CN113815847A

CN113815847A - Coaxial helicopter and flexible variable-pitch rotor wing

Info

Publication number: CN113815847A
Application number: CN202011612599.6A
Authority: CN
Inventors: 范家铭
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-12-28
Filing date: 2020-12-28
Publication date: 2021-12-21

Abstract

The application provides a coaxial helicopter and flexible displacement rotor system includes: a helicopter body, an upper rotor assembly and a lower rotor assembly; the overall appearance of the helicopter body is in a drop shape, and the external profile of any cross section of the helicopter body is one of circular, long circular or oval; the first blade of the upper rotor wing assembly tilts upwards and is connected with the first propeller clamp assembly, the first propeller clamp assembly is rotatably arranged at one end of the first variable-pitch journal, and the first variable-pitch journal and the first propeller hub are fixed; lower rotor subassembly second paddle perk downwards and be connected with second oar clamp assembly, and second oar clamp assembly is rotatable installs in second displacement journal one end, and second displacement journal and second propeller hub are fixed. The coaxial helicopter of this application passes through the design of organism appearance water droplet shape, and simple structure is compact to through making first paddle upwards skew, the downward skew of second paddle, first paddle and second paddle emergence when having avoided the high-speed maneuver flight of helicopter beat the oar accident, and the stability of operation is high, and the security is high.

Description

Coaxial helicopter and flexible variable-pitch rotor wing

Technical Field

The application relates to the technical field of coaxial helicopters, in particular to a coaxial helicopter and a flexible variable-pitch rotor wing.

Background

In the field of design of conventional helicopters, a coaxial double-rotor type helicopter adopts a coaxial reverse-rotor design, and the design of the aerodynamic layout of the appearance of a helicopter body and the distance between the upper rotor plate and the lower rotor plate are important parameters influencing the aerodynamic characteristics of the coaxial helicopter and avoiding blade collision accidents. Although the prior art scheme can meet the basic functions of helicopter flight, the following defects exist:

(1) on the rotor, the bigger the lower oar disc interval is, the smaller the induction loss is, can avoid upper and lower rotor blade to appear the collision accident. However, the height of the rotor wing control system is increased, the structure is complex, the aerodynamic resistance and the weight of the rotor wing are increased, the overall height of the helicopter is increased, the requirement on the rigidity of a rotor wing driving shaft is high, and the problems of mechanical fatigue and the like are easy to occur.

(2) On the rotor, lower oar dish interval undersize, collision accident can appear in upper and lower rotor blade to the pneumatic induced loss of blade tip region enlarges and the vibration is violent, and the noise is huge.

(3) The helicopter body has complex appearance pneumatic layout and body structure, relatively large weight, and incapability of further improving the maneuvering performance and cruising speed, and is not suitable for taking off and landing in small spaces such as ship decks and the like.

(4) The rotor downwash has a large influence on the waste resistance of the helicopter body, and part of the main aerodynamic resistance comes from the front part and the horizontal tail area of the helicopter body, so that the advantage of the coaxial helicopter in the aspect of aerodynamics is offset.

Disclosure of Invention

An object of the application is to provide a coaxial helicopter and flexible variable pitch rotor system, this type coaxial helicopter organism appearance is the drop shape, and simple structure is compact, and aerodynamic resistance is little, is fit for taking off and land in less spaces such as naval vessel deck.

And simultaneously, the flexible variable-pitch rotor system is provided, so that the collision accident of blades of the upper rotor and the lower rotor can be avoided when the helicopter flies at a high speed in a maneuvering manner, the distance between the tail ends of the blades of the upper rotor and the lower rotor is the largest, the distance between hubs is the smallest, and the flexible variable-pitch rotor system is high in operation stability, high in safety and simple in structure.

To achieve the above object, the present application provides a coaxial helicopter and a flexible pitch rotor system, comprising: a helicopter body and a flexible pitch rotor system. The overall appearance of the helicopter body is drop-shaped, and the external profile of any cross section of the body is one of circular, long circular or oval; the flexible variable pitch rotor system: including last rotor blade subassembly and lower rotor blade subassembly, go up the rotor blade subassembly include first propeller hub and with the first paddle that first propeller hub is connected, down the rotor blade subassembly include the second propeller hub and with the second paddle that the second propeller hub is connected, first paddle upwards the perk and/or the downward perk of second paddle.

When the outer contour of a certain cross section of the machine body is in an oblong shape, the value range of the ratio A of the length to the width of the oblong shape 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 or V-shaped stabilizing surfaces are arranged on the horizontal stabilizing surfaces.

Further, the outer contour of the cross section of the upper portion of the machine body is oval, recessed portions are arranged on two sides of the lower portion of the machine body, the recessed portions are provided with mounting surfaces distributed along the longitudinal direction, and the mounting surfaces are planes.

