CN103792083B - Wing aerodynamic charger - Google Patents
Wing aerodynamic charger Download PDFInfo
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- CN103792083B CN103792083B CN201410080097.1A CN201410080097A CN103792083B CN 103792083 B CN103792083 B CN 103792083B CN 201410080097 A CN201410080097 A CN 201410080097A CN 103792083 B CN103792083 B CN 103792083B
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Abstract
Wing aerodynamic charger, belongs to wing strength test technical field, the present invention solves that employing hydraulic system is to wing imposed load complicated operation, the problem without portability.The present invention includes air pump, electromagnetic proportional valve, clematis stem gas-tpe fitting, n electromagnetic valve, n cylinder and control portion；The gas outlet of air pump connects with the air intake of electromagnetic proportional valve, the gas outlet of electromagnetic proportional valve connects with the air intake of clematis stem gas-tpe fitting, n gas outlet of clematis stem gas-tpe fitting connects with the air intake one_to_one corresponding of n electromagnetic valve respectively, and the gas outlet of any one electromagnetic valve connects with the air intake of a cylinder；The air pressure instruction output end in control portion controls end with the air pressure of electromagnetic proportional valve and is connected；The n way switch instruction output end in control portion connects one to one with the control end of n electromagnetic valve respectively；Wherein: n=2 ~ 6.
Description
Technical field
The present invention relates to the load charger of a kind of wing, belong to wing strength test technical field.
Background technology
Wing is one of indispensable parts of aircraft, before wing enters application, it is necessary to it is carried out the experiment such as intensity, fatigue, is used for measuring intensity and the fatigue strength of wing.At present, load for wing that what employ up to is hydraulic system, the advantage of hydraulic system is in that the accuracy of its imposed load, the quality of one hydraulic system depends on the quality of reasonability that system designs, system element performance, and must carry out systematically polluting protection and processing, and this point is particularly important.Therefore, adopt hydraulic system to wing imposed load complicated operation, not there is portability.
Summary of the invention
The invention aims to solve to adopt hydraulic system to wing imposed load complicated operation, the problem without portability, it is provided that a kind of wing aerodynamic charger.
Wing aerodynamic charger of the present invention, it includes air pump, electromagnetic proportional valve, clematis stem gas-tpe fitting, n electromagnetic valve, n cylinder and control portion；
The gas outlet of air pump connects with the air intake of electromagnetic proportional valve, the gas outlet of electromagnetic proportional valve connects with the air intake of clematis stem gas-tpe fitting, n gas outlet of clematis stem gas-tpe fitting connects with the air intake one_to_one corresponding of n electromagnetic valve respectively, and the gas outlet of any one electromagnetic valve connects with the air intake of a cylinder；
The air pressure instruction output end in control portion controls end with the air pressure of electromagnetic proportional valve and is connected；
The n way switch instruction output end in control portion connects one to one with the control end of n electromagnetic valve respectively；
Wherein: n=2 ~ 6.
Advantages of the present invention: the wing aerodynamic charger of the present invention maximum advantage of hydraulic system of comparing is in that its portability and is easy to operability.Instruction is sent by computer, switch by Micro Controller Unit (MCU) driving multipath electrovalve, and then control whether each road cylinder exports gas, and the size of cylinder power output, can ensure that wing is when deformation by pneumatic pressurizing system of the present invention, it is ensured that power and the moment of flexure of the required loading of wing can be met.
Accompanying drawing explanation
Fig. 1 is the structural representation of wing aerodynamic charger of the present invention；
Fig. 2 is the control principle drawing of wing aerodynamic charger of the present invention.
Detailed description of the invention
Detailed description of the invention one: present embodiment is described below in conjunction with Fig. 1 and Fig. 2, wing aerodynamic charger described in present embodiment, it includes air pump 1, electromagnetic proportional valve 2, clematis stem gas-tpe fitting 3, n electromagnetic valve 5, n cylinder 8 and control portion 9；
The gas outlet of air pump 1 connects with the air intake of electromagnetic proportional valve 2, the gas outlet of electromagnetic proportional valve 2 connects with the air intake of clematis stem gas-tpe fitting 3, n gas outlet of clematis stem gas-tpe fitting 3 connects with the air intake one_to_one corresponding of n electromagnetic valve 5 respectively, and the gas outlet of any one electromagnetic valve 5 connects with the air intake of a cylinder 8；
The air pressure instruction output end in control portion 9 controls end with the air pressure of electromagnetic proportional valve 2 and is connected；
The n way switch instruction output end in control portion 9 connects one to one with the control end of n electromagnetic valve 5 respectively；
Wherein: n=2 ~ 6.
Control portion 9 includes computer 901 and single-chip microcomputer 902, and the instruction output end of computer 901 is connected with the command input of single-chip microcomputer 902, and the air pressure instruction output end of single-chip microcomputer 902 controls end with the air pressure of electromagnetic proportional valve 2 and is connected；
The n way switch instruction output end of single-chip microcomputer 902 connects one to one with the control end of n electromagnetic valve 5 respectively.
Operation principle: the diverse location of the position correspondence wing of n cylinder 8 gas outlet, the control that present embodiment realizes is whether diverse location cylinder 8 exports gas, and the size of output gas pressure, and then better carry out ionization meter and the fatigue strength measurement of wing.By given experiment parameter, it is possible to realize loading predetermined power and moment of flexure.
Computer 901 arranges relevant instruction, instruction includes two parts, a part is that computer 901 can pass through single-chip microcomputer 902 and control the switch of arbitrarily one or more electromagnetic valves 5, and then controls whether one or more cylinders 8 export gas to the switch order of n electromagnetic valve 5；Another part is to the air pressure instruction of electromagnetic proportional valve 2, computer 901 controls electromagnetic proportional valve 2 by single-chip microcomputer 902, the gas of air pump 1 exports to n cylinder 8 by electromagnetic proportional valve 2, change the ratio of electromagnetic proportional valve 2, just can control the size of gas pressure, self bear the relatively different of pressure as n cylinder 8, controlled by the barrel dliameter size of himself.
Detailed description of the invention two: embodiment one is described further by present embodiment, it also includes display 4, and the air pressure idsplay order outfan of electromagnetic proportional valve 2 is connected with the display signal input part of display 4.
The gas of air pump 1 output is after electromagnetic proportional valve 2 regulates, by its gas pressure of display 4.
Detailed description of the invention three: embodiment one or two is described further by present embodiment, it also includes n Quick air-discharge ball valve 6 and n deafener 7；Between each electromagnetic valve 5 and a cylinder 8, a Quick air-discharge ball valve 6 is set, 1 mouthful of the gas outlet of electromagnetic valve 5 and Quick air-discharge ball valve 6 is connected, 2 mouthfuls of Quick air-discharge ball valve 6 are connected with the air intake of cylinder 8, and 3 mouthfuls of Quick air-discharge ball valve 6 arrange a deafener 7.
N Quick air-discharge ball valve 6 is the Redundancy Design of electromagnetic proportional valve, when electromagnetic proportional valve 2 lost efficacy, can adjust the air pressure size of this gas circuit by regulating Quick air-discharge ball valve 6.
After experiment terminates, in cylinder 8 by Quick air-discharge ball valve 6, fall through deafener 7 quick drain.
Claims (2)
1. wing aerodynamic charger, it is characterised in that it includes air pump (1), electromagnetic proportional valve (2), clematis stem gas-tpe fitting (3), n electromagnetic valve (5), n cylinder (8) and control portion (9)；
The gas outlet of air pump (1) connects with the air intake of electromagnetic proportional valve (2), the gas outlet of electromagnetic proportional valve (2) connects with the air intake of clematis stem gas-tpe fitting (3), n gas outlet of clematis stem gas-tpe fitting (3) connects with the air intake one_to_one corresponding of n electromagnetic valve (5) respectively, and the gas outlet of any one electromagnetic valve (5) connects with the air intake of a cylinder (8)；
The air pressure instruction output end in control portion (9) controls end with the air pressure of electromagnetic proportional valve (2) and is connected；
The n way switch instruction output end in control portion (9) connects one to one with the control end of n electromagnetic valve (5) respectively；
Wherein: n=2 ~ 6；
It also includes n Quick air-discharge ball valve (6) and n deafener (7)；One Quick air-discharge ball valve (6) is set between each electromagnetic valve (5) and a cylinder (8), 1 mouthful of the gas outlet of electromagnetic valve (5) and Quick air-discharge ball valve (6) is connected, 2 mouthfuls of Quick air-discharge ball valve (6) are connected with the air intake of cylinder (8), and 3 mouthfuls of Quick air-discharge ball valve (6) arrange a deafener (7).
