CN201724807U - Connector for horizontal stabilizer and vertical stabilizer of flutter model - Google Patents
Connector for horizontal stabilizer and vertical stabilizer of flutter model Download PDFInfo
- Publication number
- CN201724807U CN201724807U CN201020119161XU CN201020119161U CN201724807U CN 201724807 U CN201724807 U CN 201724807U CN 201020119161X U CN201020119161X U CN 201020119161XU CN 201020119161 U CN201020119161 U CN 201020119161U CN 201724807 U CN201724807 U CN 201724807U
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- support arm
- vertical fin
- stabilizer
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- flutter
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Abstract
The utility model relates to a connector for a horizontal stabilizer and a vertical stabilizer of a flutter model. The connector comprises a lower stay bar, a U-shaped spring, an upper stay bar, a rotary support arm and a vertical stabilizer joint, wherein the rotary support arm is connected with a horizontal stabilizer beam, the horizontal stabilizer is connected with the rotary support arm through the horizontal stabilizer beam, one end of the rotary support arm is articulated with the vertical stabilizer joint and thereby connected with a vertical stabilizer beam, the front point of the other end of the rotary support arm is connected with the upper stay bar through clearance-adjusting nuts, the other end of the upper stay bar is connected with one U-shaped side of the U-shaped spring, and the other U-shaped side of the U-shaped spring is connected with the vertical stabilizer beam through the lower stay bar. Consequently, the utility model can realistically simulate the connection form of the horizontal stabilizer and the vertical stabilizer on the T-tailed flutter model, accurately simulate the rigidity of the spiral actuator of the jiggling horizontal stabilizer and conveniently implement the simulation of clearance nonlinearity, thus effectively meeting the requirements of the wind tunnel trial of the T-tailed flutter model.
Description
Technical field
The utility model belongs to aircraft aeroelasticity field flutter model wind-tunnel technique, relates to a kind of flat vertical fin coupling arrangement that is used for the flutter model wind tunnel test.
Background technology
Large-scale T stern construction often adopts the fine motion horizontal tail, and horizontal tail is connected the vertical fin top by 3, and back two is point articulated on the vertical fin back rest, and fixes from the rear, and preceding point then is fixed on the horizontal tail spiral actuator.This connected mode brings uncertain factor for the support rigidity of fine motion horizontal tail.In the process of aircraft utilization simultaneously, tailplane spiral actuator is owing to wear and tear, and the gap can change, thereby has backlash nonlinearity flutter problem.
Yet in the airplane flutter model wind tunnel test, particularly when the design of T tail flutter model, the type of attachment of the flat vertical fin of real simulation seldom, accurately do not simulate fine motion horizontal tail spiral actuator rigidity and this factor of backlash nonlinearity thereof yet, therefore in the flutter model wind tunnel test, can not accurately obtain the buffet characteristic of T tail, particularly can not obtain horizontal tail pitching type flutter and non-linear limit ring flutter phenomenon.
The utility model content
The purpose of this utility model is: a kind of flat vertical fin coupling arrangement that can simulate horizontal tail pressurized strut rigidity and backlash nonlinearity flutter in the wind tunnel test of T tail flutter model is provided.
The technical solution of the utility model is: a kind of flat vertical fin coupling arrangement of flutter model that is used for, it comprises lower supporting rod, U type spring, last strut, the rotation support arm, the vertical fin joint, wherein, be connected with the horizontal tail beam on the described rotation support arm, horizontal tail is joined by horizontal tail beam and rotation support arm, described rotation support arm one end is by being hinged with the vertical fin joint and linking to each other with the vertical fin beam, point links to each other with last strut by the gap adjustment nut before the other end termination of described rotation support arm, the described strut other end of going up links to each other with U type spring one U type limit, and another U type limit of described U type spring links to each other with the vertical fin beam by lower supporting rod.
Described lower supporting rod links to each other with the vertical fin beam by sway brace.
Be hinged by the rotation axis that is provided with bearing between described rotation support arm and the vertical fin joint.
Compare with prior art, on T tail flutter model real simulation the type of attachment of flat vertical fin, also accurately simulated fine motion horizontal tail spiral actuator rigidity, can conveniently realize backlash nonlinearity, satisfy the requirement of T tail flutter model wind tunnel test.
The beneficial effects of the utility model are: the flat vertical fin coupling arrangement of the utility model T tail flutter model wind tunnel test is realized the connection between horizontal tail and the vertical fin beam, thereby can simulate the type of attachment of flat vertical fin.And, the rigidity of different sizes can be provided, thereby can simulate of the influence of different fine motion horizontal tail actuator rigidity T tail buffet characteristic by different flexible U type springs are set between upper and lower strut.And change gap between horizontal tail and the vertical fin beam by the gap adjustment nut, can simulate the influence of backlash nonlinearity, and can change the horizontal tail angle of attack variation and obtain different trystates flutter.
