CN104326082A - Helicopter and blade thereof - Google Patents
Helicopter and blade thereof Download PDFInfo
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- CN104326082A CN104326082A CN201410559963.5A CN201410559963A CN104326082A CN 104326082 A CN104326082 A CN 104326082A CN 201410559963 A CN201410559963 A CN 201410559963A CN 104326082 A CN104326082 A CN 104326082A
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- blade
- tip portion
- blade tip
- main part
- helicopter
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Abstract
The invention discloses a helicopter and a blade thereof. The blade of the helicopter comprises a main body part, a blade root part and a blade tip part, wherein the main body part straightly extends along a horizontal direction; the blade root part is connected to one end of the main body part; the blade tip part is connected to the other end of the main body part, and the blade tip part downwards extends from one end, which is close to the main body part, of the blade tip part to one end, which is far away from the main body part, of the blade tip part. The blade of the helicopter disclosed by the embodiment of the invention has the advantages of high pneumatic hovering efficiency, good shock absorption and noise reduction effects, and the like.
Description
Technical field
The present invention relates to air equipment technical field, in particular to a kind of helicopter blade and there is the helicopter of blade of described helicopter.
Background technology
Helicopter in correlation technique, mostly its blade is based on straight or trapezoidal configuration, and rotates suitable negative twist angle on this basis.The hovering pneumatic efficiency of this blade is lower, and noise is larger.
Summary of the invention
The present invention is intended to solve one of above-mentioned technical matters in correlation technique at least to a certain extent.For this reason, the present invention proposes a kind of blade of helicopter, and the blade of this helicopter has the advantages such as hovering pneumatic efficiency is high, damping noise reduction is effective.
The present invention also proposes a kind of helicopter with the blade of described helicopter.
For achieving the above object, embodiment according to a first aspect of the invention proposes a kind of blade of helicopter, and the blade of described helicopter comprises: main part, and described main part is straight extension in the horizontal direction; Blade root portion, described blade root portion is connected to one end of described main part; Blade tip portion, described blade tip portion is connected to the other end of described main part, and described blade tip portion is from the one end away from described main part in one end to the described blade tip portion of the described main part of vicinity in described blade tip portion to downward-extension.
According to the blade of the helicopter of the embodiment of the present invention, there is the advantages such as hovering pneumatic efficiency is high, damping noise reduction is effective.
In addition, the blade of helicopter according to the above embodiment of the present invention can also have following additional technical characteristic:
According to one embodiment of present invention, the maximum angle between described blade tip portion and described main part is 15 degree.
According to one embodiment of present invention, the length in described blade tip portion is 5% of the length of described blade.
According to one embodiment of present invention, described blade tip portion extends linearly downwards or is bent downwardly extension with parabolic track.
According to one embodiment of present invention, the width in described blade tip portion reduces gradually from the one end away from described main part in one end to the described blade tip portion of the described main part of vicinity in described blade tip portion.
According to one embodiment of present invention, the width of the one end away from described main part in described blade tip portion is 0.75 with the ratio of the width of one end of the described main part of vicinity in described blade tip portion.
According to one embodiment of present invention, described blade tip portion is concordant in chordwise direction with 1/4 string of a musical instrument of described main part.
According to one embodiment of present invention, described main part, described blade tip portion and described blade root portion are integrally formed.
According to one embodiment of present invention, described blade root portion is provided with mounting hole.
Embodiment according to a second aspect of the invention proposes a kind of helicopter, and described helicopter comprises the blade of the helicopter described in embodiment according to a first aspect of the invention.
According to the helicopter of the embodiment of the present invention, there is the advantages such as hovering pneumatic efficiency is high, noise is little.
Accompanying drawing explanation
Fig. 1 is the perspective view of the blade of helicopter according to the embodiment of the present invention.
Fig. 2 is the lateral plan of the blade of helicopter according to the embodiment of the present invention.
Fig. 3 is the birds-eye view of the blade of helicopter according to the embodiment of the present invention.
Fig. 4 is the inverted diherdral degree of blade and the linear schematic diagram of lower anti position and hovering efficiency of helicopter according to the embodiment of the present invention.
Fig. 5 is the linear schematic diagram of anti-and hovering efficiency under anti-and non-parabolic under the parabolic in the blade tip portion of the blade of helicopter according to the embodiment of the present invention.
