阅读说明：本技术 一种新型扑翼推进装置及工作过程 (Novel flapping wing propulsion device and working process ) 是由 李永成 陈纪军 潘子英 于 2021-08-31 设计创作，主要内容包括：一种新型扑翼推进装置及工作过程,包括扑翼主体,所述扑翼主体的尾缘处铰接有一对尾封板,扑翼主体的尾部上表面和下表面分别设置有一个台阶,并形成台阶面,尾封板与台阶面之间安装有多个收缩杆,收缩杆的动作控制尾封板的打开与关闭。该尾封板可根据扑翼的运动位置进行自适应调节,尾封板的存在一方面使得扑翼上下表面的压力差大幅增加,对应的升力亦得以明显增大,由于扑翼在运动过程中存在水平方向的攻角,因此垂直方向增加的升力在水平方向的分力亦得以增大,因此扑翼的推进特性有所改善；另一方面,尾封板的存在使得扑翼周围及尾部的流场特性得以改善,扑翼尾缘的流动分离得以逐步减缓,能量耗散有所降低,系统输入功率得以大幅降低。(The utility model provides a novel flapping wing propulsion device and working process, includes the flapping wing main part, the trailing edge department of flapping wing main part articulates there is a pair of tail shrouding, and the afterbody upper surface and the lower surface of flapping wing main part are provided with a step respectively to form the step face, install a plurality of shrink poles between tail shrouding and the step face, the action control tail shrouding of shrink pole opens and closes. The tail sealing plate can be adjusted in a self-adaptive mode according to the movement position of the flapping wing, on one hand, the pressure difference between the upper surface and the lower surface of the flapping wing is greatly increased, the corresponding lift force is also obviously increased, and as the flapping wing has an attack angle in the horizontal direction in the movement process, the component force of the lift force increased in the vertical direction in the horizontal direction is also increased, so that the propulsion characteristic of the flapping wing is improved; on the other hand, the existence of the tail sealing plate improves the flow field characteristics around the flapping wings and at the tail part, the flow separation at the tail edge of the flapping wings is gradually slowed down, the energy dissipation is reduced, and the input power of the system is greatly reduced.)

1. The utility model provides a novel flapping wing propulsion device which characterized in that: including flapping wing main part (1), the trailing edge department of flapping wing main part (1) articulates there is a pair of tail shrouding (2), the afterbody upper surface and the lower surface of flapping wing main part (1) are provided with a step respectively to form step face (4), install a plurality of shrink poles (3) between tail shrouding (2) and step face (4), the action control tail shrouding (2) of shrink pole (3) open and close.

2. A novel ornithopter propulsion device as claimed in claim 1, wherein: the flapping wing main body (1) adopts a NACA0012 profile, and the aspect ratio is 3.0.

3. A novel ornithopter propulsion device as claimed in claim 1, wherein: the length of the tail sealing plate (2) is equal to the span length of the flapping wing main body (1).

4. A novel ornithopter propulsion device as claimed in claim 1, wherein: the height of the tail sealing plate (2) is equal to the maximum thickness of the flapping wing main body (1).

5. A novel ornithopter propulsion device as claimed in claim 1, wherein: when the tail sealing plate (2) is opened, the tail sealing plate (2) is vertical to the step surface (4); when the tail sealing plate (2) is closed, the tail sealing plate is arranged on the surface of the step surface (4) and is matched with the appearance of the flapping wing main body (1).

6. A work project using the new ornithopter propulsion unit of claim 1, wherein: the method comprises the following operation steps:

when the flapping wing main body (1) is in the initial position:

the tail sealing plate (2) on the surface of the flapping wing main body (1) is in a closed state, and the tail sealing plate (2) is positioned in the step surface (4);

when the flapping wing main body (1) starts to move downwards:

a tail sealing plate (2) on the upper surface of the flapping wing main body (1) is opened under the control of a contraction rod (3) and is ensured to be vertical to the upper surface of the flapping wing main body (1);

when the flapping wing main body (1) moves to the lowest position in the vertical direction:

the tail sealing plate (2) on the upper surface of the flapping wing main body (1) is contracted into the step surface (4) on the upper surface of the flapping wing main body (1) under the action of the contraction rod (3), and the surface of the flapping wing is kept smooth again at the moment;

when the flapping wing main body (1) moves from bottom to top:

the tail sealing plate (2) on the lower surface of the flapping wing main body (1) is opened and is also vertical to the lower surface of the flapping wing; with the continuous upward movement of the flapping wing main body (1), when the flapping wing main body (1) is positioned at the highest position in the vertical direction, namely the initial position of the flapping wing main body (1), the tail sealing plate (2) on the lower surface of the flapping wing main body (1) begins to shrink into the step surface (4) on the lower surface;

to this end, the movement of one movement cycle has been completed;

the subsequent movement is analogized in the same way.

