阅读说明：本技术 直升机旋翼桨尖结构、旋翼及桨尖的制作方法 (Lifting airscrew blade tip structure, the production method of rotor and blade tip ) 是由 李鑫 孟志刚 于 2019-07-12 设计创作，主要内容包括：本发明提供了直升机旋翼桨尖结构、旋翼及桨尖的制作方法,属于航空技术领域,在旋翼桨的宽度方向,包括从下到上依次连接的前缘弧线段、后缘弧线段和后缘斜线段,所述前缘弧线段和后缘弧线段均为三维曲线,所述前缘弧线段和后缘弧线段均为凸圆角结构,在旋翼桨的厚度方向,包括上表面弧面和下表面弧面,所述上表面弧面和下表面弧面在厚度方向的投影线均为凹圆角结构。本发明可有效延缓气流分离的产生,减小旋翼桨尖部阻力、减小悬停及高速飞行时的恢复力矩、提升无人直升机悬停效率、减小无人直升机飞行油耗、减小旋翼整体振动和噪声水平。(The present invention provides lifting airscrew blade tip structures, the production method of rotor and blade tip, belong to technical field of aerospace, in the width direction of rotor, including sequentially connected leading edge arc segment from top to bottom, rear arc segment and rear oblique line section, the leading edge arc segment and rear arc segment are three-dimensional curve, the leading edge arc segment and rear arc segment are dome corner structure, in the thickness direction of rotor, including upper surface cambered surface and lower surface cambered surface, the upper surface cambered surface and lower surface cambered surface are recessed rounded structure in the projection line of thickness direction.The generation that the present invention can effectively delay air-flow to separate reduces rotor tip resistance, reduces hovering and righting moment when high-speed flight, promote unmanned helicopter hovering efficiency, reduce unmanned helicopter flight oil consumption, reduce rotor body vibration and noise level.)

1. lifting airscrew blade tip structure, it is characterised in that: sequentially connected in the width direction of rotor, including from top to bottom Leading edge arc segment, rear arc segment and rear oblique line section, the leading edge arc segment and rear arc segment are three-dimensional curve, described Leading edge arc segment and rear arc segment are dome corner structure；

In the thickness direction of rotor, including upper surface cambered surface and lower surface cambered surface, the upper surface cambered surface and lower surface cambered surface It is recessed rounded structure in the projection line of thickness direction.

2. lifting airscrew blade tip structure according to claim 1, it is characterised in that: be straight up +Z direction, downwards For -Z direction, the dome corner structure be centre point relative to circular arc closer to -Z direction, the recessed rounded structure is centre point Relative to circular arc closer to +Z direction.

3. lifting airscrew blade tip structure according to claim 1, it is characterised in that: the leading edge arc segment and rear arc Line segment is parabola in the projection of rotor width direction, and the tie point of the leading edge arc segment and rotor ontology is coordinate Origin, rotor ontology leading edge outward direction are X-direction, perpendicular to X-axis, are directed toward rotor ontology rear side from coordinate origin To for Y-axis.

4. lifting airscrew blade tip structure according to claim 3, it is characterised in that: the parabola of the leading edge arc segment Geometric equation are as follows: y=a₁X²+b₁X+c₁, in which: 0.001≤a₁≤ 0.01, -10≤b₁≤ 0,1≤c₁≤ 800, unit mm.

5. lifting airscrew blade tip structure according to claim 3, it is characterised in that: the parabola of the rear arc segment Geometric equation are as follows: y=a₃X²+b₃X+c₃, in which: 0.001≤a₃≤ 0.01, -10≤b₃≤ 0,1≤c₃≤ 800, unit mm.

6. lifting airscrew blade tip structure according to claim 3, it is characterised in that: the rear oblique line section is in rotor The linear equation of the projection of width direction are as follows: y=a₂X+b₂, in which: -0.1≤a₂≤ -0.01,20≤b₂≦200；Unit is milli Rice.

