CN114486148A - Rotor suitable for research of propeller tip vortex flow control experiment - Google Patents
Rotor suitable for research of propeller tip vortex flow control experiment Download PDFInfo
- Publication number
- CN114486148A CN114486148A CN202111542600.7A CN202111542600A CN114486148A CN 114486148 A CN114486148 A CN 114486148A CN 202111542600 A CN202111542600 A CN 202111542600A CN 114486148 A CN114486148 A CN 114486148A
- Authority
- CN
- China
- Prior art keywords
- rotor
- tip
- flow control
- vortex flow
- basic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000011160 research Methods 0.000 title claims abstract description 15
- 238000002474 experimental method Methods 0.000 title claims abstract description 6
- 229910001008 7075 aluminium alloy Inorganic materials 0.000 claims description 4
- 239000004677 Nylon Substances 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 4
- 229920001778 nylon Polymers 0.000 claims description 4
- 238000005245 sintering Methods 0.000 claims description 4
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 238000010146 3D printing Methods 0.000 claims description 2
- 238000011161 development Methods 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 7
- 238000012545 processing Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000002349 favourable effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
Abstract
The invention discloses a rotor wing suitable for the research of a rotor tip eddy current dynamic control experiment, which comprises a basic rotor wing and a rotor wing tip, wherein the rotor wing tip is arranged at the end part of the basic rotor wing and detachably connected with the basic rotor wing, the basic rotor wing is provided with a connecting section, the connecting section and the basic rotor wing are integrally formed, and the rotor wing tip is provided with an inner cavity section matched with the connecting section. The basic rotor and the rotor tip are designed and processed independently, and the shape of the rotor tip can be changed only by replacing the rotor tip, so that the flow control of the tip vortex is realized, the cost for the tip vortex flow control experimental research can be reduced, the rotor tip can be replaced quickly and conveniently, and the development of the tip vortex flow control experimental research work is facilitated.
Description
Technical Field
The invention relates to the technical field of flow control, in particular to a rotor wing suitable for experimental study on tip vortex flow control.
Background
The Blade Vortex Interference (BVI) is a physical phenomenon of aerodynamic interference specific to a helicopter rotor, in which when the rotor rotates at a high speed, the free vortex of a preceding blade collides with or approaches a succeeding blade, and the aerodynamic load on the succeeding blade locally changes sharply due to the interaction of the blade vortex.
The research on the rotor blade tip vortex flow control mainly adopts a numerical research method at present, and experimental research is rare. The analysis reasons mainly include high cost, long period and high risk of experimental research. In experimental research, because rotor models are often processed by adopting light, strong and high-performance carbon fiber composite materials, the rotor and the propeller tip are required to be integrally molded by compression. The processing cost is high, the shape of the blade tip cannot be changed, and the development of blade tip vortex flow control experimental research is limited.
Disclosure of Invention
The invention aims to overcome the defects of blade tip vortex flow control experimental study, provides a rotor which realizes flow control of a rotor blade tip vortex by replacing a rotor blade tip, is convenient and quick to replace, is suitable for experimental study of various rotor blade tip vortex flow control, and has lower cost.
The purpose of the invention is realized by the following technical scheme:
the utility model provides a rotor suitable for research of oar point vortex dynamic control experiment, includes basic rotor and sets up at basic rotor tip and can dismantle the rotor oar point of being connected with basic rotor.
Preferably, the basis rotor on be equipped with the linkage segment, linkage segment and basis rotor integrated into one piece are equipped with on the rotor oar point with linkage segment complex inner chamber section.
Preferably, the connecting section is provided with a threaded hole, and the inner cavity section is provided with a fixing hole matched with the threaded hole.
Preferably, the screw hole be three, three screw hole evenly sets up, basis rotor and rotor oar point are fixed through countersunk screw and fastening nut.
Preferably, the basic rotor wing is a 7075 aluminum alloy basic rotor wing.
Preferably, the rotor blade tip is a 3D printing nylon sintering rotor blade tip.
Preferably, the profile of the rotor tip comprises a swept-back tip, a leading-edge swept-back, a combination of swept-back and swept-back, an open-hole tip, and a parabolic swept-back.
Preferably, the connecting section and the inner cavity section are in clearance fit, and a 0.05mm clearance is formed between the connecting section and the inner cavity section.
The invention has the beneficial effects that:
(1) the basis rotor and rotor blade point design and processing alone, only need be through the change to the rotor blade point, can realize the change of blade point appearance to the realization can reduce the expense cost of blade point vortex dynamic control experimental study to the flow control of blade point whirlpool, and it is quick convenient to change the rotor blade point, is favorable to developing of blade point vortex dynamic control experimental study work.
