, respectively produces a low-pressure area and a high-pressure area on the upper surface and the lower surface of the inboard flap (11A), achieving wing lift.

Description

集成有分布式涵道风扇的机翼和电动飞机Wings and electric aircraft with integrated distributed ducted fans 技术领域Technical field

本发明属于航空飞行器领域，具体涉及一种电动飞机。另外，本发明还涉及一种安装在电动飞机中的集成有分布式涵道风扇的机翼。The invention belongs to the field of aviation aircraft, and specifically relates to an electric aircraft. In addition, the invention also relates to a wing integrated with a distributed ducted fan installed in an electric aircraft.

背景技术Background technique

随着航空业的发展，飞机运行所产生的有害气体污染和油耗等环保问题逐渐受到关注。当前，主流民用大型飞机通常采用下单翼、多发大涵道比涡扇发动机、低平尾的飞机气动布局形式。发动机为了实现大推力、低油耗、高推重比等目标，兼顾高可靠性等使用要求，将性能优化到了极致，导致其组成结构非常复杂、工艺实现难度高。采用大涵道比涡扇发动机作为动力***的主流民用飞机的气动布局形式已基本趋于最优方案，其气动性能及效率难有显著的提升空间，因此难以满足人们对其绿色环保、高效低耗的要求。With the development of the aviation industry, environmental issues such as harmful gas pollution and fuel consumption generated by aircraft operation have gradually attracted attention. At present, mainstream large civilian aircraft usually adopt the aerodynamic layout of a low-wing monoplane, multiple large-bypass ratio turbofan engines, and a low horizontal tail. In order to achieve goals such as high thrust, low fuel consumption, and high thrust-to-weight ratio, as well as high reliability and other operational requirements, the engine's performance has been optimized to the extreme, resulting in a very complex structure and high difficulty in process implementation. The aerodynamic layout of mainstream civil aircraft using high-bypass-ratio turbofan engines as their power systems has basically become the optimal solution. There is little room for significant improvement in their aerodynamic performance and efficiency. Therefore, it is difficult to satisfy people's concerns about greenness, environmental protection, high efficiency and low efficiency. consumption requirements.

为了发展绿色航空，分布式电推进技术逐渐成为各国重点发展方向。分布式涵道风扇电推进是分布式电推进的一种重要动力形式，正在被越来越多的人关注。分布式涵道风扇能够提升等效涵道比，与机翼的深度耦合能够提升爬升和巡航阶段的升阻比，多台动力实现安全冗余，可以利用动力差调整飞行姿态等多种优势。In order to develop green aviation, distributed electric propulsion technology has gradually become a key development direction for various countries. Distributed ducted fan electric propulsion is an important power form of distributed electric propulsion and is attracting more and more attention. The distributed ducted fan can improve the equivalent bypass ratio, and its deep coupling with the wing can improve the lift-to-drag ratio during climb and cruise phases. Multiple power units can achieve safety redundancy, and the power difference can be used to adjust the flight attitude.

因此，迫切需要提供一种改进的集成有分布式涵道风扇的电动飞机，这种电动飞机能够克服现有技术中存在的一个或多个缺点。Therefore, there is an urgent need to provide an improved electric aircraft integrated with distributed ducted fans that can overcome one or more shortcomings of the prior art.

发明内容Summary of the invention

本发明从飞机及其机翼的气动和结构部件的角度出发，提供了一种具有或者集成有分布式涵道风扇的机翼以及包括这种机翼的电动飞机。From the perspective of the aerodynamic and structural components of an aircraft and its wing, the present invention provides an airfoil with or integrated with a distributed ducted fan and an electric aircraft including such an airfoil.

通过“分布式涵道风扇-机翼-机身”融合设计的先进气动布局形式，利用涵道风扇的抽吸作用，能够减小飞机的飞行阻力，提高其升阻比，使其能够发挥以电动机为核心的动力***的可分割性、结构简单、操纵灵敏以及能源利用效率高等优点。根据本发明的飞机可以采用诸如锂电池之类的动力 电池作为能源载体，可以实现民用飞机“低碳”排放甚至“零碳”排放，并且提高飞机的环保性和经济性。Through the advanced aerodynamic layout form of "distributed ducted fan-wing-fuselage" integrated design, the suction effect of the ducted fan can be used to reduce the aircraft's flight resistance and improve its lift-to-drag ratio, allowing it to perform The power system with the electric motor as the core has the advantages of divisibility, simple structure, sensitive operation and high energy utilization efficiency. The aircraft according to the invention can be powered by lithium batteries such as As an energy carrier, batteries can achieve "low-carbon" or even "zero-carbon" emissions for civil aircraft, and improve the environmental protection and economy of aircraft.

根据本发明的一个方面，提出了一种集成有分布式涵道风扇的机翼，该机翼可以附连到机身并且设有涵道风扇动力组，其中，涵道风扇动力组可以设置机翼的内段翼上，并且布置在机翼的上方以与机翼成整体，并且其中，内段翼包括内段翼襟翼，内段翼襟翼能够在第一伸出位置和第一缩回位置之间移动，并且其中，内段翼襟翼在位于第一伸出位置时相对于内段翼伸出并紧靠涵道风扇动力组的后缘布置，并且内段翼襟翼在位于第一缩回位置时相对于内段翼缩回并叠置在内段翼下方。According to one aspect of the present invention, an airfoil integrated with a distributed ducted fan is proposed. The airfoil can be attached to the fuselage and provided with a ducted fan power unit, wherein the ducted fan power unit can be provided with the fuselage. on the inner section of the wing and arranged above the wing to be integral with the wing, and wherein the inner section of the wing includes an inner section of wing flap, the inner section of the wing flap can be in the first extended position and the first retracted position. move between the back position, and wherein the inner wing flap extends relative to the inner wing and is arranged close to the trailing edge of the ducted fan power unit when it is in the first extended position, and the inner wing flap is in the first extended position. In the first retracted position, it is retracted relative to the inner wing and stacked below the inner wing.

根据本发明的内段翼襟翼是活动部件。这样，在需要时，例如在起飞和降落时，内段翼襟翼可以向后伸出并偏转，涵道风扇喷射出的气流在科恩达效应的作用下沿内翼段襟翼的上表面流动，产生低压区，而偏转的内翼段襟翼的下翼面阻碍气体流动，在机翼下翼面形成高压区，两者相互结合起作用，从而达到机翼增升效果。而在缩回后，内段翼襟翼在叠置在内段翼下方，可以减少气流阻力，以利于飞机的高速飞行。The inner wing flap according to the invention is a movable part. In this way, when needed, such as during takeoff and landing, the inner wing flaps can be extended rearward and deflected, and the airflow ejected from the ducted fan flows along the upper surface of the inner wing flaps under the action of the Coanda effect. , creating a low-pressure area, and the lower surface of the deflected inner wing flap blocks the flow of air, forming a high-pressure area on the lower surface of the wing. The two work together to achieve the effect of increasing wing lift. After retracting, the inner wing flaps are stacked under the inner wing, which can reduce airflow resistance and facilitate the high-speed flight of the aircraft.

根据本发明的上述方面，较佳地，内段翼可以包括设置在后缘的襟翼容纳部，襟翼容纳部具有凹入的下表面，并且内段翼襟翼具有凸起的上表面，内段翼襟翼在位于第一缩回位置时使凸起的上表面与襟翼容纳部的凹入的下表面配合。According to the above-mentioned aspect of the present invention, preferably, the inner wing may include a flap accommodating portion arranged at the trailing edge, the flap accommodating portion having a concave lower surface, and the inner wing flap having a convex upper surface, and the inner wing flap makes the convex upper surface cooperate with the concave lower surface of the flap accommodating portion when the inner wing flap is located in the first retracted position.

这样，在不需要机翼增升效果时，例如完成起飞或降落后，内翼段襟翼可以收回到襟翼容纳部，从而与主翼组合成一个完整机翼。这样，使得该机翼具有合适的气动外形，以尽可能降低飞行或地面滑行时的阻力。In this way, when the wing's lift effect is not needed, such as after takeoff or landing, the inner wing section flaps can be retracted into the flap accommodating portion, thereby being combined with the main wing to form a complete wing. In this way, the wing has a suitable aerodynamic shape to minimize drag during flight or taxiing on the ground.

根据本发明的上述方面，较佳地，内段翼襟翼在第一伸出位置与第一缩回位置之间的移动可以遵循圆弧形的移动路径，并且凹入的下表面和凸起的上表面各自形成为配合时能互补的圆弧形轮廓。According to the above aspect of the present invention, preferably, the movement of the inner section wing flap between the first extended position and the first retracted position can follow an arc-shaped movement path, and the concave lower surface and the protrusion The upper surfaces of each are formed into arc-shaped profiles that can complement each other when mated.

通过这种设置，能够使得分布式电动涵道风扇推进***与机翼主翼光滑连接，并且在内段翼襟翼的运动期间，在涵道风扇和机翼之间无间隔缝隙，从而能够更好地利用科恩达效应，进而获得期望的机翼增升效果。Through this arrangement, the distributed electric ducted fan propulsion system can be smoothly connected to the main wing of the wing, and during the movement of the inner wing flap, there is no gap between the ducted fan and the wing, so that it can better Make full use of the Coanda effect to achieve the desired wing lift effect.

根据本发明的上述方面，较佳地，内段翼襟翼可以为机翼上表面吹气襟 翼。通过这种设置，能大幅提高机翼的低速升力，从而降低起飞和降落时的速度，缩短滑跑距离，同时降低了对起降所需的跑道长度的要求。According to the above aspect of the present invention, preferably, the inner wing flap can be a wing upper surface blowing flap. This setting can greatly improve the low-speed lift of the wing, thereby reducing the speed during takeoff and landing, shortening the taxiing distance, and reducing the requirement for the runway length required for takeoff and landing.

根据本发明的上述方面，较佳地，在机身的每一侧上，内段翼襟翼在第一方向上的长度可以与涵道风扇动力组的长度相同。这样，使得机翼具有更加平滑的气动外形，从而在增大机翼升力的同时，尽可能减少阻力。According to the above aspect of the present invention, preferably, on each side of the fuselage, the length of the inner wing flap in the first direction may be the same as the length of the ducted fan power unit. This gives the wing a smoother aerodynamic shape, thereby increasing the wing's lift while minimizing drag.

根据本发明的上述方面，较佳地，涵道风扇动力组可以包括至少两个涵道动力单元，较佳地包括5个涵道动力单元，其中，每个涵道动力单元可以包括涵道、可旋转地固定在涵道内的螺旋桨、以及驱动地连接到螺旋桨的电机。According to the above aspect of the present invention, preferably, the ducted fan power unit may include at least two ducted power units, preferably 5 ducted power units, wherein each ducted power unit may include a duct, A propeller rotatably fixed within the duct, and an electric motor drivingly connected to the propeller.

通过这种布置，能够利用多个涵道动力单元实现安全冗余，并且可以利用涵道动力单元之间的动力差调整飞行姿态等。Through this arrangement, multiple ducted power units can be used to achieve safety redundancy, and the power difference between the ducted power units can be used to adjust the flight attitude, etc.

根据本发明的上述方面，较佳地，涵道可以包括在第二方向上顺序布置的涵道进气段和涵道等直段，其中，涵道进气段可以包括矩形进气段和平滑连接到矩形进气段的多个单独的圆形进气段，并且涵道等直段可以设置在每个圆形进气段的下游。这样，可以方便进气，并且利用涵道风扇的抽吸作用，进一步减小飞机的飞行阻力，提高其升阻比。According to the above aspect of the present invention, preferably, the duct may include a duct inlet section and a straight section of the duct arranged sequentially in the second direction, wherein the duct inlet section may include a rectangular inlet section and a smooth inlet section. A plurality of individual circular air inlet sections are connected to the rectangular air inlet section, and straight sections such as ducts can be provided downstream of each circular air inlet section. In this way, air intake can be facilitated, and the suction effect of the ducted fan can be used to further reduce the flight resistance of the aircraft and improve its lift-to-drag ratio.

根据本发明的上述方面，较佳地，涵道风扇动力组还可以包括设置在涵道等直段的静叶和与静叶固定连接的桨毂，电机的壳体固定到桨毂，而电机的驱动轴附连到螺旋桨。这种结构一方面可以借助静叶实现螺旋桨的固定和支承，并且借助叶片的外形优化气流的引导，另一方面，通过桨毂包围电机及各种辅助结构，可以进一步减少气动阻力。According to the above aspect of the present invention, preferably, the ducted fan power unit may also include a stator blade arranged in a straight section such as the duct and a propeller hub fixedly connected to the stator blade. The housing of the motor is fixed to the propeller hub, and the motor The drive shaft is attached to the propeller. On the one hand, this structure can use the stator blades to fix and support the propeller, and use the shape of the blades to optimize the guidance of airflow. On the other hand, the propeller hub surrounds the motor and various auxiliary structures, which can further reduce aerodynamic resistance.

根据本发明的上述方面，为了进一步有利于气流的引导并且方便涵道的排气，较佳地，涵道还可以包括在第二方向上布置在涵道等直段下游的涵道排气段，涵道排气段的后端设置有排气口，较佳地，排气口的形状为矩形、圆角矩形或圆形。According to the above aspect of the present invention, in order to further facilitate the guidance of air flow and facilitate the exhaust of the duct, preferably, the duct may also include a duct exhaust section arranged downstream of a straight section such as the duct in the second direction. , the rear end of the ducted exhaust section is provided with an exhaust port. Preferably, the shape of the exhaust port is a rectangle, a rounded rectangle or a circle.

根据本发明的上述方面，较佳地，涵道风扇动力组可以与机翼平滑连接，并且在涵道风扇动力组与机翼之间无间隔缝隙。这样，通过“分布式涵道风扇-机翼-机身”融合设计的先进气动布局形式，使得在机翼上形成平滑的气动轮廓，进一步减少飞行阻力，进而提高其升阻比。 According to the above aspects of the present invention, preferably, the ducted fan power unit can be smoothly connected to the wing, and there is no gap between the ducted fan power unit and the wing. In this way, through the advanced aerodynamic layout form of the "distributed ducted fan-wing-fuselage" fusion design, a smooth aerodynamic profile is formed on the wing, further reducing flight resistance and thereby improving its lift-to-drag ratio.

根据本发明的上述方面，较佳地，内段翼的内段翼前缘的第一后掠角可以在25°-35°的范围内，较佳地，第一后掠角为30°，而内段翼11的内段翼后缘11D的第二后掠角可以小于5°，较佳地，第二后掠角为0°。通过这种设置，能够在飞行时提供较大的升力，延缓流动分离，并且也能够避免较大的低头力矩According to the above aspect of the present invention, preferably, the first sweep angle of the inner wing leading edge of the inner wing can be in the range of 25°-35°. Preferably, the first sweep angle is 30°. The second sweep angle of the inner wing trailing edge 11D of the inner wing 11 may be less than 5°. Preferably, the second sweep angle is 0°. This arrangement can provide greater lift during flight, delay flow separation, and avoid large bowing moments.

根据本发明的上述方面，为了进一步改善机翼的操控性能并优化其气动外形，较佳地，机翼还可以包括设置在内段翼外侧的外段翼，其中，外段翼的外段翼前缘的第三后掠角可以在15°-25°的范围内，较佳地，第三后掠角为20°。According to the above aspects of the invention, in order to further improve the handling performance of the wing and optimize its aerodynamic shape, preferably, the wing may also include an outer wing arranged on the outside of the inner wing, wherein the third sweep angle of the leading edge of the outer wing of the outer wing may be in the range of 15°-25°, preferably, the third sweep angle is 20°.

根据本发明的上述方面，较佳地，外段翼可以包括外段翼襟翼，外段翼襟翼能够相对于外段翼在第二伸出位置和第二缩回位置之间移动，并且其中，在第二伸出位置中，外段翼襟翼延伸超出外段翼的后缘，而在第二缩回位置中，外段翼襟翼叠置在外段翼下方。According to the above aspect of the present invention, preferably, the outer wing section may include an outer section wing flap, the outer section wing flap can move between a second extended position and a second retracted position relative to the outer section wing, and Wherein, in the second extended position, the outer wing flaps extend beyond the trailing edge of the outer wing, and in the second retracted position, the outer wing flaps overlap below the outer wing.

同样地，这种设置可以在起飞和降落时，实现机翼增升效果，并且在完成起飞或降落后，可以尽可能降低飞行或地面滑行时的阻力，从而灵活地适应起飞、降落、滑行和巡航时的不同要求。Similarly, this setting can achieve the effect of increasing wing lift during takeoff and landing, and after completing takeoff or landing, it can reduce the resistance during flight or taxiing on the ground as much as possible, thus flexibly adapting to takeoff, landing, taxiing and Different requirements when cruising.

根据本发明的上述方面，较佳地，为了进一步增加起降时机翼的增升效果，外段翼襟翼可以采用富勒襟翼的形式。According to the above aspects of the present invention, preferably, in order to further increase the lift-increasing effect of the wing during takeoff and landing, the outer wing flaps may be in the form of Fuller flaps.

根据本发明的上述方面，较佳地，机翼还可以包括设置在外段翼外侧的翼尖小翼。这种布置能够用于减小翼尖涡流，减小诱导阻力，从而提升了飞机的能源经济性。According to the above aspect of the present invention, preferably, the wing may further include a winglet arranged outside the outer segment wing. This arrangement can be used to reduce wingtip vortices and induced drag, thereby improving the energy economy of the aircraft.

根据本发明的上述方面，较佳地，机翼还可以包括附连到外段翼的副翼，副翼在靠近翼尖小翼的位置处设置在外段翼的后缘。这样，当飞机需要滚转机动时，两侧副翼可以朝向相反的方向偏转。这样，借助两侧升力的不对称性来产生滚转力矩，从而控制飞机的滚转运动。According to the above aspect of the present invention, preferably, the wing may further include ailerons attached to the outer wing section, the ailerons being disposed on the trailing edge of the outer section wing near the wingtip winglets. In this way, when the aircraft needs to roll, the ailerons on both sides can deflect in opposite directions. In this way, the asymmetry of the lift on both sides is used to generate a rolling moment, thereby controlling the rolling motion of the aircraft.

根据本发明的另一方面，还提出了一种电动飞机，该电动飞机可以包括根据以上面中的任一项所述的集成有分布式涵道风扇的机翼，该机翼可以布置在电动飞机的机身的中部。According to another aspect of the present invention, an electric aircraft is also proposed. The electric aircraft may include a wing integrated with a distributed ducted fan according to any of the above, and the wing may be arranged on an electric The middle part of the aircraft's fuselage.

根据本发明的上述方面，较佳地，电动飞机还可以包括尾翼，尾翼采用T 型尾气动布局形式。这种布局形式能够有利地适应分布式涵道风扇布置在机翼上方的气动控制。According to the above aspect of the present invention, preferably, the electric aircraft can also include a tail wing, and the tail wing adopts T Type tail aerodynamic layout form. This layout can advantageously adapt to the aerodynamic control of distributed ducted fans placed above the wing.

根据本发明的上述方面，较佳地，尾翼可以包括垂直尾翼和水平尾翼，垂直尾翼竖直设置在电动飞机的尾部处，并且沿着电动飞机的由第二方向和第三方向限定的竖直中心平面布置，水平尾翼设置在垂直尾翼的顶部处，并且在第三方向上的高度高于机翼。通过这种布置，能够减弱机翼下洗和涵道风扇喷流的影响，避免涵道风扇动力组的喷流对平尾产生干扰。According to the above aspect of the present invention, preferably, the tail may include a vertical tail and a horizontal tail, the vertical tail being vertically disposed at the tail of the electric aircraft and along the vertical direction defined by the second direction and the third direction of the electric aircraft. In a center plane arrangement, the horizontal tail is set at the top of the vertical tail and is higher than the wing in a third direction. Through this arrangement, the effects of wing downwash and ducted fan jets can be weakened, and the jets of the ducted fan power unit can be prevented from interfering with the horizontal tail.

根据本发明的上述方面，为了更好地引导气流并且优化飞机的动力学外形，较佳地，垂直尾翼可以包括第一翼段和第二翼段，其中，第一翼段设置在第二翼段下方，并且第一翼段的前缘的后掠角可以大于第二翼段的前缘的后掠角。According to the above aspect of the present invention, in order to better guide the airflow and optimize the dynamic shape of the aircraft, preferably, the vertical tail can include a first wing section and a second wing section, wherein the first wing section is disposed on the second wing below the section, and the sweep angle of the leading edge of the first wing section may be greater than the sweep angle of the leading edge of the second wing section.

根据本发明的上述方面，较佳地，垂直尾翼包括可以方向舵，方向舵设置在垂直尾翼的后缘，并且较佳地，方向舵能够在第一方向上和与第一方向相反的方向上分别偏转30°。方向舵是产生偏航力矩的主要部件，其位于垂直尾翼的后缘，通过运动机构与垂直尾翼连接，可以向左或向右偏转，从而控制飞机的偏转运动。According to the above aspect of the present invention, preferably, the vertical tail includes a rudder, the rudder is provided on the trailing edge of the vertical tail, and preferably, the rudder can be deflected by 30 degrees in the first direction and in the direction opposite to the first direction. °. The rudder is the main component that generates yaw moment. It is located at the trailing edge of the vertical tail. It is connected to the vertical tail through a motion mechanism and can be deflected to the left or right to control the yaw movement of the aircraft.

根据本发明的上述方面，较佳地，水平尾翼可以包括升降舵，升降舵设置在水平尾翼的后缘，并且较佳地，升降舵能够在第三方向上和与第三方向相反的方向上分别偏转30°。升降舵是产生偏航力矩的主要部件，其位于垂直尾翼的后缘，通过运动机构与垂直尾翼连接，可以向上或向下偏转，从而控制飞机的俯仰运动。According to the above aspect of the present invention, preferably, the horizontal tail can include an elevator, the elevator is provided on the trailing edge of the horizontal tail, and preferably, the elevator can be deflected by 30° in the third direction and in the direction opposite to the third direction. . The elevator is the main component that generates yaw moment. It is located on the trailing edge of the vertical tail. It is connected to the vertical tail through a motion mechanism and can deflect upward or downward to control the pitching motion of the aircraft.

根据本发明的上述方面，较佳地，电动飞机可以是滑跑起飞式飞机，并且包括前三点式起落架，前三点式起落架包括前起落架和主起落架，其中，主起落架设置在机翼的内段翼下方。According to the above aspects of the present invention, preferably, the electric aircraft can be a taxiing take-off aircraft and include a tricycle landing gear. The tricycle landing gear includes a nose landing gear and a main landing gear, wherein the main landing gear is arranged on the wing. underneath the inner section of the wing.

根据本发明的上述方面，较佳地，电动飞机还包括动力电池，动力电池靠近机身布置在机翼的内段翼内部和/或布置在机身内的下部。这种布置，能够有利地减小飞机的滚动转动惯量。According to the above aspect of the present invention, preferably, the electric aircraft further includes a power battery, and the power battery is arranged inside the inner section of the wing close to the fuselage and/or arranged in the lower part of the fuselage. This arrangement can advantageously reduce the rolling moment of inertia of the aircraft.

本发明采用“分布式涵道风扇-机翼-机身”融合设计的先进气动布局形式，能够增大飞机的升阻比和减小巡航阻力，提升了飞机的经济性。本发 明运用分布式涵道风扇电推进***作为动力***，不使用燃油发动机和化石燃料，能源利用效率高、无污染、噪音小、环保性好。This invention adopts the advanced aerodynamic layout form of "distributed ducted fan-wing-fuselage" integrated design, which can increase the lift-to-drag ratio of the aircraft and reduce the cruise resistance, thereby improving the economy of the aircraft. This hair Ming uses a distributed ducted fan electric propulsion system as the power system. It does not use fuel engines and fossil fuels. It has high energy utilization efficiency, no pollution, low noise, and good environmental protection.

由此，通过本发明的集成有分布式涵道风扇的机翼和包括这种机翼的电动飞机能够满足使用要求，克服了现有技术的缺点并且实现了预定的目的。Therefore, the wing integrated with distributed ducted fans of the present invention and the electric aircraft including such wing can meet the usage requirements, overcome the shortcomings of the existing technology, and achieve the intended purpose.

附图说明Description of drawings

为了进一步清楚地描述根据本发明的集成有分布式涵道风扇的机翼和包括这种机翼的电动飞机，下面将结合附图和具体实施方式对本发明进行详细说明，在附图中：In order to further clearly describe the wing integrated with distributed ducted fans and the electric aircraft including such wing according to the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. In the accompanying drawings:

图1是根据本发明的非限制性实施例的电动飞机的后视轴测示意图，该电动飞机集成有分布式涵道风扇的机翼；FIG. 1 is a rear isometric schematic diagram of an electric aircraft according to a non-limiting embodiment of the present invention, the electric aircraft having a wing integrated with a distributed ducted fan;

图2是根据本发明的非限制性实施例的电动飞机的前视轴测示意图，该电动飞机集成有分布式涵道风扇的机翼；以及Figure 2 is a schematic front view isometric view of an electric aircraft with integrated distributed ducted fan wings in accordance with a non-limiting embodiment of the present invention; and

图3是本发明根据本发明的非限制性实施例的涵道风扇动力单元的中心截面的剖视示意图。3 is a schematic cross-sectional view of a central section of a ducted fan power unit according to a non-limiting embodiment of the present invention.

上述附图仅仅是示意性的，未严格按照比例绘制。The above drawings are schematic only and are not strictly to scale.

图中的附图标记在附图和实施例中的列表：
100-电动飞机，包括：
10-机翼，包括：
11-内段翼，包括：
11A-内段翼襟翼；
11B-襟翼容纳部；
11C-内段翼前缘；
11D-内段翼后缘；
12-外段翼，包括：
12A-外段翼前缘；
12B-外段翼襟翼；
12C-副翼；
13-翼尖小翼；
20-机身，包括：
21-机头；
22-中机身；
23-后机身；
30-涵道风扇动力组，包括：
31-涵道；
311-涵道进气段，包括：
311A-矩形进气段；
311B-圆形进气段；
312-涵道等直段；
313-涵道排气段；
32-螺旋桨；
33-电机；
34-静叶；
35-桨毂；
36-涵道顶盖；
37-涵道附件；
40-尾翼，包括：
41-垂直尾翼，包括：
41A-第一翼段；
41B-第二翼段；
41C-方向舵；
42-水平尾翼，包括：
42A-升降舵；
50-前三点式起落架；
60-动力电池；
A-第一方向；
B-第二方向；
C-第三方向。Reference numbers in the Figures List of Figures and Examples:
100-Electric aircraft, including:
10-Wing, including:
11-Inner wing, including:
11A-Inner wing flap;
11B-Flap receiving part;
11C-Inner wing leading edge;
11D-Inner wing trailing edge;
12-Outer wing, including:
12A-Outer section wing leading edge;
12B-Outer wing flap;
12C-Aileron;
13-winglets;
20-Airframe, including:
21-machine head;
22-middle fuselage;
23-rear fuselage;
30-Ducted fan power pack, including:
31-Culvert;
311-Ducted air intake section, including:
311A-rectangular air inlet section;
311B-circular air inlet section;
312-Culvert and other straight sections;
313-ducted exhaust section;
32-Propeller;
33-Motor;
34-static leaves;
35-Propeller hub;
36-Culvert top cover;
37-Duct attachment;
40-tail, including:
41-Vertical tail, including:
41A-First wing section;
41B-Second wing section;
41C-rudder;
42- Horizontal tail, including:
42A-Elevator;
50-front tricycle landing gear;
60-power battery;
A-first direction;
B-second direction;
C-Third direction.

具体实施方式Detailed ways

应当理解，除非明确地指出相反，否则本发明可以采用各种替代的取向和步骤顺序。还应当理解，附图中所示及说明书中描述的具体装置仅是本文公开和限定的发明构思的示例性实施例。因而，除非另有明确的声明，否则所公开的各种实施例涉及的具体取向、方向或其它物理特征不应被视为限制。It should be understood that, unless expressly stated otherwise, the present invention may adopt various alternative orientations and step sequences. It should also be understood that the specific devices shown in the drawings and described in the specification are merely exemplary embodiments of the inventive concepts disclosed and defined herein. Therefore, unless otherwise expressly stated, the specific orientations, directions or other physical characteristics of the various embodiments disclosed should not be considered as limiting.

图1是根据本发明的非限制性实施例的电动飞机100的后视轴测示意图；而图2是根据本发明的非限制性实施例的电动飞机100的前视轴测示意图，该电动飞机集成有分布式涵道风扇的机翼10。1 is a schematic rear view isometric view of an electric aircraft 100 according to a non-limiting embodiment of the present invention; and FIG. 2 is a schematic front view isometric view of an electric aircraft 100 according to a non-limiting embodiment of the present invention. The electric aircraft Wing 10 integrated with distributed ducted fans.

如图所示并且作为非限制性实施例，电动飞机100可以是滑跑起飞式电动飞机，并且主要可以包括机翼10、机身20、涵道风扇动力组30、尾翼40、前三点式起落架50和动力电池60等。As shown in the figure and as a non-limiting example, the electric aircraft 100 may be a roll-off electric aircraft, and may mainly include a wing 10 , a fuselage 20 , a ducted fan power unit 30 , a tail 40 , and a tricycle landing gear. 50 and power battery 60 etc.

如本领域中已知的，机翼10可以固定到机身20，并且机翼10是产生升力的主要部件，用于在飞机飞行过程中产生升力，是飞机能够飞行的根本保障。As is known in the art, the wing 10 can be fixed to the fuselage 20, and the wing 10 is the main component that generates lift. It is used to generate lift during the flight of the aircraft and is the fundamental guarantee for the aircraft to be able to fly.

