CN108036916B - A kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model - Google Patents
A kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model Download PDFInfo
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- CN108036916B CN108036916B CN201711136152.4A CN201711136152A CN108036916B CN 108036916 B CN108036916 B CN 108036916B CN 201711136152 A CN201711136152 A CN 201711136152A CN 108036916 B CN108036916 B CN 108036916B
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- ribs
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- root rib
- rib ontology
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- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 230000010354 integration Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 5
- 238000010008 shearing Methods 0.000 abstract description 4
- 238000005259 measurement Methods 0.000 abstract description 3
- 238000012360 testing method Methods 0.000 description 8
- 238000013461 design Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
A kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model, including root rib ontology, ribs, ribs are the arcuate structure to raise upward；Ribs is perpendicularly fixed at the upper surface of root rib ontology；Roof beam structure positioning intermediate plate is distributed in the upper surface of root rib ontology and the outer surface of ribs；The lower surface of root rib ontology is equipped with adapter and flange bolt fixation hole for being connected with decoupling needle, and adapter is arranged perpendicular to root rib ontology.The configuration of the present invention is simple, by the ribs of arc being arranged on root rib ontology to increase the intensity of airfoil root to the greatest extent, and roof beam structure is set on root rib ontology and ribs and positions roof beam structure of the intermediate plate to fixed wing, to achieve the effect that for root rib ontology to be fixedly connected with the roof beam structure of wing, it ensure that the moment of flexure on the roof beam structure from wing and shearing are transmitted on root rib ontology to the greatest extent；The present invention had not only solved the problems, such as the security reliability of all movable rudder surface model, but also facilitated the connection with external measurement device.
Description
Technical field
It is especially a kind of for supersonic wind tunnel all movable rudder surface model the present invention relates to aeroelastic effect test device field
Multi-functional rib.
Background technique
China's high-speed wind tunnel is intermittent wind tunnel at present, and starting ram compression is high, shock loading is big, and wing is meeting rigidity phase
Under the premise of requirement, intensity requirement is difficult to meet, and improves intensity, often will increase structure size, such case drag
Quality is similar and is extremely difficult to require.Therefore, for hypersonic wing, in addition to the aerodynamic configuration of guarantee model, the machine of model
The design of wing structure stiffness and strength is also the priority and difficulty of design.Since wing generallys use big compound of light weight rigidity at present
Material glass steel does designing material, but at root rib, especially rudder face and flange joining place, often will appear stress concentrate and
The security reliability of model is reduced, and in wind tunnel experiment, root rib usually requires to connect with testing stand or external measurement device
It connects, this just proposes very high requirement to root rib.
Summary of the invention
Simple, Optimized model structure that the object of the present invention is to provide a kind of structures, whole shearings that wing can be transmitted and curved
Square and the multi-functional rib for supersonic wind tunnel all movable rudder surface model that the security reliability of model in test is effectively ensured.
The present invention solves technical solution used by prior art problem: one kind being used for supersonic wind tunnel all movable rudder surface model
Multi-functional rib, including root rib ontology, including ribs；The ribs is the arcuate structure to raise upward and ribs is vertical
It is fixed on the upper surface of root rib ontology；Roof beam structure positioning intermediate plate is distributed on the upper surface of root rib ontology and the outer surface of ribs；
The lower surface of root rib ontology is equipped with adapter and the flange bolt fixation hole fixed for flange for being connected with decoupling needle,
And the adapter is set perpendicular to root rib ontology.
The ribs is fixed on the middle part of root rib ontology.
Wire guide is offered on described rib ontology.
The wire restraint pipe of the lower surface setting perpendicular to root rib ontology is equipped at the wire guide.
Described rib ontology and ribs are made into integration using high strength steel.
The beneficial effects of the present invention are: the configuration of the present invention is simple, by the ribs that arc is arranged on root rib ontology
To increase the intensity of airfoil root to the greatest extent.Roof beam structure is set on root rib ontology and ribs simultaneously and positions intermediate plate to solid
Determine the roof beam structure of wing, to achieve the effect that for root rib ontology to be fixedly connected with the roof beam structure of wing, ensure that the beam from wing
Moment of flexure and shearing on frame can be transmitted to the greatest extent on root rib ontology；Simultaneously by flange bolt fixation hole, adapter and
It is quick convenient that the setting of wire guide can be such that the external test arrangements such as the present invention and the conducting wire of flange, decoupling needle and sensor create
Condition of contact.Design of the invention had not only solved the problems, such as the security reliability of all movable rudder surface model, but facilitate with it is externally measured
The connection of device.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention.
Fig. 2 is the connection status diagram of the present invention with spar frame.
In figure: 1- root rib ontology, 2- wire guide, 3- flange bolt fixation hole, 4- adapter, 5- roof beam structure position intermediate plate, 6-
Ribs, 7- wire restraint pipe, 8- flange, 9- roof beam structure, 10- sensor.
Specific embodiment
Below in conjunction with the drawings and the specific embodiments, the present invention will be described:
Fig. 1 is a kind of structural schematic diagram of multi-functional rib for supersonic wind tunnel all movable rudder surface model of the invention.
A kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model mainly includes for the fixed company of roof beam structure 9 with wing
The root rib ontology 1 and ribs 6 connect, as shown in Figure 1, ribs 6 is specially the arcuate structure that raises upward, this structure can be with
Increase the intensity of airfoil root to the greatest extent；Ribs 6 is perpendicularly fixed at the upper surface of root rib ontology 1.It is good to reach
Ribs 6 is preferably fixed on the middle part of root rib ontology 1 by stablizing effect；In the upper surface of root rib ontology 1 and the arc of ribs 6
Roof beam structure positioning intermediate plate 5 is distributed on shape outer surface, is gripped (as shown in Figure 2) to the end to spar frame 9；Root
The lower surface of rib ontology 1 is equipped with adapter 4 and the flange bolt fixation hole fixed for flange 8 for being connected with decoupling needle
3, wherein adapter 4 is arranged perpendicular to root rib ontology 1.
Cabling and installation for the ease of the conductor part of the devices such as sensor 10, preferably offer on root rib ontology 1
Wire guide 2.As shown in Fig. 2, the wire restraint pipe 7 being arranged perpendicular to 1 lower surface of root rib ontology can be equipped at wire guide 2, to
Protection conducting wire prevents its fracture.
Root rib ontology 1 can be used high strength steel with ribs 6 and be made, and root rib ontology 1 and the preferably system of ribs 6
At.As shown in Fig. 2, the present invention and the roof beam structure 9 of wing are fixed together simultaneously when carrying out aeroelastic effect test using the present invention
The all movable rudder surface model that can be used for supersonic wind tunnel test is obtained after connection covering, it is in the model, complete on wing
Portion's shearing and moment of flexure are transmitted to the greatest extent on root rib ontology 1 of the invention, so that entire model is made to be in integral structure,
And then optimize the structure of entire model；In the build process of experimental rig, pass through flange 8 at flange bolt fixation hole 3
And model is finally fixed on testing stand by shaft, to measure mode of flexural vibration；And adapter 4 is connect with decoupling needle and then and spring
Piece is connected, for measuring torsion mode；In addition, facilitating the conducting wire peace of the devices such as sensor 10 the present invention provides wire guide 2
Dress and arrangement, make the present invention on the basis of meeting the design requirement and root rib stability of wing model load path, simultaneously
Consolidate fixed sum data measurement for model in wind tunnel test to provide convenience, realizes multifunction.
The above content is combine specific optimal technical scheme further detailed description of the invention, and it cannot be said that
Specific implementation of the invention is only limited to these instructions.For those of ordinary skill in the art to which the present invention belongs, exist
Under the premise of not departing from present inventive concept, a number of simple deductions or replacements can also be made, all shall be regarded as belonging to of the invention
Protection scope.
Claims (5)
1. a kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model, including root rib ontology (1), which is characterized in that
Including ribs (6)；The ribs (6) is the arcuate structure to raise upward and ribs (6) is perpendicularly fixed at root rib ontology (1)
Upper surface；Roof beam structure positioning intermediate plate (5) is distributed on the upper surface of root rib ontology (1) and the outer surface of ribs (6)；Root rib sheet
The lower surface of body (1) is equipped with the adapter (4) for being connected with decoupling needle and fixes for flange (8) fixed flange bolt
Hole (3), and the adapter (4) is set perpendicular to root rib ontology (1).
2. a kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model according to claim 1, feature exist
In the ribs (6) is fixed on the middle part of root rib ontology (1).
3. a kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model according to claim 1, feature exist
In offering wire guide (2) on described rib ontology (1).
4. a kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model according to claim 3, feature exist
In the wire restraint pipe (7) being arranged at the wire guide (2) equipped with the lower surface perpendicular to root rib ontology (1).
5. a kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model according to claim 1, feature exist
In described rib ontology (1) is made into integration with ribs (6) using high strength steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711136152.4A CN108036916B (en) | 2017-11-16 | 2017-11-16 | A kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711136152.4A CN108036916B (en) | 2017-11-16 | 2017-11-16 | A kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108036916A CN108036916A (en) | 2018-05-15 |
| CN108036916B true CN108036916B (en) | 2019-10-11 |
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ID=62093576
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711136152.4A Active CN108036916B (en) | 2017-11-16 | 2017-11-16 | A kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108036916B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108645593B (en) * | 2018-06-06 | 2023-12-22 | 大连理工大学 | Fuselage rectifying structure of hypersonic flutter wind tunnel test model |
| CN110160731B (en) * | 2018-08-09 | 2020-11-13 | 北京机电工程研究所 | Adjustable gap device for flutter test |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0854316A (en) * | 1994-08-12 | 1996-02-27 | Mitsubishi Heavy Ind Ltd | Flutter model for rudder |
| CN101893504B (en) * | 2010-07-20 | 2013-03-06 | 中国航空工业集团公司西安飞机设计研究所 | Stiffening rib of flight vehicle aerofoil experimental model |
| US8726652B1 (en) * | 2010-09-10 | 2014-05-20 | The Boeing Company | Torque controlled antagonistic shape memory alloy actuator |
| CN105150558A (en) * | 2015-06-23 | 2015-12-16 | 中国航空工业集团公司西安飞机设计研究所 | Component overall molding method, control plane of aircraft and aircraft |
| CN106289680B (en) * | 2016-08-01 | 2018-11-23 | 中国航天空气动力技术研究院 | Experimental rig for the quiet aeroelastic test of wind-tunnel |
| CN107063624A (en) * | 2017-06-06 | 2017-08-18 | 大连理工大学 | A kind of device for simulating all movable rudder face flutter model bending support stiffness |
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2017
- 2017-11-16 CN CN201711136152.4A patent/CN108036916B/en active Active
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| Publication number | Publication date |
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| CN108036916A (en) | 2018-05-15 |
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