CN203083806U - Rudder surface loading device - Google Patents
Rudder surface loading device Download PDFInfo
- Publication number
- CN203083806U CN203083806U CN 201320080421 CN201320080421U CN203083806U CN 203083806 U CN203083806 U CN 203083806U CN 201320080421 CN201320080421 CN 201320080421 CN 201320080421 U CN201320080421 U CN 201320080421U CN 203083806 U CN203083806 U CN 203083806U
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- CN
- China
- Prior art keywords
- rudder
- load bracket
- rudder face
- folder
- bearing
- 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 - Fee Related
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model relates to a rudder surface loading device. A rotary center is arranged at one end of an L-shaped load bracket; the load bracket on the rotary center is connected with a rudder clamp through a deep channel ball shaft; the upper surface and the lower surface of the deep channel ball shaft are respectively positioned with the load bracket through a bearing end cover and a clamping ring; a horizontal through hole is also formed in the rudder clamp; a joint bearing is arranged in the through hole; one end of a rod spring penetrates through the joint bearing and is connected with a nut; the other end of the rod spring sequentially penetrates through two parallel rod spring pressing blocks; the bottom surfaces of the rod spring pressing blocks are connected with the load bracket; test equipment is moveably connected with the L-shaped vertical bent surface of the load bracket; an opening groove is formed above the rudder clamp; a rudder surface is positioned in the opening groove; and the axial line of the rudder clamp and the axial line of the rudder surface are overlapped. The rudder surface loading device is simple in structure, and can simulate the air power of a guided missile on the rudder surface in the flying process of the guided missile in the air, and a product is tested.
Description
Technical field
The utility model relates to a kind of rudder face charger, the invention belongs to the automatic control technology field, relate to a kind of device of applying load for guided missile steering wheel rudder face, be used for the product test process, simulated missile is the suffered aerodynamic a kind of constructional device of steering wheel rudder face in the flight course aloft.
Background technology
Rudder face charger in the past adopts disc shaft to link to each other with rudderpost, and disk one side links to each other with spring, and opposite side hangs counterweight pulling disk and rotates, and can change the size of rudder face load by the weight of adjusting counterweight.This device volume is bigger, and the rudder face that is not suitable in the guided missile rotary test process loads.
Summary of the invention
The technical problems to be solved in the utility model provides a kind of rudder face charger, and this rudder face charger is simple in structure, and can simulated missile the suffered aerodynamic force of steering wheel rudder face in the flight course aloft, realize product test.
For overcoming the above problems, concrete technical scheme of the present utility model is as follows: a kind of rudder face charger, end in L shaped load bracket is the centre of gyration, load bracket is connected with the rudder folder by deep groove ball bearing on the centre of gyration, and the upper and lower surface of deep groove ball bearing is respectively by bearing (ball) cover and collar and load bracket location; Press from both sides the through hole that also is provided with level at rudder, be provided with oscillating bearing in through hole, an end of pole spring passes oscillating bearing and is connected with nut, and the other end of pole spring passes two pole spring briquettings that be arranged in parallel successively, and the bottom surface of pole spring briquetting is connected with load bracket; On the L shaped vertical folding surface of load bracket, flexibly connect testing apparatus; Be provided with open slot above the rudder folder, rudder face is positioned at this open slot, and the axis of rudder folder and the dead in line of rudder face.
Be provided with reinforcement between two vertical planes of described load bracket.
This rudder face charger can pass to the rotating torque that testing apparatus produced rudder face by said structure, thus can simulated missile the suffered aerodynamic force of steering wheel rudder face in the flight course aloft, realize product test.
Description of drawings
Fig. 1 is the front view of rudder face charger.
Fig. 2 is the side view of rudder face charger.
