CN208270173U - A kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model - Google Patents
A kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model Download PDFInfo
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- CN208270173U CN208270173U CN201820866774.6U CN201820866774U CN208270173U CN 208270173 U CN208270173 U CN 208270173U CN 201820866774 U CN201820866774 U CN 201820866774U CN 208270173 U CN208270173 U CN 208270173U
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- fuselage
- rectification body
- body structure
- frame section
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- 238000012360 testing method Methods 0.000 title claims abstract description 33
- 238000010276 construction Methods 0.000 claims abstract description 28
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 27
- 239000010959 steel Substances 0.000 claims abstract description 27
- 238000013461 design Methods 0.000 claims abstract description 10
- 210000003205 muscle Anatomy 0.000 claims description 18
- 238000005192 partition Methods 0.000 claims description 18
- 239000000463 material Substances 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 4
- 239000000835 fiber Substances 0.000 claims description 4
- 239000011152 fibreglass Substances 0.000 claims description 4
- 238000005457 optimization Methods 0.000 claims description 4
- 239000004033 plastic Substances 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
A kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model, belongs to wind-tunnel flutter test technical field.This fuselage rectification body structure includes the first bullet, the second bullet, third bullet, the 4th bullet and the 5th bullet for being sequentially connected and being fixed on the steel plate of bottom, first bullet includes rear conical shell and the inside load-carrying construction after-frame section that matches with rear conical shell shape, the second bullet, third bullet, the 4th bullet and the 5th bullet combination include preceding conical shell and the inside load-carrying construction front frame section that is matched with preceding taper shell shape.Conical shell is fixed on the outside of after-frame section afterwards, and preceding conical shell is fixed on the outside of front frame section.While stiffness of the fuselage rectification body structure needed for guarantee test requires, architecture quality is effectively reduced, it is convenient for assembly；Make fuselage rectification body inside configuration vacating space, for placing relevant device, mechanism and route, convenient for the design of model structure.
Description
Technical field
The utility model relates to a kind of fuselage rectification body structures of hypersonic flutter wind tunnel test model, belong to wind-tunnel and quiver
Vibration experimental technique field.
Background technique
In the test of rudder face component flutter wind tunnel, it is believed that fuselage is rigid structure, only provides fuselage sections aerodynamic force.Usually
Influence of the fuselage aerodynamic force to rudder face is simulated using rectification body structure.In hypersonic flutter wind tunnel test, traditional rectification
Body structure generallys use all-metal material or the manufacture of full process for un-metal material, and there are rectification body architecture qualities excessive, processing week
Phase and the disadvantages of cost is excessively high, assembly difficulty.Using the test model of traditional rectification body structure, there is also another disadvantage,
I.e. rectification body structure is solid construction, and the relevant device and mechanism of test model are placed without space, increases model structure design
Difficulty.Under the stiffness needed for meeting flutter wind tunnel test requires, rectification body Model answers quality low as far as possible, assembles square as far as possible
Just, while inside model space should be provided facilitate progress model structure design, be this field technical problem urgently to be resolved.
Summary of the invention
For the above-mentioned problems in the prior art, the utility model provides a kind of hypersonic flutter wind tunnel test mould
The fuselage rectification body structure of type, the fuselage rectification body structure should effectively drop while the stiffness needed for guarantee test requires
Low architecture quality, it is convenient for assembly；Make fuselage rectification body inside configuration vacating space, for placing relevant device, mechanism and route,
Convenient for the design of model structure.
The technical solution adopted in the utility model is: a kind of fuselage rectification body knot of hypersonic flutter wind tunnel test model
Structure, the test model include a rudder face model, a rudder face support construction and a fuselage rectification body structure, the rudder face
Model is fixedly connected on the steel plate of bottom by rudder face support construction, and the fuselage rectification body structure includes being sequentially connected and fixing
The first bullet, the second bullet, third bullet, the 4th bullet and the 5th bullet on the steel plate of bottom, described
One bullet includes rear conical shell and the inside load-carrying construction after-frame section matched with rear conical shell shape, second cone
Body, third bullet, the 4th bullet and the 5th bullet combination include preceding conical shell and with preceding conical shell shape
The inside load-carrying construction front frame section that shape matches；The after-frame section is using a first horizontal frame being fixed on the steel plate of bottom, more
A arc-shaped transverse bar and multiple first vertical muscle are fixed together, and one end of arc-shaped transverse bar is fastened on the steel plate of bottom
Two the first vertical muscle；The front frame section is successively arranged the horizontal frame of second be fixed on the steel plate of bottom, the horizontal frame of third, first partition
And second partition, first stringer and two are fixed on the steel plate of bottom the is equipped between the second horizontal frame and the horizontal frame of third
Two vertical muscle are equipped with second stringer between the horizontal frame of third and first partition；Conical shell is fixed on after-frame section after described
Outside, preceding conical shell are fixed on the outside of front frame section.
The first horizontal frame, the second horizontal frame and the horizontal frame of third using longitudinal and transverse link of boards plate structure or entire plate
Engraved structure.
Arc-shaped transverse bar and the first vertical muscle in the after-frame section are symmetrical arranged with fuselage rectification body symmetrical configuration face, rudder face
Support construction is fixedly connected on the steel plate of bottom, the middle position in fuselage rectification body symmetrical configuration face in after-frame section.
The first horizontal frame in the front frame section in the second horizontal frame, the horizontal frame of third, first partition, second partition and after-frame section is adopted
With the non-uniform thickness structure Jing Guo optimization design.
Inner space filling of the front frame section before covering after conical shell includes the light material of foamed plastic.
Conical shell and preceding conical shell use glass reinforced plastic or carbon fibre composite after described.
The after-frame intersegmental part is equipped with the space of the relevant device of shelf test model, mechanism and pipeline.
The fuselage rectification body structure is all fixedly connected using disassembled mechanical connection manner.
The beneficial effects of the utility model are: the fuselage rectification body structure packet of this hypersonic flutter wind tunnel test model
Include the first bullet, the second bullet, third bullet, the 4th bullet and for being sequentially connected and being fixed on the steel plate of bottom
Five bullets, the first bullet include rear conical shell and the inside load-carrying construction after-frame matched with rear conical shell shape
Section, the second bullet, third bullet, the 4th bullet and the 5th bullet combination include preceding conical shell and and inner cone
The inside load-carrying construction front frame section that shape shell shape matches.Conical shell is fixed on the outside of after-frame section, preceding conical shell afterwards
It is fixed on the outside of front frame section.While stiffness of the fuselage rectification body structure needed for guarantee test requires, it is effectively reduced
Architecture quality, it is convenient for assembly；Make fuselage rectification body inside configuration vacating space, for placing relevant device, mechanism and route, just
In the design of model structure.
Detailed description of the invention
Fig. 1 is a kind of outline drawing of the fuselage rectification body structure of hypersonic flutter wind tunnel test model.
Fig. 2 is the assembling schematic diagram of fuselage rectification body inside configuration load-carrying construction.
In figure: 1, rudder face model, 2, rudder face support construction, the 3, first bullet, 3a, the first horizontal frame, 3b, arc-shaped cross
Muscle, 3c, the first vertical muscle, the 4, second bullet, 4a, the second horizontal frame, 4b, the second vertical muscle, 4c, the first stringer, 5, third bullet,
The horizontal frame of 5a, third, 5b, the second stringer, the 6, the 4th bullet, 6a, first partition, the 7, the 5th bullet, 7a, second partition, 8,
Bottom steel plate.
Specific embodiment
The utility model is described in detail with reference to the accompanying drawings and examples.