(2) The linkage segment and basic rotor integrated into one piece for the whole mass distribution and the focus of installation back rotor are changeed and are adjusted control, can realize the static balance of rotor. Be equipped with on the rotor oar point with linkage segment complex inner chamber section, linkage segment cooperation inner chamber section can realize quick location installation, and simultaneously, linkage segment cooperation inner chamber section provides vertical holding power, more stabilizes after making on the basis rotor and the installation of rotor oar point.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an oblique view of a rotor tip;
FIG. 3 is a right side view of a rotor tip;
figure 4 is a schematic view of a swept-back, tipped rotor tip;
figure 5 is a schematic view of a swept-back tip rotor tip;
figure 6 is a schematic view of a leading edge swept rotor tip;
figure 7 is a schematic view of a forward-aft swept combined rotor tip;
FIG. 8 is a schematic view of an apertured tip rotor tip;
figure 9 is a schematic view of a parabolic swept-back tip rotor tip;
FIG. 10 is a graph of the time history of rotor pull force as a function of pitch angle measured by a balance;
in the figure, 1-basic rotor, 2-rotor tip, 3-connecting section, 4-inner cavity section, 5-threaded hole, 6-countersunk head screw and 7-fastening nut.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive effort based on the embodiments of the present invention, are within the scope of protection of the present invention.
Referring to fig. 1-10, the present invention provides a technical solution:
the utility model provides a rotor suitable for tip vortex flow control experimental study, includes basic rotor 1 and sets up at 1 tip of basic rotor and the rotor tip 2 of being connected can be dismantled with basic rotor 1. Basis rotor and 1 rotor oar point 2 design and processing alone, only need be through the change to rotor oar point 2, can realize the change of oar point appearance to the realization can reduce the expense cost of oar point vortex dynamic control experimental study to the flow control of oar point vortex, and it is quick convenient to change rotor oar point 2, is favorable to developing of oar point vortex dynamic control experimental study work.
Further, basis rotor 1 on be equipped with linkage segment 3, linkage segment 3 and 1 integrated into one piece of basis rotor, the weight of rotor oar tip 2 mainly depends on basis rotor 1 and linkage segment 3, integrated into one piece's design makes the whole mass distribution and the focus of installation back rotor change regulation and control more, can realize the static balance of rotor. And an inner cavity section 4 matched with the connecting section 3 is arranged on the rotor wing tip 2. Connecting segment 3 cooperation inner chamber section 4 can realize quick location installation, and simultaneously, connecting segment 3 cooperation inner chamber section 4 provides vertical holding power, makes on the basis rotor 1 more firm with rotor blade 2 installation back.
Furthermore, the connecting section 3 on be equipped with screw hole 5 (screw hole 5 diameter 3mm in this embodiment), inner chamber section 4 be equipped with screw hole 5 complex fixed orifices. Wherein, screw hole 5 be three, three screw hole 5 evenly sets up, guarantees that the atress is balanced (the figure and the position of screw hole 5 can be adjusted according to the experimental model), basis rotor 1 and rotor oar point 2 are fixed through countersunk screw 6 and fastening nut 7, guarantee that fixed back rotor surfacing does not have the arch.
The basic rotor wing 1 is a 7075 aluminum alloy basic rotor wing. The basic rotor wing 1 is made of 7075 aluminum alloy materials, high-precision numerical control machining is adopted, the extension length is 430mm, and the chord length is 60 mm. The basic rotor wing 1 and the connecting section 3 are integrally processed, the cross section of the connecting section 3 is in a quasi-rectangular shape, the length in the chord direction is 25mm, the length in the span direction is 14.5mm, and the thickness is 2 mm. Rotor blade tip 2 print nylon sintering rotor blade tip for 3D. The processing of rotor blade point 2 adopts 3D to print nylon sintering, and its exhibition length is 97mm, and the chord length is 60 mm. Connecting segment 3 and inner chamber section 4 adopt clearance fit, consider the precision that 3D printed, be equipped with 0.05 mm's clearance between connecting segment 3 and the inner chamber section 4, do benefit to the assembly.
During installation, the connecting section 3 is embedded into the inner cavity section 4, and the connection and matching of the basic rotor wing 1 and the rotor wing tip 2 are realized. Countersunk head screw 6 passes through screw hole 5, is fastened by fastening nut 7, realizes the fastening cooperation of basic rotor 1 and rotor blade point 2.
