CN107054673A - It is a kind of to synthesize dual-jet driver and hypersonic flow flowing control method from maintenance - Google Patents
It is a kind of to synthesize dual-jet driver and hypersonic flow flowing control method from maintenance Download PDFInfo
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- CN107054673A CN107054673A CN201710512339.3A CN201710512339A CN107054673A CN 107054673 A CN107054673 A CN 107054673A CN 201710512339 A CN201710512339 A CN 201710512339A CN 107054673 A CN107054673 A CN 107054673A
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- 238000012423 maintenance Methods 0.000 title claims abstract description 27
- 238000000034 method Methods 0.000 title claims abstract description 15
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 45
- 238000003786 synthesis reaction Methods 0.000 claims abstract description 44
- 239000012528 membrane Substances 0.000 claims abstract description 22
- 239000000919 ceramic Substances 0.000 claims description 8
- 238000012856 packing Methods 0.000 claims description 3
- 230000035939 shock Effects 0.000 description 10
- 230000000694 effects Effects 0.000 description 9
- 230000002194 synthesizing effect Effects 0.000 description 9
- 238000005516 engineering process Methods 0.000 description 7
- 238000000926 separation method Methods 0.000 description 7
- 239000010410 layer Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 239000012530 fluid Substances 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 230000009467 reduction Effects 0.000 description 4
- 230000002411 adverse Effects 0.000 description 3
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 230000005284 excitation Effects 0.000 description 3
- 230000002349 favourable effect Effects 0.000 description 3
- 238000011084 recovery Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 208000002925 dental caries Diseases 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 230000012447 hatching Effects 0.000 description 1
- 238000002513 implantation Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000002243 precursor Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000002604 ultrasonography Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Reciprocating Pumps (AREA)
Abstract
The invention belongs to flow control technique and aircraft field, it is related to a kind of from maintenance synthesis dual-jet driver and hypersonic flow control method.From maintaining to offer two entrances, two outlets on synthesis dual-jet driver described in the inventive method, described two entrances are placed in flow field higher-pressure region；Described two outlets are placed in flow field low-pressure area.Include the first cavity plate 1, the second cavity plate 2, exit plate 3, installing plate 4 and vibrating membrane 5 from synthesis driver is maintained；The first cavity plate 1, the second cavity plate 2 and exit plate 3 surround internal cavities jointly, and internal cavities are divided on the first cavity 6 and the second cavity 7, the installing plate by the installing plate 4 opens up a port for installing vibrating membrane 5；First entrance 8, first outlet 9 are offered in the corresponding exit plate of first cavity；Second entrance 10, second outlet 11 are offered in the corresponding exit plate of second cavity；The vibrating membrane is arranged on the passage port of installing plate.
Description
Technical field
The invention belongs to flow control technique and supersonic speed/hypersonic aircraft field, and in particular to a kind of from maintenance
Synthesize dual-jet driver and hypersonic flow flowing control method.
Background technology
Hypersonic aircraft refers to Mach 5 or more speed in atmosphere and across the aircraft flown in atmosphere.
Unstart phenomena occurs under less than design Mach number in hypersonic inlet, and the inoperative of air intake duct can cause air intake duct to be caught
Flow reduction, total pressure recovery reduction are obtained, engine misses can be caused when serious, the flight of hypersonic aircraft is seriously endangered
Accident can be even resulted in.So control hypersonic inlet flow field, improvement intake duct starting performance are studied as air intake duct
One of emphasis.
Flow control technique especially emerging synthesizing jet-flow/dijection flow control technology is considered as that can control air intake duct
One of flow field method.Correlative study shows that synthesizing jet-flow/dijection flow control technology has been successfully applied in subsonic speed flow field,
In boundary layer control, it can significantly delay the separation in boundary layer；In the control of Subsonic inlet interior flow field, energy
Enough suppress Secondary Flow and the flow distortion of air intake duct, improve inlet characteristic.
Current synthesizing jet-flow/dual-jet flow field control mode is applied only for Subsonic inlet and boundary layer separation control
System, the application in supersonic speed/hypersonic inlet not yet has correlative study, traditional synthesizing jet-flow/dual-jet excitation
Device produce jet energy is relatively low relative to main flow energy, control effect is not obvious.
