CN105387992A - Airfoil profile support device and support method - Google Patents
Airfoil profile support device and support method Download PDFInfo
- Publication number
- CN105387992A CN105387992A CN201510838092.5A CN201510838092A CN105387992A CN 105387992 A CN105387992 A CN 105387992A CN 201510838092 A CN201510838092 A CN 201510838092A CN 105387992 A CN105387992 A CN 105387992A
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- rotary table
- web joint
- slat
- bearing
- lower rotary
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- 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
Abstract
An airfoil profile support device and support method. When an airfoil profile aero-acoustic test is performed, an original structure generates complex aerodynamic noise, thereby influencing accuracy of a measuring result of the airfoil profile aero-acoustic test. The airfoil profile support device comprises an upper rotary table (2) and a lower rotary table (10), the upper rotary table is connected with a slat connecting plate I (3), a main wing connecting plate I (4) and a flap connecting plate I (8), the lower rotary table is connected with a slat connecting plate II, a main wing connecting plate II and a flap connecting plate II, a slat (9) is installed between the slat connecting plate I and the slat connecting plate I, a main wing is installed between the main wing connecting plate I and the main wing connecting plate II, the upper rotary table is connected with an upper rotary table support (7) through an angular contact bearing (6), and the lower rotary table is connected with a lower rotary table support (16) through a deep groove ball bearing (13). The airfoil profile support device provided by the invention is used for supporting an airfoil profile in a wind tunnel test.
Description
technical field:
the present invention relates to a kind of airfoil support device and method for supporting.
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.
summary of the invention:
the object of this invention is to provide a kind of airfoil support device and method for supporting, solve 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 is connected with slat web joint one, main wing web joint one, wing flap web joint one respectively, described lower rotary table is connected with slat web joint two, main wing web joint two, wing flap web joint two respectively, 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, and described lower rotary table is connected with lower rotary table bearing by deep groove ball bearing, and 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.
utilize a method for supporting for described airfoil support device, 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.
beneficial effect of the present invention:
airfoil support device easy accessibility of the present invention, 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:
accompanying drawing 1 is structural representation of the present invention.
accompanying drawing 2 is left views of accompanying drawing 1.
accompanying drawing 3 is vertical views 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 is connected 8 with slat web joint 1, main wing web joint 1, wing flap web joint one respectively, described lower rotary table is connected with slat web joint two, main wing web joint two, wing flap web joint two respectively, 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, and described lower rotary table is connected with lower rotary table bearing 16 by deep groove ball bearing 13, and 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:
a kind of method for supporting of the airfoil support device utilizing one of embodiment 1-3 described: 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 (4)
1. an 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, and 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.
4. a method for supporting for the airfoil support device utilizing one of claim 1-3 described, is characterized in that: 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510838092.5A CN105387992A (en) | 2015-11-26 | 2015-11-26 | Airfoil profile support device and support method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510838092.5A CN105387992A (en) | 2015-11-26 | 2015-11-26 | Airfoil profile support device and support method |
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| CN105387992A true CN105387992A (en) | 2016-03-09 |
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| CN201510838092.5A Pending CN105387992A (en) | 2015-11-26 | 2015-11-26 | Airfoil profile support device and support method |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108151999A (en) * | 2017-12-08 | 2018-06-12 | 厦门大学 | A kind of composite model support and adjusted design method |
| CN109632243A (en) * | 2018-12-30 | 2019-04-16 | 南京航空航天大学 | The device and method of wing flap parameter state in a kind of change wind-tunnel |
| CN109682569A (en) * | 2018-12-20 | 2019-04-26 | 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 allpurpose model support device |
| CN109765026A (en) * | 2019-01-21 | 2019-05-17 | 西北工业大学 | A kind of low speed dynamic test wind tunnel wall interference correction correction method |
| 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 |
| CN112556968A (en) * | 2021-02-23 | 2021-03-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Three-quarter opening test section for acoustic wind tunnel test |
| CN114608783A (en) * | 2022-03-11 | 2022-06-10 | 西北工业大学 | Wind tunnel installation structure for sectional type mixed scaling airfoil |
| CN116147882A (en) * | 2023-04-23 | 2023-05-23 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-speed wind tunnel flow field parameter measuring device and method |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108151999A (en) * | 2017-12-08 | 2018-06-12 | 厦门大学 | A kind of composite model support and adjusted design method |
| CN108151999B (en) * | 2017-12-08 | 2019-08-16 | 厦门大学 | A kind of support of composite model and adjusted design method |
| CN109682569A (en) * | 2018-12-20 | 2019-04-26 | 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 allpurpose model support device |
| CN109632243A (en) * | 2018-12-30 | 2019-04-16 | 南京航空航天大学 | The device and method of wing flap parameter state in a kind of change wind-tunnel |
| CN109765026A (en) * | 2019-01-21 | 2019-05-17 | 西北工业大学 | A kind of low speed dynamic test wind tunnel wall interference correction correction method |
| 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 |
| CN112556968A (en) * | 2021-02-23 | 2021-03-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Three-quarter opening test section for acoustic wind tunnel test |
| CN114608783A (en) * | 2022-03-11 | 2022-06-10 | 西北工业大学 | Wind tunnel installation structure for sectional type mixed scaling airfoil |
| CN114608783B (en) * | 2022-03-11 | 2024-01-09 | 西北工业大学 | Wind tunnel installation structure for sectional type mixed scaling wing section |
| CN116147882A (en) * | 2023-04-23 | 2023-05-23 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-speed wind tunnel flow field parameter measuring device and method |
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Application publication date: 20160309 |