CN103149007A - Detonation drive shock tunnel forming membrane - Google Patents
Detonation drive shock tunnel forming membrane Download PDFInfo
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- CN103149007A CN103149007A CN2013100338827A CN201310033882A CN103149007A CN 103149007 A CN103149007 A CN 103149007A CN 2013100338827 A CN2013100338827 A CN 2013100338827A CN 201310033882 A CN201310033882 A CN 201310033882A CN 103149007 A CN103149007 A CN 103149007A
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- membrane
- detonation
- shock tunnel
- drive shock
- tunnel
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- 238000005474 detonation Methods 0.000 title claims abstract description 41
- 239000012528 membrane Substances 0.000 title claims abstract description 41
- 230000035939 shock Effects 0.000 title claims abstract description 37
- 238000007493 shaping process Methods 0.000 claims description 20
- 229910001220 stainless steel Inorganic materials 0.000 claims description 9
- 239000010935 stainless steel Substances 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 5
- 238000013461 design Methods 0.000 abstract description 4
- 230000000644 propagated effect Effects 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 8
- 238000012360 testing method Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- 238000011161 development Methods 0.000 description 3
- 239000002360 explosive Substances 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 235000021152 breakfast Nutrition 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 238000007781 pre-processing Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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Abstract
The invention discloses a detonation drive shock tunnel forming membrane which comprises a membrane body. A protruding portion is formed at the center of the membrane body. A groove with the predetermined depth is formed in the protruding portion. Due to the fact that the protruding portion is formed on the membrane body and the groove with the predetermined depth is formed in the protruding portion, when detonation waves are propagated and arrive at the detonation drive shock tunnel forming membrane, the detonation drive shock tunnel forming membrane can rapidly and completely rupture according to a mode appointed in the design. Consequently, energy required by rupture of the membrane is reduced, the motion distance and the motion speed of the ruptured membrane are also reduced, and the simulable range of a detonation drive shock tunnel for hypersonic velocity flow is further improved.
Description
Technical field
The present invention relates to the technology of raising wind-tunnel driving force of detonation driven shock tunnel and operational reliability and repeatability, particularly for the detonation driven shock tunnel shaping membrane of hypersonic aircraft ground simulating device.
Background technology
The development of following hypersonic aircraft needs to produce on ground the test air-flow of high stagnation temperature and high flow rate.But the high temperature and high pressure gas that the quick detonation of detonation driven shock tunnel utilization explosive gas produces compresses empty experimental gas, makes it to reach a kind of shock tunnel technology of higher stagnation temperature and stagnation pressure.
At first the detonation driven shock tube is proposed in nineteen fifty-seven by Bird, and the Yu Hongru researcher of Inst. of Mechanics, CAS has built a detonation driven shock tube that 13.3m is long in 1981, and comes into operation in nineteen eighty-three.Use this shock tube, systematic study the hydrogen detonation driving method, the quick-fried technology of unloading of reverse detonation driven has been proposed, building up the high enthalpy shock tunnel of JF-10 detonation driven [controls with measuring referring to the performance-aerodynamic testing of the oxygen hydrogen detonation driven shock tunnel of Yu Hongru, Zhao Wei, Yuan Shengxue, 1993,7 (3): 38-42].The people such as Gronig has built in Aachen, Germany polytechnical university the high enthalpy shock tunnel (TH2-D) of using reverse detonation driven in 1993 under Yu Hongru researcher's help.1994, NASA revised the design proposal that original free-piston drives, and built up at GASL and had built forward-running detonation drivers for high-enthalpy shock tunnels (HYPULSE), and this wind-tunnel can work in reflected shock wave wind-tunnel pattern and bulged tube pattern simultaneously.
The LENS II wind-tunnel shock tunnel at U.S. CALspanUB center adopts heating lighter-than-air gas type of drive, nozzle exit diameter 1.55m, in the situation that the simulation stagnation temperature can obtain the test period of 30～80ms less than 2000K, be to use one of very successful wind-tunnel in hypersonic mobile ground simulation test.
In the detonation driven shock tunnel, but usually adopt thicker diaphragm to isolate explosive gas and driven air, form very high pressure and temperature after detonation initiation, but can promptly make the rupture of diaphragm between explosive gas and driven air, and then form to driven airborne intense shock wave, realize the operation of the high enthalpy shock tunnel of detonation driven.Diaphragm adopts ductility stainless steel material preferably usually, and the fragment that rupture of diaphragm forms is less, and detonation pressure more the high request diaphragm is thicker.In the practical operation of shock tunnel, because thicker stainless steel diaphragm rupture time is longer, the dehiscing of rupture of diaphragm is difficult for opening fully in the short period of time, caused the decline of detonation driven shock tunnel driving force, do not reach required high stagnation temperature and the requirement of stagnation pressure test gas.
