CN104122050A - Dynamic pressure and static pressure testing device of helicopter distributed atmospheric engine - Google Patents
Dynamic pressure and static pressure testing device of helicopter distributed atmospheric engine Download PDFInfo
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- CN104122050A CN104122050A CN201310145003.XA CN201310145003A CN104122050A CN 104122050 A CN104122050 A CN 104122050A CN 201310145003 A CN201310145003 A CN 201310145003A CN 104122050 A CN104122050 A CN 104122050A
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Abstract
The invention, which belongs to the field of airplane equipment testing, relates to a dynamic pressure and static pressure testing device of a helicopter distributed atmospheric engine. The testing device consisting of a hand pump, a hand-operated direction valve, a static pressure pipeline, dynamic pressure pipeline, an airspeed indicator and a vertical speed indicator is characterized in that the testing device also includes a gas detection fixture and a flexible pipe. Quick-disassembling sockets with one-way valves are respectively installed at the static pressure pipeline outlet and the dynamic pressure pipeline outlet; quick-disassembling plugs with one-way valves are installed at two static pressure interfaces and a dynamic pressure interface of the a gas detection fixture. A quick-disassembling plug and a quick-disassembling socket are installed at the two ends of the flexible pipe; and the static pressure pipeline and the dynamic pressure pipeline are connected with the gas detection fixture by the flexible pipe. According to the invention, the testing device has high universality; and the connecting assembly arranged outside the device can be stored inside the main device body after being disassembled, so that the testing device has the simple and beautiful appearance.
Description
Technical field
The invention belongs to airplane equipment field tests, relate to the distributed atmospheric engine dynamic and static pressure of a kind of helicopter testing apparatus.
Background technology
The distributed atmospheric engine dynamic and static pressure of traditional helicopter testing apparatus element is relatively backward, is not easy to operation.In the time carrying out pitot-static pressure pipeline air-tight test, due to the pitot interface size difference of each model helicopter, be furnished with respectively special dynamic and static pressure testing equipment, increase production cost, extend the lead time of this test unit, versatility is poor.
Simultaneously, the dynamic and static pressure pipeline outlet of the distributed atmospheric engine dynamic and static pressure of traditional helicopter testing apparatus has connected respectively a non-removable flexible pipe, due to the distributed atmospheric engine of helicopter and ground distance larger, this flexible pipe is about 10 meters, after test, this flexible pipe is exposed to testing apparatus outside, be unfavorable for equipment to deposit and be exposed to outer flexible pipe very easily damaged, do not meet our requirement attractive in appearance for modern testing apparatus simultaneously.There is the dismounting of being not easy to, inaesthetic shortcoming.
Summary of the invention
Technical matters to be solved by this invention is: the distributed atmospheric engine dynamic and static pressure of helicopter that a kind of convenient disassembly is quick, versatility is good testing apparatus is provided.
Technical scheme of the present invention is: the distributed atmospheric engine dynamic and static pressure of a kind of helicopter testing apparatus, comprise wobble pump, hand-operated direction valve, static line, dynamic pressure pipeline, airspeed indicator and climb meter, it is characterized by: described testing apparatus also comprises gas inspection fixture and flexible pipe; Described static line outlet is equipped with the outlet of dynamic pressure pipeline the quick-release socket with retaining valve is housed respectively; On two static pressure interfaces of described gas inspection fixture and a dynamic pressure interface, the quick-release plug with retaining valve is all housed; Quick-release plug and quick-release socket are equipped with in described flexible pipe two ends; Static line is connected with gas inspection fixture by flexible pipe with dynamic pressure pipeline.
Further, between described wobble pump and hand-operated direction valve, connect by quick-release plugs and sockets.
The invention has the beneficial effects as follows: the structure that the distributed atmospheric engine dynamic and static pressure of helicopter of the present invention testing apparatus adopts quick-release type socket and plug to coordinate in dynamic and static pressure pipeline exit, realize device external coupling assembling and equipment body part convenient disassembly is quick, can change when being necessary the gas inspection fixture in external module, have stronger versatility; And after the dismounting of the coupling assembling of device external, can leave equipment body inside in, make this testing apparatus outward appearance succinct, attractive in appearance.
