WO2020151479A1 - 一种飞行器 - Google Patents

一种飞行器 Download PDF

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Publication number
WO2020151479A1
WO2020151479A1 PCT/CN2020/070280 CN2020070280W WO2020151479A1 WO 2020151479 A1 WO2020151479 A1 WO 2020151479A1 CN 2020070280 W CN2020070280 W CN 2020070280W WO 2020151479 A1 WO2020151479 A1 WO 2020151479A1
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WO
WIPO (PCT)
Prior art keywords
fin
fins
frame
baffle
base
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Application number
PCT/CN2020/070280
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English (en)
French (fr)
Inventor
李铁
Original Assignee
李铁
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 李铁 filed Critical 李铁
Priority to JP2021542349A priority Critical patent/JP2022517844A/ja
Publication of WO2020151479A1 publication Critical patent/WO2020151479A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C33/00—Ornithopters
    • B64C33/02—Wings; Actuating mechanisms therefor

Definitions

  • This application relates to the field of flight technology, in particular to an aircraft.
  • the flight lift of an aircraft basically relies on the rotation of the propeller, or jet combined with a wing with a specific profile curve to obtain lift.
  • the flight lift of an aircraft basically relies on the rotation of the propeller, or jet combined with a wing with a specific profile curve to obtain lift.
  • the technical problem to be solved by this application is to provide a new type of flying device.
  • the present application discloses an aircraft including a fin that swings up and down or vibrates to provide flight power.
  • the fin is distributed with unidirectional ventilation for airflow from above the fin to below the fin. structure.
  • the one-way ventilation structure includes a frame, the lower surface of the frame is covered with a baffle that prevents airflow from flowing from the lower surface of the frame to the upper surface of the frame, and a part of the baffle is connected to the frame , The rest of the baffle can be freely contacted or separated from the frame body with the air flow.
  • the baffle is a flexible sheet made of a lightweight flexible material, and a part of the baffle is connected to the frame.
  • the baffle is made of EVA, non-woven fabric, kraft-like paper or film.
  • the shape of the baffle is circular, rectangular or irregular, and the shape of the frame body is adapted to the baffle, and the baffle can completely cover the frame in appearance.
  • the aircraft further includes a base, the fins are connected to the base, and the fins are distributed symmetrically with respect to the base as a whole.
  • the wing includes a main wing and an auxiliary wing, the base, the main wing, and the auxiliary wing are connected in sequence, and the auxiliary wing and the main wing are elastically connected.
  • the fin has a circular ring shape, and the base is located at the center of the circular ring fin , The auxiliary wing piece is concentric with the main wing piece;
  • the fins are round or square, and all the fins are axially symmetrically distributed on both sides of the base.
  • the fuselage part is also included as the main body, the fins are arranged above the fuselage, and the fins are connected with a linear motor/linear internal combustion engine to provide driving force for swing or vibration of the fins.
  • the shaft of the linear internal combustion engine is perpendicular to and connected to the fin.
  • a cable is connected between the middle and the end of the wing, and the cable is also connected with a drive shaft provided on the base, and the drive shaft can periodically rotate forward and backward and synchronously drive the wing The swing of the piece.
  • the lift device of the existing aircraft is changed to a fin with a specific structure.
  • the unidirectional ventilation structure distributed on the fin allows the fin to swing up and down or vibrate repeatedly, and the airflow is only It can pass in one direction, and then enough lift can be obtained.
  • FIG. 1 is a top view of a fin structure of an aircraft of this application
  • FIG. 2 is a front view of an aircraft
  • FIG. 3 is a schematic view of the closed state of the one-way ventilation structure of the flap of FIG. 1;
  • FIG. 4 is a schematic view of the open state of the one-way ventilation structure of the flap of FIG. 1;
  • FIG. 5 is a top view of the fin structure of another aircraft of the application.
  • FIG. 6 is a top view of the fin structure of another aircraft of this application.
  • FIG. 7 is a top view of the fin structure of another aircraft of this application.
  • FIG. 8 is a schematic diagram of the swing structure of the aircraft
  • FIGS. 9-12 are schematic diagrams of the swing or vibration structure of the aircraft.
