CN210793629U - Helicopter rotor blade tip structure and rotor - Google Patents
Helicopter rotor blade tip structure and rotor Download PDFInfo
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- CN210793629U CN210793629U CN201921091121.6U CN201921091121U CN210793629U CN 210793629 U CN210793629 U CN 210793629U CN 201921091121 U CN201921091121 U CN 201921091121U CN 210793629 U CN210793629 U CN 210793629U
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Abstract
The utility model provides a helicopter rotor blade tip structure and rotor belongs to the aeronautical technical field, at the width direction of rotor oar, including leading edge arc segment, trailing edge arc segment and the trailing edge diagonal that from the bottom up connected gradually, leading edge arc segment and trailing edge arc segment are three-dimensional curve, leading edge arc segment and trailing edge arc segment are protruding fillet structure, at the thickness direction of rotor oar, including upper surface cambered surface and lower surface cambered surface, upper surface cambered surface and lower surface cambered surface are concave fillet structure at the projection line of thickness direction. The utility model discloses can effectively delay the production of air current separation, reduce rotor blade tip resistance, reduce the recovery moment when hovering and flying at a high speed, promote unmanned helicopter efficiency of hovering, reduce unmanned helicopter flight oil consumption, reduce rotor overall vibration and noise level.
Description
Technical Field
The utility model belongs to the technical field of the aviation, a unmanned helicopter machine field is related to, especially relate to helicopter rotor blade tip structure and rotor.
Background
Along with the rapid development of unmanned aerial vehicle trade, rotor unmanned aerial vehicle's application is also more and more extensive, and rotor unmanned aerial vehicle rotor is undertaken rotor unmanned aerial vehicle required lift and manipulation power, is rotor unmanned aerial vehicle the most important part, and its aerodynamic appearance has very big influence to rotor unmanned aerial vehicle's aerodynamic performance and flight dynamics performance. The relative air velocity of the tip of rotor unmanned aerial vehicle rotor is high. Take rotor unmanned aerial vehicle that rotor diameter is 3 meters as an example: if the rotor speed is 1000 revolutions per minute, the linear speed of the rotor tip reaches 157 meters/second, so the aerodynamic profile of the rotor has a great influence on the aerodynamic performance of the whole rotor drone and at the same time on the aerodynamic noise and vibration level of the rotor.
The width of current rotor unmanned aerial vehicle rotor on the extending direction equals, wholly is the rectangle design, but because the rotor uses the propeller hub to become the circumferencial rotation as the center at the course of the work, so the linear velocity of rotor root is minimum, is close to zero, and the linear velocity of rotor point portion is the biggest, it is inhomogeneous to have led to the lift distribution that the rotor bore on the extending direction, root lift is minimum and point portion lift is the biggest promptly, thereby the structural safety of rotor has been influenced, and the use efficiency is influenced, the oil consumption is increased.
The shape of the rotor tip has a great influence on the performance of the rotor, the tip region is a very sensitive region which is a high dynamic pressure region of the blade and a formation and escape position of a tip vortex, and the small change of the tip shape can cause the strength and the track of the tip vortex to have large changes, so that the flow field, aerodynamic load and noise of the rotor are influenced.
SUMMERY OF THE UTILITY MODEL
The to-be-solved problem of the utility model is to provide helicopter rotor blade point structure and rotor, can effectively delay the production of air current separation, reduce rotor blade point portion resistance, reduce the recovery moment when hovering and flying at a high speed, promote unmanned helicopter efficiency of hovering, reduce unmanned helicopter flight oil consumption, reduce rotor bulk vibration and noise level.
In order to solve the technical problem, the utility model discloses a technical scheme is: the helicopter rotor wing tip structure and the rotor wing comprise a front edge arc line section, a rear edge arc line section and a rear edge inclined line section which are sequentially connected from bottom to top in the width direction of a rotor wing paddle, wherein the front edge arc line section and the rear edge arc line section are both three-dimensional curves, and the front edge arc line section and the rear edge arc line section are both convex round angle structures;
in the thickness direction of rotor oar, including upper surface cambered surface and lower surface cambered surface, the projection line of upper surface cambered surface and lower surface cambered surface in thickness direction is concave circular angle structure.
Further, the vertical direction is the + Z direction, the downward direction is the-Z direction, the convex fillet structure is that the central point is closer to the-Z direction relative to the circular arc, and the concave fillet structure is that the central point is closer to the + Z direction relative to the circular arc.
Furthermore, the projection of the front edge arc line segment and the rear edge arc line segment in the width direction of the rotor blade is a parabola, the connection point of the front edge arc line segment and the rotor blade body is a coordinate origin, the outward direction of the front edge of the rotor blade body is an X-axis direction, the direction of the front edge of the rotor blade body is perpendicular to the X-axis, and the direction of the rear edge of the rotor blade body from the coordinate origin is a Y-axis.
Further, the parabolic geometric equation of the leading edge arc segment is as follows: a is1X2+b1X+c1Wherein: 0.001 ≦ a1≦0.01，-10≦b1≦0，1≦c1≦ 800 in mm.
Further, the parabolic geometric equation of the leading edge arc segment is as follows: y is 0.002X2-0.8X +80 in mm.
Further, the parabolic geometric equation of the trailing arc segment is as follows: a is3X2+b3X+c3Wherein: 0.001 ≦ a3≦0.01，-10≦b3≦0，1≦c3≦ 800 in mm.
Further, the linear equation of the projection of the trailing edge diagonal segment in the width direction of the rotor blade is as follows: a is2X+b2Wherein: -0.1 ≦ a2≦-0.01，20≦b2≦ 200; the units are millimeters.
Further, the tie point of front edge arc line segment and rotor oar body is the origin of coordinates, and the outside direction of rotor oar body front edge is the X axle direction, and the perpendicular to X axle is followed the edge direction and is the Z axle from the origin of coordinates point to rotor oar body, at the thickness direction of rotor oar, the outer profile line of upper surface cambered surface and lower surface pitch arc projection is the parabola.
Further, the parabolic equation corresponding to the upper surface cambered surface is that Z is a4X2+c4Wherein: -0.00001 ≦ a4≦0，0≦c4≦ 50, and the lower surface arc may correspond to a parabola having a Z ═ a5X2+c5Wherein: -0.00001 ≦ a5≦0，-50≦c5≦0。
The helicopter rotor comprises a helicopter rotor, a helicopter rotor tip structure, a root and a main body, wherein the upper end of the main body comprises a first trailing edge straight line section and a second trailing edge straight line section which are connected through a chamfer angle in the width direction of a rotor blade, the rotor width corresponding to the first trailing edge straight line section is larger than that corresponding to the second trailing edge straight line section, the second trailing edge straight line section is connected with one end, away from a trailing edge arc line section, of a trailing edge inclined line section, the lower end of the main body is of a straight line structure and is connected with a leading edge arc line section, and the root is arranged at one end, away from.
Compared with the prior art, the utility model has the advantages and positive effect as follows.
1. The utility model discloses carry out further optimization to the rotor oar point, make whole structure can effectively reduce rotor point portion resistance, reduce the required moment of torsion when hovering and flying at a high speed, promote unmanned helicopter hover efficiency, reduce unmanned helicopter flight oil consumption, reduce rotor overall vibration and noise level, can effectively delay the production of air current separation, reduce rotor point portion resistance, reduce the recovery moment when hovering and flying at a high speed, promote unmanned helicopter hover efficiency, reduce unmanned helicopter flight oil consumption, reduce rotor overall vibration and noise level, this structure is more applicable to many engines, powerful helicopter, the very big condition of swing inertia of rotor oar, the stability of whole helicopter has been promoted;
2. trailing edge slope segment makes the wing section of rotor point portion move forward, reduces the restoring force moment of rotor, effectively improves unmanned aerial vehicle's mobility, reduces the burden of steering wheel.
Drawings
The accompanying drawings, which form a part hereof, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention without undue limitation. In the drawings:
FIG. 1 is a relationship diagram of the projection of the tip structure of a helicopter rotor of the present invention in the X-axis and Y-axis directions;
FIG. 2 is a relationship diagram of the projection of the tip structure of the helicopter rotor of the present invention in the X-axis and Z-axis directions;
fig. 3 is a schematic view of a helicopter rotor of the present invention in the width direction;
fig. 4 is a schematic view of the helicopter rotor of the present invention in the thickness direction.
Reference numerals:
1. a blade tip; 11. a leading edge arc segment; 12. a trailing arc segment; 13. a trailing edge diagonal segment; 14. an upper surface cambered surface; 15. a lower surface cambered surface; 2. a main body; 21. a first trailing edge straight line segment; 22. a second trailing edge straight line segment; 23. chamfering; 3. and (4) root.
