CN213008721U

CN213008721U - Tailless coaxial double-rotor unmanned helicopter

Info

Publication number: CN213008721U
Application number: CN202021610174.7U
Authority: CN
Inventors: 范家铭
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-08-05
Filing date: 2020-08-05
Publication date: 2021-04-20
Anticipated expiration: 2030-08-05

Abstract

The utility model belongs to the technical field of unmanned aerial vehicles, and provides a tailless coaxial dual-rotor unmanned helicopter, which comprises a helicopter body, a coaxial rotor system and an engine, wherein the whole helicopter body is in a water-drop shape, and the external contour of any cross section of the helicopter body is one of a circle, a long circle or an ellipse; when the external contour of a certain cross section of the fuselage is oblong, the value range of the ratio A of the length to the width of the oblong is more than 1 and less than or equal to 2; when the external contour of a certain cross section of the machine body is an ellipse, the value range of the ratio B of the length of the long axis of the ellipse to the length of the short axis is more than 1 and less than or equal to 2. The utility model provides a pair of coaxial twin rotor unmanned helicopter of no tail formula, through the improved design to the fuselage appearance, has not had the regional resistance of traditional fuselage front part and horizontal tail for the rotor is washed the air current down and is hindered the influence to the fuselage useless little. And the whole is in the design of water droplet shape, and structure weight is relatively less, and payload can improve, is fit for descending in less space such as naval vessel deck.

Description

Tailless coaxial double-rotor unmanned helicopter

Technical Field

The utility model relates to an unmanned air vehicle technique field, concretely relates to unmanned helicopter of coaxial twin-rotor of tailless formula.

Background

The coaxial double-rotor helicopter adopts a coaxial reverse-rotor design, the upper and the lower rotors simultaneously perform clockwise and anticlockwise circular motions on the same axis to provide lift force, a tail rotor is not needed, and the coaxial double-rotor helicopter has the advantages of small volume, compact structure and high hovering pneumatic efficiency.

The traditional coaxial helicopter has the following problems:

1. the structure has relatively large weight and small effective load, and is not suitable for landing in small spaces such as a deck of a ship;

2. the aerodynamic layout of the body of the helicopter is complex, the maneuvering performance and the cruising speed cannot be further improved, the resistance of the rotor wing downwash airflow to the body is greatly influenced, one part of the main aerodynamic resistance comes from the front part and the horizontal tail area of the body, and the aerodynamic advantages of the coaxial helicopter are offset.

SUMMERY OF THE UTILITY MODEL

To the defect among the prior art, the utility model aims at providing a coaxial twin rotor unmanned helicopter of no tail formula to reduce the influence of rotor downwash air current to the resistance of fuselage and increase payload.

In order to achieve the above object, the present invention provides a tailless coaxial twin-rotor unmanned helicopter, comprising a fuselage, a coaxial rotor system and an engine for driving the coaxial rotor system, wherein the fuselage is entirely drop-shaped, and the external profile of any cross section of the fuselage is one of circular, long circular or elliptical;

when the outer contour of a certain cross section of the machine body is oblong, the value range of the ratio A of the length to the width of the oblong is more than 1 and less than or equal to 2;

when the external contour of a certain cross section of the machine body is an ellipse, the value range of the ratio B of the length of the long axis to the length of the short axis of the ellipse is more than 1 and less than or equal to 2.

Furthermore, horizontal stabilizing surfaces are arranged on two sides of the machine body, and vertical stabilizing surfaces are arranged on the horizontal stabilizing surfaces.

Further, the outer contour of the cross section of the upper part of the fuselage is oblong.

Furthermore, two sides of the lower portion of the machine body are provided with recessed portions, the recessed portions are provided with installation surfaces distributed along the longitudinal direction, and the installation surfaces are planes.

Further, the engine is arranged outside the machine body and located on two sides of the machine body.

Furthermore, the engine is arranged inside the machine body, the front end of the machine body is provided with an air inlet, and the rear end of the machine body is provided with an air outlet.

The utility model has the advantages that: the utility model provides a pair of coaxial twin rotor unmanned helicopter of no tail formula through the improved design to the fuselage appearance, has not had fuselage front portion and the regional resistance of horizontal tail for the rotor is washed the air current down and is little to the resistance influence of fuselage. And the whole is in the design of water droplet shape, and structure weight is relatively less, and payload can improve, is fit for descending in less space such as naval vessel deck.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.

