CN205209729U - Wing section strutting arrangement - Google Patents
Wing section strutting arrangement Download PDFInfo
- Publication number
- CN205209729U CN205209729U CN201520957390.1U CN201520957390U CN205209729U CN 205209729 U CN205209729 U CN 205209729U CN 201520957390 U CN201520957390 U CN 201520957390U CN 205209729 U CN205209729 U CN 205209729U
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- China
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- connecting plate
- rotary table
- wing
- web joint
- slat
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Abstract
(B, ) wing section strutting arrangement. Original structure can produce complicated aerodynamic noise when carrying out the pneumatic acoustics experiment of wing section, the accuracy of the pneumatic acoustics orientation survey result of a pair of wings type exerts an influence. The utility model discloses the constitution includes: go up carousel (b) (b) 2 (b) (b), lower carousel (b) (b) 10 (b) (b), go up the carousel respectively with slat connecting plate no. 1 (b) (b) 3 (b) (b), one (b) (b) 4 (b) (b) of main wing connecting plate, one (b) (b) 8 (b) (b) of wing flap connecting plate connects, down the carousel respectively with slat connecting plate no. 2, the main wing connecting plate two, wing flap connecting plate no. 2 is connected, slat (b) (b) 9 (b) (b) is installed to slat connecting plate no. 1 and slat connecting plate between two, main wing (b) (b) 11 (b) (b) is installed to main wing connecting plate no. 1 and main wing connecting plate between two, wing flap (b) (b) 17 (b) (b) is installed to wing flap connecting plate no. 1 and wing flap connecting plate between two, last carousel passes through angular contact bearing (b) (b) 6 (b) (b) and is connected with last carousel support (b) (b) 7 (b) (b), lower carousel passes through deep groove ball bearing (b) (b) 13 (b) (b) and is connected with lower carousel support (b) (b) 16 (b) (b). The utility model is used for wind tunnel test support wing type. (B, )
Description
technical field:
the utility model relates to a kind of airfoil support device.
background technology:
airfoil support device is the visual plant carrying out aerofoil profile aerodynamic force and aerodynamic noise test, aerofoil profile is arranged on this bracing or strutting arrangement during test, dries and measure its aerodynamic force and aerodynamic noise in wind-tunnel.Traditional dynamometry aerofoil profile is generally at the inner pre-buried major axis along spanwise arrangement of its aerofoil profile, this axle is installed on test section, lower rotary table center, aerofoil profile is driven to rotate by the rotation of rotating disk, realize the change of aerofoil profile luffing angle, and the form that wing flap all adopts gusset plate to be connected with the change of slat state, the angle of change is needed to make gusset plate according to wing flap and slat, wing flap and slat are connected in main wing type by gusset plate, during blowing test, gusset plate is in test chamber runner, this kind of structure is little to aerofoil profile dynamometer check Influence on test result, but when carrying out the test of aerofoil profile aeroacoustics, gusset plate in air-flow can produce complicated aerodynamic noise, the accuracy of aerofoil profile aeroacoustics test measurement result is had an impact.
american-European aircraft industry is through the development of last 100 years, define comparatively perfect test facilities, along with people are to aerodynamic noise problem growing interest, external planemaker, research institution and institution of higher learning have built the aviation aeroacoustics wind-tunnel of a large amount of specialty and supporting model test bracing or strutting arrangement so far from the seventies in last century, in airfoil support device, support to aerodynamic noise test support from the test of aerofoil profile model typical load cell and all drop into a large amount of research and development strengths, have developed the multiple airfoil support device for special test at present, and China has just just started the research of aerodynamic noise test device, in order to form aerodynamic noise test ability fast, urgent need is developed specific aerodynamic noise test bracing or strutting arrangement and is tested accordingly, this wherein just comprises airfoil support device.
utility model content:
the purpose of this utility model is to provide a kind of airfoil support device, solves the problem that the test of aerofoil profile aeroacoustics produces complicated aerodynamic noise.
above-mentioned object is realized by following technical scheme:
a kind of airfoil support device, its composition comprises: top rotary table, lower rotary table, described top rotary table respectively with slat web joint one, main wing web joint one, wing flap web joint one connects, described lower rotary table respectively with slat web joint two, main wing web joint two, wing flap web joint two connects, between described slat web joint one and described slat web joint two, slat is installed, between described main wing web joint one and described main wing web joint two, main wing is installed, between described wing flap web joint one and described wing flap web joint two, wing flap is installed, described top rotary table is connected with top rotary table bearing by angular contact bearing, described lower rotary table is connected with lower rotary table bearing by deep groove ball bearing, described lower rotary table bearing is connected with electric rotary table by turntable terminal pad.
described airfoil support device, described top rotary table bearing is arranged on test chamber upper wall surface, and described angular contact bearing is provided with upper ball cover.
described airfoil support device, described lower rotary table bearing is arranged on test chamber lower wall surface, and described deep groove ball bearing is provided with lower ball cover.
