CN103057728B - A kind of model aircraft test attitude implement device - Google Patents
A kind of model aircraft test attitude implement device Download PDFInfo
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- CN103057728B CN103057728B CN201210563683.2A CN201210563683A CN103057728B CN 103057728 B CN103057728 B CN 103057728B CN 201210563683 A CN201210563683 A CN 201210563683A CN 103057728 B CN103057728 B CN 103057728B
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Abstract
A kind of model aircraft test attitude implement device, this device one end is connected with the joint in wind-tunnel bindiny mechanism, and the other end is connected with model, and namely experimental set-up is a part for model support mechanism.Experimental set-up comprises large joint, extension, a pre-fishplate bar partially, and multiple pin-and-holes, four waist-shaped holes on pre-fishplate bar partially.It is characterized in that: connect plane partially pre-on the basis of wind-tunnel connection structure plane, easily realize high-angle-of-attack trial state; High angles of side slip test condition is combined by the pin-and-hole on pre-fishplate bar partially and model fitting surface and easily realizes.The present invention is simple for structure, and parameter obtains through pneumatic design or calculating, is easy to realize At High Angle of Attack, high angles of side slip test condition, and installation, convenient disassembly, be applicable to the At High Angle of Attack of high speed wind tunnel, high angles of side slip air inlet experiment simultaneously.
Description
Technical field
The present invention relates to aviation aerodynamic force experimental technique field, particularly relate to the model aircraft test attitude implement device of implementation model At High Angle of Attack, high angles of side slip test condition in a kind of high speed wind tunnel air intake test.
Background technology
Advanced driving engine must could form performance-oriented engine installation by the machine of superior performance to matching.The object of air intake test is the static and dynamic Status characteristic measuring inlet channel, for the design of inlet channel provides test figures, to ensure that the performance of inlet channel in whole flight envelope can meet the requirement of driving engine.Otherwise can make driving engine that surge or parking occur aloft.Third generation opportunity of combat (the F15 opportunity of combat as Muscovite Su27 opportunity of combat and the U.S.) emphasizes high maneuverability, agility that low coverage is fought, and as fast dive, the motor-driven deceleration of At High Angle of Attack etc., wherein foremost is " Pu Jiaqiaofu Cobra maneuver ".When aircraft is when At High Angle of Attack (more than 50 degree), the area of catching of airplane intake reduces, and the flow flowing into inlet channel can reduce, and easily causes driving engine flame-out in flight.And these special feelings subjects can not realize by flight test, affect the safety of aviator.Therefore the flight angle of these At High Angle of Attacks, high angles of side slip must be realized on ground, the performance of check flight inlet channel.Owing to being limited to size and the experimental set-up in the past of wind-tunnel, Test item can not reach required At High Angle of Attack, high angles of side slip flight angle, so how to make model aircraft reach At High Angle of Attack required by test, the flight angle of high angles of side slip has become key technical problem in inlet channel At High Angle of Attack attitude test.
Summary of the invention
The technical problem to be solved in the present invention is, for realizing At High Angle of Attack, high angles of side slip test condition and a kind of model aircraft test attitude implement device that designs in high speed wind tunnel, its objective is the At High Angle of Attack, the high angles of side slip test condition that realize model aircraft, thus measure the inlet characteristic of model aircraft under At High Angle of Attack, high angles of side slip test condition, inspection inlet channel conceptual design
Feasibility.
The technical scheme adopted is:
A kind of model aircraft test attitude implement device, comprises large joint, extension, pre-fishplate bar partially.Described large upper end of joint is provided with the axis hole that two change the angle of attack, lower end is provided with multiple screw hole of change angle of side slip and multiple pin-and-hole, two axis holes of large upper end of joint are connected with the axis hole that known wind-tunnel changes the supporting plate four-bar linkage of the angle of attack by two axles, can with parallel motion, change the angle of attack, multiple screw hole of large joint lower end is connected with extension with screw and pin from the different screw hole set by extension and pin-and-hole respectively with multiple pin-and-hole, and can be connected by the screw hole different from extension and pin-and-hole and change angle of side slip.Extension connects pre-fishplate bar partially and as a whole, pre-fishplate bar being partially provided with multiple waist-shaped hole, changing multiple dowel hole and a kingpin hole of model angle of side slip for combining change, and pre-fishplate bar is partially threaded with model aircraft upper screwed hole through waist-shaped hole by screw.
Above-mentioned extension is the square plate that an outside is provided with strength beam, and extension is connected with large joint, enables model under At High Angle of Attack, high angles of side slip attitude, enter the core flow of Flow Field in Wind Tunnel.
Above-mentioned pre-fishplate bar and wind-tunnel horizontal reference are partially provided with the pre-inclination angle of 20 degree, add being connected of extension and large joint, make partially can reach 46 degree in advance with it; Model passes through the dowel hole on pre-fishplate bar partially and is threaded again, makes it partially also to reach 46 degree in advance, thus the angle of attack of model can be made under the change of wind-tunnel angle of attack mechanism maximum, reach model test attitude At High Angle of Attack demand.
