CN108045555A - It is a kind of to be arranged at the spoiler that article cabin leading edge is buried in depth open type - Google Patents
It is a kind of to be arranged at the spoiler that article cabin leading edge is buried in depth open type Download PDFInfo
- Publication number
- CN108045555A CN108045555A CN201711237895.0A CN201711237895A CN108045555A CN 108045555 A CN108045555 A CN 108045555A CN 201711237895 A CN201711237895 A CN 201711237895A CN 108045555 A CN108045555 A CN 108045555A
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- China
- Prior art keywords
- spoiler
- cabin
- article
- article cabin
- leading edge
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
Abstract
The present invention relates to a kind of are arranged to bury the spoiler of article cabin leading edge in depth open type, belong to Aeronautical Test Technology field.By designing a spoiler in the present invention, spoiler is merged for two faces with an axis, its both ends has more sharp endpoint, end point is installed on article cabin leading edge with certain deflection angle, front incoming lifts up after hitting the windward side of spoiler, air-flow reduces cabin interior air-flow amount away from nacelle, so as to reduce the impact force of air-flow and article cabin rear wall, reaches noise reduction；The leeward of spoiler should generate good low-pressure area, and high pressure draught in cabin is attracted to be flowed to the leeward of spoiler, then flow out nacelle, and a large scale whirlpool is formed in cabin, ensure that the rear surface flowing of article cabin is stablized, reduce aerodynamic noise.The design principle of the present invention is clear and definite, it is easy to accomplish, the reliability of design is improved, greatly reduces the cost that disturbing flow device designs.
Description
Technical field
The invention belongs to Aeronautical Test Technology fields more particularly to a kind of be arranged to bury article cabin leading edge in depth open type
Spoiler.
Background technology
With the development of aeronautical technology, buried in the goods equipment needs of some aircrafts.After hatch door is opened, the production of article cabin rear wall
Serious aerodynamic noise has been given birth to, article cabin rear wall structure is caused to be easy to fatigue damage, the economy for seriously reducing aircraft uses the longevity
Life.For this reason, it is necessary to design the flow control apparatus for effectively reducing article cabin rear wall aerodynamic noise.
The article cabin that article cabin length depth ratio is less than or equal to 8 is buried in depth open type.
Prevent air-flow from hitting article cabin rear wall to reduce aerodynamic noise angle from raising shear layer (holding up air-flow) both at home and abroad
Degree has carried out substantial amounts of research work, and achievement is applied on a few type aircrafts.But people so far, there is no to propose support suction flowing control
Principle, more nobody sum up the functional relation of support suction spoiler design, but use by multi-parameter changing rule design sea
It measures exemplar progress CFD emulation or the preferred method of wind tunnel test, workload and cost is huge.
The content of the invention
The object of the present invention is to provide a kind of are arranged to bury the spoiler of article cabin leading edge in depth open type, disturbed by setting
Flowing plate, to reduce shock of the air-flow to article cabin trailing edge.
In order to achieve the above objectives, the technical solution adopted by the present invention is：One kind is arranged at bury article cabin in depth open type before
The spoiler of edge, the spoiler has is arranged at article with two symmetrical smooth curved surfaces of axis and the spoiler
Out of my cabin side and according to spoiler location parameter set spoiler so that in article cabin formed large scale whirlpool, spoiler position
Putting parameter includes, spoiler and air-flow come to deflection angle theta, spoiler length L and the spoiler and article cabin antetheca formed away from
From X, spoiler and article cabin egress hatch level H.
Further, the spoiler meets with air-flow to the deflection angle theta formed：θ=20 °~30 °.
Further, spoiler length L meets：L=(1.5~2.5) δ/sin θ
In formula, δ is boundary layer thickness.
Further, article cabin antetheca distance X meets：X=0.015a~0.05a,
In formula, a is article cabin length.
Further, spoiler meets with article cabin egress hatch level H：H=-0.43X+0.46.
After the spoiler of the present invention is to the spoiler of Reasonable Parameters, a large scale whirlpool is formed in cartridges so that
Rear wall flowing is stablized, it is easy to accomplish, the reliability of design is improved, greatly reduces the cost that disturbing flow device designs.
Description of the drawings
Attached drawing herein is merged in specification and forms the part of this specification, shows the implementation for meeting the present invention
Example, and the principle for explaining the present invention together with specification.
Fig. 1 is spoiler in the present invention and article cabin position relationship schematic diagram.
Fig. 2 is the design sketch for the functional relation that the vertical distance H and lateral separation X of spoiler are unsatisfactory for invention.
Fig. 3 is the excessive design sketch of the deflection angle theta value of spoiler.
Fig. 4 is flowing control effect figure after the method according to the invention reasonable installation spoiler.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.
It is as shown in Figure 1 the spoiler 3 in the present invention and article cabin relative position parameter declaration, the length of spoiler 3 is determined
Justice is L, is defined as θ compared with the deflection angle of the egress hatch plane 2 in article cabin, spoiler 3 is close to article cabin antetheca 1 and article
The endpoint of hatch is defined as A, and terminal A and the lateral separation of article cabin antetheca 1 are defined as X, and terminal A is vertical with article cabin hatch
Distance definition is H.Leading edge 1 Turbulent Boundary Layer thickness in article cabin is δ, this is given data.
The present invention spoiler 3 generate support suction flow control principle be：A spoiler 3 is designed, spoiler 3 is two
Face is merged with an axis, and both ends have more sharp endpoint, and end point is installed on article cabin with certain deflection angle theta
Leading edge 1, front incoming lift up after hitting the windward side (lower surface face) of spoiler 3, and air-flow makes cabin interior air-flow amount away from nacelle
It reduces, so as to reduce the impact force of air-flow and article cabin rear wall, reaches noise reduction.The leeward (upper surface) of spoiler 3 should
Good low-pressure area is generated, high pressure draught in cabin is attracted to be flowed to the leeward of spoiler 3, then flows out nacelle, one is formed in cabin
A large scale whirlpool ensures that the rear surface flowing of article cabin is stablized, reduces aerodynamic noise.
For 3 Position Design of spoiler in the present invention, including：
The first step, deflection angle theta determine.The present invention control principle in, using the suction effect of 3 leeward of spoiler as
It is main, influence of the spoiler 3 to full machine aerodynamic characteristic is taken into account, final design is：θ=20 °~30 °.
Second step, 3 length L's of spoiler determines.In the control principle of the present invention, with leeward suction effect and flow-disturbing
Based on influence of the plate to full machine aerodynamic characteristic, and according to boundary layer thickness δ, final design is：L=(1.5~2.5) δ/sin θ.
3rd step, the position relationship of vertical distance H and lateral separation X determine.In the control principle of the present invention, with leeward
Based on the suction effect of face, the functional relation that the two is finally determined is：H=-0.43X+0.46, it is assumed that inside bury the length in article cabin
It spends for a, then X=0.015a~0.05a is proper.
After spoiler 3 in the present invention is set by mentioned above principle, the article cabin of aircraft is tested, is imitated
Fruit is very good.
The 3 vertical distance H of spoiler and lateral separation X for being illustrated in figure 2 setting are unsatisfactory for functional relation in the present invention
Adverse consequences figure, as can be seen from Figure in cabin tool there are two larger vortex system and a smaller vortex system complex vortex, for
The flowing of article cabin rear wall is not quietly.
The excessive adverse consequences figure of the deflection angle theta value of spoiler 2 is illustrated in figure 3, is formed as can be seen from Figure in cabin
The multiple vortex systems being unevenly distributed, also have a vortex system at article cabin rear wall, and flowing is also not quietly.
Fig. 4 is shown to be mounted with after the spoiler of Reasonable Parameters in the present inventive method, in article cabin leading edge portion shape
Into one large scale whirlpool of formation in whirlpool and cartridges is lifted with stable, finally so that rear wall flowing in article cabin is steady
It is fixed.
The design principle of the present invention is clear and definite, it is easy to accomplish, the reliability of design is improved, disturbing flow device is greatly reduced and sets
The cost of meter.
The above is only the optimal specific embodiment of the present invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Subject to enclosing.
Claims (5)
1. a kind of be arranged at the spoiler that article cabin leading edge is buried in depth open type, which is characterized in that the spoiler has with axis
Two symmetrical smooth curved surfaces of line and the spoiler are arranged at article side out of my cabin, are set according to spoiler location parameter
So that forming large scale whirlpool in article cabin, spoiler location parameter includes spoiler, and spoiler and air-flow are come to being formed
Deflection angle theta, spoiler length L and spoiler and article cabin antetheca distance X, spoiler and article cabin egress hatch level H.
2. according to claim 1 be arranged at the spoiler that article cabin leading edge is buried in depth open type, which is characterized in that described
Spoiler meets with air-flow to the deflection angle theta formed：θ=20 °~30 °.
3. according to claim 2 be arranged at the spoiler that article cabin leading edge is buried in depth open type, which is characterized in that flow-disturbing
Plate length L meets：L=(1.5~2.5) δ/sin θ
In formula, δ is boundary layer thickness.
4. according to claim 3 be arranged at the spoiler that article cabin leading edge is buried in depth open type, which is characterized in that article
Cabin antetheca distance X meets：X=0.015a~0.05a,
In formula, a is article cabin length.
