CN110435876A - A kind of co-axial rotor rotor hub fairing system with telescopic vortex generator - Google Patents
A kind of co-axial rotor rotor hub fairing system with telescopic vortex generator Download PDFInfo
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- CN110435876A CN110435876A CN201910787584.4A CN201910787584A CN110435876A CN 110435876 A CN110435876 A CN 110435876A CN 201910787584 A CN201910787584 A CN 201910787584A CN 110435876 A CN110435876 A CN 110435876A
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- vortex
- jackshaft
- fin
- fairing
- radome fairing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
- B64C11/14—Spinners
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Details Of Aerials (AREA)
Abstract
The invention discloses a kind of co-axial rotor rotor hub fairing systems with telescopic vortex generator, belong to co-axial rotor rotor hub fairing system technical field, its mainly by jackshaft radome fairing arrangement can rotate with it and periodically stretch out submerge jackshaft radome fairing appearance vortex occur fin, to generate periodically vortex, unfavorable air-flow separation when to delay or fly before eliminating, pressure drag when achieving the purpose that reduce winged before propeller hub.
Description
Technical field
The present invention relates to co-axial rotor rotor hub fairing system technical fields, more particularly to one kind to have telescopic vortex generator
Co-axial rotor rotor hub fairing system.
Background technique
Currently, the increase of propeller hub height and complex contour degree with coaxial rigid rotor high-speed helicopter, propeller hub
The influence that stream is separated after suffered rotor wake, rotor shaft is more serious, and 50% or so of the usual Zhan Quanji resistance of resistance, with beauty
For the flight test of state's XH-59 verification machine, before high speed fly when the type high-speed vertical-lifting it is confidential with 45% power of full machine come
Overcome propeller hub resistance.So propeller hub resistance is to limit coaxial rigid rotor high-speed helicopter maximum flying speed and voyage into one
One of the important element promoted is walked, to realize high-speed flight, it is necessary to solve this huge key of coaxial rigid rotor propeller hub resistance
Problem.And " coaxial rigid rotor propeller hub jackshaft vortex generator design and Research of Drag Reduction " (Nanjing Aero-Space University's journal,
In April, 2019, DOI:10.16356/j.1005-2615.2019.02.017) a kind of jackshaft propeller hub is disclosed with vortex hair
The coaxial rigid rotor propeller hub of raw device, mainly by the vortex generator of arrangement in appearance in jackshaft radome fairing to be subtracted
Resistance, and the resistance reducing performance of this vortex generator is limited, and belongs to passive flowing control, form is fixed, before facing rapidly
When the different helicopter flight situations such as degree variation, high maneuver flight, applicability is poor.
Summary of the invention
In conclusion technical problem solved by the invention is: providing a kind of pair of different flight condition of helicopter and be applicable in
The preferable active drag reduction formula co-axial rotor rotor hub fairing system of property.
And the present invention to solve above-mentioned technical problem used by scheme are as follows:
A kind of co-axial rotor rotor hub fairing system with telescopic vortex generator, includes the upper of upper and lower two sides that be placed in
Rotor hub fairing system and lower rotor hub fairing system, and the jackshaft rectification being arranged between rotor hub fairing system and lower rotor hub fairing system
Cover, the jackshaft radome fairing connect upper rotor hub fairing system and lower rotor hub fairing system, and the jackshaft radome fairing is in along jackshaft
The symmetrical shape of the first perpendicular where axis, the first perpendicular is along front end to its rear end of the jackshaft radome fairing
Direction extend, further include having at least one set of vortex generating assembly being arranged in jackshaft radome fairing, the vortex generation group
Part is mainly made of two vortex generators along the two sides that the first perpendicular is symmetrically disposed in jackshaft radome fairing, often
A vortex generator is then mainly by pivot, for driving pivot around the driving device of own axis and several vertical
The vortex that is articulated on the pivot fin occur constituted, the rotational velocity of the pivot is adjustable, the vortex generation fin
In cam plate-like or rectangular patch, several vortex occur fin and are successively arranged in parallel along direction from top to bottom, the centre
Offered on the wall of axis radome fairing two sides and occur the compatible stretching hole of fin with vortex, the vortex occur fin can with turn
It moves and is extended vertically out at corresponding stretching hole in off-balancesheet outside jackshaft radome fairing, or be submerged in jackshaft radome fairing completely
Within, when fin, which occurs, for the vortex stretches out in outside jackshaft radome fairing, vortex occurs have 0 between fin and direction of flow
To 50 ° of angle.