Meanwhile, the first blade and the first blade clamp assembly are connected with the first variable-pitch journal and the first hub, and the second blade clamp assembly are connected with the second variable-pitch journal and the second hub.

Further, the first paddle tilts upwards, and the second paddle tilts downwards.

Further, the first pitch-variable shaft neck comprises a shaft section A fixedly connected with the first propeller hub and a shaft section B which is connected with the shaft section A and is tilted upwards;

further, the second pitch-variable journal comprises a shaft segment C fixedly connected with the second hub and a shaft segment D connected with the shaft segment C and tilting downwards;

furthermore, the included angle between the first variable-pitch journal after being tilted upwards and the horizontal plane is more than or equal to 1.5 degrees and less than 20.5 degrees, and the included angle between the second variable-pitch journal after being tilted downwards and the horizontal plane is more than or equal to 1.5 degrees and less than 20.5 degrees.

Further, the diameter of a paddle disk of the upper rotor assembly is equal to that of the lower rotor assembly, and the maximum distance between the first blade and the second blade in the vertical direction is 0.05-0.28 times of the diameter of the paddle disk;

further, the distance between the first hub and the second hub in the vertical direction is 0.05-0.65 times of the maximum distance between the first blade and the second blade in the vertical direction.

In a second aspect, the present application provides a coaxial helicopter including the helicopter body profile and flexible pitch rotor technology described in any of the above aspects.

The beneficial effect of this application: the application provides a pair of coaxial helicopter and flexible displacement rotor, through the improved design to the fuselage appearance, wholly be the drop shape, has not had the fuselage front portion and the regional resistance of horizontal tail for the rotor is washed the air current down and is hindered the influence for fuselage useless little, and simple structure is compact, and weight is less relatively, is fit for taking off and land in less spaces such as naval vessel deck.

Meanwhile, according to the flexible variable-pitch rotor system provided by the application, the first blade is deflected upwards, and the second blade is deflected downwards, so that the distance between the first blade and the second blade in the vertical direction is larger as the distance is closer to the tail end, the blade mutual collision accident of the first blade and the second blade during high-speed maneuvering flight of the helicopter is avoided, the pneumatic induction loss is reduced, the minimum of the distance between a first paddle disk formed when the first blade rotates and a second paddle disk formed when the second blade rotates is realized, the vibration and the noise of the first blade and the second blade are reduced, the height of a rotor control system is reduced, the resistance and the weight of the rotor control system are reduced, the overall height of the helicopter is reduced, the influence on the rigidity of a rotor shaft is reduced, and the safety factor and the stability of the helicopter during high-speed maneuvering flight are improved.

Drawings

In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings that are needed in the detailed description of the present application 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 coaxial helicopter provided by an embodiment of the present application from one perspective;

FIG. 2 is a front view of a coaxial helicopter provided by one embodiment of the present application from another perspective;

FIG. 3 is a rear view of a coaxial helicopter provided in accordance with an embodiment of the present application from another perspective;

FIG. 4 is a right side view of a coaxial helicopter provided in accordance with an embodiment of the present application from another perspective;

FIG. 5 is a perspective view of a coaxial helicopter provided in accordance with yet another embodiment of the present application;

FIG. 6 is a front view of a coaxial helicopter provided in accordance with yet another embodiment of the present application;

FIG. 7 is a rear view of a coaxial helicopter provided in accordance with yet another embodiment of the present application;

FIG. 8 is a right side view of a coaxial helicopter provided in accordance with yet another embodiment of the present application;

figure 9 is a perspective view of a flexible, variable-pitch rotor system according to an embodiment of the present application;

figure 10 is a front view of a flexible, variable-pitch rotor system according to an embodiment of the present application;

FIG. 11 is a schematic structural view of a rotor assembly of a flexible, variable-pitch rotor system according to an embodiment of the present disclosure;

FIG. 12 is a schematic structural view of a lower rotor assembly of a flexible, variable-pitch rotor system according to an embodiment of the present disclosure;

figure 13 is a schematic view of a flexible, variable-pitch rotor system according to an embodiment of the present application;

figure 14 is a schematic structural view of a distance rotor system according to another embodiment of the present application.

Figure 15 is a schematic view of a distance rotor system according to another embodiment of the present application.

Reference numerals:

10. a flexible variable pitch rotor system; 11. a first hub; 12. a first blade; 13. a first pitch journal; 131. a shaft section A; 132. a shaft section B; 14. a first paddle clamp assembly;

21. a second hub; 22. a second blade; 23. a second pitch journal; 231. a shaft section C; 232. a shaft section D; 24. a second paddle clamp assembly;

30. a body; 31. a smooth surface; 32. a recess mounting surface; 33. an air intake dome; 34. an exhaust dome; 40. a photovoltaic pod; 50. horizontally stabilizing the flour; 60. a vertical stabilizer; 70. v-shaped stabilizing surfaces; 80. a landing gear.