Summary of the invention
Problem for the prior art existence, the object of the present invention is to provide a kind of detonation driven shock tunnel shaping membrane, can break fast at detonation driven shock tunnel diaphragm in service, breach fully opens, and can improve the repeatability of detonation driven shock tunnel, reliability and driving force.
A kind of detonation driven shock tunnel shaping membrane provided by the invention comprises: membrane body, be formed with protuberance at the center of membrane body, and offer the groove with predetermined depth on described protuberance.
Preferably, described groove is two cruciform grooves that intersect to form.
Preferably, the degree of depth of described groove is half of thickness of described membrane body.
Preferably, described protuberance is hemispherical.
Preferably, described membrane body is stainless steel material.
The present invention has the membrane body of protuberance by formation, and offer the groove with predetermined depth on protuberance, like this, when detonation driven shock tunnel shaping membrane is propagated arrival at detonation wave, can break fully fast according to the mode of design appointment, reduced the energy that rupture of membranes needs, reduced rupture disc move distance and speed, further improved the detonation driven shock tunnel for the hypersonic scope that flows and can simulate.
Description of drawings
Below the invention will be further elaborated based on the non-limiting example in following accompanying drawing.
Fig. 1 is the scheme of installation of detonation driven shock tunnel shaping membrane of the present invention;
Fig. 2 is the structural representation of the protuberance seen along the arrow A direction in Fig. 1.
Embodiment
Show as Fig. 1,2, detonation driven section 1 is connected with driven section 3 by flange, and the isolation diaphragm between detonation driven section 1 and driven section 3 adopts the stainless steel shaping membrane body 2 of moulding.Stainless steel shaping membrane body 2 has the protuberance 4 of center hemispherical projections shape, and its radius is spherical radius, selects 70% of detonation driven section pipe 1 radius, and transitional region adopts arc transition.At the protuberance 4 criss-cross grooves 5 of surface working of stainless steel shaping membrane body 2, the degree of depth of groove 5 is half of thickness of shaping membrane body 2.
Employing is with the shaping membrane of protuberance 4 and cruciform groove, when gas pressure difference to the diaphragm that improves gradually diaphragm both sides splits, the diaphragm that protrudes shape bears material stress to be increased to the center gradually from outer rim, the center material stress is maximum, shaping membrane breaks from the center, and preprocessing cruciform groove guarantees that the development in crack is according to the cross groove future development of expection.Therefore after adopting shaping membrane, diaphragm breaks according to the mode that expection is set, and with respect to the random failure mode of flat diaphragm, can reduce the broken film of the generation of broken film in the diaphragm process, particularly bulk, avoids wind-tunnel downstream other parts by the broken membrane damage of high-speed motion.
This invention is by carrying out preprocessing to the stainless steel diaphragm, make its central area have initial specific spherical shape, and in the square groove structure of diaphragm center processing designated depth.In the application of detonation driven shock tunnel operation, the stainless steel diaphragm after moulding can break fast, breach fully opens, and can improve repeatability and the reliability of detonation driven shock tunnel, and reaches higher wind-tunnel driving force.
When detonation driven shock tunnel shaping membrane is propagated arrival at detonation wave, can break fully fast according to the mode of design appointment, reduced the energy that rupture of membranes needs, reduced rupture disc move distance and speed, further improved the detonation driven shock tunnel for the hypersonic scope that flows and can simulate.
By adopting the shaping membrane technology, in service at shock tunnel, can make the diaphragm quality loss be decreased to 1 ~ 2% than ([experiment front diaphragm quality-experiment rear film quality]/test front diaphragm quality * 100%) by original 5 ~ 10%.
Claims (5)
1. a detonation driven shock tunnel shaping membrane, is characterized in that, comprising: membrane body, be formed with protuberance at the center of membrane body, and offer the groove with predetermined depth on described protuberance.
2. shaping membrane as claimed in claim 1, is characterized in that, described groove is two cruciform grooves that intersect to form.
3. shaping membrane as claimed in claim 1 or 2, is characterized in that, the degree of depth of described groove is half of thickness of described membrane body.
4. shaping membrane as claimed in claim 3, is characterized in that, described protuberance is hemispherical.