  • FIG. 1 it includes 10-frame, 11-shaft, 20-wing piece, 201-baffle piece, 202-frame, 21-square main wing piece, 22-square auxiliary wing piece, 23-square auxiliary wing piece, 31-round main fin, 32-round auxiliary fin, 41-ring main fin, 42-ring auxiliary fin, 50-fuselage, 61-fan main fin, 71-cable, 72-drive shaft, 81-pendulum Wing, 82-cable, 83-drive shaft, 84-longitudinal bearing, 91-swing wing, 92-bearing, 93-composite bearing.
  • the present application discloses an aircraft including a fin 20 that swings up and down or vibrates to provide flight power.
  • the fin 20 is provided with a unidirectional air-permeable structure that only allows airflow to flow from above the fin 20 to below the fin 20 .
  • the lift device of an existing aircraft (such as a helicopter and a flapping wing aircraft) is changed to a fin 20 with a specific structure, and the fin 20 is caused to swing up and down repeatedly or repeatedly through the unidirectional ventilation structure distributed on the fin 20
  • the airflow can only pass through in one direction, so that sufficient lift can be obtained.
  • the unidirectional ventilation structure includes a frame 202, and the lower surface of the frame 202 is covered with a baffle 201 that prevents airflow from flowing from the lower surface of the frame 202 to the upper surface of the frame 202.
  • the baffle The part 201 is connected to the frame 202, and the remaining part of the baffle 201 can contact or separate with the frame 202 according to the air flow.
  • the airflow will give the flap 201 on the flap 20 an upward force, so that the flap 201 can be tightly attached.
  • the airflow cannot pass through the frame 202.
  • the airflow will give the flap 201 on the flap 20 a downward force, so that the flap 201 can be separated from the frame 202, and the airflow can be Pass through the frame 202.
  • the downward and upward air resistance (reaction force, support force) received is different, and lift is obtained.
  • the baffle is a flexible sheet made of a lightweight flexible material, and a part of the baffle is fixedly connected to the frame.
  • the baffle is preferably made of EVA, non-woven fabric, kraft paper or film, and more preferably DuPont paper.
  • the structural materials used can be made of lightweight materials as much as possible on the premise that the strength of the material meets the requirements. This can reduce the aircraft's own gravity and reduce the power and energy required for flight.
  • the shape of the baffle is a circle, a rectangle, a sector, a polygon or an irregular shape, etc., preferably a rectangle, but it must be designed according to the overall shape of the fin to ensure that the fin can be There are enough one-way air-permeable structures formed by the frame and the baffle.
  • the shape of the frame body is adapted to the baffle, and the baffle can completely cover the frame from the appearance. Only when the baffle can completely cover the frame can the baffle and the frame fit as completely as possible. Obstruct air flow from passing through the frame.
  • the aircraft further includes a base, the fins are connected to the base, and the fins are distributed symmetrically with respect to the base as a whole.
  • the base is connected with the wing to facilitate the swing or vibration of the wing relative to the base. It can be installed on the base and connected to the wings and can drive up and down or
  • the driving device of the vibrating fin can also be manpowered or assisted by manpower to achieve up and down swing or vibration.
  • the symmetrical design of the wings is to make the power or lift provided by the wings evenly distributed.
  • the fins include main fins and auxiliary fins, the main fins are directly connected to the machine base, and the auxiliary fins are elastically connected to the main fins, for example, elastic members such as springs or elastic sheets can be used for connection, From the center to the outside, there are the base, the main wing, and the auxiliary wing.
  • the auxiliary wing can be set in multiple stages. When the main fin swings or the vibration rises, the auxiliary fins can swing asynchronously to alleviate the vibration of the aircraft.
  • the fins have an overall circular ring shape
  • the base is located at the center of the circular ring fins
  • the auxiliary fins are concentric with the main fin. That is, from the center to the outside, the frame 10, the ring main fin 41, and the auxiliary fin 42 are in order.
  • the base 10 is connected to the ring main wing 41, and the ring main wing 41 and the ring auxiliary wing 42 are connected by an elastic member, such as a spring or an elastic piece.
  • the fins are square, and all the fins are axisymmetrically distributed on both sides of the base. That is, from the center to the outside, the machine base 10, the square main wing 21, the square auxiliary wing 22, and the square secondary auxiliary wing 23 are in order.
  • the wings 23 are indirectly elastically connected, such as springs or shrapnels.
  • a larger number of auxiliary wing pieces can be further provided outside the square auxiliary wing pieces 23.
  • the fins are circular, and all the fins are axially symmetrically distributed on both sides of the base.
  • the base 10 is connected with the round main wing 31, and the round main wing 31 and the round auxiliary wing 32 are elastically connected, such as by a spring or an elastic piece.
  • the fins are fan-shaped, and the main fan fins 61 are distributed symmetrically as a whole, and the mutually symmetrical wings 1 and 3 can be driven synchronously, that is, both of them can move upward at the same time. Or swing down or vibrate at the same time.
  • the wings 2 and 4 that are symmetrical to each other can be driven synchronously, that is, both swing upward or downward simultaneously or vibrate at the same time.
  • the aircraft further includes a fuselage 50 as the main body, which should be regarded as a basic structure constituting the integrity of the aircraft, and is of the proper meaning.
  • the fins are arranged on the aircraft. Above the body 50, the fin is also connected to a linear motor/linear internal combustion engine to provide driving force for the fin to swing or vibrate relative to the base.
  • the shaft of the linear motor/linear internal combustion engine is perpendicular to the fin. In the linear motor/linear internal combustion engine, during its working process, the corresponding power shaft is periodically and repeatedly translated back and forth along its own axial direction.
  • the power shaft is connected with the fins, so that the axial reciprocating movement of the power shaft can be converted into Repeated swing of wings Movement or vibration, forming the power of flight.
  • the end of the cable 71 is fixedly connected to a certain position between the midpoint and the end of the fin, and the cable 71 is also connected to the drive provided on the base 10.
  • the shaft 72 is connected, and under the action of the drive shaft 72, the slack and tension of the cable 71 can be realized.
  • the drive shaft 72 periodically rotates forward and backward to drive the cable 71 and further drive the fin to swing repeatedly, thereby obtaining a flight Lift.
  • the cable 71 here may preferably be a steel cable.
  • the drive shaft here can be driven by a motor, an internal combustion engine, or driven by a manpower.
  • the swing wing 91 may also be connected to the outer ring of a rotatable bearing 92, and the axis of the bearing 92 is arranged in the horizontal direction.
  • the axis of the bearing 92 is arranged perpendicular to the paper surface, so that the bearing 92 can rotate clockwise or counterclockwise on the paper, and the outer ring of the bearing 92 is also connected to a composite bearing 93 that is fixed vertically and horizontally.
  • the bearing 93 is sleeved on the shaft 11 on the base 10.
  • the composite bearing 93 can periodically slide up and down along the shaft 11, and can synchronously drive the swing of the swing wing 91 connected to the bearing 92.
  • the bearing 92 is also similar to a movable fulcrum, so that the swing wing 91 swings at the fulcrum. .
  • the flap 81 is connected to a cable 82, and the cable 82 is connected to the drive shaft 83, and can pass through the drive shaft 83.
  • the periodic forward and reverse rotations realize the periodic swing up and down of the flap 81.
  • the wing 81 in order to realize the vibration of the fin, the wing 81 may be connected to the longitudinal bearing 84, and at the same time, the longitudinal bearing 84 is set on the base 10 Above the shaft 11, the vertical bearing 84 can be periodically and repeatedly moved along the axial direction to realize the up and down swing of the flap 81.
  • the mass of the fuselage, the base and the load is greater than the mass of the wing, and is preferably several times greater than the mass of the wing.
  • the aircraft When the wing swings relative to the base, the aircraft When the wing swings downwards, the wing receives greater downward (as opposed to upward) resistance, the aircraft seat receives upward force toward each other, and the force on the fuselage, aircraft seat and load exceeds gravity, and the fuselage, aircraft seat and load move upward In the second half cycle of the upward movement, the swinging wing turns upwards. Due to the wing mechanism and the removal of gravity, the upward swing resistance is less, and less energy is required.
  • a transmission device can be provided according to the traditional technology, and part or all of the power wing angle can be adjusted to control the flight direction.
  • people of appropriate size and physical ability can also control the wing swing through mechanical mechanisms to achieve human flight.
