CN106197857A - A kind of helicopter pitot-static pressure gas-tight test - Google Patents
A kind of helicopter pitot-static pressure gas-tight test Download PDFInfo
- Publication number
- CN106197857A CN106197857A CN201510230248.1A CN201510230248A CN106197857A CN 106197857 A CN106197857 A CN 106197857A CN 201510230248 A CN201510230248 A CN 201510230248A CN 106197857 A CN106197857 A CN 106197857A
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- China
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- static pressure
- helicopter
- reversal valve
- test
- pitot
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Abstract
The present invention relates to a kind of helicopter pitot-static pressure gas-tight test, by hand pump (1), reversal valve (2), airspeed-indicator (3), climb meter (4), gas inspection fixture (5) is constituted, hand pump (1) is connected with reversal valve (2) by flexible pipe, reversal valve (2) has three gears, it is respectively " total head ", " static pressure ", "Off", " total head " gear of reversal valve (2) is connected with airspeed-indicator (3) by flexible pipe, it is spigot joint that series connection is followed by exerciser " total head ", " static pressure " gear of reversal valve (2) is by flexible pipe and airspeed-indicator (3), climb meter (4) connects, it is spigot joint that series connection is followed by exerciser " static pressure "；Gas inspection fixture (5) head is complete with the pitot of helicopter according to test needs, static pressure interface connects.The present invention increases climb meter in exerciser pipeline, meets and can control pressure decay rate and the requirement of the rate of rise with observation helicopter static line.
Description
Technical field
The invention belongs to helicopter assembling test technical field, relate to a kind of helicopter pitot tube
The exerciser of road airtight test.
Background technology
Pitot-static pressure gas-tight test is to check that helicopter is complete, static line air-tightness is the most intact
Frock.Existing pitot-static pressure gas-tight test can only give complete, static line pressurization, passes through
Airspeed-indicator controls pressure, it is impossible to ensure pressure decay rate and the rate of rise.
Summary of the invention
It is an object of the invention to: provide one to be adapted to helicopter pitot-static pressure checking air tightness of pipelines
Exerciser, to meet, static line air-tight test ensures pressure decay rate and the rate of rise.
The technical scheme is that a kind of helicopter pitot-static pressure gas-tight test, by hand
Pump 1, reversal valve 2, airspeed-indicator 3, climb meter 4, gas inspection fixture 5 is constituted, wherein hands
Shaking pump 1 to be connected with reversal valve 2 by flexible pipe, reversal valve 2 has three gears, is respectively " complete
Pressure ", " static pressure ", "Off", " total head " gear of reversal valve 2 is by flexible pipe and airspeed-indicator 3
Connecting, it is spigot joint that series connection is followed by exerciser " total head ", and " static pressure " gear of reversal valve 2 leads to
Crossing flexible pipe to connect with airspeed-indicator 3, climb meter 4, series connection is followed by exerciser " static pressure "
Spigot joint；Gas inspection fixture 5 with flexible pipe with spigot joint, by spigot joint can be with " total head " of exerciser
Spigot joint, " static pressure " is spigot joint connects；Gas inspection fixture 5 head needs and helicopter according to test
Pitot is complete, static pressure interface connects.
The invention have the advantage that the present invention increases climb meter in exerciser pipeline, meet
Pressure decay rate and the requirement of the rate of rise can be controlled with observation helicopter static line.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention.
Detailed description of the invention
Seeing Fig. 1, the present invention is by hand pump 1, reversal valve 2, airspeed-indicator 3, climb meter
4, gas inspection fixture 5 is constituted.Hand pump 1 is connected with reversal valve 2 by flexible pipe, reversal valve 2
There are three gears, are respectively " total head ", " static pressure ", "Off"." total head " of reversal valve 2
Gear is connected with airspeed-indicator 3 by flexible pipe, and it is spigot joint that series connection is followed by exerciser " total head ", changes
Connected with airspeed-indicator 3, climb meter 4 by flexible pipe to " static pressure " gear of valve 2, string
It is spigot joint that connection is followed by exerciser " static pressure ".Gas examines fixture 5 with flexible pipe with spigot joint, by connecing
Mouth can spigot joint with " total head " of exerciser, " static pressure " is spigot joint connects.Gas inspection fixture 5
Portion is complete with the pitot of helicopter according to test needs, static pressure interface connects.
The work process of the present invention is: during total head system airtight test, hand pump 1 is screwed into
Outer end, reversal valve 2 knob points to " total head " position, and exerciser gas is examined fixture 5 and gone straight up to
The pitot total head interface of machine is connected, is more inwardly rotated by hand pump 1 and make system generation pressure,
When airspeed-indicator 3 instruction is to test requirements document value, reversal valve 2 is threaded to off-position, carries out
Pressurize is tested, and after off-test, hand pump 1 is to external rotation, and airspeed-indicator 3 indicates " zero " position,
Disconnect the pitot total head interface of gas inspection fixture 5 and helicopter.
During static-pressure system airtight test, hand pump 1 is screwed into innermost end, and reversal valve 2 knob refers to
To " static pressure " position, the pitot static pressure interface of exerciser gas inspection fixture 5 with helicopter is connect
Logical, then make system produce pressure to external rotation hand pump 1, controlled by climb meter 4
The static line rate of rise, when airspeed-indicator 3 instruction is to test requirements document value, revolves reversal valve 2
To off-position, carrying out pressurize test, after off-test, hand pump 1 inwardly rotates, logical
Crossing climb meter 4 and control static line pressure decay rate, airspeed-indicator 3 indicates " zero " position, disconnected
Open the pitot static pressure interface of gas inspection fixture 5 and helicopter.