7. lifting airscrew blade tip structure according to claim 1, it is characterised in that: the leading edge arc segment and rotor The tie point of ontology is coordinate origin, and rotor ontology leading edge outward direction is that X-direction refers to perpendicular to X-axis from coordinate origin To rotor ontology upper limb direction be Z axis, in the thickness direction of rotor, the upper surface cambered surface and lower surface camber line projection Outer contour is parabola.

8. lifting airscrew blade tip structure according to claim 1, it is characterised in that: the corresponding throwing of the upper surface cambered surface Object line equation is Z=a₄X²+c₄, in which: -0.00001≤a₄≤ 0,0≤c₄≤ 50, the corresponding parabola of the lower surface camber line Mode is Z=a₅X²+c₅, in which: -0.00001≤a₅≤ 0, -50≤c₅≦0。

9. lifting airscrew, it is characterised in that: including lifting airscrew blade tip structure according to any one of claims 1 to 8, root Portion and main body, in the width direction of rotor, the upper end of main body includes the first rear straightway and the second rear of chamfering connection Straightway, the corresponding rotor width of the first rear straightway are greater than the corresponding rotor width of the second rear straightway, The second rear straightway is connect with the rear oblique line section far from one end of rear arc segment, and the lower end of the main body is straight It cable architecture and is connect with leading edge arc segment, the root is located at the one end of the main body far from blade tip structure.

10. the method for manufacturing lifting airscrew blade tip structure, it is characterised in that:

Step 1: partition structure, is divided into sequentially connected leading edge camber line from top to bottom in the width direction of rotor for blade tip Section, rear arc segment and rear oblique line section；Upper surface cambered surface and lower surface cambered surface are divided into the thickness direction of rotor；

Step 2: the tie point of the coordinate system of confirmation X-axis and Y-axis, leading edge arc segment and rotor ontology is coordinate origin, rotor Paddle ontology leading edge outward direction is X-direction, and perpendicular to X-axis, being directed toward rotor ontology rear direction from coordinate origin is Y-axis；

Step 3: determining the shape of leading edge arc segment, the parabola geometric equation of leading edge arc segment are as follows: y=a₁X²+b₁X+c₁, In: 0.001≤a₁≤ 0.01, -10≤b₁≤ 0,1≤c₁≤ 800, unit mm；

Step 4: determining the shape of rear arc segment, the parabola geometric equation of rear arc segment are as follows: y=a₃X²+b₃X+c₃, In: 0.001≤a₃≤ 0.01, -10≤b₃≤ 0,1≤c₃≤ 800, unit mm；

Step 5: determining the shape of rear oblique line section, linear equation of the rear oblique line section in the projection of rotor width direction are as follows: Y=a₂X+b₂, in which: -0.1≤a₂≤ -0.01,20≤b₂≦200；Unit is millimeter；

Step 6: the tie point of the coordinate system of confirmation X-axis and Z axis, the leading edge arc segment and rotor ontology is coordinate origin, Rotor ontology leading edge outward direction is X-direction, and perpendicular to X-axis, being directed toward rotor ontology upper limb direction from coordinate origin is Z Axis；

Step 7: the corresponding parabolic equation of the upper surface cambered surface is Z=a₄X²+c₄, in which: -0.00001≤a₄≤ 0,0≤ c₄≤ 50, the corresponding parabolic manner of the lower surface camber line is Z=a₅X²+c₅, in which: -0.00001≤a₅≤ 0, -50≤c₅ ≦0；

Step 8: carrying out processing and fabricating after confirming shape according to above step.

Technical field

The invention belongs to technical field of aerospace, are related to unmanned helicopter machine field more particularly to lifting airscrew blade tip knot The production method of structure, rotor and blade tip.

Background technique

With the fast development of unmanned plane industry, the application field of rotor wing unmanned aerial vehicle is also more and more extensive, and rotor nobody Machine rotor-borne lift and steering force needed for rotor wing unmanned aerial vehicle, be the mostly important component of rotor wing unmanned aerial vehicle, it is pneumatic outer Shape has a great impact to the aeroperformance and flight dynamics performance of rotor wing unmanned aerial vehicle.The blade tip of rotor wing unmanned aerial vehicle rotor is opposite Air velocity is high.By taking rotor diameter is 3 meters of rotor wing unmanned aerial vehicle as an example: if rotor revolving speed is 1000 turns per minute, revolving The linear velocity of the blade tip of the wing just reaches 157 meter per seconds, thus rotor aerodynamic configuration is to the effect of aerodynamic performance of whole frame rotor wing unmanned aerial vehicle It is very big, and at the same time influencing the aerodynamic noise and level of vibration of rotor.

