CN105564666A - Aircraft component force measuring wind tunnel test model gap structure design method - Google Patents
Aircraft component force measuring wind tunnel test model gap structure design method Download PDFInfo
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- CN105564666A CN105564666A CN201410535668.6A CN201410535668A CN105564666A CN 105564666 A CN105564666 A CN 105564666A CN 201410535668 A CN201410535668 A CN 201410535668A CN 105564666 A CN105564666 A CN 105564666A
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- wind tunnel
- dynamometry
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- vertical fin
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention provides an aircraft component force measuring wind tunnel test model gap structure design method characterized in that a gap between a force measuring part connected with a balance and a fuselage employs a maze slot type structure. The maze slot can effectively prevent airflow from directly flowing in wing root gaps, thus preventing air vortex from affecting wing and full-aircraft load measurement.
Description
Technical field:
This invention relates to wind-tunnel technique, is specially model in wind tunnel designing technique.
Background technology
It flat component dynamometry wind tunnel test is the major part to aircraft under full machine state, as wing, horizontal tail, vertical fin, nacelle etc. carry out a kind of special test of concentrated force measurement.Parts force measurement is the important wind tunnel test of in Project R&D.This test is just as a bridge block, and the pneumatic gross load that " connection " full machine dynamometer check obtains and the distribution aerodynamic loading that parts manometric test obtains, provide significant design to input for coordinating and checking full machine load distribution.
Summary of the invention
The present invention comes from the dynamometer check of YX aircraft many balances high-speed component, in order to obtain the flight load of each major part of YX aircraft (wing, horizontal tail, vertical fin), needs to carry out first phase many balances parts at high speeds dynamometry wind tunnel test.
In many balances parts force measurement in the past, due to the crevice effect between all parts, the test results of dynamometry parts is made not to be very desirable, the direct reaction of this effect is exactly not mating between components ' load with complete airborne lotus, and the complete airborne lotus in parts force measurement does not mate with the full machine load results in full machine dynamometer check.The measurement impact of the crossfire effect that between visible parts, gap produces on load is comparatively large, therefore needs to be optimized design to the gap of dynamometry parts, to reduce the impact of crossfire effect, improves the accuracy of parts and full machine load measurement.
Accompanying drawing explanation
Fig. 1 is that dynamometry vertical fin and fuselage assemble schematic diagram
Fig. 2 is the wing dynamometry schematic diagram not adopting maze trough structure
Fig. 3 is wing maze trough structural representation
Fig. 4 is the vertical fin dynamometry schematic diagram not adopting maze trough structure
Fig. 5 is vertical fin maze trough structural representation
Detailed description of the invention
A Model slot construction design method for aircraft components dynamometry wind tunnel test, is characterized in that, employing labyrinth, the gap slot type structure between the dynamometry parts be connected with balance and fuselage, dynamometry parts comprise wing, horizontal tail and vertical fin.
See Fig. 5, described vertical fin retains original configuration, and described fuselage offers sagging groove, described vertical fin and described fuselage sink between groove and forms maze trough.
Parts force measurement mechanism
Many days flat component dynamometry wind tunnel tests are the important means of Aircraft Load design evaluation, and its test results provides foundation for Aircraft Load calculates.Whether the accuracy that Aircraft Load provides plays vital effect to the weight of aircraft and Intensity Design thereof.
As shown in Figure 1, wing, horizontal tail need to be connected with die body by balance with dynamometry parts such as vertical fins, in order to carry out load measurement to parts separately, certain gap is certainly existed between dynamometry parts and die body, see Fig. 2 and 4, the existence in gap can form crossflow effect, affect aircraft local and overall air current flow, thus cause simulation of air flow distortion, how can reduce the impact of gap on simulation of air flow distortion, improve the accuracy of parts and full machine load measurement, the structure design quality of model becomes vital factor.
