CN104764619A - Connector for helicopter static pressure test - Google Patents
Connector for helicopter static pressure test Download PDFInfo
- Publication number
- CN104764619A CN104764619A CN201510161265.4A CN201510161265A CN104764619A CN 104764619 A CN104764619 A CN 104764619A CN 201510161265 A CN201510161265 A CN 201510161265A CN 104764619 A CN104764619 A CN 104764619A
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- China
- Prior art keywords
- pipeline
- sucker
- static pressure
- suction cup
- helicopter
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- 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.)
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- Quick-Acting Or Multi-Walled Pipe Joints (AREA)
- Compressors, Vaccum Pumps And Other Relevant Systems (AREA)
Abstract
The invention provides a connector for a helicopter static pressure test. The connector is simple in structure and convenient to use. A connector body is a suction cup. Two through holes are formed in the suction cup. A pipeline penetrates through the suction cup through one through hole and is connected with the suction cup is an airtight mode. The pipeline is connected with a vacuum pump. The pipeline penetrates through the suction cup through the other through hole and is connected with the suction cup in an airtight mode. When the suction cup is in a negative-pressure state and connected with a skin of a helicopter body in an airtight mode, the free end, in the concave face of the suction cup, of the pipeline is connected with a helicopter body static pressure hole in an airtight mode. According to the connector, the suction cup is used for replacing plasticine used in the prior art for sealing, in this way, work efficiency is improved, personal errors are reduced, and the testing precision is improved.
Description
Technical field
The present invention relates to a kind of helicopter static pressure test connector.
Background technology
Be external to testing apparatus by baroport by pipeline to carry out testing or air-tight test during helicopter static pressure (highly) test, connection between helicopter baroport and external pipeline is adopt plasticine to seal at present, sealing effectiveness can not be guaranteed, randomness is too large, rely on the experience of operating personnel completely, and plasticine viscosity affects larger by environment temperature etc., result of use is not good, being finished rear plasticine can be bonded on baroport periphery body, sometimes even can block baroport, the cleaning work after using also takes time and effort.
Summary of the invention
The technical problem to be solved in the present invention: the invention provides the helicopter static pressure test connector that a kind of structure is simple, easy to use.
Technical scheme of the present invention: a kind of helicopter static pressure test connector, its main body is sucker, sucker has two through holes;
Pipeline passes described sucker through one of them through hole, and and for being tightly connected between described sucker, described pipeline is connected with vacuum pump,
Pipeline passes described sucker through another one through hole, and and for being tightly connected between described sucker;
When described sucker is in negative pressure state and is tightly connected with fuselage skin, the free end and the fuselage baroport that are positioned at the described pipeline of described sucker concave surface are tightly connected.
Further optimization, the cross sectional shape being positioned at the free end of the described pipeline of described sucker concave surface is taper, and in described pipeline, at least described free end is quality of rubber materials.
Further optimization, the cross sectional shape being positioned at the free end of the described pipeline of described sucker concave surface is round table-like, and in described pipeline, at least described free end is quality of rubber materials.
Further optimization, one end that described pipeline and pipeline are positioned at described sucker outside is all provided with unidirectional stop valve.
Further optimization, described pipeline adopts with described interambulacrum and is threaded, and one end that described pipeline is positioned at described sucker outside is provided with handle or knob, and when swing handle or knob, pipeline can relative to sucker to-and-fro movement.
Beneficial effect of the present invention: the present invention adopt sucker instead of before use plasticine seal, improve work efficiency, decrease personal error, improve measuring accuracy; Additionally by one end mounting knob or the knob of the pipeline in sucker outside, make more convenient to operate, bond tightr; The present invention can be applicable to complex environment more, such as, when manual operation inconvenience, improves the security of test job.
Accompanying drawing explanation
Fig. 1 is the structural representation of the first embodiment of the helicopter static pressure test connector that the present invention proposes;
Fig. 2 is the cut-open view of the first embodiment of the helicopter static pressure test connector that the present invention proposes;
Fig. 3 is the structural representation of the second embodiment of the helicopter static pressure test connector that the present invention proposes;
Fig. 4 is the cut-open view of the second embodiment of the helicopter static pressure test connector that the present invention proposes.