Fig. 6 is the sweepback angle of blade and the linear schematic diagram of hovering efficiency of helicopter according to the embodiment of the present invention.
Fig. 7 is the taper ratio of blade and the linear schematic diagram of hovering efficiency of helicopter according to the embodiment of the present invention.
Reference numeral: the blade 10 of helicopter, main part 100, blade root portion 200, mounting hole 210, blade tip portion 300.
Detailed description of the invention
Be described below in detail embodiments of the invention, the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.
Below with reference to the accompanying drawings blade 10 according to the helicopter of the embodiment of the present invention is described.
As shown in Fig. 1-Fig. 7, comprise main part 100, blade root portion 200 and blade tip portion 300 according to the blade 10 of the helicopter of the embodiment of the present invention.
Main part 100 straight extension in the horizontal direction (horizontal direction is as shown in the arrow A in Fig. 1-Fig. 3).Blade root portion 200 is connected to one end of main part 100, and blade root portion 200 is connected with the propeller hub of helicopter.Blade tip portion 300 is connected to the other end of main part 100.Blade tip portion 300 is from the one end away from main part 100 in one end to the blade tip portion 300 of the contiguous main part 100 in blade tip portion 300 to downward-extension (shown in above-below direction arrow B as in Figure 1 and Figure 2).In other words, blade tip portion 300 is sagging to form lower antistructure.
According to the blade 10 of the helicopter of the embodiment of the present invention, by connecting sagging blade tip portion 300 on straight main part 100, pneumatic structure anti-under forming straight blade, such one side can improve pneumatic efficiency during helicopter in hover, can improve the damping noise reduction effect of blade 10 on the other hand.Therefore, according to the blade 10 of the helicopter of the embodiment of the present invention, there is the advantages such as hovering pneumatic efficiency is high, damping noise reduction is effective.
Below with reference to the accompanying drawings blade 10 according to the helicopter of the specific embodiment of the invention is described.
In specific embodiments more of the present invention, as shown in Fig. 1-Fig. 7, comprise main part 100, blade root portion 200 and blade tip portion 300 according to the blade 10 of the helicopter of the embodiment of the present invention.
As shown in Figure 2, the maximum angle between blade tip portion 300 and main part 100 is 15 degree.That is, the lower anti-maximum angle in blade tip portion 300 is 15 degree.
As shown in Figure 3, the length in blade tip portion 300 is 5% of the length of blade 10.
Applicant draws the linear schematic diagram (as shown in Figure 4) of inverted diherdral degree and lower anti position and hovering efficiency through lot of experiments, above-mentioned inverted diherdral degree and lower anti position being set by analyzing, hovering pneumatic efficiency and the damping noise reduction effect of blade 10 can be ensured.
In concrete examples more of the present invention, blade tip portion 300 can be arranged to parabolic type and non-parabolicity type, applicant's linear schematic diagram (as shown in Figure 5) of anti-and hovering efficiency under anti-and non-parabolic under overtesting draws the parabolic in blade tip portion.In other words, blade tip portion 300 extends linearly downwards.Or blade tip portion 300 is bent downwardly extension with parabolic track.
In specific embodiments more of the present invention, as shown in Figure 3, the width in blade tip portion 300 reduces gradually from the one end away from main part 100 in one end to the blade tip portion 300 of the contiguous main part 100 in blade tip portion 300.In other words, blade tip portion 300 can be substantially trapezoidal.
Wherein, the width of the one end away from main part 100 in blade tip portion 300 is 0.75 with the ratio of the width of one end of the contiguous main part 100 in blade tip portion 300.In other words, the taper ratio of blade tip 300 is 0.75.Drawn the linear schematic diagram (as shown in Figure 7) of taper ratio and hovering efficiency by test, by analyzing, the taper ratio of blade tip 300 being arranged to above-mentioned numerical value, the hovering pneumatic efficiency of blade 10 can be improved further.
