WO2023123682A1

WO2023123682A1 - Aircraft having double-row wheel counter-rotating pneumatic effect

Info

Publication number: WO2023123682A1
Application number: PCT/CN2022/080610
Authority: WO
Inventors: 韩宇; 张毅; 季宝锋; 唐占文
Original assignee: 天津爱思达航天科技有限公司
Priority date: 2021-12-30
Filing date: 2022-03-14
Publication date: 2023-07-06
Also published as: CN114348254A

Abstract

The present invention provides an aircraft having a double-row wheel counter-rotating pneumatic effect, comprising a wing plate, rotating assemblies, and a landing gear, wherein the wing plate is connected to a position directly above each rotating assembly; the upper projection area of the wing plate is greater than the area of the rotating assembly; a first protruding end surface is provided at the middle of the outer side surface of the wing plate; there are two rotating assemblies; the two rotating assemblies are respectively connected to the left side and the right side of the inner side surface of the wing plate; the two rotating assemblies rotate in the direction of the same inner side surface a; a gap is formed between the two rotating assemblies; each rotating assembly comprises a driver, a propeller, and a rotating wheel; the propeller and the rotating wheel are connected to the power output end of the driver; and the landing gear is connected to the bottoms of the two rotating wheels of the two rotating assemblies. According to the present invention, airflow is driven by the rotating blades to rotate, the upward airflow impacts the inner side of the wing plate, a lifting force is provided, and the present invention is reasonable and novel in structural design, low in energy consumption, and low in manufacturing cost, and has a popularization application prospect.

Description

A kind of aircraft with double-row wheel pair-rotating aerodynamic effect

technical field

The invention belongs to the technical field of aircraft, and in particular relates to an aircraft with double-row wheel-to-rotation aerodynamic effect.

Background technique

Aircraft is a kind of mechanical flying object manufactured by humans, capable of flying off the ground, flying in space and controlled by humans, and flying in or outside the atmosphere. As a kind of aircraft, UAV has a wide range of uses, low cost, high efficiency, no risk of casualties, strong survivability, good maneuverability, and easy to use. It plays an extremely important role in modern warfare, especially in the civilian field. Broad prospects.

In terms of military use, UAVs are divided into reconnaissance aircraft and target aircraft. In terms of civil use, drones and industrial applications are the real rigid needs of drones; in aerial photography, agriculture, plant protection, micro selfies, express transportation, disaster relief, observing wild animals, monitoring infectious diseases, surveying and mapping, news reports, power patrols, etc. Inspection, disaster relief, film and television shooting, romantic manufacturing and other fields have greatly expanded the use of the drone itself.

However, the existing unmanned aerial vehicle has an unreasonable internal structure design. When it is started, the noise generated is relatively large, which has a certain impact on the surrounding environment, which is not conducive to investigation and detection; and when the unmanned aerial vehicle is started, it needs to consume more Large energy, high cost of use; especially when the drone is used in the field of one-time use, it consumes a lot of cost for the use of the drone.

Contents of the invention

In view of this, the present invention aims to propose an aircraft with double-row wheel-to-rotation aerodynamic effect to solve the problem in the prior art that the internal structure design of the unmanned aerial vehicle is unreasonable, and when it is started, the noise generated is large, which affects the surrounding environment. The environment is not conducive to investigation and detection, and it needs to consume a lot of energy, resulting in high use costs; especially in the field of one-time use, it consumes a lot of technical problems in the use of drones.

In order to achieve the above object, technical solution of the present invention is achieved in that way:

An aircraft with double-row wheel-to-rotation aerodynamic effect, including wing plates, rotating components and landing gear;

The wing plate is connected directly above the rotating assembly; the upper projected area of the wing plate is larger than the area of the rotating assembly; the middle position of the outer surface of the wing plate has a first raised end surface that protrudes upward;

The number of rotating assemblies is two, and the two rotating assemblies are respectively connected to the left and right sides of the inner surface of the wing plate. Both rotating assemblies rotate to the same inner surface a direction, and there is a gap between the two rotating assemblies;

The rotating assembly includes a driver, a propeller and a rotating wheel; the propeller and the rotating wheel are connected to the power output end of the driver;

The undercarriage connects the bottoms of the two rotating wheels of the two rotating assemblies.

Further, both ends of the outer surface of the wing plate have a downwardly curved arcuate structure, and the thickness of the arcuate structure gradually becomes thinner from the upper end to the lower end.

Further, the middle position of the inner surface of the wing plate has a second convex end surface protruding downward.

Further, the outer surface of the rotating wheel is provided with a plurality of blades along the length direction of the rotating wheel.

Furthermore, the blade has an aerodynamic curve, and the front and rear ends have twist angles, which can provide backward airflow power.

Further, the inner surface of the rotating wheel is connected to the side surface of the second convex end surface through the first connecting rod;

The upper side of the rotating wheel is connected to the inner side of the arc structure through the second connecting rod.

Further, the wing plates and rotating components are all made of lightweight materials.

Compared with the prior art, a kind of double row wheel of the present invention has the following advantages to the aircraft of rotating aerodynamic effect:

In the present invention, an upwardly protruding first protruding end surface is formed at the middle position of the outer surface of the wing plate to reduce the rising resistance; a rotating assembly is respectively connected to the left and right sides of the inner surface of the wing plate, and the two rotating assemblies are used to rotate inwardly. An upward high-pressure airflow is formed in the gap between the two rotating components, thereby pushing the inner surface of the wing plate, causing the wing plate to move upward and fly, and at the same time, the counter-rotating rotating component balances the internal moment; the rotating component adopts a driver, a propeller, a rotating The combination of wheels and blades, through the activation of the driver, drives the propeller and the rotating wheel to rotate. Using the rotation of the two propellers and the two rotating wheels, an upward high-pressure airflow is generated in the gap between the two rotating wheels, and the airflow pushes the wing. The board moves upwards; the outer sides of the two rotating components drive the airflow downwards, generating an upward aerodynamic force on the aircraft; at the same time, the airflow hedging area below the aircraft forms a high-pressure area, which provides upward lift to the aircraft. The internal structure design of the present invention is reasonable; two rotating wheels are used to rotate upwards to provide lift, the faster the rotation speed, the greater the lift, and by adjusting the different speeds of the left and right rotating components, the aerodynamic force in the left and right directions of the second convex surface is adjusted to provide left and right direction of lateral force.

The rotating blade of the present invention has an aerodynamic streamline design, which can increase the aerodynamic force. The front and rear ends of the rotating blade have a rotation angle, which can provide backward aerodynamic force while rotating; at the same time, the driver drives the propeller to rotate at the same time, providing backward aerodynamic force. aerodynamic force. During the vertical descent of the aircraft, due to the Magnus aerodynamic effect on the windward side, the pressure difference in the high-pressure area below the aircraft increases sharply, and the lift of the aircraft rises. stable control. The present invention does not have other start-up equipment, and when starting, the generated noise is greatly reduced, which is conducive to investigation and detection; and the present application only uses the airflow generated by the upward rotation of the two rotating wheels to push the wings, which consumes low energy; the landing gear By connecting the bottoms of the two rotating wheels, the manufacturing cost of the whole aircraft is low, the energy utilization rate is high, and there will not be a lot of expenses; the design of the aircraft can realize slow vertical multiple take-offs and landings, and the utilization efficiency is high.

Description of drawings

The drawings constituting a part of the present invention are used to provide a further understanding of the present invention, and the schematic embodiments and descriptions of the present invention are used to explain the present invention, and do not constitute an improper limitation of the present invention. In the attached picture:

Fig. 1 is a schematic diagram of the front side of an aircraft of a double-row wheel-to-rotation aerodynamic effect in an embodiment of the present invention;

Fig. 2 is a schematic diagram of the rear side of an aircraft with double-row wheel-to-rotation aerodynamic effects in an embodiment of the present invention;

Fig. 3 is a front view of an aircraft with double-row wheel-to-rotation aerodynamic effect in an embodiment of the present invention;

Fig. 4 is a rear view of an aircraft with double-row wheel-to-rotation aerodynamic effect in an embodiment of the present invention;

Fig. 5 is a front view of an aircraft with double-row wheel-to-rotation aerodynamic effect in an embodiment of the present invention.

Explanation of reference signs:

100-wing plate; 200-rotating assembly; 300-landing gear;

101-the first raised end face; 102-arc structure; 103-the second raised end face;

201-driver; 202-propeller; 203-rotating wheel;

204-blade; 205-the first connecting rod; 206-the second connecting rod.

Detailed ways

It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", " The orientations or positional relationships indicated by "vertical", "horizontal", "top", "bottom", "inner" and "outer" are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and Simplified descriptions, rather than indicating or implying that the device or element referred to must have a particular orientation, be constructed and operate in a particular orientation, and thus should not be construed as limiting the invention. In addition, the terms "first", "second", etc. are used for descriptive purposes only, and should not be interpreted as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, a feature defined as "first", "second", etc. may expressly or implicitly include one or more of that feature. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

In the description of the present invention, it should be noted that unless otherwise specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. Connected, or integrally connected; it may be mechanically connected or electrically connected; it may be directly connected or indirectly connected through an intermediary, and it may be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention based on specific situations.

The present invention will be described in detail below with reference to the accompanying drawings and examples.

