CN103057728A - Achievement device of airplane model test gestures - Google Patents
Achievement device of airplane model test gestures Download PDFInfo
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- CN103057728A CN103057728A CN2012105636832A CN201210563683A CN103057728A CN 103057728 A CN103057728 A CN 103057728A CN 2012105636832 A CN2012105636832 A CN 2012105636832A CN 201210563683 A CN201210563683 A CN 201210563683A CN 103057728 A CN103057728 A CN 103057728A
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Abstract
Provided is an achievement device of airplane model test gestures. One end of the device is connected with a joint of a wind tunnel connection mechanism, and the other end of the device is connected with a model, namely a test device is a part of a model supporting mechanism. The test device comprises a big joint, an extending section, a pre-leaning connection plate, a plurality of pin holes on the pre-leaning connection plate and four waist-shaped holes. The achievement device is characterized in that preleaning is carried out on a connection plane on the basis of a wind tunnel connection structure, high incidence test states can be easily achieved, and combination of big sideslip angle test states and the pin holes on a model cooperating face through the pre-leaning connection plate can be easily achieved. The achievement device is simple in structure, parameters are obtained through aerodynamic design or calculation, high incidence and big sideslip angle test states can be easily achieved, and simultaneously the achievement device is convenient to install and disassemble and applicable to high incidence and big sideslip angle air inlet tests of high-speed wind tunnels.
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 to being complementary by the machine of superior performance.The purpose of air intake test is to measure static state and the dynamic characteristics of inlet channel, for the design of inlet channel provides test figures, can both satisfy the requirement of driving engine to guarantee the performance of inlet channel in whole flight envelope.Otherwise can make driving engine that surge or parking occur aloft.Third generation opportunity of combat (such as the F15 opportunity of combat of Muscovite Su27 opportunity of combat and the U.S.) is emphasized high maneuverability, the agility that low coverage is fought, and such as fast dive, the motor-driven deceleration of At High Angle of Attack etc., wherein foremost is " Pu Jiaqiaofu Cobra maneuver ".When aircraft when At High Angle of Attack (surpass 50 degree), the area of catching of airplane intake reduces, the flow that flows into inlet channel can reduce, and causes easily the driving engine flame-out in flight.And these special feelings subjects can not be realized by flight test, affect aviator's safety.Therefore must realize on ground the flight angle of these At High Angle of Attacks, high angles of side slip, the performance of check flight inlet channel.Owing to be subject to the size of wind-tunnel and experimental set-up in the past, Test item can not reach desired At High Angle of Attack, high angles of side slip flight angle, and the flight angle that so how to make model aircraft reach the desired At High Angle of Attack of test, high angles of side slip has become the key technical problem in the test of inlet channel At High Angle of Attack attitude.
Summary of the invention
The technical problem to be solved in the present invention is, a kind of model aircraft test attitude implement device that designs in high speed wind tunnel, realizing At High Angle of Attack, high angles of side slip test condition, its objective is At High Angle of Attack, the high angles of side slip test condition of realizing model aircraft, thereby measure the inlet characteristic of model aircraft under At High Angle of Attack, high angles of side slip test condition, check inlet channel conceptual design
Feasibility.
The technical scheme that adopts is:
A kind of model aircraft test attitude implement device comprises large joint, extension, pre-partially fishplate bar.Described large upper end of joint is provided with two axis holes that change the angle of attack, the lower end is provided with a plurality of screw holes and a plurality of pin-and-hole that changes angle of side slip, 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 be with parallel motion, change the angle of attack, a plurality of screw holes of large joint lower end with are connected the set different screw holes of pin-and-hole and extension and are connected with pin-and-hole with screw and are connected with extension with pin, and can by from extension on different screw hole and pin-and-hole be connected to change angle of side slip.Extension connects pre-partially fishplate bar and as a whole, pre-partially fishplate bar is provided with a plurality of waist-shaped holes, is used for a plurality of dowel holes and a kingpin hole that the combination variation changes the model angle of side slip, and pre-partially fishplate bar passes waist-shaped hole by screw and is threaded with the model aircraft upper screwed hole.