Detailed Description
It should be noted that, in the present invention, the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. 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. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings.
As shown in fig. 1-4, the utility model discloses a helicopter rotor blade tip structure, in the width direction of rotor oar, blade tip 1 includes leading edge arc segment 11, trailing edge arc segment 12 and trailing edge diagonal 13 that from the bottom up connects gradually, leading edge arc segment 11 and trailing edge arc segment 12 are three-dimensional curves, leading edge arc segment 11 and trailing edge arc segment 12 are convex fillet structure, and trailing edge diagonal 13 makes the wing section of rotor tip portion move forward, reduce the recovery moment of rotor, effectively improve unmanned aerial vehicle's mobility, reduce the burden of steering wheel;
thickness direction at the rotor oar, including upper surface cambered surface 14 and lower surface cambered surface 15, upper surface cambered surface 14 and lower surface cambered surface 15 are concave fillet structure at thickness direction's projection line, whole structure can effectively reduce rotor point resistance, required torque force when reducing to hover and flight at a high speed, promote unmanned helicopter efficiency of hovering, reduce unmanned helicopter flight oil consumption, reduce rotor bulk vibration and noise level, can effectively delay the production of air current separation, reduce rotor point resistance, reduce the recovery moment when hovering and flight at a high speed, promote unmanned helicopter efficiency of hovering, reduce unmanned helicopter flight oil consumption, reduce rotor bulk vibration and noise level.
Preferably, the vertical direction is + Z direction, the downward direction is-Z direction, the convex round angle structure is that the central point is closer to the-Z direction relative to the circular arc, and the concave round angle structure is that the central point is closer to the + Z direction relative to the circular arc.
Preferably, the projections of the front edge arc line segment 11 and the rear edge arc line segment 12 in the width direction of the rotor blade are both parabolic lines, the connection point of the front edge arc line segment 11 and the rotor blade body 2 is a coordinate origin, the outward direction of the front edge of the rotor blade body 2 is the X-axis direction, the direction is perpendicular to the X-axis, and the direction from the coordinate origin to the rear edge of the rotor blade body 2 is the Y-axis.
Preferably, the parabolic geometry equation for the leading edge arc segment 11 is: a is1X2+b1X+c1Wherein: 0.001 ≦ a1≦0.01，-10≦b1≦0，1≦c1≦ 800 in mm, more preferably, the parabolic geometry equation for the leading edge arc segment 11 is: y is 0.002X2-0.8X +80 in mm; preferably, the parabolic geometry equation for the trailing arc segment 12 is: a is3X2+b3X+c3Wherein: 0.001 ≦ a3≦0.01，-10≦b3≦0，1≦c3≦ 800 in mm, more preferably, the parabolic geometry equation for the trailing arc segment 12 is: y is 0.05X2The 3X +568 unit is mm, and the combination of the shape of the front edge arc segment 11 and the shape of the rear edge arc segment can effectively delay the generation of airflow separation, reduce the resistance of the rotor tip and reduce the required restoring moment during hovering and high-speed flight.
Preferably, the linear equation of the projection of the trailing diagonal segment 13 in the width direction of the rotor blade is: a is2X+b2Wherein: -0.1 ≦ a2≦-0.01，20≦b2≦ 200; in millimeters, more preferably: y is 0.06X +136, and this equation structure makes the wing section of rotor point portion move forward, reduces the recovery moment of rotor, effectively improves unmanned aerial vehicle's mobility, reduces the burden of steering wheel.
Preferably, the connecting point of the front edge arc line segment 11 and the rotor blade body 2 is a coordinate origin, the outward direction of the front edge of the rotor blade body 2 is an X-axis direction, the direction is perpendicular to the X-axis, the direction from the coordinate origin to the upper edge of the rotor blade body 2 is a Z-axis, and the outer contour lines of the upper surface arc surface 14 and the lower surface arc projection are parabolas in the thickness direction of the rotor blade.