Fig. 3 is the axonometric drawing of rudder face charger
Embodiment
As shown in Figure 1 to Figure 3, a kind of rudder face charger, end in L shaped load bracket 10 is the centre of gyration, and load bracket 10 is connected with rudder folder 1 by deep groove ball bearing 4 on the centre of gyration, and the upper and lower surface of deep groove ball bearing 4 is respectively by bearing (ball) cover 5 and collar 6 and load bracket 10 location; Also be provided with the through hole of level at rudder folder 1, in through hole, be provided with oscillating bearing 3, one end of pole spring 8 passes oscillating bearing 3 and is connected with nut 2, and the other end of pole spring 8 passes two pole spring briquettings 9 that be arranged in parallel successively, and the bottom surface of pole spring briquetting 9 is connected with load bracket 10; On the L shaped vertical folding surface of load bracket 10, flexibly connect testing apparatus 11; Be provided with open slot above rudder folder 1, rudder face 12 is positioned at this open slot, and the axis of rudder folder 1 and the dead in line of rudder face 12.
Be provided with reinforcement between two vertical planes of described load bracket 10.
During work, when the steering wheel rudder face was loaded, rudder face 12 drove rudder folder 1 and rotates, after rudder folder 1 rotates, drive pole spring 8 swings, the moment that final pole spring swing produces is applied on the rudder face 12, can simulated missile the suffered aerodynamic force of steering wheel rudder face in the flight course aloft, realize product test.
Claims (2)
1. rudder face charger, it is characterized in that: the end in L shaped load bracket (10) is the centre of gyration, load bracket on the centre of gyration (10) is connected with rudder folder (1) by deep groove ball bearing (4), and the upper and lower surface of deep groove ball bearing (4) is respectively by bearing (ball) cover (5) and collar (6) and load bracket (10) location; Also be provided with the through hole of level at rudder folder (1), in through hole, be provided with oscillating bearing (3), one end of pole spring (8) passes oscillating bearing (3) and is connected with nut (2), the other end of pole spring (8) passes two pole spring briquettings (9) that be arranged in parallel successively, and the bottom surface of pole spring briquetting (9) is connected with load bracket (10); On the L shaped vertical folding surface of load bracket (10), flexibly connect testing apparatus (11); Top at rudder folder (1) is provided with open slot, and rudder face (12) is positioned at this open slot, and the axis of rudder folder (1) and the dead in line of rudder face (12).
2. a kind of rudder face charger as claimed in claim 1 is characterized in that: be provided with reinforcement between two vertical planes of described load bracket (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320080421 CN203083806U (en) | 2013-02-21 | 2013-02-21 | Rudder surface loading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320080421 CN203083806U (en) | 2013-02-21 | 2013-02-21 | Rudder surface loading device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203083806U true CN203083806U (en) | 2013-07-24 |
Family
ID=48829631
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320080421 Expired - Fee Related CN203083806U (en) | 2013-02-21 | 2013-02-21 | Rudder surface loading device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203083806U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106352925A (en) * | 2016-09-21 | 2017-01-25 | 中国运载火箭技术研究院 | Device for determining performance of control surface transmission mechanism in thermal-mechanical environments |
| CN106564617A (en) * | 2016-10-27 | 2017-04-19 | 北京实验工厂 | FLAP control plane loading device and function testing method |
| CN106828972A (en) * | 2016-12-15 | 2017-06-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft rudder surface drive ram performance testing device |
| CN110907157A (en) * | 2019-12-03 | 2020-03-24 | 武汉宏海兴民科技有限公司 | Multifunctional device for testing performance index of steering engine |
-
2013
- 2013-02-21 CN CN 201320080421 patent/CN203083806U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106352925A (en) * | 2016-09-21 | 2017-01-25 | 中国运载火箭技术研究院 | Device for determining performance of control surface transmission mechanism in thermal-mechanical environments |
| CN106564617A (en) * | 2016-10-27 | 2017-04-19 | 北京实验工厂 | FLAP control plane loading device and function testing method |
| CN106828972A (en) * | 2016-12-15 | 2017-06-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft rudder surface drive ram performance testing device |
| CN106828972B (en) * | 2016-12-15 | 2019-03-19 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft rudder surface drive ram performance testing device |
| CN110907157A (en) * | 2019-12-03 | 2020-03-24 | 武汉宏海兴民科技有限公司 | Multifunctional device for testing performance index of steering engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130724 Termination date: 20160221 |