CN102407947A - Shock tunnel detonation double-driving method and device - Google Patents
Shock tunnel detonation double-driving method and device Download PDFInfo
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- CN102407947A CN102407947A CN2011102325911A CN201110232591A CN102407947A CN 102407947 A CN102407947 A CN 102407947A CN 2011102325911 A CN2011102325911 A CN 2011102325911A CN 201110232591 A CN201110232591 A CN 201110232591A CN 102407947 A CN102407947 A CN 102407947A
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- 238000005474 detonation Methods 0.000 title claims abstract description 134
- 230000035939 shock Effects 0.000 title claims abstract description 38
- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000012360 testing method Methods 0.000 claims description 9
- 230000000644 propagated effect Effects 0.000 claims description 3
- 230000004913 activation Effects 0.000 claims description 2
- 230000003111 delayed effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 3
- 239000012634 fragment Substances 0.000 abstract description 3
- 238000004880 explosion Methods 0.000 abstract 1
- 230000001737 promoting effect Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 8
- 238000004088 simulation Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000009977 dual effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
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Abstract
The invention discloses a shock tunnel detonation double-driving method, which comprises the following steps of: 1) arranging a positive detonation igniter at one end close to an explosion-releasing section, of a shock tunnel detonation driving section and arranging a reverse detonation driving igniter at the end close to a driven section, of the detonation driving section; 2) igniting by the positive detonation igniter, thereby forming a positive driving detonation wave; 3) after transmitting the positive driving detonation wave along the detonation driving section for a preset period of time, igniting by the reverse detonation driving igniter, thereby forming a reverse driving detonation wave; and 4) tearing a diaphragm arranged between the driven section and the detonation driving section by the reverse driving detonation wave and forming a motion shock wave after intersecting the positive driving detonation wave with the reverse driving detonation wave. According to the method, the diaphragm arranged between the driven section and the detonation driving section is torn by the reverse driving detonation wave, the diaphragm is more regularly torn and a diaphragm fragment is difficult to form, thereby being small in interference effect on the flowing of the formed airflow and promoting the flowing quality of the driven air.
Description
Technical field
The present invention relates to a technology of air suction type high-speed aircraft experimental study, particularly be used for the shock tunnel detonation driven method and apparatus of hypersonic aircraft ground-based simulation equipment.
Background technology
In the hypersonic aircraft development process, need a large amount of ground simulation experiments, to obtain aircraft aerodynamic force and propulsion quality data.The pulse mode shock tunnel is that a kind of actv. is simulated the ground-testing plant that hypersonic flight is flowed, and in correlative study, has obtained using widely.The high temperature and high pressure gas that the detonation driven shock tunnel utilizes the detonation of fire gases to form does work, and forms high-intensity motion shock wave and drives shock tunnel is reached enough total enthalpy conditions by the section of driving test gas hypersonic simulation incoming flow.
The detonation driven shock tube is at first proposed in nineteen fifty-seven by Bird.Mr. Yu Hongru of Inst. of Mechanics, CAS has built the long detonation driven shock tube of a 13.3m in 1981, nineteen eighty-three place in operation.Inst. of Mechanics, CAS developed in 1994 JF-10 detonation driven high enthalpy shock tunnel [referring to the performance-aerodynamic testing of the hydrogen-oxygen detonation driven shock tunnel of Yu Hongru, Zhao Wei, Yuan Shengxue with measure control, 1993,7 (3): 38-42].People such as Gronig has built the high enthalpy shock tunnel (TH2-D) of using reverse detonation driven in Aachen, Germany polytechnical university in 1993 under Mr.'s Yu Hongru help.1994, NASA revised the design plan that original free piston drives, and built up at GASL and had built the high enthalpy shock tunnel of forward detonation driven (HYPULSE); This wind-tunnel can work in simultaneously reflected shock wave wind-tunnel pattern and bulged tube pattern [referring to Chue RSM, Tsai C-Y, Bakos RJ; Erdos JI, Rogers RC (2002) NASA ' s HYPULSE Facility at GASL-A Dual Mode, Dual Driver Reflected-Shock/Expansion Tunnel.In:Lu F; Marren D (eds), Advanced Hypersonic Test Facilities, Progress in Astronautics and Aeronautics; Vol.1 98; AIAA, Chapter 3, pp29-7 1].