According to the rotor wing designed by the method, the total weight of the model can be controlled to be below 0.5kg, the rotor wing model can normally run, the dynamic balance characteristic is stable, and the stable rotating speed can reach 500-1200 rpm.
During the experiment, the connection between the basic rotor wing 1 and the rotation center O is kept unchanged (figure 1), and the change of the shapes of various blade tips can be realized by replacing the rotor wing blade tips 2, so that the experimental research on the blade tip vortex flow control is realized.
Six configurations of rotor tips 2 are provided, including swept-back tapers, swept-back tips, leading-edge swept-back, combinations of swept-back and swept-back, apertured tips, and parabolic swept-back (corresponding in sequence to figures 4-9).
As shown in fig. 10, when the pitch angle α is 7 ° and 12 °, the balance force measurement result changes smoothly with the time history, and the three-time repeatability is good. The flow field established by the rotor model is stable, the dynamic balance performance is stable, and the method can be used for carrying out experimental research on the propeller tip vortex dynamic control.
The foregoing is illustrative of the preferred embodiments of this invention, and it is to be understood that the invention is not limited to the precise form disclosed herein and that various other combinations, modifications, and environments may be resorted to, falling within the scope of the concept as disclosed herein, either as described above or as apparent to those skilled in the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. The utility model provides a rotor suitable for research of oar point vortex flow control experiment which characterized in that: including basic rotor (1) and set up rotor oar point (2) in basic rotor (1) tip and can dismantle the connection with basic rotor (1).
2. A rotor suitable for experimental study of tip vortex flow control as claimed in claim 1, wherein: basic rotor (1) on be equipped with linkage segment (3), linkage segment (3) and basic rotor (1) integrated into one piece are equipped with on rotor oar point (2) with linkage segment (3) complex inner chamber section (4).
3. A rotor suitable for experimental study of tip vortex flow control as claimed in claim 2, wherein: the connecting section (3) is provided with a threaded hole (5), and the inner cavity section (4) is provided with a fixing hole matched with the threaded hole (5).
4. A rotor suitable for experimental study of tip vortex flow control as claimed in claim 3, wherein: threaded hole (5) be three, three threaded hole (5) evenly set up, basis rotor (1) and rotor oar point (2) are fixed through countersunk screw (6) and fastening nut (7).
5. A rotor suitable for experimental study of tip vortex flow control as claimed in claim 1, wherein: the basic rotor wing (1) is a 7075 aluminum alloy basic rotor wing.
6. A rotor suitable for experimental study of tip vortex flow control as claimed in claim 1, wherein: the rotor blade tip (2) is a 3D printing nylon sintering rotor blade tip.
7. A rotor suitable for experimental study of tip vortex flow control as claimed in claim 1, wherein: the appearance of the rotor wing tip (2) comprises a sweepback taper, a sweepback tip, a leading edge sweepback, a combination of the sweepback and the sweepback, an opening tip and a parabolic sweepback.
8. A rotor suitable for experimental study of tip vortex flow control as claimed in claim 2, wherein: the connecting section (3) and the inner cavity section (4) are in clearance fit, and a 0.05mm clearance is arranged between the connecting section (3) and the inner cavity section (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111542600.7A CN114486148A (en) | 2021-12-14 | 2021-12-14 | Rotor suitable for research of propeller tip vortex flow control experiment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111542600.7A CN114486148A (en) | 2021-12-14 | 2021-12-14 | Rotor suitable for research of propeller tip vortex flow control experiment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114486148A true CN114486148A (en) | 2022-05-13 |
Family
ID=81494488