Brief description of the drawings
Fig. 1 is the structural representation of the distributed atmospheric engine dynamic and static pressure of helicopter of the present invention testing apparatus;
Fig. 2 is gas inspection fixture dynamic and static pressure interface schematic diagram in the present invention;
Fig. 3 is the distributed atmospheric engine static line of helicopter schematic diagram;
Wherein, 1-wobble pump, 2-quick-release plugs and sockets, 3-hand-operated direction valve, 4-airspeed indicator, 5-climb meter, the outlet of 6-static line, 7-dynamic pressure tube way outlet, 8-quick-release plug, 9-flexible pipe, 10 quick-release sockets, 11-gas inspection fixture, 12 dynamic pressure interfaces (Pt), 13-static pressure interface (Ps1), 14-static pressure interface (Ps2).
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described further.
Referring to Fig. 1, the distributed atmospheric engine dynamic and static pressure of helicopter testing apparatus is the impermeability for checking the distributed atmospheric engine static line of helicopter and dynamic pressure pipeline, comprises wobble pump 1, quick-release plugs and sockets 2, hand-operated direction valve 3, airspeed indicator 4, climb meter 5, static line outlet 6, dynamic pressure tube way outlet 7, quick-release plug 8, flexible pipe 9, quick-release socket 10, gas inspection fixture 11; Wobble pump 1 provides test required static pressure and dynamic pressure, if the one-way trip of wobble pump cannot meet the required force value of test, utilizes quick-release plugs and sockets 2 to realize wobble pump 1 continuous operation work pressure is provided; Described quick-release plugs and sockets 2 is the quick-release sockets with retaining valve and is not used in conjunction with the quick-release plug of retaining valve, in the time that the quick-release plug of quick-release plugs and sockets 2 separates with socket, can continue to keep the pressure in pipeline with the quick-release socket of retaining valve, and the quick-release plug with retaining valve can not communicate with atmosphere, at this moment wobble pump backstroke starting point, connect quick-release plugs and sockets 2, second stroke of wobble pump continuation continues as pipeline provides pressure again; Hand-operated direction valve 3 is realized freely switching of static line and dynamic pressure pipeline; When static line air-tight test, must in testing equipment pipeline, be incorporated to an airspeed indicator 4 and a climb meter 5 as monitoring device; When dynamic pressure pipeline air-tight test, must be incorporated to an airspeed indicator 4; Static line outlet 6 and dynamic pressure tube way outlet 7 are equipped with respectively the quick-release socket with retaining valve;
Referring to Fig. 2, Fig. 3, the distributed atmospheric engine of helicopter comprises left distributed atmospheric engine and right distributed atmospheric engine; In the time carrying out static line air-tight test, one end quick-release plug 8 of flexible pipe 9 is connected with above-mentioned static line outlet 6, and the other end quick-release socket 10 of flexible pipe 9 is connected with the static pressure interface (Ps1) 13 of gas inspection fixture 11; Gas inspection fixture 11 is connected with left distributed atmospheric engine, blocks the Ps2 interface of right distributed atmospheric engine simultaneously; In like manner, flexible pipe 9 other end quick-release sockets 10 are connected with the static pressure interface (Ps2) 14 of gas inspection fixture 11, and gas inspection fixture 11 is connected with left distributed atmospheric engine, blocks the Ps1 interface of right distributed atmospheric engine simultaneously.
In the time carrying out dynamic pressure pipeline air-tight test, one end quick-release plug 8 of flexible pipe 9 is connected with above-mentioned dynamic pressure tube way outlet 7, and the other end quick-release socket 10 of flexible pipe 9 is connected with the dynamic pressure interface (Pt) 12 of gas inspection fixture 11; Gas inspection fixture 11 is connected with left distributed atmospheric engine, blocks the Pt interface of right distributed atmospheric engine simultaneously.