Above-mentioned extension is the square plate that an outside is provided with strength beam, and extension is connected with large joint, makes model can enter the core flow of Flow Field in Wind Tunnel under At High Angle of Attack, high angles of side slip attitude.
The pre-drift angle degree that above-mentioned pre-partially fishplate bar and wind-tunnel horizontal reference are provided with one 20 degree is added being connected of extension and large joint, makes partially to reach in advance with it 46 degree; Model makes it partially also to reach in advance 46 degree, thereby can make the angle of attack of model maximum under the variation of wind-tunnel angle of attack mechanism by the dowel hole on the pre-partially fishplate bar be threaded again, reaches model test attitude At High Angle of Attack demand.
Above-mentioned pre-partially fishplate bar is provided with and changes a plurality of dowel holes of changing the model angle of side slip and kingpin hole for combination and can be combined into angle of side slip-23 ° to 23 °.
The present invention is simple in structure, and the dismounting of each element of main body of device and variation are convenient, and the parameter of each element obtains through calculating, and checks than right Joint strenght in the later stage of design, has also obtained in test checking.The design science of whole device is rigorous, increases device and can ignore the impact of air intake test, and experimental performance is reliable, has guaranteed the accuracy of observed data.
Description of drawings
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.
The specific embodiment
A kind of model aircraft test attitude implement device comprises large joint 1, extension 4, pre-partially fishplate bar 7.Described large joint 1 upper end is provided with two φ 66 axis holes 2 that change the angle of attack, φ 62 axis holes 3, the lower end is provided with four M16 screw holes 12 and four φ 14 pin-and-holes 11 that change angle of side slip, two φ, 66 axis holes 2 of large joint 1 upper end, φ 62 axis holes 3 axis holes 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 be with parallel motion, change the angle of attack, four M16 screw holes 12 of large joint 1 lower end with are connected a φ 14 pin-and-holes 11 and extension 4 set different screw holes and are connected with the pin-and-hole screw hole with screw and are connected with extension 4 with pin, and can by from extension on different screw hole and pin-and-hole be connected to 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, make model can 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 the hole wall or too being interfered near the hole wall, the air-flow that assurance enters inlet channel reaches test requirements document, and take off data is accurate.Described
Extension 4 connects pre-partially fishplate bar 7 and as a whole, pre-partially fishplate bar 7 is provided with a plurality of waist-shaped holes 9, is used for 15 φ, 10 dowel holes 8 and φ 16 kingpin holes 10 that the combination variation changes the model angle of side slip, and pre-partially fishplate bar 7 passes waist-shaped hole 9 by screw and is threaded with the model aircraft upper screwed hole.Described pre-partially fishplate bar 7 is provided with one 20 pre-drift angle degree of spending with the wind-tunnel horizontal reference, adds being connected of extension 4 and large joint 1, makes partially to reach in advance with it 46 degree; Model makes it partially also to reach in advance 46 degree, thereby can make the angle of attack of model maximum under the variation of wind-tunnel angle of attack mechanism by the dowel hole 8 on the pre-partially fishplate bar 7 be threaded again, reaches 60 ° of demands of model test attitude At High Angle of Attack.Described pre-partially fishplate bar 7 is provided with and changes 15 dowel holes 8 changing the model angle of side slip and kingpin hole 10 for combination and can be combined into angle of side slip-23 ° to 23 °.
Working process of the present invention and principle:
1. the axis hole by large joint on the device is connected with wind-tunnel, and the interlock of wind-tunnel four-bar linkage, model can be changed with angle of attack mechanism change the angle of attack.
2. be connected with large joint by the extension on the device, make model can enter the core flow of Flow Field in Wind Tunnel under At High Angle of Attack, high angles of side slip attitude, guarantee that the air-flow that enters inlet channel reaches test requirements document, take off data is accurate.
3. the in advance in advance inclined to one side combination inclined to one side and pre-partially plate by large joint can make the model that is attached thereto can reach the required At High Angle of Attack of test by the change in angle of attack that partially adds in advance angle of attack mechanism.