The width of existing rotor wing unmanned aerial vehicle rotor in the direction of extension is equal, and whole is in rectangular design, but due to rotation The wing is at circle rotation centered on propeller hub during the work time, therefore the linear velocity of rotary-wing root section is minimum, close to zero, and rotor The linear velocity of tip is maximum, results in that the lift distribution that rotor is born in the direction of extension is uneven, i.e., root lift is minimum And tip lift is maximum, to affect the structure safety of rotor, and influences service efficiency, increases oil consumption.

Rotor Blade Tips Shapes have great influence to rotary wing performance, and blade tip region is a very sensitive region, it It is both that the formation in the high dynamic pressure area and blade tip whirlpool of blade and evolution place, the small change of Blade Tips Shapes lead to blade tip whirlpool Vortex strength and track have big variation, to influence the flow field of rotor, aerodynamic loading and noise, especially for multiple-motor, big The swing inertia of the helicopter of power, rotor is especially big, therefore the structure of rotor blade tip is most important, at present rotor blade tip Structure has graduallyd mature, and is further improved and is broken through even more extremely difficult on the basis of the prior art.

Summary of the invention

The problem to be solved in the present invention is to be to provide lifting airscrew blade tip structure, the production method of rotor and blade tip, The generation that can effectively delay air-flow to separate reduces rotor tip resistance, reduces hovering and righting moment when high-speed flight, mention Unmanned helicopter hovering efficiency is risen, reduces unmanned helicopter flight oil consumption, reduce rotor body vibration and noise level.

In order to solve the above technical problems, the technical solution adopted by the present invention is that: lifting airscrew blade tip structure, rotor and paddle Point production method, in the width direction of rotor, including from top to bottom sequentially connected leading edge arc segment, rear arc segment and Rear oblique line section, the leading edge arc segment and rear arc segment are three-dimensional curve, the leading edge arc segment and rear arc segment It is dome corner structure；

In the thickness direction of rotor, including upper surface cambered surface and lower surface cambered surface, the upper surface cambered surface and lower surface Cambered surface is recessed rounded structure in the projection line of thickness direction.

Further, it is straight up +Z direction, is downwards -Z direction, the dome corner structure is centre point relative to circle For arc closer to -Z direction, the recessed rounded structure is centre point relative to circular arc closer to +Z direction.

Further, the leading edge arc segment and rear arc segment are parabola in the projection of rotor width direction, The tie point of the leading edge arc segment and rotor ontology is coordinate origin, and rotor ontology leading edge outward direction is X-direction, Perpendicular to X-axis, being directed toward rotor ontology rear direction from coordinate origin is Y-axis.

Further, the parabola geometric equation of the leading edge arc segment are as follows: y=a₁X²+b₁X+c₁, in which: 0.001≤a₁ ≤ 0.01, -10≤b₁≤ 0,1≤c₁≤ 800, unit mm.

Further, the parabola geometric equation of the leading edge arc segment are as follows: y=0.002X²- 0.8X+80, unit are mm。

Further, the parabola geometric equation of the rear arc segment are as follows: y=a₃X²+b₃X+c₃, in which: 0.001≤a₃ ≤ 0.01, -10≤b₃≤ 0,1≤c₃≤ 800, unit mm.

Further, the linear equation of projection of the rear oblique line section in rotor width direction are as follows: y=a₂X+b₂, In: -0.1≤a₂≤ -0.01,20≤b₂≦200；Unit is millimeter.