The content of the invention
In order to solve the above technical problems, the present invention is on the synthesis dual-jet driver basis for solving diaphragm ballast Problem of Failure
On, propose that as its name suggests, it makes full use of supersonic speed/hypersonic inlet flow field special from synthesis dual-jet driver is maintained
Property, air inlet is arranged in high pressure Disengagement zone, gas outlet is placed in low-pressure area, pressure differential, which flows, between Liang Kou forms from dimension
Jet is held, the vibration of synthesis dual-jet driver diaphragm can increase the energy of jet, while modulating the frequency and vorticity of jet
Feature, is realized to air intake duct flow field control.Concrete technical scheme is as follows：
A kind of hypersonic flow flowing control method, it is described from maintenance synthesis dijection using from synthesis dual-jet driver is maintained
Two entrances, two outlets are offered on stream driver, described two entrances are placed in flow field higher-pressure region；By described two outlets
It is placed in flow field low-pressure area.
Present invention also offers a kind of from maintaining synthesis dual-jet driver, including the first cavity plate 1, the second cavity plate 2,
Exit plate 3, installing plate 4 and vibrating membrane 5；The first cavity plate 1, the second cavity plate 2 and exit plate 3 surround internal sky jointly
Chamber, internal cavities are divided on the first cavity 6 and the second cavity 7, the installing plate by the installing plate 4 opens up a port use
In installation vibrating membrane 5；First entrance 8, first outlet 9 are offered in the corresponding exit plate of first cavity；Described second is empty
Second entrance 10, second outlet 11 are offered in the corresponding exit plate of chamber；The vibrating membrane is arranged on the passage port of installing plate, uses
In separating first cavity and the second cavity.
Preferably, the junction of the vibrating membrane 5 and the installing plate 4 is provided with packing ring.
Preferably, the vibrating membrane 5 is piezoelectric ceramics diaphragm.
Preferably, the vibrating membrane 5 is circular film.
The beneficial effect obtained using the present invention：
1st, driver diaphragm is not influenceed by ballast.The present invention is from the unique configuration of synthesis dual-jet driver is maintained, effectively
Ground solves vibrating diaphragm ballast Problem of Failure.In supersonic flight, the precursor compression wedge of air intake duct carrys out stream to high speed and subtracted
Speed supercharging, research shows：The cavity internal pressure of driver is 14 times of incoming-flow pressure when free stream Mach number reaches 3.5.Therefore, by force
Ballast will cause synthesizing jet-flow excitor diaphragm can not normal work, or even will destroy driver structure.It is double from maintenance synthesis
Jet-flow excitor remains the advantage of synthesis dual-jet driver, and using a film double cavity structure, two cavity pressure sizableness swash
Encourage device diaphragm both sides and bear identical ballast, it ensure that can be in supersonic flow field environment from maintenance synthesis dual-jet driver
Normal work.
2nd, self-sustaining cycle design of the present invention can effectively improve jet energy with reference to driver diaphragm vibration.The present invention is maintained certainly
Synthesis dual-jet driver can drive to form self-sustaining cycle jet using pressure differential, from maintenance synthesis dual-jet driver air inlet
Mouth suction boundary-layer low energy gas, can stablize Disengagement zone, export to the higher jet of boundary-layer Implantation Energy, can delay
Flow separation, is conducive to reducing pitot loss.Gas outlet can induce weak shock to supersonic speed/Hypersonic Flow Field jetting stream,
Weak shock can weaken the intensity of downstream shock wave, be conducive to drag reduction drop heat and aerodynamic force control.Vibration vibration of membrane can increase
The energy of jet, while modulating the frequency and vorticity feature of jet, is realized to air intake duct flow field control.