Claims (2)
1. the distributed atmospheric engine dynamic and static pressure of a helicopter testing apparatus, comprises wobble pump, hand-operated direction valve, static line, dynamic pressure pipeline, airspeed indicator and climb meter, it is characterized by: described testing apparatus also comprises gas inspection fixture and flexible pipe; Described static line outlet is equipped with the outlet of dynamic pressure pipeline the quick-release socket with retaining valve is housed respectively; On two static pressure interfaces of described gas inspection fixture and a dynamic pressure interface, the quick-release plug with retaining valve is all housed; Quick-release plug and quick-release socket are equipped with in described flexible pipe two ends; Static line is connected with gas inspection fixture by flexible pipe with dynamic pressure pipeline.
2. the distributed atmospheric engine dynamic and static pressure of helicopter according to claim 1 testing apparatus, is further characterized in that: between described wobble pump and hand-operated direction valve, connect by quick-release plugs and sockets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310145003.XA CN104122050A (en) | 2013-04-24 | 2013-04-24 | Dynamic pressure and static pressure testing device of helicopter distributed atmospheric engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310145003.XA CN104122050A (en) | 2013-04-24 | 2013-04-24 | Dynamic pressure and static pressure testing device of helicopter distributed atmospheric engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104122050A true CN104122050A (en) | 2014-10-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310145003.XA Pending CN104122050A (en) | 2013-04-24 | 2013-04-24 | Dynamic pressure and static pressure testing device of helicopter distributed atmospheric engine |
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| CN (1) | CN104122050A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105425767A (en) * | 2015-11-04 | 2016-03-23 | 中国直升机设计研究所 | Method of maintenance equipment for automatically identifying different helicopter types to be tested |
| CN106197857A (en) * | 2015-05-07 | 2016-12-07 | 哈尔滨飞机工业集团有限责任公司 | A kind of helicopter pitot-static pressure gas-tight test |
| CN106969879A (en) * | 2016-01-13 | 2017-07-21 | 哈尔滨飞机工业集团有限责任公司 | A kind of dynamic and static pressure exerciser |
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| CN202101830U (en) * | 2011-06-02 | 2012-01-04 | 广东省韶关钢铁集团有限公司 | Mobile hydraulic oil cylinder leak tester |
| CN202547909U (en) * | 2012-02-28 | 2012-11-21 | 西斐（上海）工业控制有限公司 | Valve piping system test system |
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| CN2276091Y (en) * | 1996-06-25 | 1998-03-11 | 北京市海淀区中航机电研究所 | Portable hand pressure vacuum signal generator |
| CN2525499Y (en) * | 2001-09-18 | 2002-12-11 | 景博 | Pressure measurer |
| KR20100040367A (en) * | 2008-10-10 | 2010-04-20 | 삼성중공업 주식회사 | Pressure test apparatus and method for corrugated membrane |
| CN201540190U (en) * | 2009-08-11 | 2010-08-04 | 张力诚 | Improved detection device |
| CN201993208U (en) * | 2010-12-14 | 2011-09-28 | 南车南京浦镇车辆有限公司 | Bogie pipeline pressure-maintaining testing device |
| CN202101830U (en) * | 2011-06-02 | 2012-01-04 | 广东省韶关钢铁集团有限公司 | Mobile hydraulic oil cylinder leak tester |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106197857A (en) * | 2015-05-07 | 2016-12-07 | 哈尔滨飞机工业集团有限责任公司 | A kind of helicopter pitot-static pressure gas-tight test |
| CN105425767A (en) * | 2015-11-04 | 2016-03-23 | 中国直升机设计研究所 | Method of maintenance equipment for automatically identifying different helicopter types to be tested |
| CN105425767B (en) * | 2015-11-04 | 2018-05-18 | 中国直升机设计研究所 | A kind of method of the different types to be measured of maintained equipment automatic identification |
| CN106969879A (en) * | 2016-01-13 | 2017-07-21 | 哈尔滨飞机工业集团有限责任公司 | A kind of dynamic and static pressure exerciser |
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Application publication date: 20141029 |