Embodiment
Embodiment 1:
From Fig. 1 and Fig. 2, a kind of helicopter static pressure test connector that the present invention proposes, its main body is sucker 3, sucker 3 has two through holes; One of them hole is logical can be connected with vacuum pump by pipeline 1, to be used for making sucker 3 inside be in negative pressure state.Particularly, pipeline 1 passes sucker 3 through above-mentioned through hole, and and for being tightly connected between sucker 3.
The present invention also comprises pipeline 2, is used for connecting test instrument, pipeline 2 through another one through hole by pass sucker 3 and and for being tightly connected between sucker 3; The pipeline 2 be positioned at inside sucker 3 concave surface should have certain length, with ensure when use vacuum pump by the road 1 sucker 3 taken out negative pressure and sucker 3 is tightly connected with fuselage skin time, the free end of this part pipeline 2 also keeps being tightly connected with fuselage baroport.
The present invention adopt sucker 3 instead of before the plasticine that uses seal, sucker 3 is by vacuum pump automatic absorbing, and the bonding mode before breaching, improves work efficiency, decreases personal error, improves measuring accuracy.Additionally by one end mounting knob or the knob of the pipeline 2 in sucker 3 outside, make more convenient to operate, bond tightr.Further, the present invention is applicable to complex environment more, such as, when manual operation inconvenience, improves the security of test job.
The cross sectional shape being positioned at the free end of the pipeline 2 inside sucker 3 concave surface is taper (especially as shown in Figure 2), and, in pipeline 2, at least cross sectional shape is this part (i.e. the free end of pipeline 2) of taper is quality of rubber materials, such design makes pipeline 2 can realize being sealed and matched with the aircraft static pressure hole of different size, extends usable range of the present invention.
One end that pipeline 1 and pipeline 2 are positioned at sucker 3 outside is all provided with unidirectional stop valve 4 to facilitate control and to make more convenient to operate.
Adopt between pipeline 2 with sucker 3 and be threaded, one end that pipeline 2 is positioned at sucker 3 outside is provided with handle or knob, and when swing handle or knob, pipeline 2 can move reciprocatingly vertically relative to sucker 3, ensure that pipeline 2 is more tight with the connection of helicopter baroport, Leakage prevention.
Embodiment 2:
From Fig. 3 and Fig. 4, a kind of helicopter static pressure test connector that the present invention proposes, its main body is sucker 3, sucker 3 has two through holes; One of them hole is logical can be connected with vacuum pump by pipeline 1, to be used for making sucker 3 inside be in negative pressure state.Particularly, pipeline 1 passes sucker 3 through above-mentioned through hole, and and for being tightly connected between sucker 3.
The present invention also comprises pipeline 2, is used for connecting test instrument, pipeline 2 through another one through hole by pass sucker 3 and and for being tightly connected between sucker 3; The pipeline 2 be positioned at inside sucker 3 concave surface should have certain length, with ensure when use vacuum pump by the road 1 sucker 3 taken out negative pressure and sucker 3 is tightly connected with fuselage skin time, the free end of this part pipeline 2 also keeps being tightly connected with fuselage baroport.
The cross sectional shape being positioned at the free end of the pipeline 2 inside sucker 3 concave surface is round table-like (especially as shown in Figure 4), and, in pipeline 2, at least cross sectional shape is round table-like this part (i.e. the free end of pipeline 2) is quality of rubber materials, such design makes pipeline 2 can fit more tight with aircraft static pressure hole, also can expand usable range of the present invention.
One end that pipeline 1 and pipeline 2 are positioned at sucker 3 outside is all provided with unidirectional stop valve 4 to facilitate control and to make more convenient to operate.
Adopt between pipeline 2 with sucker 3 and be threaded, one end that pipeline 2 is positioned at sucker 3 outside is provided with handle or knob, and when swing handle or knob, pipeline 2 can move reciprocatingly vertically relative to sucker 3, ensure that pipeline 2 is more tight with the connection of helicopter baroport, Leakage prevention.