Multiple dowel hole and a kingpin hole that above-mentioned pre-fishplate bar is partially provided with for combining change change model angle of side slip can be combined into angle of side slip-23 ° to 23 °.
Structure of the present invention is simple, and dismounting and the change of each element of main body of device are convenient, and the parameter of each element obtains through calculating, and check than right Joint strenght in the later stage of design, in test have also been obtained checking.The design science of whole device is rigorous, and increase device and can ignore the impact of air intake test, experimental performance is reliable, ensure that the accuracy of observed data.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is the upward view of Fig. 1.
Fig. 3 is the birds-eye view of Fig. 1.
Fig. 4 is the left side view of Fig. 1.
Fig. 5 is schematic appearance of the present invention.
Detailed description of the invention
A kind of model aircraft test attitude implement device, comprises large joint 1, extension 4, pre-fishplate bar 7 partially.Described large joint 1 upper end is provided with φ 66 axis hole 2 that two change the angle of attack, φ 62 axis hole 3, lower end is provided with four M16 screw holes 12 and four φ 14 pin-and-holes 11 of change angle of side slip, two φ 66 axis holes 2 of large joint 1 upper end, φ 62 axis hole 3 axis hole is connected with the axis hole that known wind-tunnel changes the supporting plate four-bar linkage of the angle of attack by two axles, can with parallel motion, change the angle of attack, four M16 screw holes 12 of large joint 1 lower end are connected with extension 4 with screw and pin from the different screw hole set by extension 4 and pin-and-hole screw hole respectively with four φ 14 pin-and-holes 11, and can be connected by the screw hole different from extension and pin-and-hole and change angle of side slip.Described extension 4 is the square plate 5 that an outside is provided with strength beam 6, extension 4 is connected with large joint 1, enable model under At High Angle of Attack, high angles of side slip attitude, enter the core flow of Flow Field in Wind Tunnel, avoid colliding with hole wall or being too interfered close to hole wall, ensure that the air-flow entering inlet channel reaches test requirements document, take off data is accurate.Described
Extension 4 connects pre-fishplate bar 7 partially and as a whole, pre-fishplate bar 7 being partially provided with multiple waist-shaped hole 9, changing 15 φ 10 dowel holes 8 and φ 16 kingpin hole 10 of model angle of side slip for combining change, and pre-fishplate bar 7 is partially threaded with model aircraft upper screwed hole through waist-shaped hole 9 by screw.Described pre-fishplate bar 7 and wind-tunnel horizontal reference are partially provided with the pre-inclination angle of 20 degree, add being connected of extension 4 and large joint 1, make partially can reach 46 degree in advance with it; Model passes through the dowel hole 8 on pre-fishplate bar 7 partially and is threaded again, makes it partially also to reach 46 degree in advance, thus the angle of attack of model can be made under the change of wind-tunnel angle of attack mechanism maximum, reach model test attitude At High Angle of Attack 60 ° of demands.15 dowel holes 8 and a kingpin hole 10 that described pre-fishplate bar 7 is partially provided with for combining change change model angle of side slip can be combined into angle of side slip-23 ° to 23 °.
Working process of the present invention and principle:
1. be connected with wind-tunnel by the axis hole of joint large on device, and the interlock of wind-tunnel four-bar linkage, enable model change the angle of attack with angle of attack mechanism change.
2. be connected with large joint by the extension on device, enable model under At High Angle of Attack, high angles of side slip attitude, enter the core flow of Flow Field in Wind Tunnel, ensure that the air-flow entering inlet channel reaches test requirements document, take off data is accurate.
3. pass through partially to add that the change in angle of attack of angle of attack mechanism reaches the At High Angle of Attack needed for test in advance by the pre-model that can enable to be attached thereto that partially combines of the partially pre-and pre-plate partially of large joint.
4. the angle of side slip of model is changed by the multiple pin-and-hole combination changes on device.Model is enable to reach high angles of side slip attitude needed for test.
5, four waist-shaped holes are mainly used in being connected with model.Four hexagon socket head cap screws are screwed in link model in the screw hole of model surface through four waist-shaped holes, ensure that model becomes as a whole with this device.And when model needs to break away, unclamp screw and extract zero degree locating dowel pin, rotational model, screw slides with waist-shaped hole, when reaching required angle, stamps locating dowel pin, tighten the screws, has completed the change of angle of side slip.