机身20可以是传统的桶状机身。机身20主要是为电池、乘客或货物提供运载空间，并且将机翼(主翼)10、尾翼40和起落架50等各个部件固定地连接在一起。在附图示出的实施例中，机身20可以大致包括机头21、中机身22和后机身23。The fuselage 20 may be a traditional barrel-shaped fuselage. The fuselage 20 mainly provides carrying space for batteries, passengers or cargo, and fixedly connects various components such as the wing (main wing) 10, the tail 40 and the landing gear 50 together. In the embodiment shown in the drawings, the fuselage 20 may generally include a nose 21 , a middle fuselage 22 and a rear fuselage 23 .

作为较佳实施例并且如图1和2中示出的，机头21可以采用一体化流线型仿生机头，使得能够减小气动阻力。中机身22可以为近似等直段的柱体形式。As a preferred embodiment and as shown in Figures 1 and 2, the handpiece 21 may adopt an integrated streamlined bionic handpiece, so that aerodynamic resistance can be reduced. The middle fuselage 22 may be in the form of a cylinder with approximately equal straight sections.

根据本发明的实施例，机翼10可以连接到中机身22，并且在中机身22下端两侧可以设有便于与机翼10连接的整流包结构。中机身22可以有较高的客舱高度，实现大部分场景下旅客不弯腰低头进入，拥有较大的舷窗，提供更好视野，具有较好的乘坐舒适性。后机身23可以安装有尾翼40、辅助动力源(未示出)等结构。 According to an embodiment of the present invention, the wing 10 may be connected to the middle fuselage 22 , and rectification package structures may be provided on both sides of the lower end of the middle fuselage 22 to facilitate connection with the wing 10 . The mid-fuselage 22 can have a higher cabin height, allowing passengers to enter without bending down in most scenarios. It has larger portholes, provides better visibility, and has better riding comfort. The rear fuselage 23 may be equipped with structures such as a tail 40 and an auxiliary power source (not shown).

根据本发明的实施例，机翼10为下单翼布局，并且可以包括内段翼11、外段翼12以及翼尖小翼13。作为示例，内段翼也可以称为內翼段，而外段翼也可以称为外翼段。According to an embodiment of the present invention, the wing 10 has a lower wing layout and may include an inner wing 11 , an outer wing 12 and a winglet 13 . As an example, the inner wing section may also be called an inner wing section, and the outer wing section may also be called an outer wing section.

如本文所用的“内”和“外”是指相对于机身20的位置，例如内段翼11可以是机翼10的更靠近机身20的翼段。另外，如本文所用的“前”和“后”是指相对于机头21的位置，例如，前缘可以定位成更靠近机头21或朝向机头21延伸，而后缘可以定位成更远离机头21或远离机头21延伸。“Inner” and “outer” as used herein refer to a position relative to the fuselage 20 , for example the inner wing section 11 may be a section of the wing 10 closer to the fuselage 20 . Additionally, "front" and "rear" as used herein refer to positions relative to the machine head 21 , for example, the leading edge may be positioned closer to or extend toward the machine head 21 , while the trailing edge may be positioned farther away from the machine head 21 . The head 21 may extend away from the machine head 21 .

通常，机翼10可以包括多个机翼支承构件，例如纵向支承构件和横向支承构件等，这些支承构件具有期望的强度和刚度。作为较佳实施例，机翼支承构件可以由诸如碳纤维预浸料之类的复合材料制成。例如，可以将碳纤维预浸料按照铺贴方向铺贴，并且，在常温固化后按照机翼支承构件最终形状进行机械加工制成。另外，机翼10可以包括相应的蒙皮结构，蒙皮例如也可以由诸如碳纤维材料之类的复合材料制成，并且可以按照本领域已知的方式包覆固定到机翼支承构件。Generally, the wing 10 may include a plurality of wing support members, such as longitudinal support members, transverse support members, etc., having desired strength and stiffness. As a preferred embodiment, the wing support members may be made from composite materials such as carbon fiber prepreg. For example, carbon fiber prepreg can be laid according to the laying direction, and after curing at room temperature, it can be machined according to the final shape of the wing support member. Additionally, the wing 10 may include a corresponding skin structure, which may also be made of a composite material such as a carbon fiber material, for example, and may be clad and fixed to the wing support members in a manner known in the art.

虽然本文将机翼10分成了多个翼段来描述，但是应当理解，这仅是为了便于阐述本发明的原理，这些翼段仍然形成完整的机翼10的整体，以便承受相应的气动载荷，保证飞机的飞行安全。Although the wing 10 is divided into multiple wing segments for description herein, it should be understood that this is only for the convenience of explaining the principles of the present invention. These wing segments still form the complete wing 10 as a whole in order to withstand corresponding aerodynamic loads. Ensure the flight safety of the aircraft.

根据本发明并且作为较佳实施例，机翼10是集成有分布式涵道风扇的机翼，例如机翼10可以设有涵道风扇动力组30。较佳地，涵道风扇动力组30可以设置在机身20两侧的内段翼11上，即，设置在机翼10的靠近机身20的翼段上。例如，每个内段翼11的上方可以集成有一个涵道风扇动力组30。涵道风扇动力组30可以布置在机翼10的上方以与机翼10成整体。例如，涵道风扇动力组30的壳体的下部固定地连接到机翼10的机翼支承构件，而涵道风扇动力组30的壳体的侧部和上部可以包覆有蒙皮，例如该蒙皮可以与机翼10的其他位置的蒙皮相似。According to the present invention and as a preferred embodiment, the wing 10 is a wing integrated with a distributed ducted fan, for example, the wing 10 may be provided with a ducted fan power group 30. Preferably, the ducted fan power group 30 may be arranged on the inner section wings 11 on both sides of the fuselage 20, that is, on the wing section of the wing 10 close to the fuselage 20. For example, a ducted fan power group 30 may be integrated above each inner section wing 11. The ducted fan power group 30 may be arranged above the wing 10 to be integrated with the wing 10. For example, the lower part of the shell of the ducted fan power group 30 is fixedly connected to the wing support member of the wing 10, and the side and upper part of the shell of the ducted fan power group 30 may be covered with a skin, for example, the skin may be similar to the skin at other positions of the wing 10.

另外，较佳地，各部分蒙皮之间的过渡是平滑的，使得涵道风扇动力组30布置成与机翼10之间的连接形成平滑连接，并且在涵道风扇动力组30与机翼10之间无间隔缝隙。通过“分布式涵道风扇-机翼-机身”融合设计的先进气动布局形式，能够利用涵道风扇的抽吸作用，进一步减小飞机的飞行 阻力，提高其升阻比。In addition, preferably, the transition between each partial skin is smooth, so that the ducted fan power unit 30 is arranged to form a smooth connection with the wing 10, and the connection between the ducted fan power unit 30 and the wing is There is no gap between 10. Through the advanced aerodynamic layout of the "distributed ducted fan-wing-fuselage" integrated design, the suction effect of the ducted fan can be used to further reduce the flight speed of the aircraft. resistance and improve its lift-to-drag ratio.

较佳地，两侧的涵道风扇动力组30可以关于机身20对称地布置在两侧的机翼10上。Preferably, the ducted fan power units 30 on both sides can be arranged symmetrically on the wings 10 on both sides with respect to the fuselage 20 .

作为非限制性实施例，每个涵道风扇动力组30可以包括至少两个涵道动力单元，例如附图中示出的每个涵道风扇动力组30包括5个涵道动力单元，从而电动飞机100可以包括10个涵道动力单元。应当理解，附图中示出的涵道动力单元的数量和布置方式仅是示意性的，本领域技术人员可以设想其余的数量和布置方式。涵道风扇动力组30及涵道动力单元的具体结构将在下文中参照附图进一步详细描述。As a non-limiting example, each ducted fan power group 30 may include at least two ducted power units. For example, each ducted fan power group 30 shown in the drawings includes 5 ducted power units, thereby electrically Aircraft 100 may include 10 ducted power units. It should be understood that the number and arrangement of ducted power units shown in the drawings are only illustrative, and those skilled in the art can envision other numbers and arrangements. The specific structures of the ducted fan power group 30 and the ducted power unit will be described in further detail below with reference to the accompanying drawings.

图3是本发明根据本发明的非限制性实施例的涵道风扇动力单元的中心截面的剖视示意图。3 is a schematic cross-sectional view of a center section of a ducted fan power unit according to a non-limiting embodiment of the present invention.

如图所示，内段翼11可以包括内段翼襟翼11A。内段翼襟翼11A可以是活动部件，用于在电动飞机100起飞或降落时起到增升效果，并且内段翼襟翼11A可以是机翼上表面吹气襟翼的形式。作为示例，内段翼襟翼11A可以通过运动机构(附图中未详细示出，但是其作动器和连接机构的形式是本领域已知的)与机翼10(即，主翼)的内段翼11的后部连接，使得内段翼襟翼11A能够在第一伸出位置和第一缩回位置之间移动。As shown, the inner wing 11 may include an inner wing flap 11A. The inner wing flap 11A may be a movable component used to increase lift when the electric aircraft 100 takes off or lands, and the inner wing flap 11A may be in the form of an air-blown flap on the upper surface of the wing. As an example, the inner section wing flap 11A can be connected to the inner section of the wing 10 (ie, the main wing) through a kinematic mechanism (not shown in detail in the drawings, but the form of its actuator and connection mechanism is known in the art). The rear portion of the wing segment 11 is connected such that the inner segment wing flap 11A can move between a first extended position and a first retracted position.