Description of drawings
Fig. 1 is the structural representation that the utility model is used for flat vertical fin coupling arrangement one better embodiment of flutter model,
Among the figure: 1-vertical fin beam, 2-sway brace, 3-lower supporting rod, 4-U type spring, the last strut of 5-, 6-gap adjustment nut, 7-rotation support arm, 8-horizontal tail beam, 9-bearing, 10-rotation axis, 11-vertical fin joint.
Embodiment
Below by specific embodiment the utility model is described in further detail:
See also Fig. 1, it is the structural representation that the utility model is used for flat vertical fin coupling arrangement one better embodiment of flutter model.In the present embodiment, the described flat vertical fin coupling arrangement of flutter model that is used for comprises sway brace 2, lower supporting rod 3, U type spring 4, goes up strut 5, rotation support arm 7 and vertical fin joint 11.Wherein, be connected with horizontal tail beam 8 on the rotation support arm 7, so the aircraft horizontal tail links to each other with rotation support arm 7 by horizontal tail beam 8.Described rotation support arm 7 one ends are hinged with vertical fin joint 11 by the rotation axis 10 that is provided with bearing 9, and vertical fin joint 11 links to each other with vertical fin beam 1.Point links to each other with last strut 5 by gap adjustment nut 6 before the other end termination of described rotation support arm 7.The end that described upward strut 5 is not provided with gap adjustment nut 6 links to each other with a U type limit of U type spring 4.Another U type limit of described U type spring 4 links to each other with sway brace 2 by lower supporting rod 3, and described sway brace 2 links to each other with vertical fin beam 1.
Under extraneous air-flow effect, slight pitching, the therefore luffing that can simulate horizontal tail can take place through rotation support arm 7 around rotation axis 10 in horizontal tail.In addition,, link to each other with the vertical fin joint 11 of vertical fin beam 1 by rotation axis 10, therefore can simulate the type of attachment of flat vertical fin and rotate support arm 7 because horizontal tail links to each other with rotation support arm 7 by horizontal tail beam 8.
In the present embodiment, be simulation fine motion horizontal tail actuator rigidity, design one cover has different flexible U type springs 4, so that different rigidity to be provided.When having rigidity that different flexible U type springs 4 provide not simultaneously, the pulling force size of 4 pairs of rotations of U type spring support arm 7 also can be variant, thereby can cause the pitching of the different amplitudes of horizontal tail, to simulate of the influence of different fine motion horizontal tail actuator rigidity to T tail buffet characteristic.In actual wind tunnel test, under more weak U type spring rate, the flutter of horizontal tail pitching type can appear.
In addition, the utility model is by the two ends fixing with U type spring, and when strut 5 was gone up in 6 lockings of gap adjustment nut, then being used for the flat vertical fin coupling arrangement of flutter model was linear system.Yet, when the elasticity of passing through to regulate between gap adjustment nut 6 and the last strut 5, make between gap adjustment nut 6 and the last strut 5 and have certain clearance, the two links to each other but when not locking, can destroy the system linearity degree, make it to become the backlash nonlinearity system, thereby can simulate the influence of backlash nonlinearity flutter.And by adjusting play setting nut 6, the length of strut 5 can also change the horizontal tail angle of attack in the change, thereby can change the flutter test state of horizontal tail, to carry out the flutter test of different conditions.
In sum, the utility model be used for the flat vertical fin coupling arrangement of flutter model on T tail flutter model real simulation the type of attachment of flat vertical fin, accurately simulated fine motion horizontal tail spiral actuator rigidity, and can conveniently realize the simulation of backlash nonlinearity, thereby can satisfy the requirement of T tail flutter model wind tunnel test preferably.
Claims (3)
1. one kind is used for the flat vertical fin coupling arrangement of flutter model, it is characterized in that: comprise lower supporting rod [3], U type spring [4], last strut [5], rotation support arm [7], vertical fin joint [11], wherein, be connected with horizontal tail beam [8] on the described rotation support arm [7], horizontal tail is joined by horizontal tail beam [8] and rotation support arm [7], described rotation support arm [7] one ends are by being hinged with vertical fin joint [11] and linking to each other with vertical fin beam [1], point links to each other with last strut [5] by gap adjustment nut [6] before the other end termination of described rotation support arm [7], described strut [5] other end of going up links to each other with U type spring [4] one U type limits, and another U type limit of described U type spring [4] links to each other with vertical fin beam [1] by lower supporting rod [3].
2. the flat vertical fin coupling arrangement of flutter model that is used for according to claim 1 is characterized in that: described lower supporting rod [3] links to each other with vertical fin beam [1] by sway brace [2].