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111542600.7A Pending CN114486148A (en) | 2021-12-14 | 2021-12-14 | Rotor suitable for research of propeller tip vortex flow control experiment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114486148A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5320494A (en) * | 1992-12-22 | 1994-06-14 | United Technologies Corporation | Helicopter rotor blade having a replaceable anhedral tip |
| JP2013539522A (en) * | 2010-09-10 | 2013-10-24 | ヴォッベン プロパティーズ ゲーエムベーハー | Removable rotor blade tip |
| CA2845134A1 (en) * | 2013-03-07 | 2014-09-07 | Bell Helicopter Textron Inc. | Removable rotor blade tip |
| CN208070014U (en) * | 2018-04-11 | 2018-11-09 | 天津曙光天成科技有限公司 | A kind of multi-rotor unmanned aerial vehicle blade and multi-rotor unmanned aerial vehicle |
| CN209905055U (en) * | 2018-12-18 | 2020-01-07 | 辽宁壮龙无人机科技有限公司 | Rotor oar and unmanned aerial vehicle |
| CN211001827U (en) * | 2019-12-13 | 2020-07-14 | 河南昆豫无人机科技有限公司 | Unmanned aerial vehicle rotor structure compounded by aluminum profiles and plastics |
| CN214824085U (en) * | 2021-08-05 | 2021-11-23 | 河南坤宇无人机科技有限公司 | Outer end structure of compound unmanned aerial vehicle rotor of plastic-aluminum |
-
2021
- 2021-12-14 CN CN202111542600.7A patent/CN114486148A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5320494A (en) * | 1992-12-22 | 1994-06-14 | United Technologies Corporation | Helicopter rotor blade having a replaceable anhedral tip |
| JP2013539522A (en) * | 2010-09-10 | 2013-10-24 | ヴォッベン プロパティーズ ゲーエムベーハー | Removable rotor blade tip |
| CA2845134A1 (en) * | 2013-03-07 | 2014-09-07 | Bell Helicopter Textron Inc. | Removable rotor blade tip |
| EP2774847A1 (en) * | 2013-03-07 | 2014-09-10 | Bell Helicopter Textron Inc. | Removeable rotor blade tip |
| CN208070014U (en) * | 2018-04-11 | 2018-11-09 | 天津曙光天成科技有限公司 | A kind of multi-rotor unmanned aerial vehicle blade and multi-rotor unmanned aerial vehicle |
| CN209905055U (en) * | 2018-12-18 | 2020-01-07 | 辽宁壮龙无人机科技有限公司 | Rotor oar and unmanned aerial vehicle |
| CN211001827U (en) * | 2019-12-13 | 2020-07-14 | 河南昆豫无人机科技有限公司 | Unmanned aerial vehicle rotor structure compounded by aluminum profiles and plastics |
| CN214824085U (en) * | 2021-08-05 | 2021-11-23 | 河南坤宇无人机科技有限公司 | Outer end structure of compound unmanned aerial vehicle rotor of plastic-aluminum |
Non-Patent Citations (2)
| Title |
|---|
| MANTAY WR.YEAGER JR WF: "parametric tip effects for conformable rotor application", NASA TECHNICAL MEMORANDUM, pages 2 - 3 * |
| 郑华: "先进模型旋翼的设计分析与试验", 中国优秀硕士学位论文全文数据库工程科技II辑, no. 2007, pages 14 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| DE602007006292D1 (en) | AIRCRAFT WITH A DEVICE FOR GENERATING AN AERODYNAMIC EFFORT FORCE | |
| US11927196B2 (en) | Ceiling fan blade | |
| US6394397B1 (en) | Lifting surface with active variable tip member and method for influencing lifting surface behavior therewith | |
| US4150920A (en) | Rotor blade tipweight assembly | |
| RU2408499C2 (en) | Rotor blade for high-speed gyrodyne aircraft | |
| CN205499338U (en) | Self -adaptation variable -pitch propeller oar and aircraft | |
| CN206344995U (en) | Ducted fan for aircraft | |
| CN114486148A (en) | Rotor suitable for research of propeller tip vortex flow control experiment | |
| CN205418072U (en) | Screw, power component and aircraft | |
| CN101628346A (en) | Method for slowing down outlet speed of carbon fiber composite material hand-made hole and buffer device thereof | |
| JPH04293695A (en) | Low noise type tail section rotor | |
| GB2400089A (en) | Aerofoil section | |
| CN110758717B (en) | Concealed wing control surface driving mechanism | |
| CN106184672A (en) | A kind of composite propeller | |
| CN115489718A (en) | 3D who takes aileron prints wing and aircraft | |
| ITMI952519A1 (en) | PROPULSION PROPELLER GROUP FOR AIRCRAFT IN GENERAL | |
| CN205469818U (en) | Make an uproar screw and helicopter fall | |
| CN108527895A (en) | A kind of bearing-free composite material blade mold | |
| CN208816396U (en) | A kind of novel rotor and new and effective wing fan | |
| CN206068106U (en) | A kind of composite propeller | |
| CN209553499U (en) | It is a kind of with wing tip ring and the rotor that fin tip can be installed additional | |
| Wang et al. | Progress of helicopter rotor aerodynamics. | |
| CN209905055U (en) | Rotor oar and unmanned aerial vehicle | |
| CN2605405Y (en) | Wing-type fan for cooling | |
| CN219154766U (en) | Unmanned aerial vehicle screw wing fan blade structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20220513 |