例如，在电动飞机100起飞或降落时，内段翼襟翼11A可以相对于内段翼11处于第一伸出位置中，即，图3中示出的位置。此时，内段翼襟翼11A相对于内段翼11伸出(例如，图3中示出的向后下方伸出)，使得内段翼襟翼11A的前缘紧接或者紧靠涵道风扇动力组30的后缘(或者，涵道排气口的后缘)布置。换言之，此时，在内段翼襟翼11A的前缘与涵道风扇动力组30的后缘之间不存在间隙。For example, when the electric aircraft 100 takes off or lands, the inner wing flap 11A may be in a first extended position relative to the inner wing 11, that is, the position shown in FIG3 . At this time, the inner wing flap 11A is extended relative to the inner wing 11 (for example, extended backward and downward as shown in FIG3 ), so that the leading edge of the inner wing flap 11A is arranged in close contact with or close to the trailing edge of the ducted fan power group 30 (or, the trailing edge of the ducted exhaust port). In other words, at this time, there is no gap between the leading edge of the inner wing flap 11A and the trailing edge of the ducted fan power group 30.

这样，涵道风扇喷射出的气流在科恩达效应的作用下沿内段翼襟翼11A的上表面流动，产生低压区，而偏转的内段翼襟翼11A的下翼面阻碍气体流动，在内段翼襟翼11A的下翼面(下表面)形成高压区，两者综合作用，起到增升效果。In this way, the air flow ejected by the ducted fan flows along the upper surface of the inner wing flap 11A under the action of the Coanda effect, creating a low pressure area, while the deflected lower surface of the inner wing flap 11A blocks the flow of air, and The lower wing surface (lower surface) of the inner wing flap 11A forms a high-pressure area, and the combined effect of the two creates a lift-increasing effect.

在电动飞机100完成起飞或降落后，内段翼襟翼11A可以相对于内段翼11处于第一缩回位置，例如通过运动机构相对于内段翼11缩回。此时，内段 翼襟翼11A可以叠置在内段翼11下方。After the electric aircraft 100 completes takeoff or landing, the inner wing flap 11A may be in a first retracted position relative to the inner wing 11 , for example, retracted relative to the inner wing 11 through a motion mechanism. At this time, the inner section Wing flaps 11A may be stacked below the inner section wing 11 .

较佳地，在第一缩回位置中，内段翼襟翼11A与内段翼11可以共同形成平滑的流线型轮廓，即，内段翼襟翼11A与内段翼11形成完整的该机翼段的外形轮廓。Preferably, in the first retracted position, the inner wing flaps 11A and the inner wing 11 can jointly form a smooth streamlined profile, that is, the inner wing flaps 11A and the inner wing 11 form a complete wing. The outline of the segment.

具体地并且作为较佳实施例，内段翼11可以包括设置在其后缘的襟翼容纳部11B，襟翼容纳部11B可以具有凹入的下表面。相应地，内段翼襟翼11A可以具有凸起的上表面，并且该凸起的上表面的形状可以与襟翼容纳部11B的凹入的下表面配合，使得内段翼襟翼11A在位于第一缩回位置时能够完全缩回到襟翼容纳部11B中，并且与内段翼11形成完整的翼面轮廓。Specifically and as a preferred embodiment, the inner section wing 11 may include a flap receiving portion 11B provided at its trailing edge, and the flap receiving portion 11B may have a concave lower surface. Correspondingly, the inner wing flap 11A may have a convex upper surface, and the shape of the convex upper surface may cooperate with the concave lower surface of the flap receiving portion 11B, so that the inner wing flap 11A is located In the first retracted position, it can be completely retracted into the flap receiving portion 11B and form a complete airfoil profile with the inner wing section 11 .

在附图的实施例中，内段翼襟翼11A叠置在内段翼11下方可以是指内段翼襟翼11A完全接纳在襟翼容纳部11B中，即，内段翼襟翼11A的后缘与内段翼11的后缘大致对齐，并且此时，它们的后缘也与涵道风扇动力组30的后缘大致对齐。In the embodiment of the drawings, the inner wing flap 11A being stacked below the inner wing flap 11 may mean that the inner wing flap 11A is completely received in the flap receiving portion 11B, that is, the inner wing flap 11A is The trailing edges are generally aligned with the trailing edges of the inner section wings 11 , and at this time, their trailing edges are also generally aligned with the trailing edges of the ducted fan power pack 30 .

作为较佳实施例，内段翼襟翼11A在第一伸出位置与第一缩回位置之间的移动可以遵循圆弧形的移动路径。例如，内段翼襟翼11A在伸出或缩回时的偏转的方式是绕其下部的某一虚拟圆心点做圆周运动。此时，凹入的下表面和凸起的上表面各自形成为配合时能互补的圆弧形轮廓，该圆弧形轮廓是标准圆形的一部分。As a preferred embodiment, the movement of the inner wing flap 11A between the first extended position and the first retracted position may follow an arc-shaped movement path. For example, the inner section wing flap 11A deflects in a circular motion around a certain virtual center point at its lower part when extended or retracted. At this time, the concave lower surface and the convex upper surface each form an arc-shaped profile that is complementary when mated, and the arc-shaped profile is a part of a standard circle.

另外，在电动飞机起飞和降落时，内段翼襟翼11A偏转的角度可以不同。作为非限制性实施例，在起飞构型中，内段翼襟翼11A的偏转角度例如可以为16°，而在降落构型中，内段翼襟翼11A的偏转角度可以为32°。In addition, when the electric aircraft takes off and lands, the deflection angle of the inner wing flap 11A can be different. As a non-limiting example, in the take-off configuration, the deflection angle of the inner wing flap 11A may be, for example, 16°, and in the landing configuration, the deflection angle of the inner wing flap 11A may be 32°.

作为较佳实施例，在机身20的每一侧上，内段翼襟翼11A在第一方向A上的长度与涵道风扇动力组30的长度相同。As a preferred embodiment, on each side of the fuselage 20 , the length of the inner wing flap 11A in the first direction A is the same as the length of the ducted fan power unit 30 .

在本文中并且如图2中详细示出的，第一方向A可以是机翼10的纵向方向，即翼展方向；第二方向B可以是从机头到机尾的方向，即，沿着涵道风扇的气流的方向，而第三方向C可以是与第一方向A和第二方向B正交的竖直向上的方向。As used herein and as shown in detail in FIG. 2 , the first direction A may be the longitudinal direction of the wing 10 , that is, the span direction; the second direction B may be the direction from the nose to the tail, that is, along The direction of the air flow of the ducted fan, and the third direction C may be a vertical upward direction orthogonal to the first direction A and the second direction B.

继续参照图1和图2，内段翼11可以包括内段翼前缘11C和内段翼后缘11D。在本发明的实施例中，内段翼前缘11C可以采用较大后掠角，以此保证 较大的根弦长。有利的是，较大的根弦长也可以提供足够的布置空间，以用于布置相应的电池等。Continuing to refer to FIGS. 1 and 2 , the inner wing 11 may include an inner wing leading edge 11C and an inner wing trailing edge 11D. In the embodiment of the present invention, the inner wing leading edge 11C can adopt a larger sweep angle to ensure that Larger root chord length. Advantageously, a larger root chord length can also provide sufficient arrangement space for arranging corresponding batteries and the like.

具体的，在该实施例中，内段翼11的内段翼前缘11C的第一后掠角可以在25°-35°的范围内，较佳地，第一后掠角为30°，而内段翼11的内段翼后缘11D的第二后掠角可以小于5°，较佳地，第二后掠角为0°。Specifically, in this embodiment, the first sweep angle of the inner wing leading edge 11C of the inner wing 11 can be in the range of 25°-35°. Preferably, the first sweep angle is 30°. The second sweep angle of the inner wing trailing edge 11D of the inner wing 11 may be less than 5°. Preferably, the second sweep angle is 0°.

另外，如上所述，机翼10还包括设置在内段翼11外侧的外段翼12。外段翼12可以包括外段翼襟翼12B。外段翼襟翼12B是在电动飞机100起飞或降落时起到增升效果的部件。例如，外段翼襟翼12B可以采用富勒襟翼的形式。In addition, as mentioned above, the wing 10 also includes an outer wing 12 arranged outside the inner wing 11 . Outer wing 12 may include outer wing flaps 12B. The outer wing flap 12B is a component that increases lift when the electric aircraft 100 takes off or lands. For example, outer segment wing flaps 12B may take the form of Fuller flaps.

同样地，外段翼襟翼12B可以是活动部件，并且能够相对于外段翼12往复移动。例如，外段翼襟翼12B借助运动机构(附图中未详细示出，但是其作动器和连接机构的形式是本领域已知的)连接到外段翼12，并且相对于外段翼12在第二伸出位置和第二缩回位置之间移动。Likewise, the outer wing flap 12B may be a movable component and capable of reciprocating movement relative to the outer wing 12 . For example, the outer wing flap 12B is connected to the outer wing 12 by means of a kinematic mechanism (not shown in detail in the drawings, but the form of the actuator and connection mechanism is known in the art), and relative to the outer wing 12 moves between a second extended position and a second retracted position.

例如，在电动飞机100起飞或降落时，外段翼襟翼12B可以借助运动机构向后伸出并偏转到第二伸出位置中。此时，外段翼襟翼12B延伸超出外段翼12的后缘，以增加机翼10的升力。For example, when the electric aircraft 100 takes off or lands, the outer wing flaps 12B can be extended rearwardly and deflected into the second extended position by means of a kinematic mechanism. At this time, the outer wing flap 12B extends beyond the trailing edge of the outer wing 12 to increase the lift of the wing 10 .

在在电动飞机100完成起飞或降落后，外段翼襟翼12B可以借助运动机构返回到第二缩回位置中。此时，外段翼襟翼12B可以叠置在外段翼12下方或缩回到外段翼12内部的容纳空间中，以便与主翼组合形成完整的机翼部段，并具有期望的空气动力学轮廓。After the electric aircraft 100 completes takeoff or landing, the outer wing flap 12B can be returned to the second retracted position by means of a kinematic mechanism. At this time, the outer wing flaps 12B can be stacked under the outer wing 12 or retracted into the accommodation space inside the outer wing 12 so as to be combined with the main wing to form a complete wing segment with desired aerodynamics. contour.