The forward detonation driven energy of above-mentioned employing is big, and power-handling capability is strong, but the quality that flows receives the influence of Taylor's rarefaction wave behind the detonation wave, and to driving section with bigger by the diaphragm destructive effect between driving section, influences the reliability of wind tunnel test; And the mobile quality of reverse detonation driven is good, and rupture of diaphragm is good, but power-handling capability is weaker than the forward detonation driven.
Summary of the invention
The object of the present invention is to provide two driving methods of a kind of shock tunnel detonation and device, can both can improve the shock tunnel power-handling capability, can improve the rupture of membranes reliability again, thereby improve the mobile quality of wind-tunnel well with forward detonation and reverse detonation combination.
The two driving methods of a kind of shock tunnel detonation of the present invention comprise:
1) end near unloading quick-fried section in shock tunnel detonation driven section is provided with forward detonation ignition device, at the end near being driven section of detonation driven section reverse detonation driven ignition device is set;
2) light a fire through forward detonation ignition device, form the forward drive detonation wave;
3) after the forward detonation wave is propagated the schedule time along the detonation driven section, light a fire, form the reverse drive detonation wave through reverse detonation driven ignition device;
4) the reverse drive detonation wave will be arranged on the diaphragm that is driven between section and the detonation driven section and tear, and the forward detonation wave intersects the back with reverse detonation wave and forms the motion shock wave, and this motion shock wave gets into and driven section, so that the test gas that is driven section is compressed.
Preferably, when said forward detonation wave is transmitted to distance X from said diaphragm less than 50cm, light a fire through said reverse detonation driven ignition device.
The two driving devices of a kind of shock tunnel detonation of the present invention comprise: shock tunnel, and this shock tunnel tool detonation driven section, an end of this detonation driven section is provided with and unloads quick-fried section, and the other end is provided with and is driven section; Be provided with primary diaphragm said unloading between quick-fried section and the detonation driven section, be provided with secondary diaphragm said the driving between section and the detonation driven section; Said detonation driven section be provided with forward detonation driven ignition device near said a section of unloading quick-fried section, be provided with reverse detonation driven ignition device in said detonation driven section near said a section of being driven section; Between said forward detonation driven ignition device and reverse detonation driven ignition device, be connected with controlled activation time delayed device.
The present invention combines the reverse detonation driven of time-delay through the forward detonation driven; To be arranged on the diaphragm that is driven section through reverse detonation driven ripple and tear, forward detonation wave and the crossing back of reverse detonation wave form the motion shock wave and enter into by the driving section, owing to diaphragm is torn by the high pressure that reverse detonation forms; This high pressure is lower than the high pressure that forward detonation forms; Diaphragm is torn more regular, is difficult for forming the diaphragm fragment, thereby makes the air current flow of formation receive interference effect little; Therefore when guaranteeing higher power-handling capability, also improved by the mobile quality of driving gas.
Description of drawings
Below based on the non-limiting example in the figs the present invention is done further elaboration.
Fig. 1 is the two device driven structural representations of detonation of the present invention.
1 unloads quick-fried section, 2 primary diaphragms, and 3 detonation driven sections, 4 secondary diaphragms, 5 are driven section, 6 forward drive detonation ignition devices, 7 first signal wire (SW)s, 8 controlled time-delay triggers, 9 secondary signal lines, 10 reverse drive detonation ignition devices
The specific embodiment
Fig. 1 is the two device driven structural representations of detonation of the present invention.
As shown in Figure 1; The two device driven of detonation of the present invention comprise: shock tunnel 100; This shock tunnel 100 has detonation driven section 3, and an end setting of detonation driven section 3 is unloaded quick-fried section 1, and the other end is provided with and is driven section 5; Unload between quick-fried section 1 and the detonation driven section 3 and be provided with primary diaphragm 2, be provided with secondary diaphragm 4 between section of driving 5 and the detonation driven section 3.The end near unloading quick-fried section 1 in detonation driven section 3 is provided with forward detonation driven ignition device 6, is provided with reverse detonation driven ignition device 10 at the end near being driven section 5 of detonation driven section 3.Between forward detonation driven ignition device 6 and reverse detonation driven ignition device 10, be connected with controlled time-delay trigger 8; Forward detonation driven ignition device 6 is connected with controlled time-delay trigger 8 through first signal wire (SW) 7, and reverse detonation driven ignition device 10 is connected with controlled time-delay trigger 8 through secondary signal line 9.