the beneficial effects of the utility model:
airfoil support device easy accessibility of the present utility model, uses simple, and during blowing test, Stability Analysis of Structures is without additional noise.Aerofoil profile aerodynamic noise test is carried out for conventional wind-tunnel there is very important realistic meaning, aerodynamic noise test ability can be formed fast.Along with the development of aerodynamic noise test technology, sharply increase the demand of aerodynamic noise wind-tunnel, its application prospect is very wide.
accompanying drawing illustrates:
fig. 1 is structural representation of the present utility model.
fig. 2 is the left view of accompanying drawing 1.
fig. 3 is the vertical view of accompanying drawing 1.
embodiment:
embodiment 1:
a kind of airfoil support device, its composition comprises: top rotary table 2, lower rotary table 10, described top rotary table respectively with slat web joint 1, main wing web joint 1, wing flap web joint one connects 8, described lower rotary table respectively with slat web joint two, main wing web joint two, wing flap web joint two connects, between described slat web joint one and described slat web joint two, slat 9 is installed, between described main wing web joint one and described main wing web joint two, main wing 11 is installed, between described wing flap web joint one and described wing flap web joint two, wing flap 17 is installed, described top rotary table is connected with top rotary table bearing 7 by angular contact bearing 6, described lower rotary table is connected with lower rotary table bearing 16 by deep groove ball bearing 13, described lower rotary table bearing is connected with electric rotary table 15 by turntable terminal pad 14.
embodiment 2:
airfoil support device according to embodiment 1, described top rotary table bearing is arranged on test chamber upper wall surface, and described angular contact bearing is provided with upper ball cover.
embodiment 3:
airfoil support device according to embodiment 1 or 2, described lower rotary table bearing is arranged on test chamber lower wall surface, and described deep groove ball bearing is provided with lower ball cover.
embodiment 4:
according to the method for supporting of the airfoil support device one of embodiment 1-3 Suo Shu, the method comprises the steps:
electric rotary table installed by lower rotary table bearing, described electric rotary table moves described lower rotary table rotation by being rotationally connected dribbling, during test, lower rotary table described in Model angle of attack change is driven by described electric rotary table rotates and realizes, top rotary table is servo-actuated, the change of slat and flap angle state realizes respectively by the slat web joint and wing flap web joint changing different angles state, described slat angle state change is realized by the slat web joint changing different angles state, described flap angle state change is realized by the wing flap web joint changing different angles state.
Claims (3)
1.
a kind of airfoil support device, its composition comprises: top rotary table, lower rotary table, it is characterized in that: described top rotary table respectively with slat web joint one, main wing web joint one, wing flap web joint one connects, described lower rotary table respectively with slat web joint two, main wing web joint two, wing flap web joint two connects, between described slat web joint one and described slat web joint two, slat is installed, between described main wing web joint one and described main wing web joint two, main wing is installed, between described wing flap web joint one and described wing flap web joint two, wing flap is installed, described top rotary table is connected with top rotary table bearing by angular contact bearing, described lower rotary table is connected with lower rotary table bearing by deep groove ball bearing, described lower rotary table bearing is connected with electric rotary table by turntable terminal pad.
2.
airfoil support device according to claim 1, is characterized in that: described top rotary table bearing is arranged on test chamber upper wall surface, and described angular contact bearing is provided with upper ball cover.
3.
airfoil support device according to claim 1 and 2, is characterized in that: described lower rotary table bearing is arranged on test chamber lower wall surface, and described deep groove ball bearing is provided with lower ball cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520957390.1U CN205209729U (en) | 2015-11-26 | 2015-11-26 | Wing section strutting arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520957390.1U CN205209729U (en) | 2015-11-26 | 2015-11-26 | Wing section strutting arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205209729U true CN205209729U (en) | 2016-05-04 |
Family
ID=55847438
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520957390.1U Expired - Fee Related CN205209729U (en) | 2015-11-26 | 2015-11-26 | Wing section strutting arrangement |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205209729U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105387992A (en) * | 2015-11-26 | 2016-03-09 | 中国航空工业集团公司哈尔滨空气动力研究所 | Airfoil profile support device and support method |
| CN108414182A (en) * | 2018-04-23 | 2018-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerofoil profile sideway oscillation flow tunnel testing device |
| CN110514385A (en) * | 2019-08-05 | 2019-11-29 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of undercarriage aerodynamic noise test support device |
| CN112304555A (en) * | 2020-09-24 | 2021-02-02 | 西北工业大学 | Wing type pitching and sinking-floating oscillation wind tunnel test device |
-
2015
- 2015-11-26 CN CN201520957390.1U patent/CN205209729U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105387992A (en) * | 2015-11-26 | 2016-03-09 | 中国航空工业集团公司哈尔滨空气动力研究所 | Airfoil profile support device and support method |
| CN108414182A (en) * | 2018-04-23 | 2018-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerofoil profile sideway oscillation flow tunnel testing device |
| CN108414182B (en) * | 2018-04-23 | 2023-11-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing type yaw oscillation wind tunnel test device |
| CN110514385A (en) * | 2019-08-05 | 2019-11-29 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of undercarriage aerodynamic noise test support device |
| CN112304555A (en) * | 2020-09-24 | 2021-02-02 | 西北工业大学 | Wing type pitching and sinking-floating oscillation wind tunnel test device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160504 Termination date: 20171126 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |