CN106968833A - A kind of supersonic speed detonation engine and its propulsion system - Google Patents
A kind of supersonic speed detonation engine and its propulsion system Download PDFInfo
- Publication number
- CN106968833A CN106968833A CN201710197059.8A CN201710197059A CN106968833A CN 106968833 A CN106968833 A CN 106968833A CN 201710197059 A CN201710197059 A CN 201710197059A CN 106968833 A CN106968833 A CN 106968833A
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- Prior art keywords
- propulsion system
- swash plate
- air intake
- combustion chamber
- intake duct
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
Abstract
The invention discloses a kind of propulsion system, including air intake duct and combustion chamber, the ramp assemblies for guiding oblique detonation wave are installed in the combustion chamber, the ramp assemblies include being used to change come the swash plate of flow direction, and the tilt adjustable of the swash plate.Propulsion system provided by the present invention, by the swash plate that the swash plate in the ramp assemblies is set to adjustable angle, when the flow velocity that can be flowed described is different, by the angle of inclination for adjusting the swash plate, adapt to different in flow rate described flow, guarantee is smoothed out to flow pinking, prevents the oblique detonation wave of induction from occurring forward pass, improves the use reliability of the engine.The invention also discloses a kind of supersonic speed detonation engine including above-mentioned propulsion system.
Description
Technical field
The present invention relates to detonation engine apparatus field, more particularly to a kind of propulsion system.Moreover, it relates to
A kind of supersonic speed detonation engine including above-mentioned propulsion system.
Background technology
With the development of hypersonic aircraft, the efficiency of propulsion system becomes restriction motor power and further improved
One of bottleneck, and detonating combustion efficiency of thermal cycle is high, heat release is fast, the supersonic speed propulsion system layout based on detonating combustion
It is compact, it is simple in construction, therefore, pinking base engine can as hypersonic propulsion system potential scheme.
In the prior art, under the conditions of hypersonic, detonation combustor tissue by way of slope induces pinking burns,
In the supersonic speed detonation engine of integration, fuel is sprayed into precursor, is burnt and to flow rapid mixing, and slope is induced at precursor
Oblique detonation wave is produced, is promptly burnt by the premixed gas of detonation wave in combustion chamber, is expanded produce by expansion segment afterwards
Raw thrust.
However, what is considered due to existing pinking base engine is slope induced synthesis detonation wave using fixed angle
Mode tissue detonating combustion, when changing to flow operating mode, ramp angles are fixed, and burning corrugated can produce congestion and cause the oblique quick-fried of induction
Forward pass occurs for seismic wave.
Meanwhile, propulsion system of the prior art, combustion chamber and expanding nozzle are separately provided, because combustion chamber needs mixing
Fuel, therefore, the length of combustion chamber are general all longer, cause the volume of whole propulsion system larger, engine it is complicated.
Therefore, the reliability of propulsion system how is improved, is the current technical issues that need to address of those skilled in the art.
The content of the invention
It is an object of the invention to provide a kind of propulsion system, the propulsion system can effectively be prevented by adjusting the angle on slope
Forward pass occurs for the oblique detonation wave only induced.It is a further object of the present invention to provide a kind of supersonic speed including above-mentioned propulsion system is quick-fried
Shake engine.
To achieve the above object, the present invention provides following technical scheme：
It is provided with a kind of propulsion system, including air intake duct and combustion chamber, the combustion chamber for guiding oblique detonation wave
Ramp assemblies, the ramp assemblies include being used to change come the swash plate of flow direction, and the tilt adjustable of the swash plate.
It is preferred that, the ramp assemblies also include the extensible member for being used to adjust the swash plate angle, and the extensible member is installed
In a side lower part of the swash plate away from the air intake duct, and the swash plate is close to one end of the air intake duct and the burning
Room is hinged.
It is preferred that, the ramp assemblies also include the base for being used to install the swash plate, and one end of the extensible member
It is connected with the base, the other end is connected with the swash plate.
It is preferred that, the swash plate is inclined upwardly to one end away from the air intake duct from one end close to the air intake duct and set
Put.
It is preferred that, the extensible member is to hang the chain being located in the combustion chamber, one end of the chain and the burning
The inwall connection of room, the other end is connected with the swash plate.
It is preferred that, in addition to the controller being connected with the extensible member, the controller is used for：
The flow velocity to flow obtained；
The optimum tilt angle on slope described in the flow relocity calculation flowed according to described so that it is described come flow point combustion after formed
Oblique detonation wave is acted on the wall of expanding nozzle；
The length of the extensible member is adjusted, so that the slope is in optimum tilt angle.
