CN114720114B - Aviation hydraulic conduit test sample piece and sine wave pulse fatigue test method thereof - Google Patents
Aviation hydraulic conduit test sample piece and sine wave pulse fatigue test method thereof Download PDFInfo
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- CN114720114B CN114720114B CN202210653786.1A CN202210653786A CN114720114B CN 114720114 B CN114720114 B CN 114720114B CN 202210653786 A CN202210653786 A CN 202210653786A CN 114720114 B CN114720114 B CN 114720114B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
- G01N3/36—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces generated by pneumatic or hydraulic means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/003—Generation of the force
- G01N2203/0042—Pneumatic or hydraulic means
- G01N2203/0048—Hydraulic means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses an aviation hydraulic duct test sample piece and a sine wave pulse fatigue test method thereof, wherein the test sample piece comprises a test duct, a test adapter, a test tool, a sealing plug, an outer nut and a flat nozzle, wherein the test adapter, the test tool, the sealing plug, the outer nut and the flat nozzle are matched with the test duct; the test catheter end that is connected with experimental adapter, the test catheter end that is connected with the shutoff stopper all set up flat nozzle and cap nut, and flat nozzle cup joints on experimental catheter end, and cap nut one end joint is on flat nozzle, and the cap nut other end can dismantle between respectively and experimental adapter, the shutoff stopper and be connected. The invention has simple preparation, realizes the connection of the pulse testing machine and the test conduit through the matching of the test adapter, the flat nozzle and the outer sleeve nut, and has reliable connection form and good interchangeability; the sinusoidal pulse waveform is easy to obtain, and the curve characteristic of the sinusoidal pulse waveform is also suitable for evaluating the pulse fatigue test performance of the test catheter.
Description
Technical Field
The invention belongs to the technical field of pipe fittings, and particularly relates to an aviation hydraulic conduit test sample piece and a sine wave pulse fatigue test method thereof.
Background
The pulse fatigue test is one of performance tests of the aviation hydraulic pipeline, and aims to verify whether the hydraulic pulse bearing capacity of the aviation hydraulic pipeline meets the specified requirements through an acceleration test. At present, the pulse fatigue test of the aviation hydraulic conduit is measured according to HB 6133 standard, namely an aviation hydraulic hose, conduit and joint assembly pulse test method, and the pulse fatigue test method is used for evaluating the pulse fatigue test performance of the test conduit by utilizing a water hammer wave pulse waveform curve. The standard method lacks the regulation on the sine wave pulse fatigue test method, and the catheter test sample used by the current pulse fatigue test method is not suitable for the implementation of the sine wave pulse fatigue test method.
Disclosure of Invention
Aiming at the problems, the invention makes up the defects of the prior art and provides an aviation hydraulic duct test sample piece and a sine wave pulse fatigue test method thereof.
In order to achieve the purpose, the invention adopts the following technical scheme.
The invention provides an aviation hydraulic duct test sample piece which comprises a test duct, a test adapter, a test tool, a sealing plug, an outer nut and a flat nozzle, wherein the test adapter, the test tool, the sealing plug, the outer nut and the flat nozzle are matched with the test duct;
the test catheter end portion of being connected with experimental adapter, the test catheter end portion of being connected with the shutoff stopper all are provided with flat nozzle and cap nut, and flat nozzle cup joints on experimental catheter end portion, and cap nut one end joint is on flat nozzle, and the cap nut other end can dismantle between respectively and experimental adapter, the shutoff stopper and be connected.
As a preferred scheme of the invention, two ends of the test conduit are respectively provided with a conical seal flaring, the test adapter and the plugging plug are provided with conical surfaces which are matched and connected with the conical surfaces at the inner sides of the conical seal flaring, the test adapter is provided with a pressure inlet, and the pressure inlet is communicated with a test tool in the test conduit; the flat nozzle is provided with an inner conical surface which is matched and connected with the outer conical surface of the conical sealing flaring.
In another preferred embodiment of the present invention, the included angle of the inner conical surface of the cone seal flare is 74 degrees.
According to another preferred scheme of the invention, the test tool is a revolving body, two ends of the revolving body are positioned on the inner side of the conical seal flaring, two ends of the revolving body are respectively provided with a boss and a clamping groove, the bosses are abutted to the inner side surface of the test guide pipe, an O-shaped seal ring is fixedly arranged in the clamping grooves, and the end surfaces of the O-shaped seal ring are respectively in seal fit with the end surfaces of the test adapter and the plugging plug.
In another preferred embodiment of the present invention, an annular passage is formed between the boss of the rotator and the inner surface of the test tube and the outer surface of the rotator.
