CN105015802A - Pneumatic wing loading device - Google Patents
Pneumatic wing loading device Download PDFInfo
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- CN105015802A CN105015802A CN201510430582.1A CN201510430582A CN105015802A CN 105015802 A CN105015802 A CN 105015802A CN 201510430582 A CN201510430582 A CN 201510430582A CN 105015802 A CN105015802 A CN 105015802A
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Abstract
The invention provides a pneumatic wing loading device, which belongs to the technical field of wing strength tests. The pneumatic wing loading device provided by the invention is designed to solve problems that it is complicated in operation by using a hydraulic system to apply a load to a wing and the hydraulic system is not portable. The pneumatic wing loading device comprises an air pump, an electromagnetic proportional valve, a multi-way pipe joint, n electromagnetic valves, n cylinders and a control part, wherein an air outlet of the air pump is communicated with an air inlet of the electromagnetic proportional valve; an air outlet of the electromagnetic proportional valve is communicated with an air inlet of the multi-way pipe joint; n air outlets of the multi-way pipe joint are communicated with air inlets of the n electromagnetic valves in a one-to-one corresponding way, respectively; an air outlet of any electromagnetic valve is communicated with an air inlet of one cylinder; a pressure instruction output end of the control part is connected with a pressure control end of the electromagnetic proportional valve; and n switch instruction output ends of the control part are connected with control ends of the n electromagnetic valves in a one-to-one corresponding way, respectively, wherein n is a natural number which is not less than 2.
Description
Technical field
The present invention relates to a kind of load charger of wing, belong to wing strength test technical field.
Background technology
Wing is one of indispensable parts of aircraft, before wing enters application, needs to carry out the experiment such as intensity, fatigue to it, is used for measuring the intensity of wing and strength at repeated alternation.At present, load for wing that to use maximum be hydraulic efficiency pressure system, the advantage of hydraulic efficiency pressure system is the accuracy of its applied load, the quality of a hydraulic efficiency pressure system depends on the reasonableness of system, the quality of system element performance, and systematically must pollute protection and process, and this point is particularly important.Therefore, adopt hydraulic efficiency pressure system to wing applied load complicated operation, not there is portability.
Summary of the invention
The present invention seeks to adopt hydraulic efficiency pressure system to wing applied load complicated operation to solve, not there is the problem of portability, provide a kind of wing aerodynamic force-input device.
Wing aerodynamic force-input device of the present invention, it comprises air pump, electromagnetic proportional valve, many connection for breather pipes, a n electromagnetic valve, a n cylinder and control part;
The air extractor duct of air pump is communicated with the air intake of electromagnetic proportional valve, the air extractor duct of electromagnetic proportional valve is communicated with the air intake of many connection for breather pipes, n air extractor duct of many connection for breather pipes is communicated with the air intake one_to_one corresponding of n electromagnetic valve respectively, and the air extractor duct of any one electromagnetic valve is communicated with the air intake of a cylinder;
The air pressure instruction output end of control part is connected with the air pressure control end of electromagnetic proportional valve;
The n way switch instruction output end of control part connects one to one with the control end of n electromagnetic valve respectively;
Wherein: n be more than or equal to 2 natural number.
Advantage of the present invention: the wing aerodynamic force-input device of the present invention maximum advantage of hydraulic efficiency pressure system of comparing is its portability and convenient operation.Instruction is sent by computing machine, by the switch of Micro Controller Unit (MCU) driving multipath electrovalve, and then control each road cylinder and whether export gas, and the size of cylinder power output, can ensure that wing is under the condition of distortion by pneumatic pressurizing system of the present invention, ensure power and the moment of flexure that can meet the required loading of wing.
Accompanying drawing explanation
Fig. 1 is the structural representation of wing aerodynamic force-input device of the present invention;
Fig. 2 is the control principle drawing of wing aerodynamic force-input device 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 force-input device described in present embodiment, it comprises air pump 1, electromagnetic proportional valve 2, many connection for breather pipes 3, a n electromagnetic valve 5, a n cylinder 8 and control part 9;
The air extractor duct of air pump 1 is communicated with the air intake of electromagnetic proportional valve 2, the air extractor duct of electromagnetic proportional valve 2 is communicated with the air intake of many connection for breather pipes 3, n air extractor duct of many connection for breather pipes 3 is communicated with the air intake one_to_one corresponding of n electromagnetic valve 5 respectively, and the air extractor duct of any one electromagnetic valve 5 is communicated with the air intake of a cylinder 8;
The air pressure instruction output end of control part 9 is connected with the air pressure control end of electromagnetic proportional valve 2;
The n way switch instruction output end of control part 9 connects one to one with the control end of n electromagnetic valve 5 respectively;
Wherein: n be more than or equal to 2 natural number.
Control part 9 comprises computing machine 901 and micro controller system 902, and the instruction output end of computing machine 901 is connected with the instruction output end of micro controller system 902, and the air pressure instruction output end of micro controller system 902 is connected with the air pressure control end of electromagnetic proportional valve 2;
The n way switch instruction output end of micro controller system 902 connects one to one with the control end of n electromagnetic valve 5 respectively.
The diverse location of the corresponding wing in position of principle of work: a n cylinder 8 air extractor duct, 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 strength at repeated alternation measurement of wing.By given experiment parameter, just can realize loading predetermined power and moment of flexure.