3rd, configuration design of the present invention is obvious to the small, small volume of air intake duct configuration destruction, light weight and control effect.It is existing
Synthesizing jet-flow/synthesis dual-jet driver in technology is that single outlet produces jet in single-chamber, and driver opening is long to be caused
Inlet structure is destroyed to a certain extent, and can not produce self-holding circulating jet, and correlative study shows, only by excitation
It is unobvious to Supersonic Stream control effect that device diaphragm vibration produces jet.If being opened from synthesis dual-jet is maintained on air intake duct surface
Dry hole, reduces the destruction to inlet structure as far as possible.In addition, from synthesis dual-jet driver is maintained also with small volume, matter
The features such as measuring light, maximum can make Supersonic Inlet self-starting Mach number reduce by 0.5, and can significantly improve air intake duct
Total pressure recovery coefficient and discharge coefficient.
4th, driver of the present invention forms double from maintaining synthesizing jet-flow control effect good, and capacity usage ratio is high.From maintenance synthesis
Dual-jet driver is four mouthfuls of a film two-chamber, and a film double cavity structure, which can form two self-sustaining cycles arranged side by side and inhale, blows jet, and
And the vibrational energy of vibrating membrane can be made full use of, energy utilization efficiency is twice of common synthesizing jet-flow excitor, work frequency
Rate is also twice of synthesizing jet-flow.
5th, the present invention is applied widely.In supersonic speed/Hypersonic Flow Field, shock wave, flow separation etc. are widely present non-
Steady Flow phenomenon, these phenomenons can all cause part flow field pressure to produce change drastically.Encouraged from synthesis dual-jet is maintained
Device mainly uses the barometric gradient characteristic in supersonic speed/Hypersonic Flow Field, by the way that air inlet is positioned over into higher-pressure region, outlet
Mouth is positioned over low-pressure area, is controlled by pressure differential formation from maintenance jet stream field.So the present invention can be fitted widely
For supersonic speed/Hypersonic Flow Field control.In summary, the present invention makes full use of itself energy of supersonic speed/Hypersonic Flow Field
Amount, realizes control to supersonic speed/Hypersonic Flow Field effectively, with energy consumption is low, simple in construction, small light, electrical parameter control
System, advantage applied widely.
Brief description of the drawings
Fig. 1 the inventive method operating diagrams；
Fig. 2 synthesizes dual-jet driver schematic diagram for the present invention from maintenance；
Fig. 3 synthesizes the sectional view of dual-jet driver for the present invention from maintenance；
Fig. 4 synthesizes dual-jet driver two-dimensional working simplified principle figure for the present invention from maintenance；
Interior flow field figure when Fig. 5 is controls flow field under two dimensional surface from maintenance synthesis dual-jet driver；
Fig. 6 is effect inlet location figure under driver two dimensional surface of the present invention.
Embodiment
The invention will be further described with reference to the accompanying drawings and examples.
As shown in figure 1, the inventive method operating diagram.It is a kind of hypersonic flow flowing control method in figure, using dimension certainly
Synthesis dual-jet driver is held, it is described that two entrances, two outlets are offered from maintenance synthesis dual-jet driver, will be described
Two entrances are placed in flow field higher-pressure region；Described two outlets are placed in flow field low-pressure area.Dotted line represents fluid in driver in figure
Internal flow direction.Using supersonic flow field barometric gradient, formed two mouthfuls of the outlet of the entrance gone by high pressure and low-pressure area
Between pressure differential flow to be formed from jet is maintained, the effect of vibration of piezoelectric ceramics diaphragm is increase jet energy, is modulated simultaneously
The frequency and vorticity feature of jet.The inventive method is under pressure-driven, and fluid is flowed into from entrance, is flowed out through cavity from outlet,
High-speed jet is formed, the jet need not inject outside energy, Field Characteristics can be made full use of voluntarily to maintain, realized to supersonic speed
The control in flow field.Barometric gradient can be the favorable pressure gradient in the adverse pressure gradient or flow field formed after shock wave front.Excitation
The vibration of device vibrating diaphragm can increase the energy of jet, while modulating the characteristic frequency and vorticity fluctuation of jet, realize to super
The control in velocity of sound flow field.