Technical Field

The invention relates to the technical field of propulsion equipment, in particular to a novel flapping wing propulsion device and a working process.

Background

Ornithopter propulsion is another propulsion method that differs from conventional rotary machines (propellers, turbine engines) and jet propulsion.

With the recent rise of research on micro aircrafts and underwater robots, this way of propulsion shows more and more advantages. The reason is that the propulsion efficiency of the traditional propeller is low under the condition of low Reynolds number, and the flapping type unsteady motion not only can realize the high lift which cannot be achieved by the fixed wing, but also has certain superiority compared with the propulsion efficiency of the traditional mode. Birds flying in the sky and fishes swimming underwater adopt the unsteady motion mode to realize propulsion, and the excellent flying capability and swimming capability of the organisms inspire the research interest of people on flapping propulsion.

The traditional oscillating wing propulsion mode mainly comprises vertical heave motion and pitching motion around a self rotating shaft, and the oscillating wing based on the traditional motion mode can only obtain about 60% maximum propulsion efficiency under the condition of the optimal motion parameter combination, so that no higher optimization space exists at present.

Disclosure of Invention

The applicant provides a novel flapping wing propulsion device and a working process aiming at the defects in the prior art, so that the hydrodynamic performance of the flapping wing is improved by arranging a pair of tail sealing plates at the tail part of the flapping wing, the tail sealing plates can be changed in a self-adaptive mode according to the motion process of the flapping wing, and compared with the traditional flapping wing propulsion device, the novel flapping wing propulsion device can greatly improve the propulsion performance of the flapping wing, greatly improve the propulsion efficiency of the oscillating wing, and better play the boosting effect of the oscillating wing.

The technical scheme adopted by the invention is as follows:

the utility model provides a novel flapping wing propulsion device, includes the flapping wing main part, the trailing edge department of flapping wing main part articulates there is a pair of tail shrouding, the afterbody upper surface and the lower surface of flapping wing main part are provided with a step respectively to form the step face, install a plurality of shrink poles between tail shrouding and the step face, the action control tail shrouding of shrink pole opens and closes.

The further technical scheme is as follows:

the main body of the flapping wing adopts a NACA0012 section wing type, and the aspect ratio is 3.0.

The length of the tail sealing plate is equal to the span length of the flapping wing main body.

The height of the tail sealing plate is equal to the maximum thickness of the flapping wing main body.

When the tail sealing plate is opened, the tail sealing plate is vertical to the step surface; when the tail sealing plate is closed, the tail sealing plate is arranged on the surface of the step surface and is matched with the appearance of the flapping wing main body.

The working engineering of the novel flapping wing propulsion device comprises the following operation steps:

when the flapping wing main body is at the initial position:

the tail sealing plate on the surface of the flapping wing main body is in a closed state and is positioned in the step surface;

when the flapping wing main body starts to move downwards:

the tail sealing plate on the upper surface of the flapping wing main body is opened under the control of the contraction rod and is ensured to be vertical to the upper surface of the flapping wing main body;

when the flapping wing main body moves to the lowest position in the vertical direction:

the tail sealing plate on the upper surface of the flapping wing main body is contracted into the step surface on the upper surface of the flapping wing main body under the action of the contraction rod, and the surface of the flapping wing is kept smooth again at the moment;

when the flapping wing main body moves from bottom to top:

the tail sealing plate on the lower surface of the flapping wing main body is opened and is also vertical to the lower surface of the flapping wing; with the continuous upward movement of the flapping wing main body, when the flapping wing main body is positioned at the highest position in the vertical direction, namely the initial position of the flapping wing main body, the tail sealing plate on the lower surface of the flapping wing main body begins to shrink into the step surface on the lower surface;

to this end, the movement of one movement cycle has been completed;

the subsequent movement is analogized in the same way.

The invention has the following beneficial effects:

the flapping wing self-adaptive control device is compact and reasonable in structure and convenient to operate, a pair of tail sealing plates are additionally arranged, the tail sealing plates can be adaptively adjusted (closed or opened) according to the movement position of the flapping wing, on one hand, the pressure difference between the upper surface and the lower surface of the flapping wing is greatly increased due to the existence of the tail sealing plates, the corresponding lift force is also obviously increased, and the component force (namely the thrust force) of the lift force increased in the vertical direction in the horizontal direction is also increased due to the existence of the attack angle in the horizontal direction in the movement process of the flapping wing, so that the propulsion characteristic of the flapping wing is improved; on the other hand, the existence of the tail sealing plate improves the flow field characteristics around the flapping wings and at the tail part, the flow separation at the tail edge of the flapping wings is gradually slowed down, the energy dissipation is reduced, and the input power of the system is greatly reduced. The numerical calculation result shows that the maximum propelling efficiency of the novel flapping wing propelling device is improved by more than 20 percent compared with the traditional flapping wing propelling device.