Detailed Description

Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are merely for illustrating the technical solutions of the present application more clearly, and therefore are only examples, and the protection scope of the present application 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 this application belongs.

In the description of the present application, it is to be understood that the terms "central," "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 in describing the present application and to simplify the 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 of the present application.

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 application, "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 application can be understood by those of ordinary skill in the art as appropriate.

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. 1-8, the present embodiment provides a coaxial helicopter including a helicopter fuselage 30 and a flexible pitch rotor system 10.

The fuselage 30 is generally drop-shaped (drop-shaped is also a representation of streamlining), that is, the area of the outer contour of the cross section of the fuselage 30 as a whole gradually increases in the direction from top to bottom. The outer contour of any cross section of the fuselage 30 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 30 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 fuselage 30 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 1 < B < 2.

The above parametric constraints generally ensure that the fuselage 30 is entirely drop-shaped.

The photoelectric pod 40 is mounted on the lower portion of the forward end of the fuselage 30 or the bottom of the fuselage 30, and the landing gear 80 is also mounted on the bottom of the fuselage 30.

The fuselage 30 has an air inlet at the front end and an air outlet at the rear end, and preferably an air inlet cowl 33 and an air outlet cowl 34 may be installed at the air inlet and the air outlet for better air intake and exhaust.

In this embodiment, the improved design of the body 30 eliminates the resistance of the front part and the horizontal tail area of the body of the conventional helicopter, so that the influence of the rotor downwash on the waste resistance of the body 30 is small. And the whole is in the design of water droplet shape, simple structure, weight is relatively less, and payload can improve, is fit for taking off and landing in less spaces such as naval vessel deck.

In one embodiment, as shown in fig. 1-4, horizontal stabilizers 50 are mounted on both sides of the fuselage 30, and vertical stabilizers 60 are mounted on the horizontal stabilizers 50, so that the stability of course control is more easily ensured by the arrangement of the horizontal stabilizers 50 and the vertical stabilizers 60.

In one embodiment, as shown in fig. 5-8, horizontal stabilizers 50 are installed on both sides of the body 30, V-shaped stabilizers 70 are installed on the horizontal stabilizers 50, and stability of course control is more easily ensured by the horizontal stabilizers 50 and the V-shaped stabilizers 70.

In one embodiment, as shown in fig. 5-8, recessed portion mounting surfaces 32 are provided on both sides of the lower portion of the fuselage 30, and the recessed portion mounting surfaces 32 are used for realizing the function of hanging articles outside the fuselage 30, such as hanging weaponry and the like. The recess mounting surfaces 32 are provided on both sides of the lower portion of the body 30 because the mountable area of the lower portion is larger than that of the upper portion.

The intake air guide sleeve 33, the exhaust air guide sleeve 34, the photoelectric pod 40 in the foregoing embodiments, the external weapon equipment in the present embodiment, and the like are all structures attached to the fuselage 30, are not part of the fuselage 30, and do not limit the external shape of the fuselage 30.

As shown in fig. 9-13, the present embodiment provides a flexible, variable-pitch rotor system including an upper rotor assembly and a lower rotor assembly.

The upper rotor assembly includes a first hub 11 and a first blade 12 connected to the first hub 11 at one end, and the other end (i.e., tip end) of the first blade 12 is tilted upward. The lower rotor assembly includes a second hub 21 and a second blade 22 having one end connected to the second hub 21, and the other end (i.e., tip end) of the second blade 22 is tilted downward. The number of first paddles 12 and second paddles 22 is the same and is typically 2-4 (not limited to 2-4).

In the present embodiment, the tip of second blade 22 is tilted downward from the horizontal plane by tilting first blade 12 upward and second blade 22 downward, specifically by tilting the tip of first blade 12 upward from the horizontal plane, by tilting the tip of second blade 22 downward from the horizontal plane, therefore, the distance between the first blade 12 and the second blade 22 in the vertical direction is larger as the distance is closer to the tail end, so that the accident that the first blade 12 and the second blade 22 collide with each other when the helicopter is in high-speed maneuvering flight is avoided, the minimization of the distance between a first paddle disk formed when the first blade 12 rotates and a second paddle disk formed when the second blade 22 rotates is realized, the vibration and the noise of the first blade 12 and the second blade 22 are reduced, the height of a rotor wing control system is reduced, the resistance and the weight of the rotor wing control system are reduced, the influence on the rigidity of a rotor wing shaft is reduced, and the safety factor and the stability of the helicopter in high-speed maneuvering flight are improved.