As shown in Fig. 2 the present invention synthesizes dual-jet driver schematic diagram from maintenance；The present invention is to supersonic speed/high ultrasound
Fast flow field travel direction control, Supersonic Inlet interior flow field quality can be effectively improved in interior flow field control, improves super
Starting performance of the velocity of sound air intake duct under less than design Mach number, specially reduces the self-starting Mach number of air intake duct, improves total
Press recovery coefficient and Flow coefficient of inlet.It is also possible to supersonic aircraft Flow Field outside is controlled, such as shock wave, side
Interlayer is controlled, and realizes drag reduction, drop heat, aerodynamic force control.In embodiment by taking the control of supersonic aircraft Flow Field In An Inlet as an example
Illustrate.
The present invention synthesizes the sectional view of dual-jet driver from maintenance as shown in Figure 3；A-A, B-B, C-C tri- along along figure (a)
Bar hatching respectively obtains corresponding figure (b), figure (c) and figure (d) three sectional views.From figure (a), figure (b), figure (c), figure (d)
In obtain the present invention from maintaining synthesis dual-jet driver concrete composition structure, including the first cavity plate 1, goes out second cavity plate 2
Oralia 3, installing plate 4 and vibrating membrane 5；The first cavity plate 1, the second cavity plate 2 and exit plate 3 surround internal cavities jointly,
Internal cavities are divided on the first cavity 6 and the second cavity 7, the installing plate by the installing plate 4 to be opened up a port and is used for
Vibrating membrane 5 is installed；First entrance 8, first outlet 9 are offered in the corresponding exit plate of first cavity；Second cavity
Second entrance 10, second outlet 11 are offered in corresponding exit plate；The vibrating membrane is arranged on the passage port of installing plate, is used for
Separate first cavity and the second cavity.In embodiment, each cavity plate is with exit plate by being threaded hole and using bolt
It is fixed, can also be integrated by bonding or by Mold Making.Vibrating membrane 5 uses piezoelectric ceramics diaphragm,
Between two cavitys, packing ring is provided between piezoelectric ceramics diaphragm and installing plate.
Fig. 4 be under two-dimensional case from maintaining synthesis dual-jet fundamental diagram, in order to realized in Two-dimensional numerical simulation from
Maintain the function of synthesis dual-jet, in figure will from maintain synthesis dual-jet driver be reduced to a cavity, one outlet plate and
One piezoelectric ceramics diaphragm, wherein left hand inlet port are marked with flow higher-pressure region, and right-side outlet is marked with flow low-pressure area, fluid from
High-pressure side flows into driver and sprayed from low pressure port, is formed from jet is maintained, the effect of vibration of piezoelectric ceramics diaphragm is that increase is penetrated
Stream energy, while the frequency and vorticity feature of jet are modulated, due in two dimensional configurations, it is impossible to realize that vibrating membrane is located at two cavitys
Middle situation, so vibrating membrane is simplified to driver bottom, it is two-dimentional from the operation principle and three-dimensional that maintain synthesis dual-jet
From maintaining, synthesis dual-jet operation principle is consistent, is all to utilize supersonic speed/hypersonic inlet flow field characteristic, by air inlet cloth
Flow higher-pressure region is placed in, gas outlet is placed in low-pressure area, pressure differential, which flows, between Liang Kou forms from jet is maintained, and synthesis is double
The vibration of jet-flow excitor diaphragm can increase the energy of jet, while modulating the frequency and vorticity feature of jet, realize to entering
Air flue flow field control.The change of vibration film location is intended merely to realize the function of only maintaining synthesis dual-jet in two-dimensional space.
Interior flow field figure when Fig. 5 is controls flow field under two dimensional surface from maintenance synthesis dual-jet driver；From the stream in figure
Line and pressure distribution can be seen that gas and flowed into from high pressure entry, from low tension outlet outflow, and driver can be formed to be closed from maintenance
Supersonic flow field is controlled into jet.