It is preferred that, the one end of the combustion chamber away from the air intake duct is provided with expanding nozzle, and the combustion chamber and institute
State expanding nozzle formation Integrated Combustion room expanding nozzle.
It is preferred that, connected between the air intake duct and the combustion chamber by distance piece.
It is preferred that, the front end of the air intake duct is provided with precursor fuel spray mouthful, and the precursor fuel spray mouthful is used for institute
State and spray into fuel in air intake duct to premix fuel.
The present invention also provides a kind of supersonic speed detonation engine, including the propulsion system described in above-mentioned any one.
It is provided with propulsion system provided by the present invention, including air intake duct and combustion chamber, the combustion chamber for guiding
The ramp assemblies of oblique detonation wave, the ramp assemblies include being used to change come the swash plate of flow direction, and the inclination of the swash plate
Adjustable angle.The propulsion system, can be described by the way that the swash plate in the ramp assemblies to be set to the swash plate of adjustable angle
Come the flow velocity that flows it is different when, by adjusting the angle of inclination of the swash plate, adapt to different in flow rate described flow, it is ensured that quick-fried to flow
Shake is smoothed out, and is prevented the oblique detonation wave of induction from occurring forward pass, is improved the use reliability of the engine.
Supersonic speed detonation engine provided by the present invention be provided with above-mentioned propulsion system, due to the propulsion system have it is upper
Technique effect is stated, therefore, the supersonic speed detonation engine provided with the propulsion system should also be as with corresponding technique effect.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the accompanying drawing used required in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can be with
Other accompanying drawings are obtained according to these accompanying drawings.
Fig. 1 is a kind of structural representation of embodiment of propulsion system provided by the present invention；
Fig. 2 is the mplifying structure schematic diagram of ramp assemblies shown in Fig. 1；
Wherein：1- precursor fuels spray mouthful, 2- premixs fuel, 3- inlet mouths, 4- ramp assemblies, 41- swash plates, 42-
Extensible member, 43- bases, the oblique detonation waves of 5-, A- air intake ducts, B- distance pieces, C- Integrated Combustions room expanding nozzle.
Embodiment
The core of the present invention is to provide a kind of propulsion system, and the propulsion system can effectively be prevented by adjusting the angle on slope
Forward pass occurs for the oblique detonation wave only induced, significantly improves the use reliability of detonation engine.Another core of the present invention is to carry
For a kind of supersonic speed detonation engine including above-mentioned propulsion system.
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
Fig. 1 and Fig. 2 are refer to, Fig. 1 is a kind of structural representation of embodiment of propulsion system provided by the present invention
Figure；Fig. 2 is the mplifying structure schematic diagram of ramp assemblies shown in Fig. 1.
In this embodiment, the air intake duct A that propulsion system is included in air intake duct A and combustion chamber, the propulsion system is main
It is responsible to capture to flow, make more to enter combustion chamber after the compression of air intake duct A precursors to flow；It is provided with combustion chamber for drawing
The ramp assemblies 4 of oblique detonation wave 5 are led, ramp assemblies 4 include being used to change come the swash plate 41 of flow direction, and the inclination of swash plate 41
Adjustable angle, the propulsion system design point is that the speed of incoming flow in hypersonic state, combustion chamber is more than oblique detonating combustion ripple
Flame forward pass speed so that slope induction oblique detonation wave 5 can stablize in combustion chamber position.
The ramp angles of the propulsion system are adjustable, and design point is hypersonic state, carrys out flow velocity in combustion chamber
Flame forward pass speed of the degree more than oblique detonating combustion ripple.
Further, swash plate 41 is inclined upwardly settings from one end close to air intake duct A to one end away from air intake duct A, i.e., oblique
Plate 41 can be come there is provided thrust obliquely in the direction of advance that flows so that is formed to flow under the slope induction of swash plate 41
Oblique detonation wave 5.
Specifically, the ramp assemblies 4 of swash plate 41 also include the extensible member 42 for being used to adjust the angle of swash plate 41, extensible member 42 is installed
In a side lower part of the swash plate 41 away from air intake duct A, and swash plate 41 is hinged close to air intake duct A one end and combustion chamber, i.e. swash plate
41 one end is hinged with combustion chamber, and the other end can be swung up and down in the presence of extensible member 42, and then realizes that swash plate 41 is tilted
The change of angle.In above-mentioned setting, extensible member 42 is arranged on a side lower part of the swash plate 41 away from air intake duct A, can be effective
Reduce high temperature to flow the influence to extensible member 42, it is ensured that the normal of extensible member 42 is used, and is reduced and is damaged, and stability is good.