4. change the angle of side slip that changes model by a plurality of pin-and-hole combinations on the device.Make model can reach the required high angles of side slip attitude of test.
5, four waist-shaped holes are mainly used in linking to each other with model.Four hexagon socket head cap screws pass link model in the screw hole that four waist-shaped holes are screwed in model surface, guarantee that model becomes as a whole with this device.And when model need to break away, unclamp screw to extract the zero degree locating dowel pin, rotational model, screw slide with waist-shaped hole, when reaching required angle, stamp locating dowel pin, and tighten the screws has been finished the variation of angle of side slip.
Claims (4)
1. a model aircraft is tested the attitude implement device, comprise large joint (1), extension (4), pre-partially fishplate bar (7), it is characterized in that described large joint (1) upper end is provided with two axis holes (2 that change the angle of attack, 3), the lower end is provided with a plurality of screw holes (12) and a plurality of pin-and-hole (11) that changes angle of side slip, two axis holes (2 of large joint (1) upper end, 3) be connected with the axis hole that wind-tunnel changes the supporting plate four-bar linkage of the angle of attack by two axles, can be with parallel motion, change the angle of attack, a plurality of screw holes (12) of large joint (1) lower end with are connected the set different screw holes of pin-and-hole (11) and extension (4) and are connected with pin-and-hole with screw and are connected with extension (4) with pin, and can by from extension on different screw hole and pin-and-hole be connected to change angle of side slip; Extension (4) connects pre-partially fishplate bar (7) and as a whole, pre-partially fishplate bar (7) is provided with a plurality of waist-shaped holes (9), is used for a plurality of dowel holes (8) and a kingpin hole (10) that the combination variation changes the model angle of side slip, and pre-partially fishplate bar (7) passes waist-shaped hole (9) by screw and is threaded with the model aircraft upper screwed hole.
2. a kind of model aircraft according to claim 1 is tested the attitude implement device, 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), makes model can enter the core flow of Flow Field in Wind Tunnel under At High Angle of Attack, high angles of side slip attitude.
3. a kind of model aircraft according to claim 1 is tested the attitude implement device, it is characterized in that described pre-partially fishplate bar (7) and wind-tunnel horizontal reference are provided with the pre-drift angle degree of one 20 degree, add being connected of extension (4) and large joint (1), make partially to reach in advance with it 46 degree; Model makes it partially also to reach in advance 46 degree, thereby can make the angle of attack of model maximum under the variation of wind-tunnel angle of attack mechanism by the dowel hole on the pre-partially fishplate bar (7) be threaded again, reaches 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 described pre-partially fishplate bar (7) is provided with and changes a plurality of dowel holes (8) of changing the model angle of side slip and a kingpin hole (10) for combination and can be combined into angle of side slip-23 ° to 23 °.
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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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| CN201210563683.2A CN103057728B (en) | 2012-12-24 | 2012-12-24 | A kind of model aircraft test attitude implement device |
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| CN103057728A true CN103057728A (en) | 2013-04-24 |
| CN103057728B CN103057728B (en) | 2015-09-02 |
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Cited By (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 |
| CN112345194A (en) * | 2020-10-30 | 2021-02-09 | 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 |
| CN116296225A (en) * | 2023-05-18 | 2023-06-23 | 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 (6)
| 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 |
| JPH05296875A (en) * | 1992-04-23 | 1993-11-12 | Mitsubishi Heavy Ind Ltd | 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 |
| 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 |
-
2012
- 2012-12-24 CN CN201210563683.2A patent/CN103057728B/en not_active Expired - Fee Related
Patent Citations (6)
| 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 |
| JPH05296875A (en) * | 1992-04-23 | 1993-11-12 | Mitsubishi Heavy Ind Ltd | Wind tunnel test 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 |
Cited By (6)
| 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 |
| CN112345194A (en) * | 2020-10-30 | 2021-02-09 | 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 |
| 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 |
| CN116296225A (en) * | 2023-05-18 | 2023-06-23 | 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 |
| 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 |
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| CN103057728B (en) | 2015-09-02 |
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