In concrete examples more of the present invention, as shown in Figure 3, blade tip portion 300 is concordant in chordwise direction with 1/4 string of a musical instrument of main part 100.That is, blade 10 adopts without sweepback structure.The linear schematic diagram (as shown in Figure 6) of sweepback angle and hovering efficiency is drawn by test, by analyzing, sweepback not to increase significantly effect to the pneumatic efficiency under helicopter in hover state, thus blade 10 is arranged to without sweepback structure, the production technology of blade 10 can be simplified when not affecting hovering and being pneumatic.
In specific embodiments more of the present invention, in order to ensure the structural strength of blade 10 and pneumatic effect, main part 100, blade tip portion 300 and blade root portion 200 are integrally formed.
Alternatively, as shown in figures 1 and 3, blade root portion 200 is provided with mounting hole 210, to facilitate the installation of blade 10 and helicopter hub.
Helicopter according to the embodiment of the present invention is described below.
The blade 10 of helicopter according to the above embodiment of the present invention is comprised according to the helicopter of the embodiment of the present invention.
According to the helicopter of the embodiment of the present invention, by utilizing the blade 10 of helicopter according to the above embodiment of the present invention, there is the advantages such as hovering pneumatic efficiency is high, noise is little.
According to the helicopter of the embodiment of the present invention other form and operation be all known for those of ordinary skills, be not described in detail here.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ", " thickness ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", " outward ", " cw ", orientation or the position relationship of the instruction such as " conter clockwise " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limitation of the present invention can not be interpreted as.
In addition, term " first ", " second " only for describing object, and can not be interpreted as instruction or hint relative importance or imply the quantity indicating indicated technical characteristic.Thus, be limited with " first ", the feature of " second " can express or impliedly comprise one or more these features.In describing the invention, the implication of " multiple " is at least two, such as two, three etc., unless otherwise expressly limited specifically.
In the present invention, unless otherwise clearly defined and limited, the term such as term " installation ", " being connected ", " connection ", " fixing " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or integral; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals or the interaction relationship of two elements.For the ordinary skill in the art, above-mentioned term concrete meaning in the present invention can be understood as the case may be.
In the present invention, unless otherwise clearly defined and limited, fisrt feature second feature it " on " or D score can comprise the first and second features and directly contact, also can comprise the first and second features and not be directly contact but by the other characterisation contact between them.And, fisrt feature second feature " on ", " top " and " above " comprise fisrt feature directly over second feature and oblique upper, or only represent that fisrt feature level height is higher than second feature.Fisrt feature second feature " under ", " below " and " below " comprise fisrt feature immediately below second feature and tiltedly below, or only represent that fisrt feature level height is less than second feature.
In the description of this specification sheets, specific features, structure, material or feature that the description of reference term " embodiment ", " some embodiments ", " example ", " concrete example " or " some examples " etc. means to describe in conjunction with this embodiment or example are contained at least one embodiment of the present invention or example.In this manual, to the schematic representation of above-mentioned term not must for be identical embodiment or example.And the specific features of description, structure, material or feature can combine in an appropriate manner in any one or more embodiment or example.In addition, the different embodiment described in this specification sheets or example can carry out engaging and combining by those skilled in the art.
Although illustrate and describe embodiments of the invention above, be understandable that, above-described embodiment is exemplary, can not be interpreted as limitation of the present invention, and those of ordinary skill in the art can change above-described embodiment within the scope of the invention, revises, replace and modification.
Claims (10)
1. a blade for helicopter, is characterized in that, comprising:
Main part, described main part is straight extension in the horizontal direction;
Blade root portion, described blade root portion is connected to one end of described main part;
Blade tip portion, described blade tip portion is connected to the other end of described main part, and described blade tip portion is from the one end away from described main part in one end to the described blade tip portion of the described main part of vicinity in described blade tip portion to downward-extension.
2. the blade of helicopter according to claim 1, is characterized in that, the maximum angle between described blade tip portion and described main part is 15 degree.
3. the blade of helicopter according to claim 1, is characterized in that, the length in described blade tip portion is 5% of the length of described blade.
4. the blade of helicopter according to claim 1, is characterized in that, described blade tip portion extends linearly downwards or is bent downwardly extension with parabolic track.
5. the blade of helicopter according to claim 1, is characterized in that, the width in described blade tip portion reduces gradually from the one end away from described main part in one end to the described blade tip portion of the described main part of vicinity in described blade tip portion.