如图1和2所示并且作为本发明的非限制性实施例，机翼10的外段翼12可以采用较小的后掠角，以便在飞行时提供较大的升力，延缓流动分离，也可以避免较大的低头力矩。具体的，在该实施例中，外段翼12的外段翼前缘12A的第三后掠角可以在15°-25°的范围内，较佳地，第三后掠角为20°。As shown in Figures 1 and 2 and as a non-limiting embodiment of the present invention, the outer section wing 12 of the wing 10 can adopt a smaller sweep angle to provide greater lift during flight, delay flow separation, and also Large lowering moments can be avoided. Specifically, in this embodiment, the third sweep angle of the outer wing leading edge 12A of the outer wing 12 may be in the range of 15°-25°. Preferably, the third sweep angle is 20°.

另外，如图所示，机翼10还包括附连到外段翼12的副翼12C。副翼12C可以在靠近翼尖小翼13的位置处设置在外段翼12的后缘。副翼12C是产生滚转力矩的主要部件，当电动飞机100需要滚转机动时，机身20两侧的副翼12C可以向相反的方向偏转，两侧升力的不对称可以产生滚转力矩。Additionally, as shown, wing 10 also includes ailerons 12C attached to outer wing section 12 . The aileron 12C may be provided on the trailing edge of the outer wing 12 at a position close to the winglet 13 . The ailerons 12C are the main components that generate rolling torque. When the electric aircraft 100 needs to roll, the ailerons 12C on both sides of the fuselage 20 can deflect in opposite directions, and the asymmetry of the lift on both sides can generate a rolling moment.

这样，内段翼11的内段翼前缘11C的第一后掠角与外段翼12的外段翼 前缘12A的第三后掠角不同，从而在内段翼11和外段翼12的连接位置处形成拐折点，使得分离的气流不影响涵道风扇动力组30和副翼12C的效率。In this way, the first sweep angle of the inner wing leading edge 11C of the inner wing 11 is consistent with the outer wing wing 12 of the outer wing. The third sweep angle of the leading edge 12A is different, thereby forming an inflection point at the connection position of the inner wing 11 and the outer wing 12 so that the separated airflow does not affect the efficiency of the ducted fan power unit 30 and the aileron 12C.

进一步较佳地，机翼10还可以包括设置在外段翼12外侧的翼尖小翼(或称翼梢小翼)13。例如，翼尖小翼12可以位于机翼10的最外侧，主要用于减小翼尖涡流动，减小诱导阻力。在该实施例中，翼尖小翼12可以采用融合式翼尖(或翼稍)小翼。Further preferably, the wing 10 may also include a winglet (or winglet) 13 arranged outside the outer wing segment 12 . For example, the winglet 12 may be located at the outermost side of the wing 10 and is mainly used to reduce the wingtip vortex flow and reduce induced drag. In this embodiment, the winglets 12 may be fused winglets (or winglets).

下面参照附图继续描述根据本发明的涵道风扇动力组30及涵道动力单元的具体结构。The following continues to describe the specific structures of the ducted fan power group 30 and the ducted power unit according to the present invention with reference to the accompanying drawings.

如图3中更详细地示出的，每个涵道动力单元可以主要包括涵道31、螺旋桨(也称动叶)32、电机33、静叶34、桨毂35、涵道顶盖36、涵道附件37以及附图中未详细示出的电子部件(例如电子调速器等控制部件)和布线等。As shown in more detail in Figure 3, each ducted power unit may mainly include a duct 31, a propeller (also called a moving blade) 32, a motor 33, a stator blade 34, a propeller hub 35, a duct top cover 36, The duct attachment 37 as well as electronic components (such as control components such as electronic speed regulators) and wiring that are not shown in detail in the drawings.

具体地，涵道31可以包括在第二方向B上顺序布置的涵道进气段311、涵道等直段312和涵道排气段313。Specifically, the duct 31 may include a duct inlet section 311, a duct equal straight section 312, and a duct exhaust section 313 that are sequentially arranged in the second direction B.

涵道进气段311可以包括矩形进气段311A和平滑连接到矩形进气段311A的多个单独的圆形进气段311B(如图2中示出的)。例如，矩形进气段311A可以是5个涵道动力单元共用的长条矩形进气段，矩形进气段311A的进气道唇口或前缘可以与内段翼前缘11C形成附加吸力峰，达到增升和减阻的效果。矩形进气段311A在第二方向B上可以逐渐分化为5个圆形进气段311B。每个涵道动力单元的涵道等直段312可以布置在圆形进气段311B下游。在涵道等直段312中可以布置有螺旋桨32、电机33、静叶34(如图3中所示)和桨毂35等。The ducted air inlet section 311 may include a rectangular air inlet section 311A and a plurality of individual circular air inlet sections 311B smoothly connected to the rectangular air inlet section 311A (as shown in FIG. 2 ). For example, the rectangular air inlet section 311A can be a long rectangular air inlet section shared by five ducted power units. The inlet lip or leading edge of the rectangular air inlet section 311A can form an additional suction peak with the inner section wing leading edge 11C. , to achieve the effects of increasing lift and reducing drag. The rectangular air inlet section 311A can be gradually divided into five circular air inlet sections 311B in the second direction B. The straight section 312 of the duct of each ducted power unit may be arranged downstream of the circular air inlet section 311B. A propeller 32, a motor 33, a stator blade 34 (as shown in Figure 3), a propeller hub 35, etc. may be arranged in a straight section 312 such as a duct.

较佳地，涵道等直段312布置为光滑规整的涵道，例如具有圆形横截面的涵道。涵道等直段312可以支承多个静叶34，多个静叶34又可以在其中心部支承桨毂35。Preferably, the straight section 312 of the duct is arranged as a smooth and regular duct, for example, a duct with a circular cross-section. The straight section 312 such as the duct can support a plurality of stator blades 34, and the plurality of stator blades 34 can support the propeller hub 35 at the center thereof.

电机33是电动飞机100的推进动力源。电机33可以位于桨毂35内部，并且电机33的驱动轴(或输出轴)可以紧固连接到螺旋桨32。这样，在电机33通电后，电机33可以带动动叶或螺旋桨32旋转，从而产生电动飞机100需要的推力。 The motor 33 is the propulsion power source of the electric aircraft 100 . The motor 33 may be located inside the propeller hub 35 , and the drive shaft (or output shaft) of the motor 33 may be securely connected to the propeller 32 . In this way, after the motor 33 is powered on, the motor 33 can drive the blades or propeller 32 to rotate, thereby generating the thrust required by the electric aircraft 100 .

涵道排气段313可以布置在涵道等直段312下游。涵道排气段313对喷射气流有减速增压作用。其后端的排气口的形状可以为矩形、圆角矩形或圆形。在该实施例中，排气口的形状为矩形。另外，涵道顶盖36沿第二方向B可以为等直段，并且可以构成涵道风扇动力组30的壳体的上部。另外，如上所述，涵道顶盖36的外部可以相应地设有蒙皮。The duct exhaust section 313 may be arranged downstream of the straight section 312 such as the duct. The ducted exhaust section 313 has the effect of decelerating and pressurizing the jet airflow. The shape of the exhaust port at its rear end can be rectangular, rounded rectangular or circular. In this embodiment, the exhaust port is rectangular in shape. In addition, the duct top cover 36 may be a straight section along the second direction B, and may constitute the upper part of the casing of the ducted fan power group 30 . In addition, as mentioned above, the exterior of the duct roof 36 may be correspondingly provided with a skin.

继续参照图1和图2，电动飞机100的尾翼40可以采用T型尾气动布局形式。1 and 2 , the tail 40 of the electric aircraft 100 may adopt a T-type tail aerodynamic layout.

作为非限制性实施例，尾翼40可以包括垂直尾翼41和水平尾翼42。垂直尾翼41可以大致竖直地设置在电动飞机100的尾部处。垂直尾翼41是产生航向安定的主要翼面。As a non-limiting example, the tail 40 may include a vertical tail 41 and a horizontal tail 42 . The vertical tail 41 may be disposed substantially vertically at the tail of the electric aircraft 100 . The vertical tail 41 is the main airfoil that produces directional stability.

例如，垂直尾翼41可以布置成关于电动飞机100的由第二方向B和第三方向C限定的竖直中心平面对称，或者可以沿着该竖直中心平面布置。较佳地，垂直尾翼41可以包括第一翼段41A和第二翼段41B。第一翼段41A和第二翼段41B可以整体形成或者可以借助固定装置固定地连接在一起。在附图示出的实施例中，第一翼段41A可以设置在第二翼段41B下方，并且第一翼段41A的前缘的后掠角可以大于第二翼段41B的前缘的后掠角。For example, the vertical tail 41 can be arranged symmetrically about a vertical center plane defined by the second direction B and the third direction C of the electric aircraft 100, or can be arranged along the vertical center plane. Preferably, the vertical tail 41 may include a first wing section 41A and a second wing section 41B. The first wing section 41A and the second wing section 41B may be formed as a whole or may be fixedly connected together by means of a fixing device. In the embodiment shown in the accompanying drawings, the first wing section 41A may be arranged below the second wing section 41B, and the sweep angle of the leading edge of the first wing section 41A may be greater than the sweep angle of the leading edge of the second wing section 41B.

另外，垂直尾翼41还可以包括方向舵41C。方向舵41C是产生偏航力矩的主要部件。方向舵41C可以设置在垂直尾翼41的后缘。例如，方向舵41C可以通过运动机构与垂直尾翼41连接，并且可以向左或向右偏转。方向舵41C与垂直尾翼41的连接方式可以采用本领域已知的任何方式，因此本发明不再详细描述。较佳地，方向舵41C能够在第一方向A上和与第一方向A相反的方向上分别偏转30°，即，在±30°的范围内左右偏转。In addition, the vertical tail 41 may further include a rudder 41C. The rudder 41C is the main component that generates yaw moment. The rudder 41C may be provided at the trailing edge of the vertical tail 41 . For example, the rudder 41C can be connected to the vertical tail 41 through a kinematic mechanism, and can be deflected to the left or right. The connection method between the rudder 41C and the vertical tail 41 can be any method known in the art, and therefore will not be described in detail in the present invention. Preferably, the rudder 41C can deflect by 30° in the first direction A and in the direction opposite to the first direction A respectively, that is, deflect left and right within a range of ±30°.