Preferably, the upper surface arc 14 corresponds to a parabolic equation of Z ═ a4X2+c4Wherein: -0.00001 ≦ a4≦0，0≦c450, preferably, the upper surface curve 14 corresponds to a parabolic equation of Z0.00015X2+10, the parabolic mode corresponding to the surface arc is Z ═ a5X2+c5Wherein: -0.00001 ≦ a5≦0，-50≦c5≦ 0; more preferably, the surface arc corresponds to a parabolic mode of Z ═ 0.00014X2-5。
Helicopter rotor, 1 structure of helicopter rotor oar tip, root 3 and main part 2, width direction at the rotor oar, the upper end of main part 2 includes first trailing edge straightway 21 and the second trailing edge straightway 22 that chamfer 23 connects, the rotor width that first trailing edge straightway 21 corresponds is greater than the rotor width that second trailing edge straightway 22 corresponds, second trailing edge straightway 22 is connected with the one end that trailing edge sloping line section 13 kept away from trailing edge arc section 12, the lower extreme of main part 2 is linear structure and is connected with leading edge arc section 11, root 3 establishes the one end of keeping away from 1 structure of oar tip in the main part, this structure has increased the lift of root 3, and 1 structure of oar tip has reduced the lift of afterbody, make whole structure atress more even on the extending direction, the torque force has been reduced, overall structure's security has been promoted.
Taking example data as an example, the present embodiment performs comparative analysis of a conventional aerodynamic profile rotor (rectangular planar blade), only a tapered sweepback tip aerodynamic profile rotor, only a lower anti-tip aerodynamic profile rotor, and the utility model discloses a tip aerodynamic profile optimized rotor (i.e., tapered sweepback plus lower anti-tip aerodynamic profile rotor) by performing tests on a rotor test rig on which rotor pull and torque can be measured, respectively, and analyzes from the test results:
in a hovering state, for a given rotor wing tension coefficient, the torque coefficient of the rotor wing with the optimized aerodynamic shape of the blade tip reaches the minimum value compared with the rotor wings with other three aerodynamic shapes, and the advantages of the aerodynamic shapes of the sweepback tapered blade tip and the lower reverse blade tip are combined.
When C is 0.008, compared with the rectangular tip without lower back and sweepback, the rotor tip 1 structure of the embodiment has the torque coefficient reduced by about 13% compared with the rectangular tip without lower back and sweepback;
when C is 0.008, the rotor tip 1 configuration of the present embodiment provides an approximately 11% improvement in hover coefficient over a rectangular tip without under-sweep and without sweep.
The company has set up the rotor oar before aiming at other models, have applied for the relevant patent, the information is "CN 208070014U-a many rotor unmanned aerial vehicle paddle and many rotor unmanned aerial vehicle", mainly suitable for the conventional helicopter, make the coefficient of hovering promote after optimizing the rotor structure, the coefficient of torque descends, but the structure of this application is applied to after the heavy-duty helicopter, the stability is still not good enough, this application and patent authorized are directed against different helicopter series, this structure is mainly directed against the multi-engine, powerful helicopter, the swing inertia of the rotor oar is especially big, the requirement to the coefficient of hovering and coefficient of torque of the rotor is higher, but the rotor structure has already tended to mature and stable at present, even if very slight improvement is the technology difficult to break through, this application breaks through the technological problem on the basis of the previous structure, made the further targeted improvement, make the whole structure and function of the rotor obtain further promotion, effectively reduce rotor point resistance, reduce required torsional forces when hovering and flying at a high speed, promote unmanned helicopter efficiency of hovering, reduce unmanned helicopter flight oil consumption, reduce rotor overall vibration and noise level, can effectively delay the production of air current separation, reduce rotor point resistance, reduce the recovery moment when hovering and flying at a high speed, promote unmanned helicopter efficiency of hovering, reduce unmanned helicopter flight oil consumption, reduce rotor overall vibration and noise level.
While one embodiment of the present invention has been described in detail, the description is only a preferred embodiment of the present invention, and should not be considered as limiting the scope of the present invention. All the equivalent changes and improvements made according to the application scope of the present invention should still fall within the patent coverage of the present invention.
Claims (10)
1. Helicopter rotor blade point structure, its characterized in that: the rotor blade comprises a front edge arc line section, a rear edge arc line section and a rear edge inclined line section which are sequentially connected from bottom to top in the width direction of the rotor blade, wherein the front edge arc line section and the rear edge arc line section are both three-dimensional curves, and the front edge arc line section and the rear edge arc line section are both convex round angle structures;
in the thickness direction of rotor oar, including upper surface cambered surface and lower surface cambered surface, the projection line of upper surface cambered surface and lower surface cambered surface in thickness direction is concave circular angle structure.