Claims (3)
1. a helicopter pitot-static pressure gas-tight test, it is characterised in that by hand pump (1),
Reversal valve (2), airspeed-indicator (3), climb meter (4), gas inspection fixture (5) are constituted,
Wherein hand pump (1) is connected with reversal valve (2) by flexible pipe, and reversal valve (2) has three
Gear, is respectively " total head ", " static pressure ", "Off", " total head " gear of reversal valve (2)
Being connected with airspeed-indicator (3) by flexible pipe, it is spigot joint that series connection is followed by exerciser " total head ", changes
To " static pressure " gear of valve (2) by flexible pipe and airspeed-indicator (3), climb meter (4)
Connecting, it is spigot joint that series connection is followed by exerciser " static pressure "；Gas inspection fixture (5) with flexible pipe with
Spigot joint, by spigot joint can spigot joint with " total head " of exerciser, " static pressure " is spigot joint connects；
Gas inspection fixture (5) head is complete with the pitot of helicopter according to test needs, static pressure interface phase
Connect.
2. helicopter pitot-static pressure gas-tight test as claimed in claim 1, its feature exists
In, during total head system airtight test, hand pump (1) is screwed into outermost end, reversal valve (2)
Knob points to " total head " position, by the pitot of exerciser gas inspection fixture (5) with helicopter
Total head interface is connected, then makes system produce pressure hand pump (1) inwardly rotation, works as air speed
When table (3) instruction is to test requirements document value, reversal valve (2) is threaded to off-position, carries out
Pressurize is tested, and after off-test, hand pump (1) is to external rotation, airspeed-indicator (3) instruction " zero "
Position, disconnects the pitot total head interface of gas inspection fixture (5) and helicopter.
3. helicopter pitot-static pressure gas-tight test as claimed in claim 1, its feature exists
In, during static-pressure system airtight test, hand pump (1) is screwed into innermost end, reversal valve (2)
Knob points to " static pressure " position, by the pitot of exerciser gas inspection fixture (5) with helicopter
Static pressure interface is connected, then makes system produce pressure to external rotation hand pump (1), by rising
Fall speedometer (4) controls the static line rate of rise, when airspeed-indicator (3) instruction is wanted to test
During evaluation, reversal valve (2) is threaded to off-position, carries out pressurize test, off-test
After, hand pump (1) inwardly rotates, and controls static line blood pressure lowering by climb meter (4)
Speed, airspeed-indicator (3) instruction " zero " position, disconnect the sky of gas inspection fixture (5) and helicopter
Speed pipe static pressure interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510230248.1A CN106197857A (en) | 2015-05-07 | 2015-05-07 | A kind of helicopter pitot-static pressure gas-tight test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510230248.1A CN106197857A (en) | 2015-05-07 | 2015-05-07 | A kind of helicopter pitot-static pressure gas-tight test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106197857A true CN106197857A (en) | 2016-12-07 |
Family
ID=57459700
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510230248.1A Pending CN106197857A (en) | 2015-05-07 | 2015-05-07 | A kind of helicopter pitot-static pressure gas-tight test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106197857A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61251731A (en) * | 1984-09-03 | 1986-11-08 | バデイ・クロ−ゼツト | Aerodynamic characteristic measuring device |
| JP2000111442A (en) * | 1998-10-05 | 2000-04-21 | Fuji Heavy Ind Ltd | Ventilation inspection method and device |
| CN2525499Y (en) * | 2001-09-18 | 2002-12-11 | 景博 | Pressure measurer |
| CN202938972U (en) * | 2012-12-04 | 2013-05-15 | 中信海直通用航空维修工程有限公司 | Dynamic-static pressure tester for helicopter out-field maintenance |
| CN104122050A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Dynamic pressure and static pressure testing device of helicopter distributed atmospheric engine |
| CN204269306U (en) * | 2014-12-30 | 2015-04-15 | 哈尔滨通航科技开发有限公司 | Aircraft pitot-static pressure exerciser |
-
2015
- 2015-05-07 CN CN201510230248.1A patent/CN106197857A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61251731A (en) * | 1984-09-03 | 1986-11-08 | バデイ・クロ−ゼツト | Aerodynamic characteristic measuring device |
| JP2000111442A (en) * | 1998-10-05 | 2000-04-21 | Fuji Heavy Ind Ltd | Ventilation inspection method and device |
| CN2525499Y (en) * | 2001-09-18 | 2002-12-11 | 景博 | Pressure measurer |
| CN202938972U (en) * | 2012-12-04 | 2013-05-15 | 中信海直通用航空维修工程有限公司 | Dynamic-static pressure tester for helicopter out-field maintenance |
| CN104122050A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Dynamic pressure and static pressure testing device of helicopter distributed atmospheric engine |
| CN204269306U (en) * | 2014-12-30 | 2015-04-15 | 哈尔滨通航科技开发有限公司 | Aircraft pitot-static pressure exerciser |
Non-Patent Citations (2)
| Title |
|---|
| 景博 等: "《飞机全静压系统检查仪的研制》", 《空军工程大学学报（自然科学版）》 * |
| 汤黄华: "《飞机全、静压系统性能指标值的设计要求与检验》", 《洪都科技》 * |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20161207 |
|
| WD01 | Invention patent application deemed withdrawn after publication |