Fig. 1,2 show a kind of fuselage rectification body structure chart of hypersonic flutter wind tunnel test model.In figure,
This hypersonic flutter wind tunnel test model includes 1, rudder face support construction 2 of a rudder face model and one
Fuselage rectification body structure.Rudder face model 1 is fixedly connected on bottom steel plate 8 by rudder face support construction 2.Fuselage rectification body structure
Including the first bullet 3, the second bullet 4, third bullet 5, the 4th taper being sequentially connected and be fixed on bottom steel plate 8
Body 6 and the 5th bullet 7.First bullet 3 includes rear conical shell and the inside load matched with rear conical shell shape
Structure after-frame section.Second bullet 4, third bullet 5, the 4th bullet 6 and the 5th bullet 7 combination include preceding taper
Shell and the inside load-carrying construction front frame section matched with preceding taper shell shape.After-frame section is fixed on bottom steel plate using one
The first horizontal frame 3a, four arc-shaped transverse bar 3b and six the first vertical muscle 3c on 8 are fixed together, arc-shaped transverse bar 3b's
One end is fastened on two the first vertical muscle 3c on bottom steel plate 8, and the other end connects rudder face support construction 2.Front frame section is successively
Equipped with the second horizontal frame 4a, the horizontal frame 5a of third, first partition 6a and the second partition 7a being fixed on bottom steel plate 8, in the second cross
The a first stringer 4c and vertical muscle 4b of two second be fixed on bottom steel plate 8 is equipped between frame 4a and the horizontal frame 5a of third,
A second stringer 5b is equipped between third horizontal frame 5a and first partition 6a.Conical shell is fixed on the outside of after-frame section afterwards, preceding
Conical shell is fixed on the outside of front frame section.
First horizontal frame 3a, the second horizontal frame 4a and the horizontal frame 5a of third use the plate structure or entire plate of longitudinal and transverse link of boards
Engraved structure.Inner space filling of the front frame section before covering after conical shell includes the light material of foamed plastic.After-frame
Intersegmental part is equipped with the space of the relevant device of shelf test model, mechanism and pipeline.
The vertical muscle 3c of arc-shaped transverse bar 3b and first in after-frame section is symmetrical arranged with fuselage rectification body symmetrical configuration face, rudder face
Support construction 2 is fixedly connected on the middle position in fuselage rectification body symmetrical configuration face in after-frame section.Second horizontal frame 4a in front frame section,
The first horizontal frame 3a in the horizontal frame 5a of third, first partition 6a, second partition 7a and after-frame section is used by the non-etc. of optimization design
Thick structure.Conical shell and preceding conical shell use glass reinforced plastic or carbon fibre composite afterwards.Fuselage rectification body structure is all adopted
It is fixedly connected with disassembled mechanical connection manner.
Using above-mentioned technical solution, in the front frame section of the internally positioned load-carrying construction in filling with light material part, shape with
Preceding conical shell and the matching of front frame section.In the front frame section of internal load-carrying construction, the first stringer and the second stringer are located at rectification body
On the plane of symmetry, contacted with bottom steel plate.Second vertical muscle is contacted with bottom steel plate, the second horizontal frame and the horizontal frame of third.Internal load knot
In the after-frame section of structure, the first vertical muscle is symmetrical arranged about the rectification body plane of symmetry, outside the first vertical muscle and arc-shaped transverse bar and rear taper
The contact of shell inner surface.Fuselage rectification body construction profile, as shown in the picture, size of main body are about 3.0m × 1.0m × 0.5m, main
To apply glass reinforced plastic or carbon fibre composite machine-shaping.Each component of internal load-carrying construction, conical shell and bottom steel plate, entirely
Portion is connected by screw bolts, and can be disassembled when in order to need.Internal load-carrying construction Steel material machine-shaping, in front frame section
The first horizontal frame is the non-uniform thickness knot by optimization design in second horizontal frame, the horizontal frame of third, first partition, second partition and after-frame section
Structure keeps architecture quality most light on the basis of meeting rigidity requirement.Exist in internal load-carrying construction, inside after-frame segment structure empty
Between, it can be used for disposing relevant device, mechanism and the pipeline of test model, model structure facilitated to design.