The propulsion system, by the way that the swash plate 41 in ramp assemblies 4 to be set to the swash plate 41 of adjustable angle, can flow
Flow velocity it is different when, by adjusting the angle of inclination of swash plate 41, adapt to different in flow rate flow, it is ensured that smoothly enter to flow pinking
OK, prevent the oblique detonation wave 5 of induction from occurring forward pass, improve the use reliability of the engine.
On the basis of the respective embodiments described above, ramp assemblies 4 also include the base 43 for being used to install swash plate 41, and stretch
One end of contracting part 42 is connected with base 43, and the other end is connected with swash plate 41.In above-mentioned setting, first end and the base 43 of swash plate 41
It is hinged, the second end is risen in the presence of extensible member 42, one end of extensible member is connected with the second end of swash plate 41, the other end and bottom
Seat 43 is connected.
It is preferred that, extensible member 42 is telescopic oil cylinder.
On the basis of the respective embodiments described above, extensible member 42 can also be to hang the chain set in a combustion chamber, chain
The inwall connection of one end and combustion chamber, the other end is connected with swash plate 41, when the angle of inclination for needing to change swash plate 41 is, by changing
Become the length of chain.
On the basis of the respective embodiments described above, the propulsion system also includes the controller being connected with extensible member 42, control
Device is used for：
Obtain come the flow velocity that flows；
According to come the optimum tilt angle on flow relocity calculation slope that flows, specifically, the optimum tilt angle of above-mentioned swash plate 41
Determination principle be make to come flow point fire after the oblique detonation wave 5 that is formed act on the wall of expanding nozzle, specifically can be by many
Secondary Test Summary comes out the relation between stream flow velocity and the optimum tilt angle on slope, and in this, as the data reference of controller
Foundation；
Then, controller is by adjusting the length of extensible member 42, so that slope is in optimum tilt angle.
On the basis of the respective embodiments described above, the one end of combustion chamber away from air intake duct A is provided with expanding nozzle, and burns
Room is structure as a whole with expanding nozzle, and combustion chamber and expanding nozzle collectively form Integrated Combustion room expanding nozzle C, by oblique pinking
Combustion chamber and thrust expanding nozzle are combined to one piece, can effectively reduce the reflection between oblique detonation wave 5 and expanding nozzle wall
Angle.
On the basis of the respective embodiments described above, connected between air intake duct A and combustion chamber by distance piece B, distance piece B structures
Into the distance piece of the propulsion system, distance piece is located between air intake duct A and Integrated Combustion room expanding nozzle C, and distance piece B is removed
Possess outside the effect that interferes between isolation air intake duct A and combustion chamber, fuel can distance piece it is relatively long away from
From interior further mixing, the entrance in the outlet of distance piece, i.e. combustion chamber forms the uniform flammable premixed gas cmpletely mixed
Body.
On the basis of the respective embodiments described above, air intake duct A front end is provided with precursor fuel spray mouthful 1, precursor fuel spray
Geat 1 is used to spray into fuel into air intake duct A to premix fuel 2.Specifically, air intake duct A has the function of fuel blending, entering
Air flue A preceding body position is provided with precursor fuel spray mouthful 1, and spray is hydrogen fuel, and the fuel of penetrating has certain penetration depth,
The distance of air intake duct A precursors, it is uniform to fuel elementary mixing during distance piece, and fuel just can be completely into air intake duct
Entrance 3, will not overflow from following lip, i.e. inlet mouth 3.
In the propulsion system, due to being provided with precursor fuel spray mouthful 1 in air intake duct A front end, and in air intake duct A and combustion
Setting distance piece B between room is burnt, therefore, fuel can be mixed in air intake duct A precursor portions and distance piece, reach combustion
When burning room, by evenly mixing, the length of combustion chamber can shorten as far as possible, and then form integrative-structure with expanding nozzle,
Integrated Combustion room expanding nozzle C referred herein refers to set length to be enough to form oblique detonation wave in one end of expanding nozzle
Length so that Integrated Combustion room expanding nozzle C total length is relative to combustion chamber of the prior art and expanding nozzle
Length substantially reduce so that the reduction of the length of engine, simplify structure, save cost of manufacture, weight reduction can also drop
The cost of transportation of low engine.
The propulsion system that the present embodiment is provided uses detonating combustion, improves efficiency of combustion, utilizes the oblique of angle adjustable
Slope induction detonates to flow premixed gas so that fully burns, is fully expanded after burning to flow premix gas, and makes full use of tiltedly quick-fried
Expanding nozzle and combustion chamber compact design are integrated by the characteristic of gas expansion after seismic wave 5, greatly shortened, are simplified engine
Structure.