Fig. 6 is the two-dimentional sketch being placed in from maintenance synthesis dual-jet driver in Supersonic Inlet.It is two to scheme (a)
The lower inlet location overall schematic of dimension effect, figure (b), figure (c) are the partial enlarged drawing under different situations.According to grinding before
Study carefully result to understand, make full use of supersonic speed/Hypersonic Flow Field barometric gradient feature, air inlet is (i.e.：First entrance, second enter
Mouthful) higher-pressure region is placed in, gas outlet is (i.e.：First outlet, second outlet) it is placed in low-pressure area.Supersonic speed/Hypersonic Flow Field
Pressure distribution gradient, is primarily referred to as the favorable pressure gradient of supersonic speed/Hypersonic Flow Field proper flow and due to shock wave, flowing
Adverse pressure gradient caused by the UNSTEADY FLOW phenomenons such as separation, shown in such as cloud atlas (b), (c).Scheme the favorable pressure gradient of (b) using flow field,
Driver air inlet of the present invention is located at the dot again of compression section separate bubble in air intake duct, using the higher-pressure region formed after shock wave, and
Gas outlet is located on distance piece, and pressure is relatively low herein, and pressure differential is formed between outlet and entrance；Figure (c) utilizes adverse pressure gradient, this
Invention driver air inlet is located at the dot again of air intake duct separate bubble, and gas outlet is located in stream compression face, before and after separate bubble
Pressure differential.Under the vibration of piezoelectric ceramics diaphragm, the low energy fluid of air inlet suction separation, outlet sprays kinetic energy and penetrated
Stream, reaches the effect in control air intake duct flow field.From the periodicity that synthesis dual-jet driver is produced is maintained from maintenance synthesis dijection
Stream, supersonic speed/Hypersonic Flow Field shock wave, shock wave boundary layer interaction and flowing is controlled using from maintenance synthesis dual-jet driver
The flow phenomenons such as separation, so as to realize effective control to supersonic speed/Hypersonic Flow Field.For structure of the present invention size and
Outlet and the relation of entrance, the present invention not are fixed from the size and dimension of synthesis dual-jet driver is maintained, and being can be with
According to changing the need for controlled flow field, but the basic configuration of film two-chamber four of the invention outlet and formed using fluid field pressure gradient
It is constant from the basic thought for maintaining synthesis dual-jet stream field to be controlled.
It is described above, only it is the present embodiment, any limitation is not done to the present invention.It is any to be familiar with those skilled in the art
Member, in the case where not departing from technical solution of the present invention scope, all using the technology contents of the disclosure above to the technology of the present invention
Scheme makes many possible equivalent embodiments for changing, modifying or be revised as equivalent variations.Therefore, it is every without departing from the present invention
The content of technical scheme, according to the technology of the present invention essence is to any simple modification made for any of the above embodiments, equivalent variations and repaiies
Decorations, all should fall in the range of technical solution of the present invention protection.
Claims (5)
1. a kind of hypersonic flow flowing control method, described from maintenance synthesis dual-jet using from synthesis dual-jet driver is maintained
Two entrances, two outlets are offered on driver, it is characterised in that：Described two entrances are placed in flow field higher-pressure region；By institute
State two outlets and be placed in flow field low-pressure area.
2. it is a kind of from maintenance synthesis dual-jet driver, it is characterised in that：Including the first cavity plate (1), the second cavity plate (2),
Exit plate (3), installing plate (4) and vibrating membrane (5)；The first cavity plate (1), the second cavity plate (2) and exit plate (3) are common
Internal cavities are surrounded, internal cavities are divided into the first cavity (6) and the second cavity (7), the installing plate by the installing plate (4)
On open up a port be used for vibrating membrane (5) is installed；Offered in the corresponding exit plate of first cavity first entrance (8),
First outlet (9)；Second entrance (10), second outlet (11) are offered in the corresponding exit plate of second cavity；It is described to shake
Dynamic film is arranged on the passage port of installing plate, for separating first cavity and the second cavity.
3. it is as claimed in claim 2 a kind of from maintenance synthesis dual-jet driver, it is characterised in that：The vibrating membrane (5) with
The junction of the installing plate (4) is provided with packing ring.
4. it is as claimed in claim 3 a kind of from maintenance synthesis dual-jet driver, it is characterised in that：The vibrating membrane (5) is
Piezoelectric ceramics diaphragm.