  • Can also be knotted Combine some of the existing manpower flight technology and material technology to improve, reduce the size and physical requirements of the situation to achieve manpower flight.
  • it can also be used for glider wings to increase its lift in flight.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

一种飞行器，涉及飞行技术领域。该飞行器的特点在于：包括通过上下摆动或振动以提供飞行动力的翼片(20)，翼片(20)上分布有仅供气流从翼片(20)上方流向翼片(20)下方的单向透气结构。如此，在翼片(20)的反复摆动或振动过程中，气流仅能从翼片(20)的一侧面流向翼片(20)的另一侧面，进而获得飞行器飞行的升力。

Description

一种飞行器
[0001] 本申请是以申请号为 201910074210.8、 申请日为 2019年 1月 25日的中国专利申请 为基础， 并主张其优先权， 该申请的全部内容在此作为整体引入本申请中。
[0002] 技术领域
[0003] 本申请涉及飞行技术领域， 尤其是指一种飞行器。
[0004] 背景技术
[0005] 在现有技术中， 飞行器的飞行升力基本靠螺旋桨的旋转， 或喷气式结合具有特 定外形曲线的机翼以获得升力。 此外， 还有结构复杂但效率极低的扑翼结构。
[0006] 申请内容
[0007] 本申请所要解决的技术问题是： 提供一种新型的飞行装置。
[0008] 为了解决上述技术问题， 本申请公开了一种飞行器， 包括通过上下摆动或振动 以提供飞行动力的翼片， 翼片上分布有仅供气流从翼片上方流向翼片下方的单 向透气结构。
[0009] 在进一步的方案中， 所述单向透气结构包括框体， 框体的下表面覆盖有防止气 流从框体下表面流向框体上表面的挡片， 挡片的部分与框体相连， 挡片的其余 部分可随气流而与框体自由接触或分离。
[0010] 在进一步的方案中， 所述挡片为轻质柔性材料制成的柔性片， 所述挡片的部分 与框体相连。
[0011] 在进一步的方案中， 所述挡片由 EVA、 无纺布、 类牛皮纸或薄膜制成。
[0012] 在进一步的方案中， 所述挡片的形状为圆形、 矩形或不规则形状， 所述框体的 形状与挡片相适配， 挡片从外形上可完全覆盖框体。
[0013] 在进一步的方案中， 所述飞行器还包括一机座， 所述翼片与机座相连， 所述翼 片整体相对于机座呈对称分布。
[0014] 在进一步的方案中， 所述翼片包括主翼片和辅翼片， 机座、 主翼片、 辅翼片依 次连接， 辅翼片与主翼片间为弹性连接。
[0015] 在进一步的方案中， 所述翼片呈圆环形， 所述机座位于呈圆环形翼片的圆心处 ， 所述辅翼片与主翼片同心；
[0016] 或所述翼片呈圆形或方形， 所有翼片呈轴对称分布于所述机座的两侧。
[0017] 在进一步的方案中， 还包括作为主体的机身部分， 所述翼片设置于机身上方， 翼片连接有一直线电机 /直线内燃机以提供翼片摆动或振动的驱动力， 直线电机 / 直线内燃机的轴与翼片垂直并相连。
[0018] 在进一步的方案中， 在所述翼片的中部至末端间连接有拉索， 拉索同时连接有 设置于机座上的驱动轴， 驱动轴可周期性正反转并同步带动翼片的摆动。
[0019] 本申请中的飞行器， 将现有飞行器的升力装置改为具有特定结构的翼片， 通过 翼片上分布的单向透气结构， 使得该翼片在上下反复上下摆动或振动时， 气流 仅仅可以单向通过， 进而可获得足够的升力。
[0020] 附图说明
[0021] 下面结合附图详述本申请的具体结构