Further, it is in the arc surfaced gradually expanded from the bottom to top that the lateral edge of fin, which occurs, for the vortex.
Further, the quantity of the vortex generating assembly is 2 groups, and two groups of vortex generating assemblies are along jackshaft radome fairing
The direction of front end to rear end is sequentially arranged.
Further, occur in fin in the vortex of the vortex generating assembly close to jackshaft radome fairing front end, stretch out
It is parallel with direction of flow in the part of jackshaft radome fairing, and the vortex in another group of vortex generating assembly occurs in fin,
Its part for stretching out in jackshaft radome fairing then has angle with direction of flow, and the vortex for constituting angle with direction of flow occurs
Fin tilts upwards along direction of flow.
Further, in each vortex generator, the quantity that fin occurs for the vortex is 2 to 30.
Further, the driving device is variable-frequency motor.
In conclusion by adopting the above-described technical solution, the invention has the benefit that
(1) telescopic vortex generator provided by the present invention belongs to a kind of active vortex generator, can week
Phase property generates vortex, and unfavorable air-flow separation, achievees the purpose that reduce radome fairing resistance when delaying or eliminate preceding fly.It may be used also
According to the different state of flight of helicopter (including various forward flight speeds, high maneuver flight etc.), and adjusts vortex and fin occurs
The span, chord length, and then make vortex generator that can be in preferably drag reduction state under different flying conditions, applicability is more
By force.
(2) in telescopic vortex generator provided by the present invention, the entire rotation period that fin occurs for vortex can be with
It is divided into protruding and to two processes of contract, and in vortex process of the fin to contract can occur for its generated whirlpool
In, it is brought into jackshaft radome fairing boundary-layer, to slow down the low energy banking of the current and reduce adverse pressure gradient, is avoided because air-flow is too early
It separates and generates biggish pressure drag, it is stronger that fin resistance reducing performance occurs compared to fixed vortex.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of co-axial rotor rotor hub fairing system；
Fig. 2 is co-axial rotor rotor hub fairing arrangement schematic diagram provided by the embodiment of the present invention；
Fig. 3 is the structural schematic diagram that fin occurs for vortex in the embodiment of the present invention.
[specific symbol description]
Fin, 6- occur for the upper rotor hub fairing system of 1-, rotor hub fairing system under 2-, 3- jackshaft radome fairing, 4- pivot, 5- vortex
Stretch out hole.
Specific embodiment
Below in conjunction with attached drawing to a kind of co-axial rotor propeller hub with telescopic vortex generator provided by the present invention
Radome fairing is described in detail.
