CN203921195U - Depopulated helicopter rotor blade tip - Google Patents
Depopulated helicopter rotor blade tip Download PDFInfo
- Publication number
- CN203921195U CN203921195U CN201420379007.4U CN201420379007U CN203921195U CN 203921195 U CN203921195 U CN 203921195U CN 201420379007 U CN201420379007 U CN 201420379007U CN 203921195 U CN203921195 U CN 203921195U
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- China
- Prior art keywords
- rotor
- blade tip
- camber line
- depopulated helicopter
- rotor blade
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- Expired - Lifetime
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- 230000035939 shock Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000037237 body shape Effects 0.000 description 1
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Abstract
The utility model relates to heligyro, further relates to the optimal design of depopulated helicopter rotor blade tip.The utility model provides a kind of and effectively reduce rotor blade tip resistance, reduces hovering and required torque power when high-speed row, promote driverless operation heligyro hovering efficiency, reduce the sweepback taper blade tip blade form of unmanned helicopter flight oil consumption.Depopulated helicopter rotor blade tip, comprising: leading edge convex camber line and trailing edge spill camber line.The utility model is with respect to the advantage of prior art: under floating state, for given tension coefficient, new blade tip aerodynamic configuration is optimized the little of the more conventional aerodynamic configuration rotor of rotor torque coefficient.
Description
Technical field:
The utility model relates to heligyro, further relates to the optimal design of depopulated helicopter rotor blade tip.
Background technology:
Along with the fast development of unmanned plane helicopter industry, the application of unmanned plane helicopter is more and more extensive, and rotor blade is being born the required lift of depopulated helicopter and actuating force, be the most important parts of depopulated helicopter, aeroperformance and the flight dynamics performance of its aerodynamic configuration to depopulated helicopter has a significant impact.Depopulated helicopter blade tip relative air speed is high.Taking rotor diameter as the depopulated helicopter of 3 meters is as example: if gyroplane rotate speed turns as per minute 1000, the linear velocity of its rotor wing tip just reaches 565.2 kilometers of 157 meter per seconds, speed per hours so! , thereby its aerodynamic configuration is very large to whole airplane effect of aerodynamic performance, while especially flying before high speed, because incoming flow and advancing blade relative wind relatively superpose mutually, makes advancing blade blade tip place be easy to enter shock stall.
At present, as shown in most of depopulated helicopter blade aerodynamic configurations aerodynamic configuration rotor as conventional in Fig. 1, the wing tip of the lifting airscrew in history evolution history of enumerating from Fig. 1, why having the evolution of wing-tip shape in Fig. 1, is mainly because the generation of helicopter lift is rotated taking main shaft as the center of circle, produced relative motion generation with air by rotor.The relative wind of rotor from root to wing tip longitudinally distributes and sees Fig. 6, as seen from the figure due to rotatablely moving of rotor be superimposed with helicopter before fly motion, will bring following problem:
(1) local shock problem
The advancing blade rotating is windward because the stack of air rate causes having produced local shock, and local shock can reduce rotor pneumatic efficiency greatly, thereby affects rotor forward direction pulling force.
(2) burbling problem
The retreating blade of rotation is because folded the subtracting of air rate reduces its actual air rate greatly with the wind, for the lift of balance advancing blade generation, retreating blade will increase the angle of attack, thereby causing its airflow on surface to produce separates, the pneumatic efficiency that this also can reduce rotor greatly, causes rotor forward direction pulling force to reduce.
Therefore, need badly and improve.
Summary of the invention:
For addressing the above problem, the utility model proposes and a kind ofly effectively reduce rotor blade tip resistance, required torque power while reducing hovering and high-speed flight, promote driverless operation heligyro hovering efficiency, reduce the sweepback taper blade tip blade form of unmanned helicopter flight oil consumption.
Depopulated helicopter rotor blade tip, comprising: leading edge convex camber line and trailing edge spill camber line;
Described leading edge convex camber line and trailing edge spill camber line are parabola;
Definition: convex camber line with it is characterized in that, the point of connection of described convex camber line and rotor oar body is the origin of coordinates, rotor oar body leading edge outward direction is X-direction; Perpendicular to X-axis, pointing to rotor oar body trailing edge direction from the origin of coordinates is Y-axis;
The geometric equation of described leading edge convex camber line is: y=a
1x
2, wherein :-0.06≤a
1≤-0.04;
The geometric equation of described trailing edge spill camber line is: y=a
1x
2+ b
2x+c
2, wherein :-0.003≤a
2≤-0.002,0.1≤b
2≤ 0.2 ,-100≤c
2≤-800.
The utility model is with respect to the advantage of prior art:
With embodiment data instance, the utility model, by the test of carrying out on the Rotor Test stand that can survey rotor thrust and moment of torsion, carries out Experimental Comparison analysis result as Fig. 4, Fig. 5 to traditional rotor and the utility model rotor, by test result analysis:
Under floating state, for given tension coefficient, new blade tip aerodynamic configuration is optimized the little of the more conventional aerodynamic configuration rotor of rotor torque coefficient.
Work as C
t=0.01 o'clock, the utility model blade tip aerodynamic configuration was optimized rotor torque coefficient and has been reduced approximately 10.5% than the torque coefficient of conventional aerodynamic configuration rotor;
Work as C
t=0.01 o'clock, the utility model blade tip aerodynamic configuration was optimized rotor torque coefficient and has been improved approximately 9.5% than the hovering efficiency of conventional aerodynamic configuration rotor.
Brief description of the drawings:
Fig. 1 is that pure helicopter rotor blade tip develops schematic diagram.
Fig. 2 is the utility model lifting airscrew blade tip profile schematic diagram.
Fig. 3 is lifting airscrew blade tip geometric parameter in the utility model embodiment; Wherein, 1 represent leading edge convex camber line; 2 represent trailing edge spill camber line.
Fig. 4 is pulling force-moment of torsion correlation curve of rotor in benchmark rotor and the utility model embodiment; Wherein, 3 represent benchmark rotor thrust-torque curve; 4 represent rotor thrust-torque curve in the utility model embodiment.
Fig. 5 is pulling force-hovering efficiency (FOM) correlation curve of rotor in benchmark rotor and the utility model embodiment; Wherein, 5 represent benchmark rotor thrust-hovering efficiency (FOM) curve; 6 represent rotor thrust-hovering efficiency in the utility model embodiment (FOM) curve.
Fig. 6 is rotor relative air speed schematic diagram while flying before benchmark heligyro; Wherein, before 7 representatives, fly relative velocity; 8 representative rotation relative velocities; 9 represent the speed that is involutory; 10 represent hand of rotation; 11 represent reversed flow region.
Detailed description of the invention:
Depopulated helicopter rotor blade tip, comprising: leading edge convex camber line and trailing edge spill camber line;
Described leading edge convex camber line and trailing edge spill camber line are parabola;
Definition: convex camber line with it is characterized in that, the point of connection of described convex camber line and rotor oar body is the origin of coordinates, rotor oar body leading edge outward direction is X-direction; Perpendicular to X-axis, pointing to rotor oar body trailing edge direction from the origin of coordinates is Y-axis;
The geometric equation of described leading edge convex camber line is: y=-0.05x
2; Unit is millimeter.
The geometric equation of described trailing edge spill camber line is: y=-0.025x
2+ 0.15x-100; Unit is millimeter.
Rotor oar body shape centre portion (except wing tip) is rectangle, and oar is wide is 110 millimeters, long 1300 millimeters of single-blade, 1000 revs/min of rotating speeds, 80 kilograms of take-off weights.The correlation data of the parameter of benchmark rotor and employing the utility model rotor blade tip as Figure 4-Figure 6.
Technical scheme effect is remarkable.
Claims (4)
1. depopulated helicopter rotor blade tip, is characterized in that, comprising: leading edge convex camber line and trailing edge spill camber line.
2. depopulated helicopter rotor blade tip according to claim 1, is characterized in that, described leading edge convex camber line and trailing edge spill camber line are parabola.
3. depopulated helicopter rotor blade tip according to claim 2, definition: convex camber line with it is characterized in that, the point of connection of described convex camber line and rotor oar body is the origin of coordinates, rotor oar body leading edge outward direction is X-direction; Perpendicular to X-axis, pointing to rotor oar body trailing edge direction from the origin of coordinates is Y-axis; It is characterized in that, the geometric equation of described leading edge convex camber line is: y=a
1x
2, wherein :-0.06≤a
1≤-0.04.
4. depopulated helicopter rotor blade tip according to claim 2, definition: convex camber line with it is characterized in that, the point of connection of described convex camber line and rotor oar body is the origin of coordinates, rotor oar body leading edge outward direction is X-direction; Perpendicular to X-axis, pointing to rotor oar body trailing edge direction from the origin of coordinates is Y-axis; It is characterized in that, the geometric equation of described trailing edge spill camber line is: y=a
1x
2+ b
2x+c
2, wherein :-0.003≤a
2≤-0.002,0.1≤b
2≤ 0.2 ,-100≤c
2≤-800.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420379007.4U CN203921195U (en) | 2014-07-08 | 2014-07-08 | Depopulated helicopter rotor blade tip |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420379007.4U CN203921195U (en) | 2014-07-08 | 2014-07-08 | Depopulated helicopter rotor blade tip |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203921195U true CN203921195U (en) | 2014-11-05 |
Family
ID=51817054
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420379007.4U Expired - Lifetime CN203921195U (en) | 2014-07-08 | 2014-07-08 | Depopulated helicopter rotor blade tip |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203921195U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104044736A (en) * | 2014-07-08 | 2014-09-17 | 天津宏泽天成科技有限公司 | Rotor blade tip of unmanned helicopter |
-
2014
- 2014-07-08 CN CN201420379007.4U patent/CN203921195U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104044736A (en) * | 2014-07-08 | 2014-09-17 | 天津宏泽天成科技有限公司 | Rotor blade tip of unmanned helicopter |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170223 Address after: 300301 Tianjin city Dongli District Junliangcheng Tengfei Road No. 3 floor of building B Patentee after: TIANJIN AURORA UAV TECHNOLOGY Co.,Ltd. Address before: 300201 Tianjin science and Technology Museum, Longchang Road, Tianjin, No. 94, Patentee before: TIANJIN HONGZE TIANCHENG TECHNOLOGY CO.,LTD. |
|
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. Assignor: TIANJIN AURORA UAV TECHNOLOGY Co.,Ltd. Contract record no.: 2017990000085 Denomination of utility model: Rotor blade tip of unmanned helicopter Granted publication date: 20141105 License type: Exclusive License Record date: 20170314 |
|
| EE01 | Entry into force of recordation of patent licensing contract | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170418 Address after: 300000 Tianjin city Dongli District Junliangcheng Tengfei Road No. 3 floor of building B Patentee after: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. Address before: 300301 Tianjin city Dongli District Junliangcheng Tengfei Road No. 3 floor of building B Patentee before: TIANJIN AURORA UAV TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220928 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: Floor 1, block B, No.3, Tengfei Road, Junliang City, Dongli District, Tianjin Patentee before: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| CX01 | Expiry of patent term |
Granted publication date: 20141105 |
|
| CX01 | Expiry of patent term |