Fig. 1 is a perspective view of a tailless coaxial dual-rotor unmanned helicopter according to an embodiment of the present invention;

fig. 2 is a perspective view of a tailless coaxial dual-rotor unmanned helicopter according to an embodiment of the present invention from another perspective view;

fig. 3 is a perspective view of a tailless coaxial twin-rotor unmanned helicopter according to another embodiment of the present invention;

fig. 4 is a perspective view of a tailless coaxial twin-rotor unmanned helicopter according to yet another embodiment of the present invention;

fig. 5 is a perspective view of a tailless coaxial twin-rotor unmanned helicopter according to yet another embodiment of the present invention;

fig. 6 is a perspective view of a tailless coaxial twin-rotor unmanned helicopter according to yet another embodiment of the present invention;

fig. 7 is a perspective view of a tailless coaxial twin-rotor unmanned helicopter according to yet another embodiment of the present invention;

fig. 8 is a perspective view of a tailless coaxial twin rotor unmanned helicopter according to yet another embodiment of the present invention;

fig. 9 is a perspective view of a tailless coaxial twin-rotor unmanned helicopter according to another embodiment of the present invention.

Reference numerals:

10-fuselage, 11-smooth surface, 12-recess, 13-installation surface, 14-cabin door, 20-air inlet guide cover, 30-air outlet guide cover, 40-photoelectric pod, 50-horizontal stabilizer, 60-vertical stabilizer, 70-coaxial rotor system, 81-medicine box, 82-spraying system, 90-early warning radar system and 100-engine.

Detailed Description

Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.

It is to be noted that unless otherwise specified, technical or scientific terms used herein shall have the ordinary meaning as understood by those skilled in the art to which the present invention belongs.

In the description of the present application, it is to be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience of description and simplicity of description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting.

Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.

In this application, unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, removable connections, or integral parts; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through intervening media. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

As shown in fig. 1 to 9, the present embodiment provides a tailless coaxial dual-rotor unmanned helicopter including a fuselage 10, a coaxial rotor system 70, and an engine 100 (including a decelerator) for driving the coaxial rotor system 70 to operate.

The fuselage 10 is generally drop-shaped (drop-shaped is also a manifestation of streamlining), that is, the area of the outer contour of the cross section of the fuselage 10 as a whole gradually increases in the direction from top to bottom. The outer contour of any cross section of the fuselage 10 is one of circular, oblong (i.e., two ends are circular arc-shaped lines, two sides are two parallel straight lines), or elliptical. The method comprises the following specific steps:

when the external profile of a certain cross section of the machine body 10 is oblong, the value range of the ratio A of the length to the width of the oblong is more than 1 and less than or equal to 2;

when the external contour of a certain cross section of the machine body 10 is an ellipse, the value range of the ratio B of the length of the long axis of the ellipse to the length of the short axis is more than 1 and less than or equal to 2.

The above-mentioned parameterised constraints generally ensure that the fuselage 10 is entirely drop-shaped.

The photoelectric pod 40 is mounted on the lower portion of the front end of the fuselage 10 or the bottom of the fuselage 10, and the landing gear is also mounted on the bottom of the fuselage 10.

The engine 100 may be mounted inside the fuselage 10 or outside the fuselage.

When the engine 100 is installed inside the body 10, the body 10 has an air inlet at the front end and an air outlet at the rear end, and preferably an air inlet guide 20 and an air outlet guide 30 may be installed at the air inlet and the air outlet for better air inlet and exhaust.

When the engine 100 is mounted outside the body 10, that is, the engine 100 is mounted on both sides of the body 10, it is not necessary to open an intake port and an exhaust port in the body 10. The front end and the rear end of the engine 100 are respectively provided with an intake port and an exhaust port.

In one usage scenario, the fuselage 10 may be equipped with an openable and closable door 14 to place goods or cargo into the fuselage 10, and the design of the door 14 does not affect the overall configuration of the fuselage 10, i.e., the door 14 forms a part of the fuselage 10 in terms of configuration.

In a use scene, the detachable medicine boxes 81 are installed on two sides of the helicopter body 10, and the spraying system 82 is installed at the front end of the helicopter body 10, so that the tailless coaxial double-rotor unmanned helicopter can be used for pesticide spraying in the agricultural field. Similarly, the design of the medicine box 81 does not affect the overall outer shape layout of the main body 10.

