CN202599637U - Gesture adjusting mechanism of T-tail flutter model - Google Patents
Gesture adjusting mechanism of T-tail flutter model Download PDFInfo
- Publication number
- CN202599637U CN202599637U CN 201220212466 CN201220212466U CN202599637U CN 202599637 U CN202599637 U CN 202599637U CN 201220212466 CN201220212466 CN 201220212466 CN 201220212466 U CN201220212466 U CN 201220212466U CN 202599637 U CN202599637 U CN 202599637U
- Authority
- CN
- China
- Prior art keywords
- vertical fin
- model
- tail
- jointing
- adjusting mechanism
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Abstract
The utility model belongs to the aeroelasticity technical field and relates to a gesture adjusting mechanism of a T-tail flutter model. The gesture adjusting mechanism of the T-tail flutter model comprises a two-way adjusting threaded rod, a supporting nut, a positioning support base, a press block, a flat tail connection joint, a vertical tail upper joint, a bearing and a shaft pin. The whole structure is simple, adjustment of pitching gestures of the T-tail flutter model can be achieved by a simple connection of the threaded rod, the nut, the bearing, a screw, a bolt and the like, the operation of the system is very convenient, and gesture control can be achieved by rotating the threaded rod manually by an operator; and the size of an attack angle of a flat tail model corresponding to a vertical tail model can be obtained by rotating the threaded rod forward or reversely. Compared with the prior art, the structure of the design adjusting mechanism is simple, the cost is low, the mounting is convenient, and requirements of flutter model wind tunnel tests can be met completely.
Description
Technical field
The utility model belongs to the aeroelasticity technical field, relates to a kind of T tail flutter model attitude governor motion.
Background technology
For general T tail flutter model design, need not consider to regulate the horizontal tail of model and the attitude between the vertical fin usually.But when doing some investigation tests; Will consider the airplane flutter changes of properties that the variation of research horizontal tail vertical fin relative angle causes; And, need to consider on T tail flutter model, to solve the problem that attitude is regulated this moment to becoming ginseng analysis under all angles operating mode.Classic method uses electric steering engine to regulate the relative position between two parts model usually, and cost is higher relatively; Simultaneously, between two models, steering wheel is installed, need be adjusted accordingly, special web member is set, when reality is used in wind-tunnel, also need carry out wiring, bring bigger difficulty to flutter test to electric steering engine to model structure.
Summary of the invention
The purpose of the utility model is to propose a kind of low cost, simple in structure, the convenient model attitude governor motion that uses.
The technical solution of the utility model is, governor motion is by back nut, the bidirectional modulation screw rod; Briquetting, flat vertical fin jointing, positioning supports base; End connector on the vertical fin, the connection support arm of end connector on the vertical fin, bearing and pivot pin are formed; Flat vertical fin jointing is connected to through bolt on the horizontal tail beam of model, and flat vertical fin jointing is connected to being connected on the support arm of end connector on the vertical fin through bearing and pivot pin, and end connector is connected on the vertical fin beam of model on the vertical fin through bolt; The auricle place is provided with the positioning supports base in the upper end of vertical fin beam, and a back nut is clamped on the auricle of positioning supports base, is provided with briquetting at the front end yoke place of flat vertical fin jointing; Through briquetting another back nut is installed on the flat vertical fin jointing, in the middle of two back nuts, is installed with the bidirectional modulation screw rod.
The length that described bidirectional modulation screw rod stretches out the positioning supports base is greater than 20cm.
Advantage that the utlity model has and beneficial effect: total is simple with material; Only need just can realize the adjusting of T tail flutter model pitch attitude through screw rod and simple annexation such as nut, bearing, screw and bolt; And the operation of this system is also very convenient; Rotation through personnel's manual adjustment screw rod can realize attitude control, does not need extra layout circuit; Can obtain the size of the relative vertical fin model of the horizontal tail model angle of attack through rotating screw bolt forward or backwards.Compare with prior art, the attitude governor motion of design is simple in structure, with low cost, easy for installation here, can satisfy the requirement of flutter model wind tunnel test fully.
