CN108825405A - A kind of full runner of axially symmetric structure RBCC using multistep rocket - Google Patents
A kind of full runner of axially symmetric structure RBCC using multistep rocket Download PDFInfo
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- CN108825405A CN108825405A CN201810716579.XA CN201810716579A CN108825405A CN 108825405 A CN108825405 A CN 108825405A CN 201810716579 A CN201810716579 A CN 201810716579A CN 108825405 A CN108825405 A CN 108825405A
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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
- F02K7/18—Composite ram-jet/rocket engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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- Testing Of Engines (AREA)
Abstract
The invention discloses a kind of full runners of axially symmetric structure RBCC using multistep rocket, including shell, a conical inner body is axially arranged in shell, one section of the front end of the conical inner body is pierced by shell, is pierced by the external compression section that air inlet section is formed between the part of shell and the entrance of shell；Circular passage is formed between shell and conical inner body, which sequentially forms interior compression section, distance piece and the combustion section of air inlet section from front to back, and rear end and the jet pipe of the shell are slidably connected, and jet pipe is connected with circular passage；It is slidably connected between shell and conical inner body, under different rocket mode, shell can slide back and forth relative to conical inner body.A kind of full runner of axially symmetric structure RBCC using multistep rocket, effectively reduces architecture quality and aerodynamic drag, under different modalities, selects corresponding Rocket ejector, improve the performance of rocket.
Description
Technical field
The invention belongs to rocket engine technical fields, and in particular to a kind of axially symmetric structure RBCC using multistep rocket
Full runner.
Background technique
Rocket punching press combines (RBCC) engine to realize wide range of Mach numbers work, and it is adjustable to generally use throat area
Structure changes air intake duct and expansion the adjustable structure changes jet pipe of area.For the structure changes air intake duct of diadactic structure, venturi face
Product, which is adjusted, will lead to entry of combustion chamber part and adjusts with inlet throat or form step structure, for engine performance and
The realization of sealing is unfavorable；For structure changes jet pipe, since body can not be adjusted or be adjusted after matching aircraft
Cost is larger, therefore the expansion area adjusting of jet pipe can only actually realize that part is adjusted.In conclusion the RBCC of diadactic structure
Engine realizes that wide range of Mach numbers need of work pays additional cost.
RBCC engine is usually only with one-stage rocket, and engine is when Ejector Mode works, one-stage rocket plume and sky
Gas contact area is small, weaker to air acting ability, causes engine injection suction ability of air insufficient, and due to injection mould
State incoming flow stagnation pressure is lower, rocket plume and the insufficient air stagnation pressure for flowing into engine chamber of the energy exchange of air by
To limitation, cause engine that cannot obtain preferably performance in Ejector Mode.
Summary of the invention
It is a kind of using multistage fire technical problem to be solved by the present invention lies in view of the above shortcomings of the prior art, providing
The full runner of axially symmetric structure RBCC of arrow, effectively reduces architecture quality and aerodynamic drag, under different modalities, selects corresponding draw
Rocket is penetrated, the performance of rocket is promoted.
In order to solve the above technical problems, the technical solution adopted by the present invention is that, a kind of axial symmetry knot using multistep rocket
The full runner of structure RBCC, including shell are axially arranged with a conical inner body in shell, and one section of the front end of the conical inner body is pierced by
Shell is pierced by the external compression section that air inlet section is formed between the part of shell and the entrance of shell；It is formed between shell and conical inner body
Circular passage, the circular passage sequentially form interior compression section, distance piece and the combustion section of air inlet section, the shell from front to back
Rear end be slidably connected with jet pipe, and jet pipe is connected with circular passage；It is slidably connected between shell and conical inner body, not
Under same rocket mode, shell can slide back and forth relative to conical inner body.
Further, which includes being sequentially connected the cone connect, the first cylindrical tube and the second circle from front to back
Column casing body；Cone include from front to back integrally connected conical section, etc. straight sections, inverted round stage section；Wherein, conical section is located at shell
Outside, the first cylindrical tube and the second cylindrical tube are located at combustion section；The shape of shell and the shape of the conical inner body of position in the inner
Shape is adapted, and waits straight sections and the inverted round stage section interior compression section for forming air inlet section corresponding between shell and distance piece.