Drawings

FIG. 1 is a schematic structural diagram of the present invention.

FIG. 2 is a schematic view of another embodiment of the present invention.

Fig. 3 is a partially enlarged view of a portion F in fig. 1.

Fig. 4 is a front view of the present invention.

Fig. 5 is a partially enlarged view of a portion G in fig. 4.

Fig. 6 is a diagram of the operation of the present invention (first half motion cycle).

Fig. 7 is a diagram of the operation of the present invention (second half cycle).

Fig. 8 is a diagram of the whole movement process of the invention.

Wherein: 1. a flapping wing main body; 2. a tail sealing plate; 3. a retracting lever; 4. a step surface.

Detailed Description

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

As shown in fig. 1-8, the novel flapping wing propulsion device of the present embodiment includes a flapping wing main body 1, a pair of tail sealing plates 2 is hinged at the tail edge of the flapping wing main body 1, a step is respectively arranged on the upper surface and the lower surface of the tail of the flapping wing main body 1, a step surface 4 is formed, a plurality of contraction rods 3 are installed between the tail sealing plates 2 and the step surface 4, and the opening and closing of the tail sealing plates 2 are controlled by the actions of the contraction rods 3.

The main body 1 of the flapping wing adopts a NACA0012 section wing type, and the aspect ratio is 3.0.

The length of the tail seal plate 2 is equal to the span length of the flapping wing main body 1.

The height of the tail seal plate 2 is equal to the maximum thickness of the flapping wing main body 1.

When the tail sealing plate 2 is opened, the tail sealing plate 2 is vertical to the step surface 4; when the tail sealing plate 2 is closed, the tail sealing plate is arranged on the surface of the step surface 4 and is matched with the appearance of the flapping wing main body 1.

The working engineering of the novel flapping wing propulsion device comprises the following operation steps:

when the flapping wing body 1 is in the initial position:

the tail sealing plate 2 on the surface of the flapping wing main body 1 is in a closed state, and the tail sealing plate 2 is positioned in the step surface 4;

when the flapping wing body 1 starts to move downwards:

the tail sealing plate 2 on the upper surface of the flapping wing main body 1 is opened under the control of the contraction rod 3 and is ensured to be vertical to the upper surface of the flapping wing main body 1;

after the flapping wing main body 1 moves to the lowest position in the vertical direction:

the tail sealing plate 2 on the upper surface of the flapping wing main body 1 is contracted into the step surface 4 on the upper surface of the flapping wing main body 1 under the action of the contraction rod 3, and the surface of the flapping wing is kept smooth again at the moment;

when the flapping wing main body 1 moves from bottom to top:

the tail sealing plate 2 on the lower surface of the flapping wing main body 1 is opened and is also vertical to the lower surface of the flapping wing; with the continuous upward movement of the flapping wing main body 1, when the flapping wing main body 1 is positioned at the highest position in the vertical direction, namely the initial position of the flapping wing main body 1, the tail seal plate 2 on the lower surface of the flapping wing main body 1 begins to shrink into the step surface 4 on the lower surface;

to this end, the movement of one movement cycle has been completed;

the subsequent movement is analogized in the same way.

The specific structure and function of the invention are as follows:

the flapping wing mainly comprises a flapping wing main body 1 and a tail closing plate 2.

For the main body 1 of the flapping wing, the wing with the NACA0012 section is adopted in the invention, and the aspect ratio is 3.0.

Two tail seal plates 2 are arranged and are respectively arranged on the upper surface and the lower surface of the tail edge of the flapping wing.

The length of the tail seal plate 2 is equal to the span length of the flapping wing main body 1, and the height of the tail seal plate 2 is equal to the maximum thickness of the flapping wing main body 1. The numerical calculation result shows that when the height of the tail seal plate 2 is equal to the maximum thickness of the flapping wing main body 1, the boosting effect is most obvious; the tail seal plate 2 is perpendicular to the upper surface and the lower surface of the wing profile, and the rear edge of the tail seal plate 2 is consistent with the tail edge of the flapping wing, namely the tail seal plate 2 is arranged at the rearmost end of the flapping wing. The tail sealing plate 2 is hinged with the surface of the flapping wing main body 1, and the retraction and release of the flapping wing main body are controlled by the retraction rod 3.