如图所示，尾翼40的水平尾翼42可以大致水平地设置在垂直尾翼41的顶部处，以便与垂直尾翼41一起形成大致T型的尾翼40。水平尾翼42是产生纵向安定的主要翼面。另外，较佳地，水平尾翼42在第三方向C上的高度可以高于机翼10，以减弱机翼下洗和涵道风扇喷流的影响。As shown in the figure, the horizontal tail 42 of the tail 40 may be disposed substantially horizontally at the top of the vertical tail 41 so as to form a generally T-shaped tail 40 together with the vertical tail 41 . The horizontal tail 42 is the main airfoil that produces longitudinal stability. In addition, preferably, the height of the horizontal tail 42 in the third direction C may be higher than the wing 10 to reduce the influence of wing downwash and ducted fan jets.

如图所示，水平尾翼42可以包括升降舵42A。升降舵42A可以设置在水平尾翼42的后缘。升降舵42A可以通过运动机构与水平尾翼42连接，并且可以向上或向下偏转。较佳地，升降舵42A能够在第三方向C上和与第三方 向C相反的方向上分别偏转30°，即，在±30°的范围内上下偏转。As shown in the figure, the horizontal tail 42 may include an elevator 42A. The elevator 42A may be disposed at the trailing edge of the horizontal tail 42. The elevator 42A may be connected to the horizontal tail 42 via a motion mechanism and may be deflected upward or downward. Preferably, the elevator 42A may be able to move in the third direction C and with respect to the third direction C. Deflect 30° in the direction opposite to C, that is, deflect up and down within the range of ±30°.

继续参照图1和图2，电动飞机100可以包括前三点式起落架50。例如，前三点式起落架50可以包括前起落架51和主起落架52。前起落架51可以设置在机头21下方，而主起落架52可以设置在机翼10的内段翼11下方。此时，在机身20的前部和中部可以相应地设有起落架舱(未示出)。Continuing with reference to FIGS. 1 and 2 , the electric aircraft 100 may include a tricycle landing gear 50 . For example, the nose tricycle landing gear 50 may include a nose landing gear 51 and a main landing gear 52 . The nose landing gear 51 may be disposed below the nose 21 , and the main landing gear 52 may be disposed below the inner wing 11 of the wing 10 . At this time, landing gear bays (not shown) may be provided at the front and middle portions of the fuselage 20 accordingly.

前三点式起落架50和起落架舱的结构和布置形式是本领域已知的，并且根据本发明的电动飞机100可以采用任何合适的结构和布置形式，因此，为简洁起见，本文不再详细描述。The structure and arrangement of the tricycle landing gear 50 and the landing gear compartment are known in the art, and the electric aircraft 100 according to the present invention can adopt any suitable structure and arrangement. Therefore, for the sake of brevity, they will not be described in detail herein. .

另外，电动飞机100还可以包括动力电池60，动力电池60可以是诸如锂电池之类的本领域已知的各种类型的电池。较佳地，动力电池60可以靠近机身20布置在机翼10的内段翼11内部和/或布置在机身20内的下部，以减小电动飞机的滚动转动惯量，从而便于电动飞机100的操控。In addition, the electric aircraft 100 may also include a power battery 60 , and the power battery 60 may be various types of batteries known in the art, such as lithium batteries. Preferably, the power battery 60 can be arranged inside the inner section of the wing 11 of the wing 10 close to the fuselage 20 and/or arranged in the lower part of the fuselage 20 to reduce the rolling inertia of the electric aircraft, thereby facilitating the operation of the electric aircraft 100 control.

如本文所用的表示方位或取向的术语“上部”、“下部”以及用于表示顺序的用语“第一”、“第二”等仅仅是为了使本领域普通技术人员更好地理解以较佳实施例形式示出的本发明的构思，而非用于限制本发明。除非另有说明，否则所有顺序、方位或取向仅用于区分一个元件/部件/结构与另一个元件/部件/结构的目的，并且除非另有说明，否则不表示任何特定顺序、操作顺序、方向或取向。例如，在替代实施例中，“第一方向”可以是“第二方向”。As used herein, the terms "upper" and "lower" indicating an orientation or orientation, and the terms "first" and "second" used to express a sequence are merely intended to enable those of ordinary skill in the art to better understand how to best The concepts of the invention are illustrated in the form of examples and are not intended to limit the invention. Unless otherwise stated, all orders, orientations or orientations are solely for the purpose of distinguishing one element/component/structure from another element/component/structure and are not intended to imply any specific order, order of operations, direction unless otherwise stated. or orientation. For example, in alternative embodiments, the "first direction" may be the "second direction."

综上所述，根据本发明的实施例的集成有分布式涵道风扇的机翼10和包括这种机翼10的电动飞机100克服了现有技术中的缺点，实现了预期的发明目的。In summary, the wing 10 integrated with a distributed ducted fan and the electric aircraft 100 including such wing 10 according to embodiments of the present invention overcome the shortcomings of the prior art and achieve the intended purpose of the invention.

虽然以上结合了较佳实施例对本发明的集成有分布式涵道风扇的机翼和包括这种机翼的电动飞机进行了说明，但是本技术领域的普通技术人员应当认识到，上述示例仅是用来说明的，而不能作为对本发明的限制。因此，可以在权利要求书的实质精神范围内对本发明进行各种修改和变型，这些修改和变型都将落在本发明的权利要求书所要求的范围之内。 Although the wings integrated with distributed ducted fans of the present invention and the electric aircraft including such wings have been described above in conjunction with the preferred embodiments, those of ordinary skill in the art should realize that the above examples are only It is used for illustration and should not be used as a limitation of the present invention. Therefore, various modifications and variations can be made to the present invention within the spirit and scope of the claims, and these modifications and variations will fall within the scope of the claims of the present invention.

Claims (24)

1. 一种集成有分布式涵道风扇的机翼(10)，所述机翼附连到机身(20)并且设有涵道风扇动力组(30)，An airfoil (10) integrated with distributed ducted fans, said airfoil is attached to the fuselage (20) and provided with a ducted fan power pack (30),

   其中，所述涵道风扇动力组设置在所述机翼(10)的内段翼(11)上，并且布置在所述机翼(10)的上方以与所述机翼(10)成整体，并且Wherein, the ducted fan power unit is provided on the inner section of the wing (11) of the wing (10), and is arranged above the wing (10) to be integrated with the wing (10). ,and