6. the blade of helicopter according to claim 5, is characterized in that, the width of the one end away from described main part in described blade tip portion is 0.75 with the ratio of the width of one end of the described main part of vicinity in described blade tip portion.
7. the blade of helicopter according to claim 1, is characterized in that, described blade tip portion is concordant in chordwise direction with 1/4 string of a musical instrument of described main part.
8. the blade of helicopter according to claim 1, is characterized in that, described main part, described blade tip portion and described blade root portion are integrally formed.
9. the blade of helicopter according to claim 1, is characterized in that, described blade root portion is provided with mounting hole.
10. a helicopter, is characterized in that, comprises the blade of the helicopter according to any one of claim 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410559963.5A CN104326082A (en) | 2014-10-20 | 2014-10-20 | Helicopter and blade thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410559963.5A CN104326082A (en) | 2014-10-20 | 2014-10-20 | Helicopter and blade thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104326082A true CN104326082A (en) | 2015-02-04 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410559963.5A Pending CN104326082A (en) | 2014-10-20 | 2014-10-20 | Helicopter and blade thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104326082A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104816827A (en) * | 2015-04-01 | 2015-08-05 | 天峋创新（北京）科技有限公司 | Low-induced-resistance helicopter rotor wing with sweepback anhedral wingtip |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04317892A (en) * | 1991-04-17 | 1992-11-09 | Mitsubishi Heavy Ind Ltd | Helicopter rotor blade |
| EP0689990A1 (en) * | 1994-06-30 | 1996-01-03 | Kawada Industries, Inc. | Noise reduction device for rotorcraft |
| EP1035014A2 (en) * | 1999-03-12 | 2000-09-13 | Advanced Technology Institute of Commuter-Helicopter, Ltd. | Rotor blade for rotorcraft |
| JP2001301697A (en) * | 2000-04-18 | 2001-10-31 | Tech Res & Dev Inst Of Japan Def Agency | Helicopter blade with upper and lower camber angle |
| KR20100111983A (en) * | 2009-04-08 | 2010-10-18 | 건국대학교 산학협력단 | Rotor blade for rotorcraft to change sweep-back angle of the blade tip actively |
| EP2730503A2 (en) * | 2012-11-12 | 2014-05-14 | Sikorsky Aircraft Corporation | Flexbeam rotor attachment to rotor blade |
| CN203666968U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Negative dihedral aerofoil winglet structure |
-
2014
- 2014-10-20 CN CN201410559963.5A patent/CN104326082A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04317892A (en) * | 1991-04-17 | 1992-11-09 | Mitsubishi Heavy Ind Ltd | Helicopter rotor blade |
| EP0689990A1 (en) * | 1994-06-30 | 1996-01-03 | Kawada Industries, Inc. | Noise reduction device for rotorcraft |
| EP1035014A2 (en) * | 1999-03-12 | 2000-09-13 | Advanced Technology Institute of Commuter-Helicopter, Ltd. | Rotor blade for rotorcraft |
| JP2001301697A (en) * | 2000-04-18 | 2001-10-31 | Tech Res & Dev Inst Of Japan Def Agency | Helicopter blade with upper and lower camber angle |
| KR20100111983A (en) * | 2009-04-08 | 2010-10-18 | 건국대학교 산학협력단 | Rotor blade for rotorcraft to change sweep-back angle of the blade tip actively |
| EP2730503A2 (en) * | 2012-11-12 | 2014-05-14 | Sikorsky Aircraft Corporation | Flexbeam rotor attachment to rotor blade |
| CN203666968U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Negative dihedral aerofoil winglet structure |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104816827A (en) * | 2015-04-01 | 2015-08-05 | 天峋创新（北京）科技有限公司 | Low-induced-resistance helicopter rotor wing with sweepback anhedral wingtip |
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| PB01 | Publication | ||
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| C41 | Transfer of patent application or patent right or utility model | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20161128 Address after: 518057 Guangdong city of Shenzhen province high tech Industrial Park, high-tech South Road seven Shenzhen Research Institute of Tsinghua University Applicant after: Shenzhen Institute of Stinghua University Address before: 100084 Haidian District 100084-82 mailbox Beijing Applicant before: Tsinghua University Applicant before: Shenzhen Institute of Stinghua University |
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150204 |