As shown in FIGS. 1 to 5 , the present invention provides an aircraft with double-row wheel-to-rotation aerodynamic effect, including a wing plate 100, a rotating assembly 200 and an undercarriage 300;

The wing plate 100 is connected directly above the rotating assembly 200; the upper projected area of the wing plate 100 is larger than the area of the rotating assembly 200; the middle position of the outer surface of the wing plate 100 has a first raised end surface 101 protruding upward;

The number of rotating assemblies 200 is two, and the two rotating assemblies 200 are respectively connected to the left and right sides of the inner surface of the wing plate 100. The two rotating assemblies 200 both rotate to the same direction of the inner surface a. gap;

The rotating assembly 200 includes a driver 201, a propeller 202 and a turning wheel 203; the propeller 202 and the turning wheel 203 are connected to the power output end of the driver 201;

The landing gear 300 connects the bottoms of the two rotating wheels 203 of the two rotating assemblies 200 .

In the embodiment of the present application, referring to FIG. 1 and FIG. 2 , the wing plate 100 is located above the double-row rotating assembly 200 and bears upward aerodynamic force. The inner side of the wing plate 100 faces the rotating assembly 200 to form an enveloping layout, and the spacing is not large, which can bear the aerodynamic force to the greatest extent. The middle of the first convex end surface 101 has an upward sharp shape to guide the airflow on both sides of the outer surface of the wing plate 100 . The driver 201 adopts a driving motor. The two rotating wheels 203 are respectively fixedly connected to the left and right sides of the inner surface of the wing plate 100. When the two driving motors are activated, the two rotating wheels 203 both rotate toward the direction a of the inner surface.

When in use, the two driving motors are started simultaneously, and the two propellers 202 and the two rotating wheels 203 are rotated in the direction of the inner surface a at the same time, forming an upward high-pressure airflow at the gap between the two rotating wheels 203, and the high-pressure airflow impacts the wing The inner surface of the panel 100 uses the inner surface of the wing panel 100 to provide upward lift force to the wing panel 100 , thereby driving the landing gear 300 at the bottom to fly upward, realizing the flight mode.

The internal structure design of the present application is reasonable. When starting, the rotation of the two rotating wheels 203 is used to generate upward high-pressure airflow, which drives the wing plate 100 to move upward, thereby driving the entire aircraft to move. The generated noise is small and will not affect the surrounding environment. It is suitable for investigation, detection and other fields; and the application utilizes the impact of airflow to start, without consuming large energy and low manufacturing cost, and is especially suitable for the field of one-time use.

Further, both ends of the outer surface of the wing plate 100 have a downwardly curved arcuate structure 102 , and the thickness of the arcuate structure 102 gradually becomes thinner from the upper end to the lower end.

In this embodiment, referring to FIG. 3 and FIG. 4, the two ends of the outer surface of the wing plate 100 form a downwardly curved arc surface structure 102 to reduce the resistance on both sides of the wing plate 100, so that the first convex end surface 101 The guided airflow moves downward along the two arc structures 102 , and at the same time, an upward buffer force is formed on both ends of the inner surface of the wing plate 100 .

The thickness of the arc structure 102 gradually becomes thinner from the upper end to the lower end, which is not only beneficial to guide the airflow movement, but also can reduce the weight of the entire wing plate 100 .

Furthermore, the middle position of the inner surface of the wing plate 100 has a second convex end surface 103 protruding downwards, and forms an envelope for the counter-rotating moving assembly 200 below, and the aerodynamic force is increased by designing the gap distance. By adjusting the respective speeds of the left and right rotation components 200, the second convex end surface 103 generally bears the unilateral aerodynamic force either to the left or to the right.

In this embodiment, referring to FIG. 3 and FIG. 4 , a second raised end surface 103 is provided at the middle position of the inner surface of the wing plate 100 , and the second raised end surface 103 is sharp so that it can enter the middle position of the inner surface of the wing plate 100 . The high-pressure airflow can move upwards along the arc surfaces on both sides of the second convex end surface 103 respectively, and then disperse outward. And when the left and right rotation speeds are different, lateral power is provided.

Further, the outer surface of the rotating wheel 203 is provided with a plurality of blades 204 along the length direction of the rotating wheel 203 .

In this embodiment, referring to Fig. 3 and Fig. 4, a plurality of blades 204 are arranged on the outer surface of the rotating wheel 203, and the blades 204 are strip-shaped plates, and the plurality of blades 204 are used to drive the rotation of the rotating wheel 203, so that the wing plate 100 The airflow in the middle of the inner surface moves upwards, and at the same time, drives the airflows at both ends of the inner surface of the wing plate 100 to move downwards. The blade 204 has an aerodynamically curved surface. The front and rear end surfaces of the blade 204 have a rotation angle, and the rotation can provide backward aerodynamic force.