   其中，所述内段翼(11)包括内段翼襟翼(11A)，所述内段翼襟翼能够在第一伸出位置和第一缩回位置之间移动，并且其中，所述内段翼襟翼(11A)在位于所述第一伸出位置时相对于所述内段翼(11)伸出并紧靠所述涵道风扇动力组(30)的后缘布置，并且所述内段翼襟翼(11A)在位于所述第一缩回位置时相对于所述内段翼(11)缩回并叠置在所述内段翼(11)下方。Wherein, the inner section wing (11) includes an inner section wing flap (11A), the inner section wing flap can move between a first extended position and a first retracted position, and wherein the inner section wing flap (11A) is movable between a first extended position and a first retracted position. When the segment wing flap (11A) is in the first extended position, it extends relative to the inner segment wing (11) and is arranged close to the trailing edge of the ducted fan power group (30), and the The inner wing flap (11A) is retracted relative to the inner wing (11) and stacked below the inner wing (11) when in the first retracted position.
2. 根据权利要求1所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述内段翼(11)包括设置在后缘的襟翼容纳部(11B)，所述襟翼容纳部(11B)具有凹入的下表面，并且所述内段翼襟翼(11A)具有凸起的上表面，所述内段翼襟翼(11A)在位于所述第一缩回位置时使所述凸起的上表面与所述襟翼容纳部(11B)的所述凹入的下表面配合。The wing (10) integrated with a distributed ducted fan according to claim 1, characterized in that the inner section wing (11) includes a flap receiving portion (11B) arranged at the trailing edge, and the flap The wing receiving portion (11B) has a concave lower surface, and the inner wing flap (11A) has a convex upper surface, and the inner wing flap (11A) is in the first retracted position. The convex upper surface is matched with the concave lower surface of the flap receiving part (11B).
3. 根据权利要求2所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述内段翼襟翼(11A)在所述第一伸出位置与所述第一缩回位置之间的移动遵循圆弧形的移动路径，并且所述凹入的下表面和所述凸起的上表面各自形成为配合时能互补的圆弧形轮廓。The wing (10) integrated with a distributed ducted fan according to claim 2, characterized in that the inner section wing flap (11A) is in the first extended position and the first retracted position. Movement between positions follows an arc-shaped movement path, and the concave lower surface and the convex upper surface each form an arc-shaped profile that is complementary when mated.
4. 根据权利要求1所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述内段翼襟翼(11A)为机翼上表面吹气襟翼。The wing (10) integrated with a distributed ducted fan according to claim 1, characterized in that the inner wing flap (11A) is a blowing flap on the upper surface of the wing.
5. 根据权利要求4所述的集成有分布式涵道风扇的机翼(10)，其特征在于，在所述机身(20)的每一侧上，所述内段翼襟翼(11A)在第一方向(A) 上的长度与所述涵道风扇动力组(30)的长度相同。The wing (10) integrated with distributed ducted fans according to claim 4, characterized in that on each side of the fuselage (20), the inner section wing flap (11A) is First direction (A) The length on is the same as the length of the ducted fan power group (30).
6. 根据权利要求1所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述涵道风扇动力组(30)包括至少两个涵道动力单元，其中，每个涵道动力单元包括涵道(31)、可旋转地固定在所述涵道(31)内的螺旋桨(32)、以及驱动地连接到所述螺旋桨(32)的电机(33)。The wing (10) integrated with distributed ducted fans according to claim 1, characterized in that the ducted fan power group (30) includes at least two ducted power units, wherein each ducted fan The power unit includes a duct (31), a propeller (32) rotatably fixed within the duct (31), and an electric motor (33) drivingly connected to the propeller (32).
7. 根据权利要求6所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述涵道(31)包括在第二方向(B)上顺序布置的涵道进气段(311)和涵道等直段(312)，其中，所述涵道进气段(311)包括矩形进气段(311A)和平滑连接到所述矩形进气段(311A)的多个单独的圆形进气段(311B)，并且所述涵道等直段(312)设置在每个圆形进气段(311B)的下游。The wing (10) integrated with a distributed ducted fan according to claim 6, characterized in that the duct (31) includes ducted air inlet sections (31) arranged sequentially in the second direction (B) 311) and ducted straight sections (312), wherein the ducted air inlet section (311) includes a rectangular air inlet section (311A) and a plurality of individual air inlet sections smoothly connected to the rectangular air inlet section (311A). circular air inlet sections (311B), and the straight sections (312) of the ducts are provided downstream of each circular air inlet section (311B).
8. 根据权利要求7所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述涵道风扇动力组(30)还包括设置在所述涵道等直段(312)的静叶(34)和与所述静叶固定连接的桨毂(35)，所述电机(33)的壳体固定到所述桨毂(35)，而所述电机(33)的驱动轴附连到所述螺旋桨(32)。The wing (10) integrated with a distributed ducted fan according to claim 7, characterized in that the ducted fan power unit (30) further includes a straight section (312) of the duct. The stator blade (34) and the propeller hub (35) fixedly connected to the stator blade, the housing of the motor (33) is fixed to the propeller hub (35), and the drive shaft of the motor (33) is attached Connected to the propeller (32).
9. 根据权利要求8所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述涵道(31)还包括在所述第二方向(B)上布置在所述涵道等直段(312)下游的涵道排气段(313)，所述涵道排气段(313)的后端设置有排气口。The wing (10) integrated with a distributed ducted fan according to claim 8, characterized in that the duct (31) further includes an airfoil arranged in the duct in the second direction (B). There is a ducted exhaust section (313) downstream of the straight section (312), and an exhaust port is provided at the rear end of the ducted exhaust section (313).
10. 根据权利要求6所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述涵道风扇动力组(30)与所述机翼(10)平滑连接，并且在所述涵道风扇动力组(30)与所述机翼(10)之间无间隔缝隙。The wing (10) integrated with distributed ducted fans according to claim 6, characterized in that the ducted fan power group (30) is smoothly connected to the wing (10), and in the There is no gap between the ducted fan power unit (30) and the wing (10).
11. 根据权利要求1-10中任一项所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述内段翼(11)的内段翼前缘(11C)的第一后掠角 在25°-35°的范围内，而所述内段翼(11)的内段翼后缘(11D)的第二后掠角小于5°。The wing (10) integrated with a distributed ducted fan according to any one of claims 1 to 10, characterized in that the inner wing leading edge (11C) of the inner wing (11) is a sweep angle In the range of 25°-35°, the second sweep angle of the inner wing trailing edge (11D) of the inner wing (11) is less than 5°.
12. 根据权利要求1-10中任一项所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述机翼(10)还包括设置在所述内段翼(11)外侧的外段翼(12)，其中，所述外段翼(12)的外段翼前缘(12A)的第三后掠角在15°-25°的范围内。The wing (10) integrated with a distributed ducted fan according to any one of claims 1 to 10, characterized in that the wing (10) further includes a An outer outer section wing (12), wherein the third sweep angle of the outer section wing leading edge (12A) of the outer section wing (12) is in the range of 15°-25°.
13. 根据权利要求12所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述外段翼(12)包括外段翼襟翼(12B)，所述外段翼襟翼能够相对于所述外段翼(12)在第二伸出位置和第二缩回位置之间移动，并且其中，在所述第二伸出位置中，所述外段翼襟翼(12B)延伸超出所述外段翼(12)的后缘，而在所述第二缩回位置中，所述外段翼襟翼(12B)叠置在所述外段翼(12)下方。The wing (10) integrated with a distributed ducted fan according to claim 12, characterized in that the outer wing section (12) includes an outer section wing flap (12B), and the outer section wing flap (12B) is moveable relative to the outer segment wing (12) between a second extended position and a second retracted position, and wherein in the second extended position, the outer segment wing flap (12B) Extending beyond the trailing edge of the outer wing (12), the outer wing flap (12B) overlaps below the outer wing (12) in the second retracted position.
14. 根据权利要求13所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述外段翼襟翼(12B)采用富勒襟翼的形式。The wing (10) integrated with a distributed ducted fan according to claim 13, characterized in that the outer section wing flap (12B) adopts the form of a Fuller flap.
15. 根据权利要求12所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述机翼(10)还包括设置在所述外段翼(12)外侧的翼尖小翼(13)。The wing (10) integrated with a distributed ducted fan according to claim 12, characterized in that the wing (10) further includes a winglet arranged outside the outer wing section (12). (13).
16. 根据权利要求15所述的集成有分布式涵道风扇的机翼(10)，其特征在于，所述机翼(10)还包括附连到所述外段翼(12)的副翼(12C)，所述副翼在靠近所述翼尖小翼(13)的位置处设置在所述外段翼(12)的后缘。The wing (10) with integrated distributed ducted fan according to claim 15, characterized in that the wing (10) further includes an aileron (12C) attached to the outer segment wing (12) ), the aileron is provided on the trailing edge of the outer wing section (12) at a position close to the winglet (13).
17. 一种电动飞机(100)，所述电动飞机包括根据权利要求1-16中任一项所述的集成有分布式涵道风扇的机翼(10)，所述机翼(10)布置在所述电动飞机(100)的所述机身(20)的中部。 An electric aircraft (100), the electric aircraft includes a wing (10) integrated with a distributed ducted fan according to any one of claims 1-16, the wing (10) is arranged on the The middle part of the fuselage (20) of the electric aircraft (100).
18. 根据权利要求17所述的电动飞机(100)，其特征在于，所述电动飞机(100)还包括尾翼(40)，所述尾翼采用T型尾气动布局形式。The electric aircraft (100) according to claim 17, characterized in that the electric aircraft (100) further includes a tail wing (40), and the tail wing adopts a T-tail aerodynamic layout.
19. 根据权利要求18所述的电动飞机(100)，其特征在于，所述尾翼(40)包括垂直尾翼(41)和水平尾翼(42)，所述垂直尾翼(41)竖直设置在所述电动飞机(100)的尾部处，并且沿着所述电动飞机(100)的由第二方向(B)和第三方向(C)限定的竖直中心平面布置，所述水平尾翼(42)设置在所述垂直尾翼(41)的顶部处，并且在所述第三方向(C)上的高度高于所述机翼(10)。The electric aircraft (100) according to claim 18, characterized in that the tail wing (40) includes a vertical tail wing (41) and a horizontal tail wing (42), the vertical tail wing (41) is arranged vertically on the electric At the tail of the aircraft (100) and arranged along the vertical center plane of the electric aircraft (100) defined by the second direction (B) and the third direction (C), the horizontal tail (42) is disposed on The top of the vertical tail (41) and the height in the third direction (C) are higher than the wing (10).
20. 根据权利要求19所述的电动飞机(100)，其特征在于，所述垂直尾翼(41)包括第一翼段(41A)和第二翼段(41B)，其中，所述第一翼段(41A)设置在所述第二翼段(41B)下方，并且所述第一翼段(41A)的前缘的后掠角大于所述第二翼段(41B)的前缘的后掠角。The electric aircraft (100) according to claim 19, characterized in that the vertical tail (41) includes a first wing section (41A) and a second wing section (41B), wherein the first wing section (41B) 41A) is provided below the second wing section (41B), and the sweep angle of the leading edge of the first wing section (41A) is greater than the sweep angle of the leading edge of the second wing section (41B).
21. 根据权利要求19所述的电动飞机(100)，其特征在于，所述垂直尾翼(41)包括方向舵(41C)，所述方向舵设置在所述垂直尾翼(41)的后缘，并且，所述方向舵(41C)能够在第一方向(A)上和与所述第一方向(A)相反的方向上分别偏转30°。The electric aircraft (100) according to claim 19, characterized in that the vertical tail (41) includes a rudder (41C), the rudder is provided at the trailing edge of the vertical tail (41), and the The rudder (41C) is deflectable by 30° in a first direction (A) and in a direction opposite to said first direction (A) respectively.
22. 根据权利要求19所述的电动飞机(100)，其特征在于，所述水平尾翼(42)包括升降舵(42A)，所述升降舵设置在所述水平尾翼(42)的后缘，并且，所述升降舵(42A)能够在所述第三方向(C)上和与所述第三方向(C)相反的方向上分别偏转30°。The electric aircraft (100) according to claim 19, characterized in that the horizontal tail (42) includes an elevator (42A), the elevator is provided at the trailing edge of the horizontal tail (42), and the The elevator (42A) can be deflected by 30° in the third direction (C) and in the direction opposite to the third direction (C) respectively.
23. 根据权利要求17所述的电动飞机(100)，其特征在于，所述电动飞机(100)是滑跑起飞式飞机，并且包括前三点式起落架(50)，所述前三点式起落架包括前起落架(51)和主起落架(52)，其中，所述主起落架(52)设置在所述机翼(10)的所述内段翼(11)下方。 The electric aircraft (100) according to claim 17, characterized in that the electric aircraft (100) is a rolling take-off aircraft and includes a front tricycle landing gear (50), and the front tricycle landing gear includes a nose landing gear. Landing gear (51) and main landing gear (52), wherein the main landing gear (52) is provided below the inner section wing (11) of the wing (10).
24. 根据权利要求17所述的电动飞机(100)，其特征在于，所述电动飞机还包括动力电池(60)，所述动力电池靠近所述机身(20)布置在所述机翼(10)的所述内段翼(11)内部和/或布置在所述机身(20)内的下部。 The electric aircraft (100) according to claim 17, characterized in that the electric aircraft further includes a power battery (60), and the power battery is arranged on the wing (10) close to the fuselage (20). The inner section wing (11) is arranged inside and/or in the lower part of the fuselage (20).