In one embodiment, as shown in FIGS. 9-13, the first pitch journal 13 is tilted upward and makes an angle α with the horizontal plane, where α is 1.5 ≦ α < 20.5 °. The included angle between the second variable-pitch journal 23 and the horizontal plane after tilting downwards is beta, and the beta is more than or equal to 1.5 degrees and less than 20.5 degrees.

And meanwhile, in the same embodiment, the angle α is equal to angle β, that is, the included angles between the upwarp and the downwarp of the first pitch journal 13 and the second pitch journal 23 and the horizontal plane are the same.

The first pitch journal 13 includes a shaft segment a131 fixedly connected to the first hub 11 and a shaft segment B132 integrally connected to the shaft segment a131 and tilted upward, and similarly, the second pitch journal 23 includes a shaft segment C231 fixedly connected to the second hub 21 and a shaft segment D232 integrally connected to the shaft segment C231 and tilted downward.

One end of the first blade clamp assembly 14 is rotatably sleeved on the shaft section B132, and the other end is fixedly connected with the first blade 12. Similarly, one end of the second blade clamp assembly 24 is rotatably sleeved on the shaft section D232, and the other end is fixedly connected with the second blade 22.

In addition, the rotor system of the embodiment only needs to change the mechanical structures of the first pitch journal 13 and the second pitch journal 23, and the first blade 12 is tilted upwards and the second blade 22 is tilted downwards through angle control without changing the structures of the blades, so that the rotor system is convenient to process and manufacture.

The present embodiment is applicable to a variable pitch coaxial helicopter.

In one embodiment, as shown in fig. 13, the disk diameter of the upper rotor assembly and the disk diameter of the lower rotor assembly are equal and are denoted by D, the maximum pitch (denoted by H) of the first blade 12 and the second blade 22 in the vertical direction is 0.05 to 0.28 times the disk diameter D, and the pitch (denoted by H) of the first hub 11 and the second hub 21 in the vertical direction is 0.05 to 0.65 times the maximum pitch H of the first blade 12 and the second blade 22 in the vertical direction.

In one embodiment, as shown in fig. 14 and 15, first blade 12 is fixedly attached to first hub 11 and second blade 22 is fixedly attached to second hub 21. Preferably, the first hub 11 is tilted up 6 °, but not limited to 6 °, at the location where the first blade 12 is mounted. Similarly, the portion of second hub 21 for mounting second blades 22 is tilted downward by 6 °, but is not limited to 6 °. The rotor system in this embodiment is applicable to on the unmanned aerial vehicle, because paddle and propeller hub fixed connection, consequently for the structure of distance paddle, the change of lift size and reaction torque is realized through the rotational speed height and the differential of first rotor subassembly and second rotor subassembly to the coaxial rotor of this kind of distance paddle, realizes the direction change of first oar dish and second oar dish pulling force through the slope rotor axle.

In the description of the present application, numerous specific details are set forth. However, it is understood that embodiments of the application 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 for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill 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 depart from the spirit and scope of the present disclosure, and the present disclosure should be construed as being covered by the claims and the specification.

Claims

1. A coaxial helicopter and flexible variable-pitch rotor system is characterized in that: comprising a helicopter body and a flexible variable-pitch rotor system.

The overall appearance of the helicopter body is drop-shaped, and the external profile of any cross section of the body is one of circular, long circular or oval;

the flexible variable pitch rotor system comprises an upper rotor assembly and a lower rotor assembly;

the upper rotor assembly comprises a first hub and first blades connected with the first hub, the lower rotor assembly comprises a second hub and second blades connected with the second hub, and the first blades tilt upwards and/or the second blades tilt downwards.

2. The helicopter body of claim 1, wherein: when the outer contour of a certain cross section of the machine body is in an oblong shape, the value range of the ratio A of the length to the width of the oblong shape is more than 1 and less than or equal to 2;

3. The flexible variable pitch rotor system of claim 1, wherein: the first blade and the first blade clamp assembly are connected with the first variable-pitch journal and the first propeller hub, and the second blade clamp assembly are connected with the second variable-pitch journal and the second propeller hub.

4. The flexible variable pitch rotor system of claim 3, wherein: the first paddle tilts upwards, and the second paddle tilts downwards.

5. The flexible variable pitch rotor system of claim 1, wherein: the diameter of a paddle disk of the upper rotor assembly is equal to that of the paddle disk of the lower rotor assembly, and the maximum distance between the first blade and the second blade in the vertical direction is 0.05-0.28 times of the diameter of the paddle disk;

6. A coaxial helicopter, characterized by: comprising the features of any of claims 1-5.