As shown in Figure 1, a kind of co-axial rotor rotor hub fairing system with telescopic vortex generator provided by the present invention,
Include the be placed in upper rotor hub fairing system 1 and lower rotor hub fairing system 2 of upper and lower two sides, and is arranged in 1 He of rotor hub fairing system
Jackshaft radome fairing 3 between lower rotor hub fairing system 2, the jackshaft radome fairing 3 connects upper rotor hub fairing system 1 and lower propeller hub is whole
Stream cover 2, the jackshaft radome fairing 3 are in vertical flat along the symmetrical shape of the first perpendicular where countershaft axis, first
Face extends along the direction of front end to its rear end of the jackshaft radome fairing 3, further includes that have at least one set to be arranged in jackshaft whole
Vortex generating assembly in stream cover 3, the vortex generating assembly are mainly symmetrically disposed on centre along the first perpendicular by two
The vortex generator of two sides in axis radome fairing 3 is constituted, and each vortex generator is then mainly by pivot 4, for driving pivot 4
5 structures of fin occur around the driving device of own axis and several vertical vortex being articulated on the pivot 4
At the rotational velocity of the pivot 4 is adjustable, and it is in cam plate-like or rectangular patch, several vortex hairs that fin 5, which occurs, for the vortex
Raw fin 5 is successively arranged in parallel along direction from top to bottom, offers and is vortexed on the wall of 3 two sides of jackshaft radome fairing
The compatible stretching hole 6 of fin 5 occurs, fin 5, which occurs, for the vortex vertically to stretch at corresponding stretching hole 6 with rotation
It for the outer off-balancesheet of jackshaft radome fairing 3, or is submerged within jackshaft radome fairing 3, is stretched when fin 5 occurs for the vortex completely
When outer for jackshaft radome fairing 3, the angle between fin 5 and direction of flow with 0 to 50 ° occurs for vortex.
More specifically, as shown in Fig. 2, wherein arrow direction i.e. finger meets stream direction, the front end of jackshaft radome fairing 3 refers to
Its windward side, and then correspondence refers to its leeward end for its rear end, and as shown in figure 3, fin refers to wing shape.Wherein, vortex occurs
Fin 5 be in 4 cam disc of pivot or this non-circular shape of rectangular patch, so vortex occur fin 5 its around pivot turn
During dynamic, the part of 3 appearance of jackshaft radome fairing is stretched out in, i.e., the span of fin occurs for vortex and chord length is to become
Change, the state of flight (including different forward flight speeds, high maneuver flight etc.) that user can be different according to helicopter passes through
Rotation pivot 4 and adjust vortex and the span of fin 5, chord length occur, rotating to after perfect condition, stopping vortex fin 5 occurs,
So that vortex generator it is stronger can be in preferably drag reduction state, applicability under different flying conditions.Meanwhile
In the present embodiment 1, vortex occur fin 5 specifically be arranged to can also to rotate with it and be submerged in completely jackshaft radome fairing 3 it
Interior, to be suitable for not needing vortex, there is a situation where fins 5.In addition, in the present embodiment 1, vortex occur fin 5 and pivot 4 it
Between be eccentric.
Even more important, 4 uniform rotation of pivot can also be driven by driving device by implementing personnel, so that each vortex is sent out
Pivot 4 in raw device drives the vortex being pivotally connected with it fin 5 to occur around 4 axis uniform rotation of pivot, vortex generation fin 5 in
It stretches out hole 6 periodically to be stretched, the generation vortex in period.Wherein, the entire rotation period that fin 5 occurs for vortex can divide
It is protruding and to two processes of contract, and in vortex process of the fin 5 to contract can occur for its generated whirlpool
In, it is brought into 3 boundary-layer of jackshaft radome fairing, to slow down the low energy banking of the current and reduce adverse pressure gradient, avoids flowing through because of gas
It early separates and generates biggish pressure drag, it is stronger that 5 resistance reducing performance of fin occurs compared to fixed vortex.
In present embodiment, as shown in figure 3, then specifically having selected the vortex of cam face that fin 5 occurs, and described
The lateral edge that fin 5 occurs for vortex is in the arc surfaced gradually expanded from the bottom to top, to improve control effect.
