CN103149007B - A kind of detonation driven shock tunnel shaping membrane - Google Patents
A kind of detonation driven shock tunnel shaping membrane Download PDFInfo
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- CN103149007B CN103149007B CN201310033882.7A CN201310033882A CN103149007B CN 103149007 B CN103149007 B CN 103149007B CN 201310033882 A CN201310033882 A CN 201310033882A CN 103149007 B CN103149007 B CN 103149007B
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- shock tunnel
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- 238000005474 detonation Methods 0.000 title claims abstract description 40
- 239000012528 membrane Substances 0.000 title claims abstract description 39
- 230000035939 shock Effects 0.000 title claims abstract description 36
- 238000007493 shaping process Methods 0.000 title claims abstract description 25
- 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
- 239000007789 gas Substances 0.000 description 8
- 238000005516 engineering process Methods 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- 238000011161 development Methods 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 239000002360 explosive Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 235000021152 breakfast Nutrition 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 238000007781 pre-processing Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000013461 design Methods 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
- 238000004088 simulation Methods 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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- Diaphragms And Bellows (AREA)
Abstract
The invention discloses a kind of detonation driven shock tunnel shaping membrane, comprising: membrane body, be formed with protuberance at the center of membrane body, described protuberance offers the groove with predetermined depth.The present invention has the membrane body of protuberance by being formed, and on protuberance, offer the groove with predetermined depth, like this, detonation driven shock tunnel shaping membrane is when detonation wave propagates arrival, can break fully fast according to designing the mode of specifying, reduce the energy that rupture of membranes needs, reduce rupture disc move distance and speed, further increase the scope can simulated for hypersonic flowing of detonation driven shock tunnel.
Description
Technical field
The present invention relates to the technology of detonation driven shock tunnel raising wind-tunnel driving force 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 the test air-flow that can produce high stagnation temperature and high flow rate on ground.Detonation driven shock tunnel utilize can the quick detonation of explosive gas produce high temperature and high pressure gas compress empty experimental gas, make it a kind of shock tunnel technology reaching higher stagnation temperature and stagnation pressure.
First detonation driven shock tube is proposed in nineteen fifty-seven by Bird, and the Yu Hongru researcher of Inst. of Mechanics, CAS has built the long detonation driven shock tube of a 13.3m in 1981, and comes into operation in nineteen eighty-three.Apply this shock tube, systematic study oxygen hydrogen detonation driven method, what propose reverse detonation driven unloads quick-fried technology, build up JF-10 detonation driven high enthalpy shock tunnel [see performance-aerodynamic testing and the Survey control of the oxygen hydrogen detonation driven shock tunnel of Yu Hongru, Zhao Wei, Yuan Shengxue, 1993,7 (3): 38-42].Under the help of Yu Hongru researcher, the people such as Gronig has built the high enthalpy shock tunnel (TH2-D) of the reverse detonation driven of application in 1993 in Aachen, Germany polytechnical university.1994, NASA revised the design proposal that original free-piston drives, and builds up built forward-running detonation drivers for high-enthalpy shock tunnels (HYPULSE) at GASL, 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, can obtain the test period of 30 ~ 80ms when simulating stagnation temperature and being less than 2000K, be apply one of very successful wind-tunnel in hypersonic flowing ground simulation test.
In detonation driven shock tunnel, the thicker diaphragm of usual employing is isolated can explosive gas and by driving air, very high pressure and temperature is formed after detonation initiation, can promptly make can explosive gas and by the rupture of diaphragm driven between air, and then formed to by the airborne intense shock wave of driving, realize the operation of detonation driven high enthalpy shock tunnel.Diaphragm adopts the good stainless steel material of ductility usually, rupture of diaphragm formed fragment less, and detonation pressure more 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 not easily opened in the short period of time fully, result in the decline of detonation driven shock tunnel driving force, does not reach required high stagnation temperature and the requirement of stagnation pressure test gas.