Furthermore, the blade 204 has an aerodynamic curve, and the front and rear ends have twist angles, which can provide backward airflow power when rotating.

In this embodiment, referring to FIG. 3 , an acute angle or a right angle is adopted between the blade 204 and the outer surface of the rotating wheel 203 to increase the rotational force and facilitate the upward rotation of the rotating wheel 203 .

Further, the inner surface of the rotating wheel 203 is connected to the side surface of the second raised end surface 103 through the first connecting rod 205;

The upper side of the rotating wheel 203 is connected to the inner side of the arc structure 102 through the second connecting rod 206 .

In this embodiment, referring to FIG. 1 , the inner surface of the rotating wheel 203 is connected to the side of the second convex end surface 103 through two first connecting rods 205 , and the upper side of the rotating wheel 203 is connected through two second connecting rods 206 On the inner side of the arc structure 102, four connecting rods are used to fix the rotating wheel 203 from the inner side and the upper side respectively, so as to ensure that the outer direction of the rotating wheel 203 rotates stably.

Further, both the wing plate 100 and the rotating assembly 200 are made of lightweight materials.

Optionally, vertical rudder surfaces can be set at the rear of the aircraft.

In this embodiment, the wing plate 100 and the rotating assembly 200 can adopt a carbon fiber skin structure or a lightweight film skeleton structure to ensure the structural strength of the wing plate 100 and the rotating assembly 200, and can also reduce the weight of the entire wing plate 100 and rotating assembly 200. the weight of.

The present invention proposes a new type of aircraft aerodynamic layout. Rotating blades 204 drive the airflow to rotate, and the upward airflow impacts the inner side of the wing plate 100 to provide lift. The wing plate 100 is connected to the rotating shaft. This part of the lift force and the reverse force of the airflow to the blades 204 Offset balance; the reverse force brought by the downward airflow provides lift for the aircraft; the counter-rotating rotating assembly 200 drives the airflow to form a high-pressure area under the aircraft, and at the same time provides lift for the aircraft.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention. Within the spirit and principles of the present invention, any modifications, equivalent replacements, and improvements are made, such as: modifying the aerodynamic shape of the front end of the cover plate 1. The addition of horizontal rudders and vertical rudders to the front and rear ends of the aircraft should all be included within the protection scope of the present invention.

Claims

An aircraft with dual-row wheel-to-rotation aerodynamic effect, characterized in that it includes a wing plate (100), a rotating assembly (200) and a landing gear (300);

The wing plate (100) is connected directly above the rotating assembly (200); the upper projected area of the wing plate (100) is larger than the area of the rotating assembly (200); the wing plate (100) There is an upwardly protruding first protruding end surface (101) at the middle position on the outer surface;

The number of the rotating assemblies (200) is two, and the two rotating assemblies (200) are respectively connected to the left and right sides of the inner surface of the wing plate (100), and the two rotating assemblies (200) are The same inner surface rotates in a direction, and there is a gap between the two rotating components (200);

The rotating assembly (200) includes a driver (201), a propeller (202) and a turning wheel (203); the propeller (202), the turning wheel (203) are all connected to the power output end of the driver (201);

The undercarriage (300) connects the bottoms of the two rotating wheels (203) of the two rotating assemblies (200).
According to claim 1, the aircraft with double-row wheel counter-rotation aerodynamic effect is characterized in that: both ends of the outer surface of the wing plate (100) have a downwardly curved arc surface structure (102), and the arc surface The thickness of the structure (102) gradually becomes thinner from the upper end to the lower end.
According to claim 2, the double-row wheel contrarotating aerodynamic effect aircraft is characterized in that: the middle position of the inner surface of the wing plate (100) has a second convex end surface (103) convex downward.
According to claim 3, the double-row wheel counter-rotation aerodynamic effect aircraft is characterized in that: the outer surface of the rotating wheel (203) is provided with a plurality of blades (204) along the length direction of the rotating wheel (203) ).
According to claim 4, the double-row wheel counter-rotating aerodynamic aircraft is characterized in that: the blade (204) has an aerodynamic curve, and the front and rear ends have twist angles, which can provide backward aerodynamic force.
According to claim 5, the double-row wheel contrarotating aerodynamic effect aircraft is characterized in that: the inner surface of the rotating wheel (203) is connected to the second convex end surface (103) through a first connecting rod (205) side of

The upper side of the rotating wheel (203) is connected to the inner side of the arc structure (102) through the second connecting rod (206).
According to claim 6, the double-row wheel counter-rotation aerodynamic effect aircraft is characterized in that: the wing plate (100) and the rotating assembly (200) are both made of lightweight materials.