2. wing aerodynamic charger according to claim 1, it is characterised in that it also includes display (4), and the air pressure idsplay order outfan of electromagnetic proportional valve (2) is connected with the display signal input part of display (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410080097.1A CN103792083B (en) | 2014-03-06 | 2014-03-06 | Wing aerodynamic charger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410080097.1A CN103792083B (en) | 2014-03-06 | 2014-03-06 | Wing aerodynamic charger |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103792083A CN103792083A (en) | 2014-05-14 |
| CN103792083B true CN103792083B (en) | 2016-07-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410080097.1A Active CN103792083B (en) | 2014-03-06 | 2014-03-06 | Wing aerodynamic charger |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105015802A (en) * | 2015-07-21 | 2015-11-04 | 哈尔滨工业大学 | Pneumatic wing loading device |
| CN109932196A (en) * | 2019-03-13 | 2019-06-25 | 浙江大学城市学院 | A kind of pneumatic loading system of portable simulation Subway Train Operation in Existed Subway |
| CN110195821B (en) * | 2019-05-09 | 2021-05-07 | 中国飞机强度研究所 | Hydraulic substation and electromagnetic valve control device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004065926A1 (en) * | 2003-01-23 | 2004-08-05 | William Marsh Rice University | Smart materials: strain sensing and stress determination by means of nanotube sensing systems, composites, and devices |
| CN1818599A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Apparatus for testing fatigue strength of axial hinge bearing of helicopter |
| CN201503355U (en) * | 2009-09-27 | 2010-06-09 | 北汽福田汽车股份有限公司 | Accelerator pedal durability test device |
| JP5160489B2 (en) * | 2009-03-25 | 2013-03-13 | 住友金属テクノロジー株式会社 | High pressure material strength test equipment |
| CN103411784A (en) * | 2013-08-05 | 2013-11-27 | 浙江省泵阀产品质量检验中心 | Linear valve pneumatic actuator testing device |
-
2014
- 2014-03-06 CN CN201410080097.1A patent/CN103792083B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004065926A1 (en) * | 2003-01-23 | 2004-08-05 | William Marsh Rice University | Smart materials: strain sensing and stress determination by means of nanotube sensing systems, composites, and devices |
| CN1818599A (en) * | 2006-03-17 | 2006-08-16 | 燕山大学 | Apparatus for testing fatigue strength of axial hinge bearing of helicopter |
| JP5160489B2 (en) * | 2009-03-25 | 2013-03-13 | 住友金属テクノロジー株式会社 | High pressure material strength test equipment |
| CN201503355U (en) * | 2009-09-27 | 2010-06-09 | 北汽福田汽车股份有限公司 | Accelerator pedal durability test device |
| CN103411784A (en) * | 2013-08-05 | 2013-11-27 | 浙江省泵阀产品质量检验中心 | Linear valve pneumatic actuator testing device |
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| CN103792083A (en) | 2014-05-14 |
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Effective date of registration: 20170410 Address after: 150028 Heilongjiang province high tech Industrial Development Zone, Harbin City, science and technology innovation city enterprise accelerator building, No. 12, wisdom Valley, No. two street, unit 1, layer 4058 Patentee after: Harbin science and Technology Co., Ltd. Address before: 150000 Harbin, Nangang, West District, large straight street, No. 92 Patentee before: Harbin Institute of Technology |
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Effective date of registration: 20170509 Address after: Room D710, Shenzhen Institute of aerospace technology No. 6 building, 518054 Guangdong city of Shenzhen province Nanshan District Guangdong streets Science Park, ten South Road Patentee after: Shenzhen innovation Advanced Material Research Institute Co Ltd Address before: 150028 Heilongjiang province high tech Industrial Development Zone, Harbin City, science and technology innovation city enterprise accelerator building, No. 12, wisdom Valley, No. two street, unit 1, layer 4058 Patentee before: Harbin science and Technology Co., Ltd. |
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