During use, light a fire through forward detonation ignition device 6 earlier, form the forward drive detonation wave; After the forward detonation wave is propagated the schedule time along detonation driven section 3, during preferably near secondary diaphragm 4, light a fire through reverse detonation driven ignition device 10 again, form the reverse drive detonation wave; At this moment, the reverse drive detonation wave is torn secondary diaphragm 4, and the forward detonation wave intersects the back with reverse detonation wave and forms the motion shock wave, and this motion shock wave gets into and driven section 5, thereby the test gas that is driven section 5 is compressed.Time-delay control is undertaken by controlled time-delay trigger 8.
As for 100 meters long detonation driven section 3, the detonation wave propagation velocity is 2800 meter per seconds for above-mentioned time-delay, and then the spark delay time is at 30～35 milliseconds.Time-delay is provided with and preferably is controlled at the forward detonation wave and triggers during less than 50cm from the distance X of secondary diaphragm 4; Like this high pressure that reverse detonation forms make drive section and driven diaphragm between the section and tear after, forward detonation just in time gets into through the diaphragm zone and is driven section and test gas is compressed.
The present invention is owing to adopt the two driving methods of time-delay;, forward detonation lights oppositely directed detonation wave when being about to arrive secondary diaphragm 4 positions; Secondary diaphragm 4 is torn by the high pressure that reverse detonation forms, and this high pressure is lower than the high pressure that forward detonation forms, and secondary diaphragm 4 is torn more regular; Be difficult for forming the diaphragm fragment, the air current flow of formation receives interference effect little.Therefore when guaranteeing higher power-handling capability, improved by the mobile quality of driving gas.
Claims (3)
1. the two driving methods of shock tunnel detonation is characterized in that, comprising:
1) end near unloading quick-fried section in shock tunnel detonation driven section is provided with forward detonation ignition device, at the end near being driven section of detonation driven section reverse detonation driven ignition device is set;
2) light a fire through forward detonation ignition device, form the forward drive detonation wave;
3) after the forward detonation wave is propagated the schedule time along the detonation driven section, light a fire, form the reverse drive detonation wave through reverse detonation driven ignition device;
4) the reverse drive detonation wave will be arranged on the diaphragm that is driven between section and the detonation driven section and tear, and the forward detonation wave intersects the back with reverse detonation wave and forms the motion shock wave, and this motion shock wave gets into and driven section, so that the test gas that is driven section is compressed.
2. the method for claim 1 is characterized in that, when said forward detonation wave is transmitted to distance X from said diaphragm less than 50cm, lights a fire through said reverse detonation driven ignition device.
3. the two driving devices of shock tunnel detonation is characterized in that, comprising: shock tunnel, and this shock tunnel tool detonation driven section, an end of this detonation driven section is provided with and unloads quick-fried section, and the other end is provided with and is driven section; Be provided with primary diaphragm said unloading between quick-fried section and the detonation driven section, be provided with secondary diaphragm said the driving between section and the detonation driven section; Said detonation driven section be provided with forward detonation driven ignition device near said a section of unloading quick-fried section, be provided with reverse detonation driven ignition device in said detonation driven section near said a section of being driven section; Between said forward detonation driven ignition device and reverse detonation driven ignition device, be connected with controlled activation time delayed device.