Claims (8)
1. a kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model, the test model includes a rudder face mould
Type (1), a rudder face support construction (2) and a fuselage rectification body structure, it is characterized in that: the rudder face model (1) passes through rudder
Face support construction (2) is fixedly connected on bottom steel plate (8), and the fuselage rectification body structure includes being sequentially connected and being fixed on bottom
The first bullet (3), the second bullet (4), third bullet (5), the 4th bullet (6) and the 5th cone on portion's steel plate (8)
Body (7), first bullet (3) include rear conical shell and the inside load-carrying construction matched with rear conical shell shape
After-frame section, second bullet (4), third bullet (5), the 4th bullet (6) and the 5th bullet (7) combination packet
Containing preceding conical shell and the inside load-carrying construction front frame section matched with preceding taper shell shape；The after-frame section is solid using one
The horizontal frame (3a) of first be scheduled on bottom steel plate (8), multiple arc-shaped transverse bars (3b) are fixedly connected with the multiple first vertical muscle (3c)
Together, one end of arc-shaped transverse bar (3b) is fastened on two the first vertical muscle (3c) on bottom steel plate (8)；The front frame
Section be successively arranged the horizontal frame (4a) of second be fixed on bottom steel plate (8), the horizontal frame of third (5a), first partition (6a) and second every
Plate (7a) is equipped with first stringer (4c) between the second horizontal frame (4a) and the horizontal frame of third (5a) and two is fixed on bottom steel
The second vertical muscle (4b) on plate (8) is equipped with second stringer (5b) between the horizontal frame of third (5a) and first partition (6a)；Institute
The outside that rear conical shell is fixed on after-frame section is stated, preceding conical shell is fixed on the outside of front frame section.
2. a kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model according to claim 1, feature
Be: the first horizontal frame (3a), the second horizontal frame (4a) and the horizontal frame of third (5a) use the plate structure or whole of longitudinal and transverse link of boards
The engraved structure of block plate.
3. a kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model according to claim 1, feature
Be: inner space filling of the front frame section before covering after conical shell includes the light material of foamed plastic.
4. a kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model according to claim 1, feature
Be: the after-frame intersegmental part is equipped with the space of the relevant device of shelf test model, mechanism and pipeline.
5. a kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model according to claim 1, feature
Be: the vertical muscle (3c) of arc-shaped transverse bar (3b) and first in the after-frame section is symmetrical arranged with fuselage rectification body symmetrical configuration face,
Rudder face support construction (2) is fixedly connected on bottom steel plate (8), the centre in fuselage rectification body symmetrical configuration face in after-frame section
Position.
6. a kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model according to claim 1, feature
It is: in the front frame section in the second horizontal frame (4a), the horizontal frame of third (5a), first partition (6a), second partition (7a) and after-frame section
The first horizontal frame (3a) using the non-uniform thickness structure Jing Guo optimization design.
7. a kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model according to claim 1, feature
Be: conical shell and preceding conical shell are using glass reinforced plastic or carbon fibre composite after described.
8. a kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model according to claim 1, feature
Be: the fuselage rectification body structure is all fixedly connected using disassembled mechanical connection manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820866774.6U CN208270173U (en) | 2018-06-06 | 2018-06-06 | A kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820866774.6U CN208270173U (en) | 2018-06-06 | 2018-06-06 | A kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model |
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| CN208270173U true CN208270173U (en) | 2018-12-21 |
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| CN201820866774.6U Withdrawn - After Issue CN208270173U (en) | 2018-06-06 | 2018-06-06 | A kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108645593A (en) * | 2018-06-06 | 2018-10-12 | 大连理工大学 | A kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model |
| CN112304557A (en) * | 2020-11-25 | 2021-02-02 | 大连理工大学 | Supersonic wind tunnel flutter test device and test method |
-
2018
- 2018-06-06 CN CN201820866774.6U patent/CN208270173U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108645593A (en) * | 2018-06-06 | 2018-10-12 | 大连理工大学 | A kind of fuselage rectification body structure of hypersonic flutter wind tunnel test model |
| CN108645593B (en) * | 2018-06-06 | 2023-12-22 | 大连理工大学 | Fuselage rectifying structure of hypersonic flutter wind tunnel test model |
| CN112304557A (en) * | 2020-11-25 | 2021-02-02 | 大连理工大学 | Supersonic wind tunnel flutter test device and test method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20181221 Effective date of abandoning: 20231222 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20181221 Effective date of abandoning: 20231222 |