Claims (5)
1. a helicopter static pressure test connector, is characterized in that: its main body is sucker (3), sucker (3) has two through holes;
Pipeline (1) passes described sucker (3) through one of them through hole, and and for being tightly connected between described sucker (3), described pipeline (1) is connected with vacuum pump;
Pipeline (2) passes described sucker (3) through another one through hole (2), and and for being tightly connected between described sucker (3);
When described sucker (3) is in negative pressure state and is tightly connected with fuselage skin, the free end and the fuselage baroport that are positioned at the described pipeline (2) of described sucker (3) concave surface are tightly connected.
2. helicopter static pressure test connector according to claim 1, it is characterized in that: the cross sectional shape being positioned at the free end of the described pipeline (2) of described sucker (3) concave surface is taper, in described pipeline (2), at least described free end is quality of rubber materials.
3. helicopter static pressure test connector according to claim 1, it is characterized in that: the cross sectional shape being positioned at the free end of the described pipeline (2) of described sucker (3) concave surface is round table-like, in described pipeline (2), at least described free end is quality of rubber materials.
4. helicopter static pressure test connector according to claim 1, is characterized in that: one end that described pipeline (1) and pipeline (2) are positioned at described sucker (3) outside is all provided with unidirectional stop valve (4).
5. according to the arbitrary described helicopter static pressure test connector of Claims 1 to 4, it is characterized in that: adopt between described pipeline (2) with described sucker (3) and be threaded, one end that described pipeline (2) is positioned at described sucker (3) outside is provided with handle or knob.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510161265.4A CN104764619B (en) | 2015-04-07 | 2015-04-07 | A kind of helicopter static pressure test connector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510161265.4A CN104764619B (en) | 2015-04-07 | 2015-04-07 | A kind of helicopter static pressure test connector |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104764619A true CN104764619A (en) | 2015-07-08 |
| CN104764619B CN104764619B (en) | 2019-05-07 |
Family
ID=53646586
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510161265.4A Active CN104764619B (en) | 2015-04-07 | 2015-04-07 | A kind of helicopter static pressure test connector |
Country Status (1)
| Country | Link |
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| CN (1) | CN104764619B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04147643A (en) * | 1990-10-09 | 1992-05-21 | Nippon Telegr & Teleph Corp <Ntt> | Vacuum coupler with built-in discharge preventing contact, pallet, and method of feeding power to pallet |
| CN202083523U (en) * | 2011-02-17 | 2011-12-21 | 中国航空工业集团公司西安飞机设计研究所 | Clamping joint for airplane airspeed head static pressure inspection |
| CN102866201A (en) * | 2012-09-13 | 2013-01-09 | 南京航空航天大学 | Aircraft skin health monitoring robot and control system for same |
| CN203698667U (en) * | 2013-12-19 | 2014-07-09 | 中国航空工业集团公司西安飞机设计研究所 | Plane static pressure sensor plug cover |
-
2015
- 2015-04-07 CN CN201510161265.4A patent/CN104764619B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04147643A (en) * | 1990-10-09 | 1992-05-21 | Nippon Telegr & Teleph Corp <Ntt> | Vacuum coupler with built-in discharge preventing contact, pallet, and method of feeding power to pallet |
| CN202083523U (en) * | 2011-02-17 | 2011-12-21 | 中国航空工业集团公司西安飞机设计研究所 | Clamping joint for airplane airspeed head static pressure inspection |
| CN102866201A (en) * | 2012-09-13 | 2013-01-09 | 南京航空航天大学 | Aircraft skin health monitoring robot and control system for same |
| CN203698667U (en) * | 2013-12-19 | 2014-07-09 | 中国航空工业集团公司西安飞机设计研究所 | Plane static pressure sensor plug cover |
Non-Patent Citations (1)
| Title |
|---|
| 张晓飞等: "复杂型面壁面静压联校接头设计", 《工程与试验》 * |
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| Publication number | Publication date |
|---|---|
| CN104764619B (en) | 2019-05-07 |
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