On the basis of the above embodiment, in present embodiment, the quantity of the vortex generating assembly is 2 groups,
As shown in Fig. 2, two groups of vortex generating assemblies are sequentially arranged along the direction of jackshaft radome fairing 3 front end to rear end, to improve whirlpool
Flow generating ability.More specifically, in present embodiment, in the vortex generating assembly close to 3 front end of jackshaft radome fairing
Vortex occur in fin 5, the part for stretching out in jackshaft radome fairing 3 is parallel with direction of flow, and in another group of vortex
The part that jackshaft radome fairing 3 occurs to stretch out in fin 5 for the vortex of generating assembly then has angle with direction of flow, i.e.,
It is 0 ° that angle between fin 5 and direction of flow, which occurs, for the vortex in one group of vortex generating assembly, and another group of vortex generating assembly
In vortex fin 5 occur then have an angle with direction of flow composition, and 5 edge of fin occurs for the vortex for constituting angle with direction of flow
Direction of flow tilts upwards, and so setting is to reduce upper and lower paddle to descend 3 tail wind of jackshaft radome fairing will not partially
The pressure drag of hub radome fairing 2, and then play drag-reduction effect.
In each vortex generator, quantity 2 to 30 of fin 5 occur for the vortex, more specifically, in this implementation
In example 1, the quantity that fin 5 occurs for vortex is 8.Implementation personnel can select quantity according to self-demand and specifically, in addition,
In present embodiment, the driving device is variable-frequency motor, and motor can adjust pivot 4 and changing it and exporting revolving speed
Velocity of rotation, and then adjust vortex occur fin 5 stretch out in the frequency of the outer off-balancesheet of jackshaft radome fairing 3, to realize change
Vortex generates the effect in period.That is, user can also be different according to helicopter state of flight (before different
Rapidly degree, high maneuver flight etc.), the slewing rate by changing pivot 4 adjusts vortex and the week that fin 5 generates vortex occurs
Phase, and then improve resistance reducing performance of the vortex generator under different flying conditions.
Claims (6)
- It include the upper paddle of upper and lower two sides of being placed in 1. a kind of co-axial rotor rotor hub fairing system with telescopic vortex generator Hub radome fairing and lower rotor hub fairing system, and the jackshaft rectification being arranged between rotor hub fairing system and lower rotor hub fairing system Cover, the jackshaft radome fairing connect upper rotor hub fairing system and lower rotor hub fairing system, and the jackshaft radome fairing is in along jackshaft The symmetrical shape of the first perpendicular where axis, the first perpendicular is along front end to its rear end of the jackshaft radome fairing Direction extend, it is characterised in that: further include having at least one set of vortex generating assembly being arranged in jackshaft radome fairing, it is described Vortex generating assembly is mainly symmetrically disposed on the vortex generator of two sides in jackshaft radome fairing by two along the first perpendicular It being constituted, each vortex generator is then mainly by pivot, for driving pivot to surround the driving device of own axis, and Several vertical vortex being articulated on the pivot occur fin and are constituted, and it is in cam plate-like or rectangle that fin, which occurs, for the vortex The rotational velocity of sheet, the pivot is adjustable, several vortex occur fin and are successively arranged in parallel along direction from top to bottom, institute It states and offers stretching hole compatible with vortex generation fin on the wall of jackshaft radome fairing two sides, fin occurs for the vortex It can be extended vertically out with rotation and at corresponding stretching hole in off-balancesheet outside jackshaft radome fairing, or be submerged in jackshaft completely Within radome fairing, when fin, which occurs, for the vortex stretches out in outside jackshaft radome fairing, vortex occur fin and direction of flow it Between with 0 to 50 ° of angle.
- 2. a kind of co-axial rotor rotor hub fairing system with telescopic vortex generator as described in claim 1, feature exist In: the lateral edge that fin occurs for the vortex is in the arc surfaced gradually expanded from the bottom to top.
- 3. a kind of co-axial rotor rotor hub fairing system with telescopic vortex generator as described in claim 1, feature exist In: it is described vortex generating assembly quantity be 2 groups, two groups of vortex generating assemblies along jackshaft radome fairing front end to rear end side To being sequentially arranged.