Description of drawings
Fig. 1 is the structural representation of the utility model.
Fig. 2 is the front view of the utility model.
Embodiment
Below in conjunction with accompanying drawing the utility model is elaborated.
The utility model is by back nut 1, bidirectional modulation screw rod 2, and briquetting 3, flat vertical fin jointing 4, positioning supports base 6, coupling bolt 8 and 11, end connector 9 on the vertical fin, the connection support arm 10 of end connector on the vertical fin, bearing 12 and pivot pin 13 are formed.Flat vertical fin jointing 4 is connected on the horizontal tail beam 5 of model through bolt 11; Flat vertical fin jointing 4 is connected to being connected on the support arm 10 of end connector on the vertical fin through bearing 12 and pivot pin 13; End connector 9 is connected on the vertical fin beam 7 of model on the vertical fin through bolt 8; 6, one back nuts 1 of positioning supports base are set at auricle place, the upper end of vertical fin beam 7 are clamped on the auricle of positioning supports base 6, be provided with briquetting 3 at the front end yoke place of flat vertical fin jointing 4; Through briquetting 3 another back nut 1 is installed on the flat vertical fin jointing 4, in the middle of two back nuts 1, is installed with bidirectional modulation screw rod 2.
The length of said bidirectional modulation screw rod is wanted long enough, and bidirectional modulation screw rod 2 stretches out the length of positioning supports base 6 greater than 20cm.Thereby guarantee the adjusting of flat vertical fin model attitude; Briquetting is connected with flat vertical fin jointing, positioning supports base and vertical fin beam be connected and flat vertical fin jointing and vertical fin on want firmly being connected of end connector.
Holding nut can rotate around self in the front cross-arm of positioning supports base peace vertical fin jointing; Through rotating the bidirectional modulation screw rod; Can make and drive flat vertical fin jointing is that fulcrum rotates with the bearing place, rotates the purpose of regulating horizontal tail model and vertical fin model attitude to reach through forward and direction.
Claims (2)
1. a T tail flutter model attitude governor motion is characterized in that governor motion is by back nut (1); Bidirectional modulation screw rod (2), briquetting (3), flat vertical fin jointing (4); Positioning supports base (6); End connector on the vertical fin (9), the connection support arm (10) of end connector on the vertical fin, bearing (12) and pivot pin (13) are formed; Flat vertical fin jointing (4) is connected on the horizontal tail beam (5) of model through bolt; Flat vertical fin jointing (4) is connected to being connected on the support arm (10) of end connector on the vertical fin through bearing (12) and pivot pin (13), and end connector on the vertical fin (9) is connected to through bolt on the vertical fin beam (7) of model, at the auricle place, upper end of vertical fin beam (7) positioning supports base (6) is set; A back nut (1) is clamped on the auricle of positioning supports base (6); Front end yoke place at flat vertical fin jointing (4) is provided with briquetting (3), through briquetting (3) another back nut (1) is installed on the flat vertical fin jointing (4), in the middle of two back nuts (1), is installed with bidirectional modulation screw rod (2).
2. a kind of T tail flutter model attitude governor motion according to claim 1, it is characterized in that: described bidirectional modulation screw rod (2) stretches out the length of positioning supports base (6) greater than 20cm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220212466 CN202599637U (en) | 2012-05-11 | 2012-05-11 | Gesture adjusting mechanism of T-tail flutter model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220212466 CN202599637U (en) | 2012-05-11 | 2012-05-11 | Gesture adjusting mechanism of T-tail flutter model |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202599637U true CN202599637U (en) | 2012-12-12 |
Family
ID=47317165
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220212466 Expired - Lifetime CN202599637U (en) | 2012-05-11 | 2012-05-11 | Gesture adjusting mechanism of T-tail flutter model |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202599637U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
-
2012
- 2012-05-11 CN CN 201220212466 patent/CN202599637U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
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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: 20121212 |