Specifically, this propulsion system is under hypersonic inlet flow conditions, combustion chamber and export expansion type face are combined one
Rise, do not occur the oblique detonation wave 5 of forward pass, premixed gas by what the slope induced synthesis of the adjustable angle of combustion chamber wall surface was stablized
Fuel is burnt by oblique detonation wave 5, and heat is discharged rapidly, and expansion produces thrust.
Moreover, air intake duct A is by the way of preceding body position fuel shifts to an earlier date spray premix, combustion chamber and expansion segment are combined,
The oblique detonation wave 5 of slope induced synthesis of adjustable angle, the integrated hypersonic Jet propulsion system based on detonating combustion.Such as
Shown in Fig. 1, the integrated thermojet is detonated, and oblique pinking propulsion system is main to be expanded by air intake duct A, distance piece, Integrated Combustion room
Jet pipe C, precursor fuel spray mouthful 1 and adjustable angle slope apparatus composition.
The slope of angle adjustable and Integrated Combustion room expanding nozzle C cooperation are the characteristics of propulsion system are maximum.Tool
Body, it is assumed that ramp angles are θ1, the propagation Mach 2 ship of oblique detonation wave 5 M of premixed gasCJ, it is θ for ramp angles1, when next
Flow Mach number M0Between [MUnder, MOn] and have a MUnder>MCJWhen, can be by the oblique detonation wave 5 of slope induction detonation to flow premix gas.
Work as θ1During reduction, MUnderAnd MOnIt can increase simultaneously；Otherwise θ1During increase, MUnderAnd MOnIt can reduce simultaneously.At distance piece end
Before tail, combustion chamber, fuel is sufficiently mixed, and speed is more than the forward pass speed M of oblique detonating combustion ripple0>MCJ, can be lured by slope
Oblique detonation wave 5 is given birth in artificial delivery.When speed of incoming flow is relatively low still above oblique detonating combustion ripple forward pass speed, it is necessary to larger ramp angle
Degree could induce the oblique detonation wave 5 of generation, but ramp angles can not be excessive, otherwise can cause oblique detonation wave 5 and the expansion face produced
Angle it is too big, burning produce congestion, occur forward pass, cause detonation fail.When speed of incoming flow is slightly larger than the oblique forward pass of detonation wave 5 speed
Spend MCJWhen, can be by that can be detonated in pinking in the range of, be adjusted slightly reduction ramp angles so as to avoid occur congestion.Cause
This, ramp angles can be with flexible modulation so that when speed of incoming flow changes from small to big, and ramp angles are from diminishing greatly, it is ensured that can induce
Quick-fried oblique detonation wave 5, but detonation wave is occurred congestion forward pass causes detonation to fail.The slope of appropriate angle passes through induced ultrasonic speed
Carry out manifold archwise shock wave, bowshock is lighted rapidly forms oblique detonation wave 5 to flow combustible gas.At the oblique face of detonation wave 5, fuel is fast
Quick burning, which burns, to be become combustion product and discharges substantial amounts of heat, and oblique detonation wave 5 just acts on expanding nozzle wall, and tiltedly pinking
Ripple 5 and wall angle are small, and the high-temperature combustion product after detonation wave is expanded in jet pipe, speed increase so that propulsion system is produced
Raw thrust.Generally speaking, when speed of incoming flow is more than MCJAfterwards, slope at an angle, induces oblique detonation wave 5, and ensure oblique pinking
Ripple 5 reflects expansion on Integrated Combustion room expansion wall, and ensures that congestion forward pass does not occur for oblique detonation wave 5；Speed of incoming flow increases
After big, control reduces ramp angles, and now slope is still able to the oblique detonation wave 5 that detonates, and ensure that oblique detonation wave 5 is not gathered around
Plug.
In addition to above-mentioned propulsion system, present invention also offers a kind of supersonic speed pinking hair including above-mentioned propulsion system
Motivation, other Each parts of the supersonic speed detonation engine refer to prior art, repeat no more herein.
The embodiment of each in this specification is described by the way of progressive, and what each embodiment was stressed is and other
Between the difference of embodiment, each embodiment identical similar portion mutually referring to.
Propulsion system provided by the present invention is described in detail above.Specific case used herein is to this hair
Bright principle and embodiment is set forth, the explanation of above example be only intended to help to understand the present invention method and its
Core concept.It should be pointed out that for those skilled in the art, not departing from the premise of the principle of the invention
Under, some improvement and modification can also be carried out to the present invention, these are improved and modification also falls into the protection of the claims in the present invention
In the range of.