Summary of the invention
For prior art Problems existing, the object of the present invention is to provide a kind of detonation driven shock tunnel shaping membrane, in detonation driven shock tunnel runs, diaphragm can break fast, 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, is formed with protuberance at the center of membrane body, and described protuberance offers the groove with predetermined depth.
Preferably, described groove is two cross-like groove intersected to form.
Preferably, the degree of depth of described groove is the half of the 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 being formed, and on protuberance, offer the groove with predetermined depth, like this, detonation driven shock tunnel shaping membrane is when detonation wave propagates arrival, can break fully fast according to designing the mode of specifying, reduce the energy that rupture of membranes needs, reduce rupture disc move distance and speed, further increase the scope can simulated for hypersonic flowing of detonation driven shock tunnel.
Accompanying drawing explanation
Based on the non-limiting example in accompanying drawing below, the invention will be further elaborated below.
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 arrow A direction in Fig. 1.
Embodiment
As Fig. 1,2 shows, detonation driven section 1 is connected with being driven section 3 by flange, adopts shaping stainless steel shaping membrane body 2 in detonation driven section 1 with by the isolation diaphragm driven between section 3.Stainless steel shaping membrane body 2 has the protuberance 4 of center hemispherical projections shape, and its radius is spherical radius, and select 70% of detonation driven section pipe 1 radius, transitional region adopts arc transition.At the criss-cross groove 5 of protuberance 4 surface working of stainless steel shaping membrane body 2, the degree of depth of groove 5 is the half of the thickness of shaping membrane body 2.
Adopt the shaping membrane of band protuberance 4 and cross-like groove, when the gas pressure difference improving diaphragm both sides is gradually split to diaphragm, the diaphragm protruding shape bears material stress to be increased to center gradually from outer rim, center material stress is maximum, shaping membrane breaks from center, and preprocessing cross-like groove ensures the crisscross grooves future development of the development in crack according to expection.Therefore, after adopting shaping membrane, diaphragm breaks according to the mode of expection setting, relative to the random breakage mode of flat diaphragm, can reduce the broken film of the generation of broken film in diaphragm process, particularly bulk, avoid wind-tunnel downstream other parts by the broken membrane damage of high-speed motion.
This invention by carrying out preprocessing to stainless steel diaphragm, making its central area have initial specific spherical shape, and processes the square groove structure of designated depth at its center.In the application that detonation driven shock tunnel runs, the stainless steel diaphragm after shaping 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.
Detonation driven shock tunnel shaping membrane is when detonation wave propagates arrival, can break fully fast according to designing the mode of specifying, reduce the energy that rupture of membranes needs, reduce rupture disc move distance and speed, further increase the scope can simulated for hypersonic flowing of detonation driven shock tunnel.
By adopting shaping membrane technology, in shock tunnel running, diaphragm quality can be made to lose and to be decreased to 1 ~ 2% than ([experiment front diaphragm quality-experiment rear film quality]/experiment 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, is formed with protuberance at the center of membrane body, and described protuberance offers the groove with predetermined depth; Described groove is the square groove in its center processing designated depth.
2. shaping membrane as claimed in claim 1, it is characterized in that, described groove is two cross-like groove intersected to form.
3. shaping membrane as claimed in claim 1 or 2, it is characterized in that, the degree of depth of described groove is the half of the thickness of described membrane body.
4. shaping membrane as claimed in claim 3, it is characterized in that, described protuberance is hemispherical.
5. shaping membrane as claimed in claim 4, it is characterized in that, described membrane body is stainless steel material.
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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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| Application Number | Priority Date | Filing Date | Title |
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| 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 CN103149007A (en) | 2013-06-12 |
| CN103149007B true CN103149007B (en) | 2015-08-12 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
| 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 |
| CN110044576B (en) * | 2019-05-23 | 2024-01-26 | 重庆大学 | Bypass device for realizing plane movement of wind tunnel inlet |
| CN110595719B (en) * | 2019-09-10 | 2024-09-27 | 中国空气动力研究与发展中心超高速空气动力研究所 | Shock tunnel with isolating device |
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 |
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| CN103149007A (en) | 2013-06-12 |
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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 |