Claims (4)
1. a model aircraft test attitude implement device, comprise large joint (1), extension (4), pre-fishplate bar (7) partially, it is characterized in that described large joint (1) upper end is provided with the axis hole (2 that two change the angle of attack, 3), lower end is provided with multiple screw holes (12) and multiple pin-and-hole (11) of change angle of side slip, two axis holes (2 of large joint (1) upper end, 3) axis hole being changed the supporting plate four-bar linkage of the angle of attack by two axles and wind-tunnel is connected, can with parallel motion, change the angle of attack, multiple screw holes (12) of large joint (1) lower end are connected with extension (4) with screw and pin from the different screw hole set by extension (4) and pin-and-hole respectively with multiple pin-and-hole (11), and can be connected by the screw hole different from extension and pin-and-hole and change angle of side slip, extension (4) connects pre-fishplate bar (7) partially and as a whole, pre-fishplate bar (7) being partially provided with multiple waist-shaped hole (9), changing multiple dowel holes (8) and a kingpin hole (10) of model angle of side slip for combining change, and pre-fishplate bar (7) is partially threaded with model aircraft upper screwed hole through waist-shaped hole (9) by screw.
2. a kind of model aircraft test attitude implement device according to claim 1, it is characterized in that described extension (4) is the square plate (5) that an outside is provided with strength beam (6), extension (4) is connected with large joint (1), enables model under At High Angle of Attack, high angles of side slip attitude, enter the core flow of Flow Field in Wind Tunnel.
3. a kind of model aircraft test attitude implement device according to claim 1, it is characterized in that described pre-fishplate bar (7) and wind-tunnel horizontal reference are partially provided with the pre-inclination angle of 20 degree, add being connected of extension (4) and large joint (1), make partially can reach 46 degree in advance with it; Model passes through the dowel hole on pre-fishplate bar (7) partially and is threaded again, makes it partially also to reach 46 degree in advance, thus the angle of attack of model can be made under the change of wind-tunnel angle of attack mechanism maximum, reach model test attitude At High Angle of Attack demand.
4. a kind of model aircraft test attitude implement device according to claim 1, is characterized in that multiple dowel holes (8) and a kingpin hole (10) that described pre-fishplate bar (7) is partially provided with for combining change change model angle of side slip can be combined into angle of side slip-23 ° to 23 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201210563683.2A CN103057728B (en) | 2012-12-24 | 2012-12-24 | A kind of model aircraft test attitude implement device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210563683.2A CN103057728B (en) | 2012-12-24 | 2012-12-24 | A kind of model aircraft test attitude implement device |
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| CN103057728A CN103057728A (en) | 2013-04-24 |
| CN103057728B true CN103057728B (en) | 2015-09-02 |
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| CN201210563683.2A Expired - Fee Related CN103057728B (en) | 2012-12-24 | 2012-12-24 | A kind of model aircraft test attitude implement device |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106441785A (en) * | 2016-09-07 | 2017-02-22 | 中国航空工业集团公司沈阳空气动力研究所 | Support mechanism for small propulsion device inlet engine compatibility test in intermittent wind tunnel |
| CN107830986A (en) * | 2017-11-29 | 2018-03-23 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of air intake duct model flow control device |
| CN112345194B (en) * | 2020-10-30 | 2022-03-04 | 中国航天空气动力技术研究院 | Low-speed wind tunnel test method for realizing extremely large sideslip angle attitude |
| CN116296225B (en) * | 2023-05-18 | 2023-07-21 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel large-attack-angle test device based on arc-shaped curved knife attack-angle mechanism |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4658635A (en) * | 1985-03-13 | 1987-04-21 | Deutsche Forschungs- Und Versuchsanstalt | Simulator for aerodynamic investigations of models in a wind tunnel |
| US5020364A (en) * | 1990-05-30 | 1991-06-04 | Grumman Aerospace Corporation | Wind tunnel model positioning device |
| CN101832851A (en) * | 2010-05-31 | 2010-09-15 | 中国航空工业空气动力研究院 | Air flotation force measuring device of wind tunnel model |
| CN102095567A (en) * | 2009-12-11 | 2011-06-15 | 中国航空工业空气动力研究院 | Forced yawing-free rolling wind tunnel test device |
| CN203078763U (en) * | 2012-12-24 | 2013-07-24 | 中国航空工业集团公司沈阳空气动力研究所 | Device for achieving test poses of airplane model |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05296875A (en) * | 1992-04-23 | 1993-11-12 | Mitsubishi Heavy Ind Ltd | Wind tunnel test device |
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2012
- 2012-12-24 CN CN201210563683.2A patent/CN103057728B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4658635A (en) * | 1985-03-13 | 1987-04-21 | Deutsche Forschungs- Und Versuchsanstalt | Simulator for aerodynamic investigations of models in a wind tunnel |
| US5020364A (en) * | 1990-05-30 | 1991-06-04 | Grumman Aerospace Corporation | Wind tunnel model positioning device |
| CN102095567A (en) * | 2009-12-11 | 2011-06-15 | 中国航空工业空气动力研究院 | Forced yawing-free rolling wind tunnel test device |
| CN101832851A (en) * | 2010-05-31 | 2010-09-15 | 中国航空工业空气动力研究院 | Air flotation force measuring device of wind tunnel model |
| CN203078763U (en) * | 2012-12-24 | 2013-07-24 | 中国航空工业集团公司沈阳空气动力研究所 | Device for achieving test poses of airplane model |
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