2. A helicopter rotor tip structure according to claim 1, wherein: the vertical direction is + Z direction, the downward direction is-Z direction, the convex fillet structure is that the central point is closer to-Z direction relative to the circular arc, and the concave fillet structure is that the central point is closer to + Z direction relative to the circular arc.
3. A helicopter rotor tip structure according to claim 1, wherein: the projections of the front edge arc line segment and the rear edge arc line segment in the width direction of the rotor blade are parabolas, the connection point of the front edge arc line segment and the rotor blade body is a coordinate origin, the outward direction of the front edge of the rotor blade body is an X-axis direction, the direction of the front edge of the rotor blade body is perpendicular to an X-axis, and the direction of the rear edge of the rotor blade body from the coordinate origin is a Y-axis.
4. A helicopter rotor tip structure according to claim 3, wherein: the parabolic geometric equation of the leading edge arc segment is as follows: a is1X2+b1X+c1Wherein: 0.001 ≦ a1≦0.01，-10≦b1≦0，1≦c1≦ 800 in mm.
5. A helicopter rotor tip structure according to claim 4, wherein: the parabolic geometric equation of the leading edge arc segment is as follows: y is 0.002X2-0.8X +80 in mm.
6. A helicopter rotor tip structure according to claim 3, wherein: the parabolic geometric equation of the trailing edge arc segment is as follows: a is3X2+b3X+c3Wherein: 0.001 ≦ a3≦0.01，-10≦b3≦0，1≦c3≦ 800 in mm.
7. A helicopter rotor tip structure according to claim 3, wherein: the linear equation of the projection of the trailing edge diagonal segment in the width direction of the rotor blade is as follows: a is2X+b2Wherein: -0.1 ≦ a2≦-0.01，20≦b2≦ 200; the units are millimeters.
8. A helicopter rotor tip structure according to claim 1, wherein: the tie point of front edge arc line section and rotor oar body is the origin of coordinates, and the outside direction of rotor oar body front edge is the X axle direction, and the perpendicular to X axle is followed the edge direction and is the Z axle on the directional rotor oar body of origin of coordinates, at the thickness direction of rotor oar, the projected outer contour line of upper surface cambered surface and lower surface pitch arc is the parabola.
9. A helicopter rotor tip structure according to claim 8, wherein: the parabolic equation corresponding to the upper surface cambered surface is Z ═ a4X2+c4Wherein: -0.00001 ≦ a4≦0，0≦c4≦ 50, and the lower surface arc may correspond to a parabola having a Z ═ a5X2+c5Wherein: -0.00001 ≦ a5≦0，-50≦c5≦0。
10. Helicopter rotor, its characterized in that: the helicopter rotor blade tip structure comprises a helicopter rotor blade tip structure, a root and a main body according to any one of claims 1 to 9, wherein the upper end of the main body comprises a first trailing edge straight line section and a second trailing edge straight line section which are connected in a chamfering mode, the rotor width corresponding to the first trailing edge straight line section is larger than that corresponding to the second trailing edge straight line section, the second trailing edge straight line section is connected with one end, away from a trailing edge arc line section, of the trailing edge inclined line section, the lower end of the main body is of a straight line structure and is connected with the leading edge arc line section, and the root is arranged at one end, away from the blade tip structure, of.
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| CN201921091121.6U CN210793629U (en) | 2019-07-12 | 2019-07-12 | Helicopter rotor blade tip structure and rotor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525644A (en) * | 2019-07-12 | 2019-12-03 | 天津曙光天成科技有限公司 | Lifting airscrew blade tip structure, the production method of rotor and blade tip |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525644A (en) * | 2019-07-12 | 2019-12-03 | 天津曙光天成科技有限公司 | Lifting airscrew blade tip structure, the production method of rotor and blade tip |
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Effective date of registration: 20221013 Address after: 300457 No. 105, Building 9, Zone B3 (formerly Zone 2 of Ronghui Business Park), Binhai Zhongguancun Science and Technology Park, Tianjin Economic and Technological Development Zone, Binhai New Area, Tianjin Patentee after: Tianjin Phoenix Intelligent Technology Co.,Ltd. Address before: No. 3, Tengfei Road, Junliangcheng, Dongli District, Tianjin 300457 Patentee before: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. |
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