Claims (10)
1. a kind of propulsion system, it is characterised in that including air intake duct (A) and combustion chamber, is provided with the combustion chamber for luring
The ramp assemblies (4) of oblique detonation wave (5) are led, the ramp assemblies (4) include being used to change come the swash plate (41) of flow direction, and
The tilt adjustable of the swash plate (41).
2. propulsion system according to claim 1, it is characterised in that the ramp assemblies (4) also include being used to adjust institute
The extensible member (42) of swash plate (41) angle is stated, the extensible member (42) is installed on the swash plate (41) away from the air intake duct (A)
A side lower part, and the swash plate (41) is hinged close to one end of the air intake duct (A) with the combustion chamber.
3. propulsion system according to claim 2, it is characterised in that the ramp assemblies (4) also include being used to install institute
State the base (43) of swash plate (41), and one end of the extensible member (42) is connected with the base (43), the other end with it is described
Swash plate (41) is connected.
4. propulsion system according to claim 2, it is characterised in that the swash plate (41) is from close to the air intake duct (A)
One end be inclined upwardly setting to one end away from the air intake duct (A).
5. propulsion system according to claim 2, it is characterised in that the extensible member (42) is located at the combustion chamber to hang
In chain, one end of the chain is connected with the inwall of the combustion chamber, and the other end is connected with the swash plate (41).
6. propulsion system according to claim 2, it is characterised in that the also control including being connected with the extensible member (42)
Device, the controller is used for：
The flow velocity to flow obtained；
The optimum tilt angle on slope described in the flow relocity calculation flowed according to described so that it is described come flow point combustion after formed it is oblique quick-fried
Seismic wave (5) is acted on the wall of expanding nozzle；
The length of the extensible member (42) is adjusted, so that the slope is in optimum tilt angle.
7. the propulsion system according to claim 1 to 6 any one, it is characterised in that the combustion chamber is entered away from described in
One end of air flue (A) is provided with expanding nozzle, and the combustion chamber is sprayed with the room expansion of expanding nozzle formation Integrated Combustion
Manage (C).
8. the propulsion system according to claim 1 to 6 any one, it is characterised in that the air intake duct (A) and the combustion
Burning is connected between room by distance piece (B).
9. the propulsion system according to claim 1 to 6 any one, it is characterised in that the front end of the air intake duct (A) is set
There is precursor fuel spray mouthful (1), the precursor fuel spray mouthful (1) is used to spray into fuel into the air intake duct (A) to premix
Fuel (2).
10. a kind of supersonic speed detonation engine, including propulsion system, it is characterised in that the propulsion system be claim 1 to
Propulsion system described in 9 any one.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108488004A (en) * | 2018-01-25 | 2018-09-04 | 南京航空航天大学 | It is a kind of based on variable inclined wedge angle stay determine detonation engine |
| CN109114591A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | It is a kind of to change the combustion chamber for realizing detonation control by wall angle |
| CN109114590A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | A kind of combustion chamber of movable step control detonation |
| CN109110143A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of unmanned vehicle engine progress mouth device |
| CN109114593A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | A kind of multi-step cascade combustion chamber for controlling detonation |
| CN109140497A (en) * | 2018-07-25 | 2019-01-04 | 南京理工大学 | A kind of combustion chamber for controlling oblique detonation and starting interior detonation point initiation |
| CN109322761A (en) * | 2018-10-12 | 2019-02-12 | 中国空气动力研究与发展中心吸气式高超声速技术研究中心 | High Mach number in-flight engine annular combustion chamber and the oblique detonating combustion method of spiral |
| CN111207009A (en) * | 2019-12-26 | 2020-05-29 | 中国空气动力研究与发展中心 | Method for initiating oblique detonation wave in supersonic velocity airflow by using external instantaneous energy source |
| CN111608820A (en) * | 2020-04-30 | 2020-09-01 | 南京理工大学 | Wedge surface structure for controlling oblique detonation waves by utilizing local large-angle wedge surface |
| CN112648638A (en) * | 2020-12-16 | 2021-04-13 | 南京航空航天大学 | Scramjet engine based on combined combustion law |
| CN112761817A (en) * | 2021-01-28 | 2021-05-07 | 北京理工大学 | Oblique detonation engine combustion chamber spray pipe integrated control method and device |
| CN113048516A (en) * | 2021-04-08 | 2021-06-29 | 中国人民解放军国防科技大学 | Detonation combustion chamber, scramjet engine and hypersonic aircraft |
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| 林志勇: "高静温超声速预混气爆震起爆与发展过程机理研究", 《中国博士学位论文全文数据库工程科技Ⅰ辑》 * |
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