The contraction rod is mainly used for controlling the contraction of the tail sealing plate, and an electric push rod can be generally adopted.

According to the novel flapping wing propulsion device designed by the invention, the upper surface and the lower surface of the tail edge are respectively provided with the tail sealing plate 2, the existence of the tail sealing plates 2 prolongs the tail flow field separation, the vortex dissipation energy is reduced, the hydrodynamic performance is improved, and the corresponding propulsion performance is improved. In addition, the tail sealing plate on the surface of the flapping wing can be self-adaptively adjusted according to the movement position of the flapping wing. Specifically, when the flapping wings move downwards, the tail sealing plates on the upper surfaces of the flapping wings are in an open state for improving the flow field structure; the tail sealing plate on the lower surface is in a closed state and is packaged in a pre-designed groove. The benefit of this design is that the airfoil surface can be guaranteed to be smooth, thereby reducing the energy consumption of the flapping system.

The motion equation of the flapping wing main body 1 consists of motion in two directions. I.e. heave movement in the vertical direction (y-direction) and pitch movement about its own axis of rotation (about the z-axis).

The specific equations are respectively: h (t) ═ h₀·cos(2πft),Wherein h is₀And theta₀The amplitude of the heave motion and the amplitude of the pitch motion are respectively, and f is the motion frequency.

In the inventionThe value is 90 degrees to obtain better propelling characteristics.

Fig. 6, 7 and 8 are diagrams of the movement process of the present invention.

A represents that the flapping wing is at an initial position, the displacement in the vertical direction reaches the maximum (y is y0), the pitch angle is 0 (theta is 0), and the tail sealing plate at the tail part of the flapping wing is contracted to the inner groove of the flapping wing;

b indicates that the flapping wing is at the equilibrium position, the displacement in the vertical direction is 0(y is 0), and the pitch angle reaches the maximum value (theta is 0), and the tail sealing plate on the upper surface of the flapping wing is in an open state;

c represents that the flapping wing is located at the lowest position in the vertical direction, the displacement in the vertical direction is the minimum value (y is-y 0), the pitch angle is 0 (theta is 0), and the tail sealing plate of the surface of the flapping wing is contracted into the groove of the surface of the flapping wing again;

d represents that the flapping wing is located at a balance position, the displacement in the vertical direction is 0(y is 0), the pitch angle reaches a minimum value (theta is-theta 0), and the tail sealing plate of the lower surface of the flapping wing is in an open state;

e indicates that the flapping wing is again at equilibrium, the vertical displacement is maximized (y is y0), and the pitch angle is 0(θ is 0), and the tail seal plate at the tail of the flapping wing is also retracted into the inner flapping wing slot.

F represents the main part of the flapping wing, the section of the main part is NACA0012 airfoil profile, and the aspect ratio is 3.0;

in the actual working process:

when the flapping wing main body 1 is at an initial position, the tail sealing plate 2 on the surface of the flapping wing main body 1 is in a closed state, the tail sealing plate 2 is positioned in a pre-designed step surface 4, and the surface of the wing profile is ensured to be smooth so as to reduce energy consumption;

when the flapping wing body 1 starts to move downwards, the tail sealing plate 2 on the upper surface of the flapping wing body 1 is controlled by the contraction rod 3 to be opened and is ensured to be vertical to the upper surface of the flapping wing body 1 (at the position C in the figure 6, y is-y 0);

when the flapping wing main body 1 moves to the lowest position in the vertical direction, the tail sealing plate 2 on the upper surface of the flapping wing main body 1 is contracted into the step surface 4 on the upper surface of the flapping wing main body 1 under the action of the contraction rod 3, and the surface of the flapping wing main body 1 is kept smooth again and is consistent with the traditional flapping wing;

then, when the flapping wing body 1 moves from bottom to top, the tail sealing plate 2 of the lower surface of the flapping wing body 1 starts to be opened and is also perpendicular to the lower surface of the flapping wing body 1.

As the flapping wing body 1 continues to move upwards, when the flapping wing body 1 is located at the highest position in the vertical direction (i.e. the initial flapping wing position) (position E in fig. 7, y is y0), the tail sealing plate 2 on the lower surface of the flapping wing body 1 begins to shrink into the step surface 4 on the lower surface of the flapping wing body 1.

At this point, the motion of one motion cycle is completed.

The subsequent movement is analogized in the same way.

The propulsion performance of the flapping wing is improved by the periodic movement of the tail sealing plate 2.

The above description is intended to be illustrative and not restrictive, and the scope of the invention is defined by the appended claims, which may be modified in any manner within the scope of the invention.