1) wing dynamometry member slots optimal design
See Fig. 3, for wing dynamometry parts, need wing to be separated with fuselage, between wing and fuselage, there is certain gap.Before gap structure optimal design, method is separated to fuselage by wing and leaves corresponding gap, and air-flow directly can form more serious crossflow effect by this gap.On certain aircraft components dynamometer check model, wing root section takes the method for designing of maze trough, and maze trough can effectively prevent air-flow from directly altering logical from the gap in wing root portion, reduces air-flow and forms the impact of channelling on wing and full machine load measurement herein.
2) vertical fin dynamometry member slots optimal design
See Fig. 5, for vertical fin dynamometry parts, be separated with fuselage by vertical fin balance, between vertical fin and fuselage, there is gap.Before optimal design, method is that the part connected with fuselage by reaming vertical fin reaches vertical fin and fuselage is separated, and the method not only reduces vertical fin area, and air-flow directly by both gaps, can form more serious crossflow effect simultaneously.On certain aircraft components dynamometer check model, the method taken by cutting down the part that fuselage contacts with vertical fin reaches both and is separated, make fuselage and vertical fin form maze trough simultaneously, the Optimization Design of this kind of vertical fin not only ensure that vertical fin area is constant, air-flow crossfire effect can also be reduced, improve the accuracy of vertical fin and full machine load measurement.
Claims (3)
1. a Model slot construction design method for aircraft components dynamometry wind tunnel test, is characterized in that, employing labyrinth, the gap slot type structure between the dynamometry parts be connected with balance and fuselage.
2. the Model slot construction design method of aircraft components dynamometry wind tunnel test according to claim 1, it is characterized in that, dynamometry parts comprise wing, horizontal tail and vertical fin.
3. the Model slot construction design method of aircraft components dynamometry wind tunnel test according to claim 2, it is characterized in that, described vertical fin retains original configuration, and described fuselage offers sagging groove, described vertical fin and described fuselage sink between groove and forms maze trough.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410535668.6A CN105564666A (en) | 2014-10-11 | 2014-10-11 | Aircraft component force measuring wind tunnel test model gap structure design method |
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| CN201410535668.6A CN105564666A (en) | 2014-10-11 | 2014-10-11 | Aircraft component force measuring wind tunnel test model gap structure design method |
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| CN105564666A true CN105564666A (en) | 2016-05-11 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106525385A (en) * | 2016-12-02 | 2017-03-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Model integrated type flat/vertical fin aerodynamic force measurement device |
| CN108303227A (en) * | 2018-02-14 | 2018-07-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Aeroelastic effect wind tunnel test half model system and test method |
| CN113670560A (en) * | 2021-10-21 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Pneumatic load measuring device of horizontal tail |
Citations (1)
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| CN1190073A (en) * | 1997-02-03 | 1998-08-12 | 中国航空工业总公司第六二六研究所 | Quadruple cross-position support for semi-model wind channel test |
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2014
- 2014-10-11 CN CN201410535668.6A patent/CN105564666A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1190073A (en) * | 1997-02-03 | 1998-08-12 | 中国航空工业总公司第六二六研究所 | Quadruple cross-position support for semi-model wind channel test |
Non-Patent Citations (1)
| Title |
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| 杨连波等: "飞机多天平部件测力风洞试验模型优化设计方法", 《航空科学技术》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106525385A (en) * | 2016-12-02 | 2017-03-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Model integrated type flat/vertical fin aerodynamic force measurement device |
| CN106525385B (en) * | 2016-12-02 | 2023-01-24 | 中国航空工业集团公司哈尔滨空气动力研究所 | Model integrated horizontal vertical tail aerodynamic force measuring device |
| CN108303227A (en) * | 2018-02-14 | 2018-07-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Aeroelastic effect wind tunnel test half model system and test method |
| CN108303227B (en) * | 2018-02-14 | 2024-04-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Static aeroelastic wind tunnel test semi-model system and test method |
| CN113670560A (en) * | 2021-10-21 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Pneumatic load measuring device of horizontal tail |
| CN113670560B (en) * | 2021-10-21 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Pneumatic load measuring device of horizontal tail |
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Application publication date: 20160511 |