[0022] 图 1为本申请一种飞行器的翼片结构俯视图；
[0023] 图 2为一飞行器的前视图；
[0024] 图 3为图 1翼片的单向透气结构闭合状态示意图；
[0025] 图 4为图 1翼片的单向透气结构打开状态示意图；
[0026] 图 5为本申请另一种飞行器的翼片结构俯视图；
[0027] 图 6为本申请又一种飞行器的翼片结构俯视图；
[0028] 图 7为本申请再一种飞行器的翼片结构俯视图；
[0029] 图 8为飞行器摆动结构示意图；
[0030] 图 9- 12为飞行器摆动或振动结构示意图。
[0031] 图中， 包括 10-机座、 11-轴、 20-翼片、 201-挡片、 202 -框体、 21 -方主翼片、 22 -方辅翼片、 23 -方次辅翼片、 31 -圆主翼片、 32 -圆辅翼片、 41 -环主翼片、 42 -环 辅翼片、 50-机身、 61 -扇主翼片、 71-拉索、 72 -驱动轴、 81-摆翼、 82 -拉索、 83- 驱动轴、 84 -纵向轴承、 91-摆翼、 92 -轴承、 93 -复合轴承。
[0032] 具体实施方式
[0033] 为详细说明本申请的技术内容、 构造特征、 所实现目的及效果， 以下结合实施 方式并配合附图详予说明。 [0034] 本申请公开了一种飞行器， 包括通过上下摆动或振动以提供飞行动力的翼片 20 ， 翼片 20上分布有仅供气流从翼片 20上方流向翼片 20下方的单向透气结构。 即 ， 将现有飞行器 （例如直升机、 扑翼机） 的升力装置改为具有特定结构的翼片 2 0, 通过翼片 20上分布的单向透气结构， 使得该翼片 20在上下反复摆动或振动时 ， 气流仅仅可以单向通过， 进而可获得足够的升力。
[0035] 结合图 3、 图 4， 所述单向透气结构包括框体 202， 框体 202的下表面覆盖有防止 气流从框体 202下表面流向框体 202上表面的挡片 201， 挡片 201的部分与框体 202 相连， 挡片 201的其余部分可随气流而与框体 202接触或分离。 亦即是说， 当翼 片 20向下摆动或振动时， 根据作用力与反作用力， 气流会给翼片 20上的挡片 201 一个向上的力， 从而使得挡片 201可以紧紧地贴合上框体 202, 气流无法从框体 2 02中穿过。 而当翼片 20向上摆动或振动时， 根据作用力与反作用力， 气流会给 翼片 20上的挡片 201—个向下的力， 从而使得挡片 201可以与框体 202分离， 气流 可以从框体 202中穿过。 如此， 翼片 20在反复摆动或振动过程中， （其他条件相同 、 相近情况下）向下和向上受到的空气阻力 （反作用力， 支撑力） 不同， 获得升 力。
[0036] 此外， 所述挡片为轻质柔性材料制成的柔性片， 所述挡片的部分与框体固定相 连。 且挡片优选为 EVA、 无纺布、 类牛皮纸或薄膜制成， 且更优选为杜邦纸。 作为飞行器， 其所用的结构性材料， 在保证材料的强度满足要求的前提下， 可 尽量采用轻质材料制成， 如此可减少飞行器自身的重力， 减少飞行所需动力和 能耗。
[0037] 此外， 所述挡片的形状为圆形、 矩形、 扇形、 多边形或不规则形状等等， 较为 优选的为长方形， 不过也得根据翼片整体的形状来进行设计， 保证翼片上能够 分布有足够多的由框体和挡片所形成的单向透气结构。 所述框体的形状与挡片 相适配， 挡片从外形上可完全覆盖框体， 只有挡片外形上可完全覆盖住框体， 才可保证挡片与框体贴合时尽可能地完全阻碍气流从框体通过。
[0038] 在一具体实施例中， 所述飞行器还包括一机座， 所述翼片与机座相连， 所述翼 片整体相对于机座呈对称分布。 机座与翼片相连， 是为了便于驱动翼片相对于 机座的上下摆动或振动。 即可在机座上设置于翼片相连的并可驱动上下摆动或 振动翼片的驱动装置，也可人力,或辅助人力实现上下摆动或振动。 而翼片的对称 设计， 则是为了使得翼片所提供的动力或升力分布均匀。
[0039] 此外， 所述翼片包括主翼片和辅翼片， 主翼片直接与所述机座连接， 辅翼片与 主翼片间弹性连接， 如可采用弹簧或弹性片等弹性件进行连接， 从中心至外依 次为机座、 主翼片、 辅翼片， 辅翼片可多级设置。 当主翼片摆动或振动上升时， 辅翼片可以不同步摆动，以缓解飞行器的震动。
[0040] 结合图 6 , 所述翼片整体呈圆环形， 所述机座位于呈圆环形翼片的圆心处， 所 述辅翼片与主翼片同心。 即从中心至外， 依次为机座 10、 环主翼片 41、 辅助翼 片 42。 机座 10与环主翼片 41连接， 而环主翼片 41和环辅翼片 42之间通过弹性件 相连， 如弹簧或弹片。
[0041] 结合图 1和图 2, 在一具体实施例中， 所述翼片呈方形， 所有翼片呈轴对称分布 于所述机座的两侧。 即从中心至外， 依次为机座 10、 方主翼片 21、 方辅翼片 22 、 方次辅翼片 23， 机座 10与方主翼片 21连接， 方辅翼片 22与方主翼片 21、 方次 辅翼片 23间接为弹性连接， 如弹簧或弹片。 当然， 在方次辅翼片 23至外， 还可 以继续设置更多数量的辅翼片。
[0042] 结合图 5 , 在一具体实施例中， 所述翼片呈圆形， 所有翼片呈轴对称分布于所 述机座的两侧。 机座 10与圆主翼片 31连接， 圆主翼片 31与圆辅翼片 32弹性连接 ， 如通过弹簧或弹片相连。
[0043] 结合图 7， 在一具体实施例中， 所述翼片呈扇形， 且扇主翼片 61整体呈对称分 布， 且相互对称的翼 1、 翼 3可被同步驱动， 即两者同时向上或同时向下摆动或 振动。 而相互对称的翼 2、 翼 4可被同步驱动， 即两者同时向上或同时向下摆动 或振动。
[0044] 再结合图 2， 在一具体实施例中， 飞行器还包括作为主体的机身 50部分， 这应 该算是构成飞行器完整性的基本结构， 属于应有之义， 所述翼片设置于机身 50 上方， 翼片还连接有一直线电机 /直线内燃机以提供翼片相对于机座摆动或振动 的驱动力， 直线电机 /直线内燃机的轴与翼片垂直相连。 直线电机 /直线内燃机， 其工作过程中， 对应的动力轴是沿着自身轴向周期性反复来回平移， 通过该动 力轴与翼片相连， 可使得动力轴的这种轴向往复移动可以转化为翼片的反复摆 动或振动， 形成飞行动力。
[0045] 再结合图 8 , 在一具体实施例中， 利用拉索 71—端固定连接于翼片中点与端点 间的某个位置， 同时拉索 71还与设置于机座 10上的驱动轴 72相连， 并可在驱动 轴 72的作用下， 实现拉索 71的松弛与拉紧， 当驱动轴 72周期性顺反转带动拉索 7 1并进一步带动翼片反复摆动， 从而获得飞行的升力。 且， 此处的拉索 71可优选 为钢索。 此处的驱动轴， 可以是电机驱动、 内燃机驱动， 也可以是人力驱动。
[0046] 结合图 12， 在一具体实施例中， 为实现翼片的摆动， 也可以是摆翼 91连接于一 可转动轴承 92的外圈上， 轴承 92的轴线沿水平方向设置， 具体到图 12， 可类似 认为是轴承 92的轴线垂直纸面设置， 如此轴承 92可于纸面上顺时针或逆时针旋 转， 轴承 92外圈还连接一横向和竖向垂直固定的复合轴承 93 , 复合轴承 93套设 于机座 10上的轴 11之上。 如此， 复合轴承 93处可沿轴 11上下来回周期性滑动， 并可同步带动与轴承 92相连的摆翼 91的摆动， 轴承 92处也类似于一活动支点， 使摆翼 91以该支点摆动。
[0047] 再结合图 9， 在一具体实施例中， 为实现翼片的振动， 也可以是振翼 81连接一 拉索 82, 同时拉索 82连接到驱动轴 83 , 并可通过驱动轴 83的周期性正反转实现 振翼 81周期性上下摆动。
[0048] 再结合图 10和图 11， 在一具体实施例中， 为实现翼片的振动， 也可以是振翼 81 连接纵向轴承 84， 同时， 纵向轴承 84套与设置在机座 10上的轴 11之上， 从而可 通过纵向轴承 84沿着轴向的周期性反复移动而实现振翼 81的上下摆动。
[0049] 本申请中的飞行器， 机身、 机座和载物 （包括驾驶员， 下同） 质量大于机翼质 量， 大于机翼质量数倍比较理想， 机翼相对于机座摆动时， 机翼向下摆动时， 机翼向下受到较大 （相对于向上） 阻力， 机座相向受向上力， 机身、 机座和载 物受力超过重力， 机身、 机座和载物向上移动， 在向上移动后半周期， 摆动机 翼转而向上， 因机翼机构， 除去重力等， 向上摆动阻力较少， 需要的能较少， 机身、 机座和载物的动能减去重力做功， 其余部分抵消机翼向上所需的做功， 使机翼复位。 如此往复， 实现整体上升。 在本申请基础上， 可依传统技术， 设 置传动装置， 可调整部分或全部动力翼角度， 以控制飞行方向等。 同时， 适当 体型和体能人士， 还可以通过机械机构操纵机翼摆动， 实现人力飞行。 也可结 合一些现有的人力飞行技术和材料技术提升,减少对体型和体能要求的情况下实 现人力飞行。 此外， 还可用于滑翔机机翼， 提升其飞行中升力。
[0050] 需要说明的是， 此处， 上、 下、 左、 右、 前、 后只代表其相对位置而不表示其 绝对位置。 以上所述仅为本申请的实施例， 并非因此限制本申请的专利范围， 凡是利用本申请说明书及附图内容所作的等效结构或等效流程变换， 或直接或 间接运用在其他相关的技术领域， 均同理包括在本申请的专利保护范围内。 发明概述
技术问题
问题的解决方案
发明的有益效果

Claims

权利要求书
[权利要求 1] 一种飞行器， 其特征在于： 包括通过上下摆动或振动以提供飞行动力 的翼片， 翼片上分布有仅供气流从翼片上方流向翼片下方的单向透气 结构。
[权利要求 2] 如权利要求 1所述的飞行器， 其特征在于： 所述单向透气结构包括框 体， 框体的下表面覆盖有防止气流从框体下表面流向框体上表面的挡 片， 挡片的部分与框体相连， 挡片的其余部分可随气流而与框体自由 接触或分离。
[权利要求 3] 如权利要求 2所述的飞行器， 其特征在于： 所述挡片为轻质柔性材料 制成的柔性片， 所述挡片的部分与框体相连。
[权利要求 4] 如权利要求 3所述的飞行器， 其特征在于： 所述挡片由 EVA、 无纺布 、 类牛皮纸或薄膜制成。
[权利要求 5] 如权利要求 3所述的飞行器， 其特征在于： 所述挡片的形状为圆形、 矩形或不规则形状， 所述框体的形状与挡片相适配， 挡片从外形上可 完全覆盖框体。
[权利要求 6] 如权利要求 1-5任一项所述的飞行器， 其特征在于： 所述飞行器还包 括一机座， 所述翼片与机座相连， 所述翼片整体相对于机座呈对称分 布。
[权利要求 7] 如权利要求 6所述的飞行器， 其特征在于： 所述翼片包括主翼片和辅 翼片， 机座、 主翼片、 辅翼片依次连接， 辅翼片与主翼片间为弹性连 接。
[权利要求 8] 如权利要求 7所述的飞行器， 其特征在于： 所述翼片呈圆环形， 所述 机座位于呈圆环形翼片的圆心处， 所述辅翼片与主翼片同心； 或所述翼片呈圆形或方形， 所有翼片呈轴对称分布于所述机座的两侧
[权利要求 9] 如权利要求 6所述的飞行器， 其特征在于： 还包括作为主体的机身部 分， 所述翼片设置于机身上方， 翼片连接有一直线电机 /直线内燃机 以提供翼片摆动或振动的驱动力， 直线电机 /直线内燃机的轴与翼片 垂直并相连。
[权利要求 10] 如权利要求 6所述的飞行器， 其特征在于： 在所述翼片的中部至末端 间连接有拉索， 拉索同时连接有设置于机座上的驱动轴， 驱动轴可周 期性正反转并同步带动翼片的摆动。
PCT/CN2020/070280 2019-01-25 2020-01-03 一种飞行器 WO2020151479A1 (zh)

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