As another preferable scheme of the invention, both ends of the revolving body are provided with an axial hole and a radial hole, the axial hole is vertically communicated with the radial hole, the radial hole leads to the annular channel inside the test conduit, and the radial holes at both ends of the revolving body are oppositely arranged relative to the axis of the revolving body.
As another preferred scheme of the invention, threads are arranged on the middle surface of the test adapter and the middle surface of the plugging plug, and the test adapter, the plugging plug and the outer nut are connected through the threads.
The invention provides a sine wave pulse fatigue test method of an aviation hydraulic conduit test sample piece, which comprises the following steps:
(a) connecting the test adapter of the aviation hydraulic conduit test sample piece with a pulse tester, and not mounting a seal plug;
(b) injecting hydraulic oil into the test tool through a pressure inlet of the test adapter, wherein the oil passes through an axial hole and a radial hole on the test tool, fills an annular channel formed between a boss of the test tool and the inner side surface of the test guide pipe and the outer side surface of the test tool, discharges air in the test sample piece of the aviation hydraulic guide pipe and enables the test guide pipe to be subjected to pure circumferential force of hydraulic pulse;
(c) then, screwing the plugging plug on the outer sleeve nut, and sealing the plugging plug on the conical sealing flaring at the end part of the test conduit;
(d) the test is carried out under a specified stress level, the pulse testing machine is adjusted according to the relationship of the pressing force-time cycle characteristic, and the test cycle frequency is according to the formula:
determining so as to obtain a required sine pulse waveform through a pulse testing machine; in the formula, Pmax represents the highest pressure value.
Further, the characteristics of the obtained sinusoidal pulse waveform include: the maximum pressure increasing rate is 862 +/-172 MPa/s, the overshoot of the maximum pressure value Pmax is less than or equal to 2%, the period distortion rate is less than or equal to 0.1C, the maximum residence time is less than or equal to 0.1C, and C represents 1 cycle period.
The invention has the beneficial effects that:
1. the test sample piece of the aviation hydraulic conduit is simple to prepare, the connection between the pulse testing machine and the test conduit is realized through the matching of the test adapter, the flat nozzle and the outer sleeve nut, the connection form is reliable, and the interchangeability is good.
2. The invention adopts a sealing mode of combining the conical sealing flaring with an included angle of 74 degrees and the O-shaped sealing ring to realize perfect sealing among the test conduit, the test adapter and the plugging plug; simple and reliable, excellent sealing performance and low cost. Under the sealing condition, the test tool can enable the test conduit to be subjected to pure circumferential force.
3. The sine pulse waveform can be set and adjusted by the pulse testing machine in the sine wave pulse fatigue testing method, and is easy to obtain; and the sinusoidal pulse waveform curve characteristic is also suitable for evaluating the pulse fatigue test performance of the test conduit.
Drawings
Fig. 1 is a schematic structural diagram of an aviation hydraulic conduit test sample provided by the invention.
Fig. 2 is a sinusoidal pulse waveform diagram obtained by a sinusoidal pulse fatigue test method using an aviation hydraulic conduit test sample of the present invention.
The labels in the figure are: the test adapter is 1, the outer sleeve nut is 2, the O-shaped sealing ring is 3, the flat nozzle is 4, the test guide pipe is 5, the test tool is 6, the seal plug is 7, the pressure inlet is 8, the annular channel is 9, the thread is 10, the conical seal flaring is 11, the clamping groove is 12, the boss is 13, the axial hole is 14, and the radial hole is 15.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and the detailed description. It should be understood that the detailed description and specific examples, while indicating the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.
Referring to fig. 1, the aviation hydraulic duct test sample provided by the embodiment of the invention comprises a test duct 5, and a test adapter 1, a test fixture 6, a plugging plug 7, an outer nut 2 and a flat nozzle 4 which are used in cooperation with the test duct 5, wherein the test fixture 6 is arranged in the test duct 5, and two ends of the test duct 5 are respectively connected with the test adapter 1 and the plugging plug 7; the 5 tip of experimental pipe of being connected with experimental adapter 1, the 5 tip of experimental pipe of being connected with shutoff stopper 7 all are provided with flat mouthpiece 4 and outer cover nut 2, and flat mouthpiece 4 cup joints on 5 tips of experimental pipe, and 2 one end joint of outer cover nut are on flat mouthpiece 4, and the 2 other ends of outer cover nut can dismantle between respectively with experimental adapter 1, shutoff stopper 7 and be connected.
The two ends of the test conduit 5 are respectively provided with a conical seal flaring 11, the test adapter 1 and the plugging plug 7 are provided with conical surfaces which are matched and connected with the conical surfaces at the inner sides of the conical seal flaring 11, the test adapter 1 is provided with a pressure inlet 8, and the pressure inlet 8 leads to a test tool 6 in the test conduit 5; the flat nozzle 4 is provided with an inner conical surface which is matched and connected with the outer conical surface of the conical seal flaring 11; the included angle of the inner conical surface of the conical seal flaring 11 is 74 degrees.
The test tool 6 is a revolving body, two ends of the revolving body are located on the inner sides of the conical seal flaring openings 11, bosses 13 and clamping grooves 12 are arranged at two ends of the revolving body, the bosses 13 are abutted to the inner side surface of the test guide pipe 5, O-shaped seal rings 3 are fixedly mounted in the clamping grooves 12, and the end surfaces of the O-shaped seal rings 3 are in seal fit with the end surfaces of the test adapter 1 and the plugging plug 7 respectively.
An annular channel 9 is formed between the boss 13 of the revolving body and the inner side surface and the outer side surface of the test conduit 5.
The length of the test conduit 5 between the flat nozzles 4 is the free length of the test conduit 5, and the free length of the test conduit 5 is set differently according to the different outer diameters of the test conduit 5; specifically, if the outer diameter of the test tube 5 is 6mm, 8mm, 10mm, 12mm, 14mm, 16mm, 18mm, 20mm, the free length of the test tube 5 is set to 200 mm; if the outer diameter of the test tube 5 is 25mm, the free length of the test tube 5 is set to 250 mm.
The sine wave pulse fatigue test method of the aviation hydraulic conduit test sample piece provided by the embodiment of the invention can be used for carrying out sine wave pulse fatigue tests on the test conduits 5 with different outer diameters, and specifically comprises the following steps:
(a) connecting the test adapter 1 of the aviation hydraulic conduit test sample piece with a pulse tester, and not installing a sealing plug 7;
(b) hydraulic oil is added into the test tool 6 through a pressure inlet 8 of the test adapter 1, the oil is filled in an annular channel 9 formed between a boss 13 of the test tool 6 and the inner side surface of the test conduit 5 and the outer side surface of the test tool 6 through an axial hole 14 and a radial hole 15 on the test tool 6, air in a test sample of the aviation hydraulic conduit is discharged, and the test conduit 5 is subjected to pure circumferential force of hydraulic pulse;
(c) then, screwing the plugging plug 7 on the outer sleeve nut 2, and sealing the plugging plug 7 on a conical seal flaring 11 at the end part of the test conduit 5;
(d) the test is carried out under a specified stress level, the pulse testing machine is adjusted according to the relationship of the pressing force-time cycle characteristic, and the test cycle frequency is according to the formula:
determining so as to obtain a sine wave test pulse trace through a pulse testing machine, wherein the obtained sine wave test pulse trace is the required sine pulse waveform; in the formula, Pmax represents the highest pressure value.
As shown in fig. 2, which is a sine pulse waveform diagram obtained by the sine wave pulse fatigue test method using the aviation hydraulic conduit test sample piece of the invention, the parameter meanings appearing in the diagram are as follows: pmax represents the highest pressure value, Pmin represents the lowest pressure value, Pmean represents the average pressure value; the characteristics of the obtained sinusoidal pulse waveform include: the maximum pressure increasing rate is 862 +/-172 MPa/s, the overshoot of the maximum pressure value Pmax is less than or equal to 2%, the period distortion rate is less than or equal to 0.1C, the maximum residence time is less than or equal to 0.1C, and C represents 1 cycle period.
It should be understood that the detailed description of the present invention is only for illustrating the present invention and is not limited by the technical solutions described in the embodiments of the present invention, and those skilled in the art should understand that the present invention can be modified or substituted equally to achieve the same technical effects; as long as the use requirements are met, the method is within the protection scope of the invention.
Claims (5)
1. Aviation hydraulic pressure pipe test sample spare, its characterized in that: the test device comprises a test conduit, and a test adapter, a test tool, a plugging plug, an outer nut and a flat nozzle which are matched with the test conduit, wherein the test tool is arranged in the test conduit, and two ends of the test conduit are respectively connected with the test adapter and the plugging plug; the end part of the test conduit connected with the test adapter and the end part of the test conduit connected with the plugging plug are respectively provided with a flat nozzle and an outer nut, the flat nozzle is sleeved on the end part of the test conduit, one end of the outer nut is clamped on the flat nozzle, and the other end of the outer nut is respectively detachably connected with the test adapter and the plugging plug; the test tool is a revolving body, two ends of the revolving body are positioned on the inner side of the conical seal flaring, bosses and clamping grooves are arranged at two ends of the revolving body, the bosses are abutted to the inner side surface of the test conduit, O-shaped seal rings are fixedly arranged in the clamping grooves, and the end surfaces of the O-shaped seal rings are respectively in seal fit with the end surfaces of the test adapter and the plugging plug; an annular channel is formed between the boss of the revolving body and the inner side surface of the test conduit and between the boss of the revolving body and the outer side surface of the revolving body; axial holes and radial holes are formed in the two ends of the revolving body, the axial holes are vertically communicated with the radial holes, the radial holes are communicated with an annular channel inside the test conduit, and the radial holes in the two ends of the revolving body are arranged oppositely relative to the axis of the revolving body.