Further, the tie point of the leading edge arc segment and rotor ontology is coordinate origin, rotor ontology leading edge Outward direction is X-direction, and perpendicular to X-axis, being directed toward rotor ontology upper limb direction from coordinate origin is Z axis, in rotor The outer contour of thickness direction, the upper surface cambered surface and the projection of lower surface camber line is parabola.

Further, the corresponding parabolic equation of the upper surface cambered surface is Z=a₄X²+c₄, in which: -0.00001≤a₄ ≤ 0,0≤c₄≤ 50, the corresponding parabolic manner of the lower surface camber line is Z=a₅X²+c₅, in which: -0.00001≤a₅≤ 0 ,- 50≦c₅≦0。

Lifting airscrew, lifting airscrew blade tip structure, root and main body, in the width direction of rotor, main body it is upper End includes the first rear straightway and the second rear straightway of chamfering connection, and the corresponding rotor of the first rear straightway is wide Degree is greater than the corresponding rotor width of the second rear straightway, and the second rear straightway and the rear oblique line section are separate One end of rear arc segment connects, and the lower end of the main body is linear structure and connect with leading edge arc segment that the root is located at The one end of the main body far from blade tip structure.

The method for manufacturing lifting airscrew blade tip structure, follows the steps below:

Step 1: partition structure, is divided into sequentially connected leading edge from top to bottom in the width direction of rotor for blade tip Arc segment, rear arc segment and rear oblique line section；Upper surface cambered surface and lower surface cambered surface are divided into the thickness direction of rotor；

Step 2: the tie point of the coordinate system of confirmation X-axis and Y-axis, leading edge arc segment and rotor ontology is coordinate origin, Rotor ontology leading edge outward direction is X-direction, and perpendicular to X-axis, being directed toward rotor ontology rear direction from coordinate origin is Y Axis；

Step 3: determining the shape of leading edge arc segment, the parabola geometric equation of leading edge arc segment are as follows: y=a₁X²+b₁X+ c₁, in which: 0.001≤a₁≤ 0.01, -10≤b₁≤ 0,1≤c₁≤ 800, unit mm；

Step 4: determining the shape of rear arc segment, the parabola geometric equation of rear arc segment are as follows: y=a₃X²+b₃X+ c₃, in which: 0.001≤a₃≤ 0.01, -10≤b₃≤ 0,1≤c₃≤ 800, unit mm；

Step 5: determining the shape of rear oblique line section, rear oblique line section is in the straight line side of the projection of rotor width direction Journey are as follows: y=a₂X+b₂, in which: -0.1≤a₂≤ -0.01,20≤b₂≦200；Unit is millimeter；

Step 6: the tie point of the coordinate system of confirmation X-axis and Z axis, the leading edge arc segment and rotor ontology is coordinate Origin, rotor ontology leading edge outward direction are X-direction, perpendicular to X-axis, are directed toward rotor ontology upper limb side from coordinate origin To for Z axis；

Step 7: the corresponding parabolic equation of the upper surface cambered surface is Z=a₄X²+c₄, in which: -0.00001≤a₄≦ 0,0≤c₄≤ 50, the corresponding parabolic manner of the lower surface camber line is Z=a₅X²+c₅, in which: -0.00001≤a₅≤ 0, -50 ≦c₅≦0；

Step 8: carrying out processing and fabricating after confirming shape according to above step.

Compared with prior art, the present invention has the advantage that as follows with good effect.

1, the present invention further optimizes rotor blade tip, so that total can effectively reduce the resistance of rotor tip Power reduces required torsional forces when hovering and high-speed flight, promotes unmanned helicopter hovering efficiency, reduces unmanned helicopter flight oil Consumption reduces rotor body vibration and noise level, the generation that can effectively delay air-flow to separate, and reduces rotor tip resistance, reduces Righting moment, promotion unmanned helicopter hovering efficiency when hovering and high-speed flight, reduction unmanned helicopter flight oil consumption, reduction Rotor body vibration and noise level, this structure are more suitable for multiple-motor, powerful helicopter, the swing inertia of rotor King-sized situation improves the stability of entire helicopter；

2, rear oblique line section is moved along the aerofoil profile of rotor tip, reduces the righting moment of rotor, effectively improves nobody The mobility of machine reduces the burden of steering engine.

Detailed description of the invention

The attached drawing for constituting a part of the invention is used to provide further understanding of the present invention, schematic reality of the invention It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:

Fig. 1 is the relational graph that lifting airscrew blade tip structure of the present invention is projected in X-axis and Y direction；

Fig. 2 is the relational graph that lifting airscrew blade tip structure of the present invention is projected in X-axis and Z-direction；

Fig. 3 is schematic diagram of the lifting airscrew of the present invention in width direction；

Fig. 4 is schematic diagram of the lifting airscrew of the present invention in thickness direction.

Appended drawing reference:

1, blade tip；11, leading edge arc segment；12, rear arc segment；13, rear oblique line section；14, upper surface cambered surface；15, under Surface cambered surface；2, main body；21, the first rear straightway；22, the second rear straightway；23, chamfering；3, root.

Specific embodiment

It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the present invention can phase Mutually combination.

In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower", The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as pair Limitation of the invention.In addition, term " first ", " second " etc. are used for description purposes only, it is not understood to indicate or imply phase To importance or implicitly indicate the quantity of indicated technical characteristic.The feature for defining " first ", " second " etc. as a result, can To explicitly or implicitly include one or more of the features.In the description of the present invention, unless otherwise indicated, " multiple " It is meant that two or more.

In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood by concrete condition Concrete meaning in the present invention.

Specific embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

As shown in Figure 1 to 4, the present invention is lifting airscrew blade tip structure, and in the width direction of rotor, blade tip 1 is wrapped Sequentially connected leading edge arc segment 11, rear arc segment 12 and rear oblique line section 13 from top to bottom are included, leading edge arc segment 11 is with after Edge arc segment 12 is three-dimensional curve, and leading edge arc segment 11 and rear arc segment 12 are dome corner structure, and rear oblique line Section 13 is moved along the aerofoil profile of rotor tip, reduces the righting moment of rotor, effectively improves the mobility of unmanned plane, reduces rudder The burden of machine；

In the thickness direction of rotor, including upper surface cambered surface 14 and lower surface cambered surface 15, upper surface cambered surface 14 and following table Face cambered surface 15 is recessed rounded structure in the projection line of thickness direction, and total can effectively reduce rotor tip resistance, reduce Required torsional forces, promotion unmanned helicopter hovering efficiency, reduction unmanned helicopter flight oil consumption, reduction when hovering and high-speed flight Rotor body vibration and noise level, the generation that can effectively delay air-flow to separate reduce rotor tip resistance, reduce hovering and height Righting moment, promotion unmanned helicopter hovering efficiency when fast flight, reduction unmanned helicopter flight oil consumption, reduction rotor are whole Vibration and noise level.

Preferably, it is straight up +Z direction, is downwards -Z direction, dome corner structure is that centre point is more leaned on relative to circular arc Nearly -Z direction, recessed rounded structure be centre point relative to circular arc closer to +Z direction.

Preferably, leading edge arc segment 11 and rear arc segment 12 are parabola in the projection of rotor width direction, preceding The tie point of edge arc segment 11 and rotor ontology 2 is coordinate origin, and 2 leading edge outward direction of rotor ontology is X-direction, is hung down Directly in X-axis, being directed toward 2 rear direction of rotor ontology from coordinate origin is Y-axis.

Preferably, the parabola geometric equation of leading edge arc segment 11 are as follows: y=a₁X²+b₁X+c₁, in which: 0.001≤a₁≦ 0.01, -10≤b₁≤ 0,1≤c₁≤ 800, unit mm, it is highly preferred that the parabola geometric equation of leading edge arc segment 11 are as follows: y =0.002X²- 0.8X+80, unit mm；Preferably, the parabola geometric equation of rear arc segment 12 are as follows: y=a₃X²+b₃X+ c₃, in which: 0.001≤a₃≤ 0.01, -10≤b₃≤ 0,1≤c₃≤ 800, unit mm, it is highly preferred that rear arc segment 12 Parabola geometric equation are as follows: y=0.05X²- 3X+568, unit mm, the either shape of leading edge arc segment 11 or rear arc The shape of shape section, the two reduce rotor tip resistance, reduce hovering and height in conjunction with the generation that can effectively delay air-flow to separate is arranged Required righting moment when fast flight.

Preferably, linear equation of the rear oblique line section 13 in the projection of rotor width direction are as follows: y=a₂X+b₂, in which:- 0.1≦a₂≤ -0.01,20≤b₂≦200；Unit is millimeter, more preferably: y=0.06X+136, this equation structure makes rotor The aerofoil profile of tip is moved along, and reduces the righting moment of rotor, effectively improves the mobility of unmanned plane, reduces the burden of steering engine.

Preferably, the tie point of leading edge arc segment 11 and rotor ontology 2 is coordinate origin, 2 leading edge of rotor ontology to Outside direction is X-direction, and perpendicular to X-axis, being directed toward 2 upper limb direction of rotor ontology from coordinate origin is Z axis, in the thickness of rotor Direction is spent, the outer contour that upper surface cambered surface 14 and lower surface camber line project is parabola.

Preferably, the corresponding parabolic equation of upper surface cambered surface 14 is Z=a₄X²+c₄, in which: -0.00001≤a₄≤ 0,0 ≦c₄≤ 50, it may be preferable that the corresponding parabolic equation of upper surface cambered surface 14 is Z=0.00015X²+ 10, the corresponding throwing of surface camber line Object line mode is Z=a₅X²+c₅, in which: -0.00001≤a₅≤ 0, -50≤c₅≦0；It is highly preferred that the corresponding throwing of surface camber line Object line mode is Z=0.00014X²-5。

Lifting airscrew, 1 structure of lifting airscrew blade tip, root 3 and main body 2, in the width direction of rotor, main body 2 Upper end include the first rear straightway 21 and the second rear straightway 22 that chamfering 23 connects, the first rear straightway 21 is corresponding Rotor width be greater than the corresponding rotor width of the second rear straightway 22, the second rear straightway 22 is remote with rear oblique line section 13 One end connection from rear arc segment 12, the lower end of main body 2 are linear structure and connect with leading edge arc segment 11 that root 3 is located at The one end of main body far from 1 structure of blade tip, this construction increases the lift of root 3, and 1 structure of blade tip reduces the liter of tail portion Power reduces torsional forces so that total is more uniformly stressed in the direction of extension, improves integrally-built safety.

With embodiment data instance, present embodiment passes through enterprising in the Rotor Test rack that can survey rotor thrust and torque Row test, carried out respectively traditional, pneumatic shape rotor (rectangle plane blade), taper swept tip aerodynamic configuration rotor, only Under anti-blade tip aerodynamic configuration rotor and blade tip aerodynamic configuration design rotor of the present invention (i.e. taper sweepback under adding anti-blade tip it is pneumatically outer Shape rotor) comparative analysis, by test result analysis:

Under floating state, for given rotor thrust coefficient, the torsion of present embodiment blade tip aerodynamic configuration design rotor Moment coefficient reaches minimum value compared with other three kinds of aerodynamic configuration rotors, and it is pneumatically outer to combine above-mentioned sweepback taper blade tip and lower anti-blade tip The respective advantage of shape.

As C=0.008,1 structure of rotor blade tip of present embodiment is compared with without the lower rectangle blade tip instead without sweepback, 1 structure of this rotor blade tip is than having dropped about 13% without the lower rectangle blade tip torque coefficient instead without sweepback；

As C=0.008,1 structure of rotor blade tip of present embodiment is than the hovering without the lower rectangle blade tip instead without sweepback Coefficient improves about 11%.