3. the flat vertical fin coupling arrangement of flutter model that is used for according to claim 1 is characterized in that: be hinged by the rotation axis [10] that is provided with bearing [9] between rotation support arm [7] and the vertical fin joint [11].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020119161XU CN201724807U (en) | 2010-02-26 | 2010-02-26 | Connector for horizontal stabilizer and vertical stabilizer of flutter model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020119161XU CN201724807U (en) | 2010-02-26 | 2010-02-26 | Connector for horizontal stabilizer and vertical stabilizer of flutter model |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201724807U true CN201724807U (en) | 2011-01-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201020119161XU Expired - Lifetime CN201724807U (en) | 2010-02-26 | 2010-02-26 | Connector for horizontal stabilizer and vertical stabilizer of flutter model |
Country Status (1)
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| CN (1) | CN201724807U (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102494866A (en) * | 2011-12-13 | 2012-06-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Framework-type support component for wind tunnel test model |
| CN104048809A (en) * | 2014-05-06 | 2014-09-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Three-freedom-degree simulation external store flutter model for wind tunnel test |
| CN104880362A (en) * | 2015-05-13 | 2015-09-02 | 浙江工业大学 | Self-coordinated transverse micromotion loading device for micromotion fatigue testing |
| CN105486484A (en) * | 2014-10-11 | 2016-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Pylon pitching modal simulation device suitable to be used for flutter wind tunnel model |
| CN105571816A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Combined flutter model with adjustable gap |
| CN106017851A (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Movable surface operation gap simulating device |
| CN108750143A (en) * | 2018-06-23 | 2018-11-06 | 中电科芜湖钻石飞机制造有限公司 | Empennage support device applied to aircraft wind tunnel test |
| CN108910078A (en) * | 2018-06-25 | 2018-11-30 | 中国商用飞机有限责任公司 | For the manipulation gap of flutter model and rigidity analogue |
| CN109506908A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test horizontal tail load charger |
| CN109870289A (en) * | 2019-04-11 | 2019-06-11 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of T-type horizontal tail flutter model protective device and its application |
| CN112213070A (en) * | 2020-09-21 | 2021-01-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Device for simulating suspension clearance of plug-in under flutter wind tunnel test wing |
| CN114674547A (en) * | 2022-05-30 | 2022-06-28 | 中国飞机强度研究所 | Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test |
-
2010
- 2010-02-26 CN CN201020119161XU patent/CN201724807U/en not_active Expired - Lifetime
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102494866A (en) * | 2011-12-13 | 2012-06-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Framework-type support component for wind tunnel test model |
| CN104048809A (en) * | 2014-05-06 | 2014-09-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Three-freedom-degree simulation external store flutter model for wind tunnel test |
| CN104048809B (en) * | 2014-05-06 | 2016-05-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Three Degree Of Freedom simulation store Combinations flutter model for wind tunnel test |
| CN105486484A (en) * | 2014-10-11 | 2016-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Pylon pitching modal simulation device suitable to be used for flutter wind tunnel model |
| CN105571816A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Combined flutter model with adjustable gap |
| CN105486484B (en) * | 2014-10-11 | 2017-11-28 | 中国航空工业集团公司西安飞机设计研究所 | A kind of hanger pitching mode analogue means suitable for flutter wind tunnel model |
| CN105571816B (en) * | 2014-10-11 | 2018-01-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of combined type flutter model of adjustable clearance |
| CN104880362A (en) * | 2015-05-13 | 2015-09-02 | 浙江工业大学 | Self-coordinated transverse micromotion loading device for micromotion fatigue testing |
| CN104880362B (en) * | 2015-05-13 | 2017-06-20 | 浙江工业大学 | Self-coordinating formula fretting fatigue testing transverse direction fine motion loading device |
| CN106017851B (en) * | 2016-05-16 | 2018-11-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of active face manipulation gap simulator |
| CN106017851A (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Movable surface operation gap simulating device |
| CN108750143A (en) * | 2018-06-23 | 2018-11-06 | 中电科芜湖钻石飞机制造有限公司 | Empennage support device applied to aircraft wind tunnel test |
| CN108750143B (en) * | 2018-06-23 | 2020-05-05 | 中电科芜湖钻石飞机制造有限公司 | Empennage supporting device applied to airplane wind tunnel test |
| CN108910078A (en) * | 2018-06-25 | 2018-11-30 | 中国商用飞机有限责任公司 | For the manipulation gap of flutter model and rigidity analogue |
| CN108910078B (en) * | 2018-06-25 | 2021-09-10 | 中国商用飞机有限责任公司 | Control gap and rigidity simulation device for flutter model |
| CN109506908A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test horizontal tail load charger |
| CN109506908B (en) * | 2018-11-09 | 2020-10-23 | 中国直升机设计研究所 | Tail end load loading device for fatigue test of tail section test piece |
| CN109870289A (en) * | 2019-04-11 | 2019-06-11 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of T-type horizontal tail flutter model protective device and its application |
| CN109870289B (en) * | 2019-04-11 | 2024-04-09 | 中国空气动力研究与发展中心高速空气动力研究所 | T-shaped horizontal tail flutter model protection device and application thereof |
| CN112213070A (en) * | 2020-09-21 | 2021-01-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Device for simulating suspension clearance of plug-in under flutter wind tunnel test wing |
| CN112213070B (en) * | 2020-09-21 | 2023-03-14 | 中国航空工业集团公司沈阳飞机设计研究所 | External object hangs clearance analogue means under flutter wind tunnel test wing |
| CN114674547A (en) * | 2022-05-30 | 2022-06-28 | 中国飞机强度研究所 | Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test |
| CN114674547B (en) * | 2022-05-30 | 2022-08-05 | 中国飞机强度研究所 | Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20110126 |