- 4. a kind of co-axial rotor rotor hub fairing system with telescopic vortex generator as claimed in claim 3, feature exist In: occur to stretch out in jackshaft radome fairing in fin in the vortex of the vortex generating assembly close to jackshaft radome fairing front end Part it is parallel with direction of flow, and another group vortex generating assembly vortex occur fin in, stretch out in jackshaft The part of radome fairing then has angle with direction of flow, and fin occurs for the vortex for constituting angle with direction of flow along direction of flow Inclination upwards.
- 5. a kind of co-axial rotor rotor hub fairing system with telescopic vortex generator as described in claim 1, feature exist In: in each vortex generator, the quantity that fin occurs for the vortex is 2 to 30.
- 6. a kind of co-axial rotor propeller hub with telescopic vortex generator as described in any one of claim 1 to 5 is whole Stream cover, it is characterised in that: the driving device is variable-frequency motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910787584.4A CN110435876B (en) | 2019-08-26 | 2019-08-26 | Coaxial rotor hub fairing with telescopic vortex generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910787584.4A CN110435876B (en) | 2019-08-26 | 2019-08-26 | Coaxial rotor hub fairing with telescopic vortex generator |
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| Publication Number | Publication Date |
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| CN110435876A true CN110435876A (en) | 2019-11-12 |
| CN110435876B CN110435876B (en) | 2020-06-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910787584.4A Active CN110435876B (en) | 2019-08-26 | 2019-08-26 | Coaxial rotor hub fairing with telescopic vortex generator |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113460299A (en) * | 2021-09-02 | 2021-10-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet structure for reducing drag of coaxial rigid rotor hub and using method thereof |
| CN113830290A (en) * | 2021-09-03 | 2021-12-24 | 中国空气动力研究与发展中心低速空气动力研究所 | Telescopic vortex generator and propeller hub formed by same |
| CN114771817A (en) * | 2022-04-29 | 2022-07-22 | 中国航空研究院 | Coaxial high-speed helicopter with deflection intermediate shaft fairing |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101213131A (en) * | 2005-06-30 | 2008-07-02 | 贝尔直升机特克斯特龙有限公司 | Retractable vortex generator |
| EP2258941A1 (en) * | 2009-06-05 | 2010-12-08 | Jia-Yuan Lee | Wind turbine |
| CN101932507A (en) * | 2008-02-29 | 2010-12-29 | 空中客车英国有限公司 | Aerodynamic structure with series of shock bumps |
| CN109018310A (en) * | 2018-09-03 | 2018-12-18 | 中国科学院工程热物理研究所 | A kind of adjustable vortex generating means |
-
2019
- 2019-08-26 CN CN201910787584.4A patent/CN110435876B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101213131A (en) * | 2005-06-30 | 2008-07-02 | 贝尔直升机特克斯特龙有限公司 | Retractable vortex generator |
| CN101932507A (en) * | 2008-02-29 | 2010-12-29 | 空中客车英国有限公司 | Aerodynamic structure with series of shock bumps |
| EP2258941A1 (en) * | 2009-06-05 | 2010-12-08 | Jia-Yuan Lee | Wind turbine |
| CN109018310A (en) * | 2018-09-03 | 2018-12-18 | 中国科学院工程热物理研究所 | A kind of adjustable vortex generating means |
Non-Patent Citations (1)
| Title |
|---|
| 龙海斌等: "《共轴刚性旋翼桨毂中间轴涡流发生器设计与减阻研究》", 《南京航空航天大学学报》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113460299A (en) * | 2021-09-02 | 2021-10-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet structure for reducing drag of coaxial rigid rotor hub and using method thereof |
| CN113830290A (en) * | 2021-09-03 | 2021-12-24 | 中国空气动力研究与发展中心低速空气动力研究所 | Telescopic vortex generator and propeller hub formed by same |
| CN114771817A (en) * | 2022-04-29 | 2022-07-22 | 中国航空研究院 | Coaxial high-speed helicopter with deflection intermediate shaft fairing |
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| Publication number | Publication date |
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| CN110435876B (en) | 2020-06-19 |
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