The method for manufacturing lifting airscrew blade tip structure, follows the steps below:

Step 1: partition structure, is divided into sequentially connected leading edge from top to bottom in the width direction of rotor for blade tip 1 Arc segment 11, rear arc segment 12 and rear oblique line section 13；Upper surface cambered surface 14 is divided into under in the thickness direction of rotor Surface cambered surface 15；

Step 2: the tie point of the coordinate system of confirmation X-axis and Y-axis, leading edge arc segment 11 and rotor ontology is that coordinate is former Point, rotor ontology leading edge outward direction are X-direction, perpendicular to X-axis, are directed toward rotor ontology rear direction from coordinate origin For Y-axis；

Step 3: determining the shape of leading edge arc segment 11, the parabola geometric equation of leading edge arc segment 11 are as follows: y=a₁X²+ b₁X+c₁, in which: 0.001≤a₁≤ 0.01, -10≤b₁≤ 0,1≤c₁≤ 800, unit mm；

Step 4: determining the shape of rear arc segment 12, the parabola geometric equation of rear arc segment 12 are as follows: y=a₃X²+ b₃X+c₃, in which: 0.001≤a₃≤ 0.01, -10≤b₃≤ 0,1≤c₃≤ 800, unit mm；

Step 5: determine rear oblique line section 13 shape, rear oblique line section 13 rotor width direction projection it is straight Line equation are as follows: y=a₂X+b₂, in which: -0.1≤a₂≤ -0.01,20≤b₂≦200；Unit is millimeter；

Step 6: the tie point of the coordinate system of confirmation X-axis and Z axis, the leading edge arc segment 11 and rotor ontology is to sit Origin is marked, rotor ontology leading edge outward direction is X-direction, perpendicular to X-axis, is directed toward rotor ontology upper limb from coordinate origin Direction is Z axis；

Step 7: the corresponding parabolic equation of the upper surface cambered surface 14 is Z=a₄X²+c₄, in which: -0.00001≤a₄ ≤ 0,0≤c₄≤ 50, the corresponding parabolic manner of the lower surface camber line is Z=a₅X²+c₅, in which: -0.00001≤a₅≤ 0 ,- 50≦c₅≦0；

Step 8: carrying out processing and fabricating after confirming shape according to above step.

It can reach what the application to be realized in strict accordance with the rotor blade tip structure that above step and shape setting process Technical effect, and each following every section of structure individually can realize the opposite better function of existing structure according to camber line processing, And put together technical effect can be more obvious, such as leading edge arc segment 11, rear arc segment 12 and rear oblique line section 13；Upper table Face cambered surface 14 and lower surface cambered surface 15, these sections separately machined can come out, have the meaning independently implemented, be applied in combination only Preferred embodiment should not be considered as limiting the scope of the invention, and independent implementation or all the changes and improvements etc. are all Within the scope of protection of this application.

It is directed to other types before our company provided with rotor, has applied for that relevant patent, information are " a kind of multi-rotor unmanned aerial vehicle blade of CN208070014U- and multi-rotor unmanned aerial vehicle ", is primarily adapted for use in conventional helicopter, optimization Make coefficient promotion of hovering, torque coefficient decline after rotor structure, but structure of this application is applied after heavy helicopter, surely It is qualitative should not enough, for different helicopters series, this structure is primarily directed to multiple for the application and granted patent The swing inertia of motivation, powerful helicopter, rotor is especially big, to rotor hovering coefficient and torque coefficient requirement more Height, but rotor structure has tended to be mature and has stablized at present, even very subtle improvement is all the technology for being difficult to break through, this Shen The please break-through skill problem in structure basis before, has done the improvement further directed to property so that the total of rotor and Function is had been further upgraded, and is effectively reduced rotor tip resistance, is reduced required torsional forces, promotion when hovering and high-speed flight Unmanned helicopter hovering efficiency reduces unmanned helicopter flight oil consumption, reduces rotor body vibration and noise level, can effectively prolong The generation for flow separation of getting a breathing space reduces rotor tip resistance, reduces hovering and righting moment when high-speed flight, promote nobody and go straight up to Machine hovering efficiency reduces unmanned helicopter flight oil consumption, reduces rotor body vibration and noise level.

One embodiment of the present invention has been described in detail above, but the content is only preferable implementation of the invention Example, should not be considered as limiting the scope of the invention.It is all according to all the changes and improvements made by the present patent application range Deng should still be within the scope of the patent of the present invention.