In computing machine 901, relevant instruction is set, instruction comprises two parts, a part is to the switch order of n electromagnetic valve 5, and computing machine 901 can control the switch of arbitrarily one or more electromagnetic valves 5 by micro controller system 902, and then controls one or more cylinders 8 and whether export gas; Another part is to the air pressure instruction of electromagnetic proportional valve 2, computing machine 901 controls electromagnetic proportional valve 2 by micro controller system 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 gaseous tension, self bear the relatively different of pressure as n cylinder 8, controlled by the barrel dliameter size of himself.
For n=6, many connection for breather pipes 3 are six connection for breather pipes, and a joint is used for air inlet, and other five joints are for connecting five electromagnetic valves 5.
Detailed description of the invention two: present embodiment is described further embodiment one, it also comprises telltale 4, and the air pressure idsplay order mouth of electromagnetic proportional valve 2 is connected with the display input end of telltale 4.
Air pump 1 export gas through electromagnetic proportional valve 2 regulate after, by its gaseous tension of telltale 4.
Detailed description of the invention three: present embodiment is described further embodiment one or two, it also comprises n Quick air-discharge ball valve 6 and n silencer 7; Between each electromagnetic valve 5 and a cylinder 8, a Quick air-discharge ball valve 6 is set, the air extractor duct of electromagnetic valve 5 is connected with 1 mouthful of Quick air-discharge ball valve 6,2 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 silencer 7.
N Quick air-discharge ball valve 6 is Redundancy Design of electromagnetic proportional valve, when electromagnetic proportional valve 2 lost efficacy, by the air pressure size regulating Quick air-discharge ball valve 6 to adjust this gas circuit.
After experiment terminates, in cylinder 8 by Quick air-discharge ball valve 6, fall through silencer 7 quick drain.
Claims (4)
1. wing aerodynamic force-input device, it is characterized in that, it comprises air pump (1), electromagnetic proportional valve (2), many connection for breather pipes (3), a n electromagnetic valve (5), a n cylinder (8) and control part (9);
The air extractor duct of air pump (1) is communicated with the air intake of electromagnetic proportional valve (2), the air extractor duct of electromagnetic proportional valve (2) is communicated with the air intake of many connection for breather pipes (3), n air extractor duct of many connection for breather pipes (3) is communicated with the air intake one_to_one corresponding of n electromagnetic valve (5) respectively, and the air extractor duct of any one electromagnetic valve (5) is communicated with the air intake of a cylinder (8);
The air pressure instruction output end of control part (9) is connected with the air pressure control end of electromagnetic proportional valve (2);
The n way switch instruction output end of control part (9) connects one to one with the control end of n electromagnetic valve (5) respectively;
Wherein: n be more than or equal to 2 natural number.
2. wing aerodynamic force-input device according to claim 1, it is characterized in that, control part (9) comprises computing machine (901) and micro controller system (902), the instruction output end of computing machine (901) is connected with the instruction output end of micro controller system (902), and the air pressure instruction output end of micro controller system (902) is connected with the air pressure control end of electromagnetic proportional valve (2);
The n way switch instruction output end of micro controller system (902) connects one to one with the control end of n electromagnetic valve (5) respectively.
3. wing aerodynamic force-input device according to claim 1 or 2, it is characterized in that, it also comprises telltale (4), and the air pressure idsplay order mouth of electromagnetic proportional valve (2) is connected with the display input end of telltale (4).
4. wing aerodynamic force-input device according to claim 1 or 2, is characterized in that, it also comprises n Quick air-discharge ball valve (6) and n silencer (7); A Quick air-discharge ball valve (6) is set between each electromagnetic valve (5) and a cylinder (8), the air extractor duct of electromagnetic valve (5) is connected with 1 mouthful of Quick air-discharge ball valve (6), 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 silencer (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510430582.1A CN105015802A (en) | 2015-07-21 | 2015-07-21 | Pneumatic wing loading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510430582.1A CN105015802A (en) | 2015-07-21 | 2015-07-21 | Pneumatic wing loading device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105015802A true CN105015802A (en) | 2015-11-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510430582.1A Pending CN105015802A (en) | 2015-07-21 | 2015-07-21 | Pneumatic wing loading device |
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| CN (1) | CN105015802A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN114633900A (en) * | 2022-05-20 | 2022-06-17 | 中国飞机强度研究所 | Large-stroke aircraft airfoil static loading system and method for aircraft strength test |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4651927A (en) * | 1983-03-21 | 1987-03-24 | Godtfred Vestergaard | Plant for de-icing surfaces |
| CN103792083A (en) * | 2014-03-06 | 2014-05-14 | 哈尔滨工业大学 | Wing pneumatic loading device |
-
2015
- 2015-07-21 CN CN201510430582.1A patent/CN105015802A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4651927A (en) * | 1983-03-21 | 1987-03-24 | Godtfred Vestergaard | Plant for de-icing surfaces |
| CN103792083A (en) * | 2014-03-06 | 2014-05-14 | 哈尔滨工业大学 | Wing pneumatic loading device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN114633900A (en) * | 2022-05-20 | 2022-06-17 | 中国飞机强度研究所 | Large-stroke aircraft airfoil static loading system and method for aircraft strength test |
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Application publication date: 20151104 |