In a use scenario, the early warning radar system 90 is installed at the bottom of the body 10, the early warning radar system 90 is detachably connected with the body 10, and the undercarriage is installed at the bottom of the early warning radar system 90. The early warning radar system 90 is physically formed as part of the fuselage 10.

In this embodiment, by improving the shape of the fuselage 10, there is no resistance in the front part and the horizontal tail region of the fuselage 10, so that the effect of the rotor downwash on the resistance of the fuselage 10 is small. And the whole is in the design of water droplet shape, and structure weight is relatively less, and payload can improve, is fit for descending in less space such as naval vessel deck. And the volume tailless coaxial dual-rotor unmanned helicopter in the embodiment can be applied to various scenes for use.

In one embodiment, as shown in fig. 1-5, horizontal stabilizers 50 are mounted on both sides of the fuselage 10, and vertical stabilizers 60 are mounted on the horizontal stabilizers 50, preferably the vertical stabilizers 60 are mounted on the ends of the horizontal stabilizers 50 away from the fuselage. The vertical stabilizer 60 may not be perpendicular to the horizontal stabilizer 50, i.e., the vertical stabilizer 60 may be angled away from the vertical plane. By providing the horizontal stabilizer 50 and the vertical stabilizer 60, the stability of course steering is more easily ensured.

In one embodiment, as shown in fig. 1-9, the outer contour of the cross-section of the upper part of the fuselage 10 is oblong, i.e. on both sides of the upper part of the fuselage 10 there are longitudinally distributed smooth surfaces 11, which smooth surfaces 11 are mainly planar and also comprise transition curves at the upper and lower ends. The plane may be in a vertical plane or in an inclined plane slightly deviating from the vertical plane. In the present embodiment, the upper portion of the body 10 is a portion having an oblong outer contour in cross section, and the other portion is the lower portion of the body 10. This has the advantage that the smooth surface 11 corresponds to a vertical stabilizer, which increases the stability of the unmanned helicopter in flight.

In one embodiment, as shown in fig. 1-2 and 4-5, the lower portion of the body 10 is provided with recesses 12 on both sides, the recesses 12 having mounting surfaces 13 distributed along the longitudinal direction, and the mounting surfaces 13 are flat. The mounting surface 13 is used for realizing the function of hanging articles outside the fuselage 10, such as hanging weaponry and the like. The mounting surfaces 13 are provided at both sides of the lower portion of the body 10 because the mountable area of the lower portion is relatively large with respect to the upper portion. In addition, the intake air guide casing 20, the exhaust air guide casing 30, the photoelectric pod 40, the engine 100 mounted outside the fuselage 10, the external weapon equipment in the present embodiment, and the like in the foregoing embodiments are all structures attached to the fuselage 10, are not part of the fuselage 10, and do not limit the external shape of the fuselage 10. The mounting surface 13 also functions as a vertical stabilizer.

In the specification of the present invention, a large number of specific details are explained. It is understood, however, that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, structures and techniques have not been shown in detail in order not to obscure an understanding of this description.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the scope of the embodiments of the present invention, and are intended to be covered by the claims and the specification.

Claims

1. A tailless coaxial dual-rotor unmanned helicopter comprises a helicopter body, a coaxial rotor system and an engine for driving the coaxial rotor system, and is characterized in that: the whole body of the machine body is in a drop shape, and the external profile of any cross section of the machine body is one of circular, long circular or oval;

2. The tailless coaxial twin rotor unmanned helicopter of claim 1, further comprising: horizontal stabilizing surfaces are arranged on two sides of the machine body, and vertical stabilizing surfaces are arranged on the horizontal stabilizing surfaces.

3. The tailless coaxial twin rotor unmanned helicopter of claim 1, further comprising: the outer contour of the cross section of the upper part of the fuselage is oblong.

4. The tailless coaxial twin rotor unmanned helicopter of claim 3, further comprising: the fuselage's both sides of lower part are provided with the depressed part, the depressed part has along the installation face of longitudinal distribution, the installation face is the plane.

5. The tailless coaxial twin rotor unmanned helicopter of any of claims 1-4, further comprising: the engine is arranged outside the machine body and positioned on two sides of the machine body.

6. The tailless coaxial twin rotor unmanned helicopter of any of claims 1-4, further comprising: the engine is arranged in the machine body, the front end of the machine body is provided with an air inlet, and the rear end of the machine body is provided with an air outlet.