5. shaping membrane as claimed in claim 4, is characterized in that, described membrane body is stainless steel material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310033882.7A CN103149007B (en) | 2013-01-29 | 2013-01-29 | A kind of detonation driven shock tunnel shaping membrane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310033882.7A CN103149007B (en) | 2013-01-29 | 2013-01-29 | A kind of detonation driven shock tunnel shaping membrane |
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| Publication Number | Publication Date |
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| CN103149007A true CN103149007A (en) | 2013-06-12 |
| CN103149007B CN103149007B (en) | 2015-08-12 |
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| CN201310033882.7A Active CN103149007B (en) | 2013-01-29 | 2013-01-29 | A kind of detonation driven shock tunnel shaping membrane |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840580A (en) * | 2016-12-07 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of diaphragm positioning clamping device |
| CN107421712A (en) * | 2017-08-16 | 2017-12-01 | 武汉理工大学 | A kind of device and method for weakening hydrogen detonation shock tube rarefaction wave |
| CN108801580A (en) * | 2018-08-15 | 2018-11-13 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of ballistic range target chamber quick-opening device based on rupture disk mode |
| CN109799055A (en) * | 2019-02-14 | 2019-05-24 | 重庆交通大学 | Can continuous uniform adjust and unload the shock tunnel of quick-fried efficiency and unload quick-fried device |
| CN110044576A (en) * | 2019-05-23 | 2019-07-23 | 重庆大学 | Realize the mobile shunting device of wind-tunnel plane of inlet |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2496006Y (en) * | 2001-03-16 | 2002-06-19 | 中国科学院力学研究所 | Metal formed matrix used for high enthalpy pulse wind tunnel |
| CN2663964Y (en) * | 2003-09-08 | 2004-12-15 | 中国科学院力学研究所 | Equipment for damping Taylor wave in detonation wind tunnel |
| KR100654607B1 (en) * | 2005-12-27 | 2006-12-08 | 한국항공우주연구원 | A gust generator for wind tunnel |
| CN201259461Y (en) * | 2008-09-27 | 2009-06-17 | 中国科学院沈阳应用生态研究所 | Low speed wind tunnel |
| CN102407947A (en) * | 2011-08-15 | 2012-04-11 | 中国科学院力学研究所 | Shock tunnel detonation double-driving method and device |
-
2013
- 2013-01-29 CN CN201310033882.7A patent/CN103149007B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2496006Y (en) * | 2001-03-16 | 2002-06-19 | 中国科学院力学研究所 | Metal formed matrix used for high enthalpy pulse wind tunnel |
| CN2663964Y (en) * | 2003-09-08 | 2004-12-15 | 中国科学院力学研究所 | Equipment for damping Taylor wave in detonation wind tunnel |
| KR100654607B1 (en) * | 2005-12-27 | 2006-12-08 | 한국항공우주연구원 | A gust generator for wind tunnel |
| CN201259461Y (en) * | 2008-09-27 | 2009-06-17 | 中国科学院沈阳应用生态研究所 | Low speed wind tunnel |
| CN102407947A (en) * | 2011-08-15 | 2012-04-11 | 中国科学院力学研究所 | Shock tunnel detonation double-driving method and device |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840580A (en) * | 2016-12-07 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of diaphragm positioning clamping device |
| CN106840580B (en) * | 2016-12-07 | 2019-01-15 | 中国航天空气动力技术研究院 | A kind of diaphragm positioning clamping device |
| CN107421712A (en) * | 2017-08-16 | 2017-12-01 | 武汉理工大学 | A kind of device and method for weakening hydrogen detonation shock tube rarefaction wave |
| CN107421712B (en) * | 2017-08-16 | 2019-05-03 | 武汉理工大学 | A kind of device and method weakening hydrogen detonation shock tube rarefaction wave |
| CN108801580A (en) * | 2018-08-15 | 2018-11-13 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of ballistic range target chamber quick-opening device based on rupture disk mode |
| CN108801580B (en) * | 2018-08-15 | 2024-01-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Quick-opening device of ballistic target chamber based on blasting film mode |
| CN109799055A (en) * | 2019-02-14 | 2019-05-24 | 重庆交通大学 | Can continuous uniform adjust and unload the shock tunnel of quick-fried efficiency and unload quick-fried device |
| CN109799055B (en) * | 2019-02-14 | 2020-09-01 | 重庆交通大学 | Shock tunnel explosion-discharging device capable of continuously and uniformly adjusting explosion-discharging efficiency |
| CN110044576A (en) * | 2019-05-23 | 2019-07-23 | 重庆大学 | Realize the mobile shunting device of wind-tunnel plane of inlet |
| CN110044576B (en) * | 2019-05-23 | 2024-01-26 | 重庆大学 | Bypass device for realizing plane movement of wind tunnel inlet |
Also Published As
| Publication number | Publication date |
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| CN103149007B (en) | 2015-08-12 |
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Effective date of registration: 20231116 Address after: 511458 Room 501, building 1, 1119 Haibin Road, Nansha District, Guangzhou City, Guangdong Province Patentee after: Guangdong Aerospace Science and Technology Research Institute (Nansha) Address before: 100190, No. 15 West Fourth Ring Road, Beijing, Haidian District Patentee before: INSTITUTE OF MECHANICS, CHINESE ACADEMY OF SCIENCES |