2. The aviation hydraulic conduit test sample of claim 1, wherein: the two ends of the test conduit are provided with conical seal flaring ports, the test adapter and the plugging plug are provided with conical surfaces which are matched and connected with the conical surfaces on the inner sides of the conical seal flaring ports, the test adapter is provided with a pressure inlet, and the pressure inlet is communicated with a test tool in the test conduit; the flat nozzle is provided with an inner conical surface which is matched and connected with the outer conical surface of the conical sealing flaring.
3. The aviation hydraulic conduit test sample of claim 2, wherein: the included angle of the inner side conical surface of the conical sealing flaring is 74 degrees.
4. The aviation hydraulic conduit test sample of claim 1, wherein: the surface of the middle part of the test adapter and the surface of the middle part of the plugging plug are both provided with threads, and the test adapter, the plugging plug and the outer nut are connected through the threads.
5. The sine wave pulse fatigue test method of the aviation hydraulic conduit test sample piece is characterized in that: the method comprises the following steps:
(a) connecting the test adapter of the aviation hydraulic conduit test sample piece as claimed in any one of claims 1 to 4 with a pulse tester without installing a seal plug;
(b) injecting hydraulic oil into the test tool through a pressure inlet of the test adapter, wherein the oil passes through an axial hole and a radial hole on the test tool, fills an annular channel formed between a boss of the test tool and the inner side surface of the test guide pipe and the outer side surface of the test tool, discharges air in the test sample piece of the aviation hydraulic guide pipe and enables the test guide pipe to be subjected to pure circumferential force of hydraulic pulse;
(c) then, screwing the plugging plug on the outer sleeve nut, and sealing the plugging plug on the conical sealing flaring at the end part of the test conduit;
(d) the test is carried out under a specified stress level, the pulse testing machine is adjusted according to the relationship of the pressing force-time cycle characteristic, and the test cycle frequency is according to the formula:
determining so as to obtain a required sine pulse waveform through a pulse testing machine; in the formula, Pmax represents the highest pressure value.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210653786.1A CN114720114B (en) | 2022-06-10 | 2022-06-10 | Aviation hydraulic conduit test sample piece and sine wave pulse fatigue test method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210653786.1A CN114720114B (en) | 2022-06-10 | 2022-06-10 | Aviation hydraulic conduit test sample piece and sine wave pulse fatigue test method thereof |
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| CN114720114A CN114720114A (en) | 2022-07-08 |
| CN114720114B true CN114720114B (en) | 2022-08-12 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101881287A (en) * | 2010-06-03 | 2010-11-10 | 西北工业大学 | High-pressure and hydraulic pulsation test system of aircraft |
| CN210037462U (en) * | 2019-03-12 | 2020-02-07 | 青岛苏试海测检测技术有限公司 | Aviation high pressure fuel pipe high temperature pulse test device |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008083961A1 (en) * | 2007-01-12 | 2008-07-17 | Friedrich-Alexander-Universität Erlangen-Nürnberg | Method for high-pressure pulsation testing of machinery components |
| CN201344883Y (en) * | 2009-01-11 | 2009-11-11 | 江苏常牵庞巴迪牵引***有限公司 | Hydraulic pulse fatigue device in pipe |
| CN201561902U (en) * | 2009-10-15 | 2010-08-25 | 徐州天地重型机械制造有限公司 | Hydraulic hose performance test experiment table |
| CN105938073A (en) * | 2015-12-24 | 2016-09-14 | 石油和化学工业橡胶及再生产品质量监督检验中心（天津市质量监督检验站第四十二站） | Pressure pulse test hydraulic system for rubber hose detection |
| CN112326441B (en) * | 2020-10-26 | 2024-03-08 | 沈阳明日航材先进制造科技有限公司 | Pressure pulse test method and test equipment for guide pipe and joint assembly |
| CN214097007U (en) * | 2020-12-25 | 2021-08-31 | 中辽检测(辽宁)有限公司 | Hose pressure pulse fatigue test device |
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- 2022-06-10 CN CN202210653786.1A patent/CN114720114B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101881287A (en) * | 2010-06-03 | 2010-11-10 | 西北工业大学 | High-pressure and hydraulic pulsation test system of aircraft |
| CN210037462U (en) * | 2019-03-12 | 2020-02-07 | 青岛苏试海测检测技术有限公司 | Aviation high pressure fuel pipe high temperature pulse test device |
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