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102706533A (en) * | 2012-05-23 | 2012-10-03 | 浙江理工大学 | Device for researching mutual action of shock wave and liquids in different forms |
| CN103149007A (en) * | 2013-01-29 | 2013-06-12 | 中国科学院力学研究所 | Detonation drive shock tunnel forming membrane |
| CN106741938A (en) * | 2016-05-11 | 2017-05-31 | 鲁正祥 | The linear hypersonic speed of stray bullet flies hole passenger plane |
| CN107024355A (en) * | 2017-05-12 | 2017-08-08 | 中国科学院力学研究所 | A kind of method that jet engine high-temperature fuel gas is simulated based on double detonation driven clean gas |
| CN107976294A (en) * | 2017-11-08 | 2018-05-01 | 武汉理工大学 | A kind of device and method for weakening hydrogen detonation shock tube rarefaction wave |
| CN108051176A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high enthalpy tube wind tunnel driving tube body of width Mach number |
| CN111665014A (en) * | 2020-05-20 | 2020-09-15 | 中国科学院力学研究所 | Hypersonic aircraft boundary layer electron density diagnostic system based on high-frequency electrostatic probe |
| CN111693247A (en) * | 2020-06-22 | 2020-09-22 | 中国科学院力学研究所 | Bidirectional detonation driving technology for detonation-driven shock tunnel |
| CN111912597A (en) * | 2020-08-03 | 2020-11-10 | 北京环境特性研究所 | Test system and method for simulating plasma to target scattering spectrum spreading effect |
| CN113916492A (en) * | 2021-12-15 | 2022-01-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Diaphragm-free shock tunnel throat device and test method thereof |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102706533A (en) * | 2012-05-23 | 2012-10-03 | 浙江理工大学 | Device for researching mutual action of shock wave and liquids in different forms |
| CN102706533B (en) * | 2012-05-23 | 2014-09-03 | 浙江理工大学 | Device for researching mutual action of shock wave and liquids in different forms |
| CN103149007A (en) * | 2013-01-29 | 2013-06-12 | 中国科学院力学研究所 | Detonation drive shock tunnel forming membrane |
| CN103149007B (en) * | 2013-01-29 | 2015-08-12 | 中国科学院力学研究所 | A kind of detonation driven shock tunnel shaping membrane |
| CN106741938A (en) * | 2016-05-11 | 2017-05-31 | 鲁正祥 | The linear hypersonic speed of stray bullet flies hole passenger plane |
| CN107024355A (en) * | 2017-05-12 | 2017-08-08 | 中国科学院力学研究所 | A kind of method that jet engine high-temperature fuel gas is simulated based on double detonation driven clean gas |
| CN107976294A (en) * | 2017-11-08 | 2018-05-01 | 武汉理工大学 | A kind of device and method for weakening hydrogen detonation shock tube rarefaction wave |
| CN107976294B (en) * | 2017-11-08 | 2020-01-14 | 武汉理工大学 | Device and method for weakening rarefaction wave of oxyhydrogen detonation shock tube |
| CN108051176B (en) * | 2017-11-29 | 2019-11-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high enthalpy tube wind tunnel of width Mach number drives tube body |
| CN108051176A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high enthalpy tube wind tunnel driving tube body of width Mach number |
| CN111665014A (en) * | 2020-05-20 | 2020-09-15 | 中国科学院力学研究所 | Hypersonic aircraft boundary layer electron density diagnostic system based on high-frequency electrostatic probe |
| CN111665014B (en) * | 2020-05-20 | 2022-02-22 | 中国科学院力学研究所 | Hypersonic aircraft boundary layer electron density diagnostic system based on high-frequency electrostatic probe |
| CN111693247A (en) * | 2020-06-22 | 2020-09-22 | 中国科学院力学研究所 | Bidirectional detonation driving technology for detonation-driven shock tunnel |
| CN111693247B (en) * | 2020-06-22 | 2021-04-20 | 中国科学院力学研究所 | Bidirectional detonation driving method for detonation-driven shock tunnel |
| CN111912597A (en) * | 2020-08-03 | 2020-11-10 | 北京环境特性研究所 | Test system and method for simulating plasma to target scattering spectrum spreading effect |
| CN113916492A (en) * | 2021-12-15 | 2022-01-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Diaphragm-free shock tunnel throat device and test method thereof |
| CN113916492B (en) * | 2021-12-15 | 2022-02-25 | 中国空气动力研究与发展中心超高速空气动力研究所 | Diaphragm-free shock tunnel throat device and test method thereof |
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