5. according to claim 4 be arranged at the spoiler that article cabin leading edge is buried in depth open type, which is characterized in that flow-disturbing
Plate meets with article cabin egress hatch level H：H=-0.43X+0.46.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711237895.0A CN108045555B (en) | 2017-11-30 | 2017-11-30 | Spoiler arranged on front edge of deep open type embedded article cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711237895.0A CN108045555B (en) | 2017-11-30 | 2017-11-30 | Spoiler arranged on front edge of deep open type embedded article cabin |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108045555A true CN108045555A (en) | 2018-05-18 |
| CN108045555B CN108045555B (en) | 2021-01-19 |
Family
ID=62120904
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711237895.0A Active CN108045555B (en) | 2017-11-30 | 2017-11-30 | Spoiler arranged on front edge of deep open type embedded article cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108045555B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114486159A (en) * | 2021-12-30 | 2022-05-13 | 中国航天空气动力技术研究院 | Control and verification method for embedded weapon machine bomb separation compatibility front edge sawtooth spoiler |
| CN116147880A (en) * | 2023-04-23 | 2023-05-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Cabin door and turbulence combined control mechanism for wind tunnel test |
Citations (9)
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| US5699981A (en) * | 1996-03-18 | 1997-12-23 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft cavity acoustic resonance suppression system |
| US6739554B1 (en) * | 2003-06-02 | 2004-05-25 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft weapons bay acoustic resonance suppression system |
| EP1247735B1 (en) * | 2001-04-06 | 2005-04-20 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method to reduce oscillations in cavities and surface arrangement in a fluid flow |
| EP2778045A1 (en) * | 2013-03-15 | 2014-09-17 | BAE Systems PLC | Cavity acoustic tones suppression |
| EP2778046A1 (en) * | 2013-03-15 | 2014-09-17 | BAE Systems PLC | Cavity acoustic tones suppression |
| WO2014140589A1 (en) * | 2013-03-15 | 2014-09-18 | Bae Systems Plc | Cavity acoustic tones suppression |
| CN205365773U (en) * | 2016-01-25 | 2016-07-06 | 重庆长安汽车股份有限公司 | Car spoiler subassembly |
| FR2957052B1 (en) * | 2010-03-03 | 2016-08-05 | Airbus Operations Sas | AERODYNAMIC DEVICE FOR REDUCING VIBRATION OF TRAPPES OF A LANDING TRAIN BEFORE AN AIRCRAFT. |
| CN106840596A (en) * | 2016-11-24 | 2017-06-13 | 中国空气动力研究与发展中心高速空气动力研究所 | One kind is applied to Asia across supersonic Cavity Flow model in wind tunnel |
-
2017
- 2017-11-30 CN CN201711237895.0A patent/CN108045555B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5699981A (en) * | 1996-03-18 | 1997-12-23 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft cavity acoustic resonance suppression system |
| EP1247735B1 (en) * | 2001-04-06 | 2005-04-20 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method to reduce oscillations in cavities and surface arrangement in a fluid flow |
| US6739554B1 (en) * | 2003-06-02 | 2004-05-25 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft weapons bay acoustic resonance suppression system |
| FR2957052B1 (en) * | 2010-03-03 | 2016-08-05 | Airbus Operations Sas | AERODYNAMIC DEVICE FOR REDUCING VIBRATION OF TRAPPES OF A LANDING TRAIN BEFORE AN AIRCRAFT. |
| EP2778045A1 (en) * | 2013-03-15 | 2014-09-17 | BAE Systems PLC | Cavity acoustic tones suppression |
| EP2778046A1 (en) * | 2013-03-15 | 2014-09-17 | BAE Systems PLC | Cavity acoustic tones suppression |
| WO2014140589A1 (en) * | 2013-03-15 | 2014-09-18 | Bae Systems Plc | Cavity acoustic tones suppression |
| CN205365773U (en) * | 2016-01-25 | 2016-07-06 | 重庆长安汽车股份有限公司 | Car spoiler subassembly |
| CN106840596A (en) * | 2016-11-24 | 2017-06-13 | 中国空气动力研究与发展中心高速空气动力研究所 | One kind is applied to Asia across supersonic Cavity Flow model in wind tunnel |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114486159A (en) * | 2021-12-30 | 2022-05-13 | 中国航天空气动力技术研究院 | Control and verification method for embedded weapon machine bomb separation compatibility front edge sawtooth spoiler |
| CN116147880A (en) * | 2023-04-23 | 2023-05-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Cabin door and turbulence combined control mechanism for wind tunnel test |
| CN116147880B (en) * | 2023-04-23 | 2023-06-27 | 中国空气动力研究与发展中心高速空气动力研究所 | Cabin door and turbulence combined control mechanism for wind tunnel test |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108045555B (en) | 2021-01-19 |
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