5. it is as claimed in claim 4 a kind of from maintenance synthesis dual-jet driver, it is characterised in that：The vibrating membrane (5) is
Circular film.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710512339.3A CN107054673A (en) | 2017-06-29 | 2017-06-29 | It is a kind of to synthesize dual-jet driver and hypersonic flow flowing control method from maintenance |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710512339.3A CN107054673A (en) | 2017-06-29 | 2017-06-29 | It is a kind of to synthesize dual-jet driver and hypersonic flow flowing control method from maintenance |
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| CN107054673A true CN107054673A (en) | 2017-08-18 |
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| CN201710512339.3A Pending CN107054673A (en) | 2017-06-29 | 2017-06-29 | It is a kind of to synthesize dual-jet driver and hypersonic flow flowing control method from maintenance |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109760818A (en) * | 2019-03-21 | 2019-05-17 | 中国人民解放军国防科技大学 | Supersonic velocity boundary layer transition control method based on novel synthetic double-jet actuator |
| CN110035635A (en) * | 2018-01-12 | 2019-07-19 | 广达电脑股份有限公司 | The combination of air pipeline and electronic device |
| CN118128641A (en) * | 2024-05-08 | 2024-06-04 | 中国人民解放军国防科技大学 | Wide-speed-range air inlet channel control device, control method and aircraft air inlet system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104154512A (en) * | 2014-07-10 | 2014-11-19 | 中国人民解放军国防科学技术大学 | LED lamp heat radiation device based on synthetic double-jet exciter |
| CN104168743A (en) * | 2014-07-10 | 2014-11-26 | 中国人民解放军国防科学技术大学 | Vector synthesis dual-jet exciter-based electronic element and heat radiation method thereof |
| CN104554712A (en) * | 2013-10-16 | 2015-04-29 | 波音公司 | Frequency response and health tracker for a synthetic jet generator |
| CN104859843A (en) * | 2014-02-21 | 2015-08-26 | 波音公司 | Plasma-assisted Synthetic Jets For Active Air Flow Control |
-
2017
- 2017-06-29 CN CN201710512339.3A patent/CN107054673A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554712A (en) * | 2013-10-16 | 2015-04-29 | 波音公司 | Frequency response and health tracker for a synthetic jet generator |
| CN104859843A (en) * | 2014-02-21 | 2015-08-26 | 波音公司 | Plasma-assisted Synthetic Jets For Active Air Flow Control |
| CN104154512A (en) * | 2014-07-10 | 2014-11-19 | 中国人民解放军国防科学技术大学 | LED lamp heat radiation device based on synthetic double-jet exciter |
| CN104168743A (en) * | 2014-07-10 | 2014-11-26 | 中国人民解放军国防科学技术大学 | Vector synthesis dual-jet exciter-based electronic element and heat radiation method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 罗振兵，夏智勋等: ""合成双射流及其流动控制技术研究进展"", 《空气动力学学报》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110035635A (en) * | 2018-01-12 | 2019-07-19 | 广达电脑股份有限公司 | The combination of air pipeline and electronic device |
| CN110035635B (en) * | 2018-01-12 | 2020-12-04 | 广达电脑股份有限公司 | Combination of air duct and electronic device |
| CN109760818A (en) * | 2019-03-21 | 2019-05-17 | 中国人民解放军国防科技大学 | Supersonic velocity boundary layer transition control method based on novel synthetic double-jet actuator |
| CN109760818B (en) * | 2019-03-21 | 2020-11-20 | 中国人民解放军国防科技大学 | Supersonic velocity boundary layer transition control method based on synthetic double-jet actuator |
| CN118128641A (en) * | 2024-05-08 | 2024-06-04 | 中国人民解放军国防科技大学 | Wide-speed-range air inlet channel control device, control method and aircraft air inlet system |
| CN118128641B (en) * | 2024-05-08 | 2024-07-12 | 中国人民解放军国防科技大学 | Wide-speed-range air inlet channel control device, control method and aircraft air inlet system |
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Application publication date: 20170818 |