Further, the intracorporal rear end of the cone and multiple one-stage rockets are provided within one week around the first cylindrical tube；First
The intracorporal rear end of cylindrical drum and multiple booster-missile combinations are provided within one week around the second cylindrical tube；One-stage rocket and booster-missile combination
Nozzle hole be connected with combustion section.
Further, the rear end of second cylindrical tube is axially provided with three-stage rocket, the nozzle hole and tail of three-stage rocket
Jet pipe is connected.
Further, be slidably connected between the shell and conical inner body by three-level branch board group, respectively first order branch board group,
Second level branch board group and third level branch board group, first order branch board group, second level branch board group and third level branch board group are correspondingly arranged at
The outer wall of cone, the first cylindrical tube and the second cylindrical tube one week, and it is axially disposed；Supporting plate in same branch board group
Position is corresponding, and the position of the supporting plate in adjacent branch board group is staggered and the position of supporting plate and one-stage rocket and booster-missile combination
It sets staggered；Supporting plate in branch board group is connected with fuel, for the spray fuel into corresponding channel.
Further, axial on the supporting plate side wall of the branch board group to be provided with sliding rail, edge on the corresponding position of inner walls
Axis is mutually provided with the track matched with sliding rail.
Further, the diameter of the cone rear end is greater than the diameter of the first cylindrical tube, and the diameter of the first cylindrical tube is big
In the diameter of the second cylindrical tube.
Further, which extends out horn-like for rear end, and can extend out or shrink.
A kind of working method of above-mentioned full runner of axially symmetric structure RBCC using multistep rocket, which are as follows：
In Ejector Mode, shell slides engine operation towards direction of flow, and the shrinkage ratio of air intake duct is 4, level-one fire
Arrow and booster-missile combination starting, third level branch board group are mixed and burned towards combustion section spray fuel with incoming flow, three-stage rocket starting
Work, jet pipe are adjusted to expansion ratio 1.2；
When mode is fired in Asia, shell slides engine operation towards direction of flow, and the shrinkage ratio of air intake duct is 5.5, closes
One-stage rocket and three-stage rocket, booster-missile combination work normally, first order branch board group and second level branch board group spray fuel combustion, tail
It is 1.8 that jet pipe, which is adjusted to expansion ratio,；
In super burn mode, shell slides engine operation towards direction of flow, and the shrinkage ratio of air flue is 6.5, level-one fire
Arrow, booster-missile combination and three-stage rocket are turned off, first order branch board group, second level branch board group spray fuel, are blended with incoming air
Burning, it is 2.4 that jet pipe, which is adjusted to expansion ratio,.
The present invention is a kind of to be had the following advantages that using the full runner of axially symmetric structure RBCC of multistep rocket：
(1) full tunnel use axially symmetric structure, compared to diadactic structure, axialsymmetrical inlet and axial symmetry jet pipe length compared with
It is short, guarantee that engine full tunnel entire length is shorter, architecture quality and aerodynamic drag can be effectively reduced；It is slided by shell real
Existing inlet throat area is adjusted, and structure changes actuation form and sealing are relatively easy, it is easy to accomplish；It is sprayed using axisymmetric vectoring tail
Pipe, jet pipe expansion ratio adjustable range is big and expansion efficiency is higher.
(2) multistep rocket：By arranging multistep rocket in the channel, aspirated in Ejector Mode using multistep rocket injection,
The contact area of rocket plume and air is increased, injection air mass flow can be increased, promotes rocket plume using multistep rocket
To the acting ability of air, the stagnation pressure of air is promoted, realizes Ejector Mode performance boost；Using the three-stage rocket of channel tail portion,
Realize and take off and low-speed stage accelerates and the demand climbed, at the same three-stage rocket can big flow work, can assist being formed pneumatic
Thermal choke reduces Ejector Mode jet pipe and crosses degrees of expansion；By opening the rocket of different location in different modalities, realization is helped
Fire the effect of steady flame.
(3) efficient burning tissue：In Ejector Mode work, enhanced by one-stage rocket and booster-missile combination injection, three-level
Rocket forms pneumatic boundary in jet pipe, and auxiliary aerothermodynamic is jammed, and the efficient combustion of three-level supporting plate spray fuel may be implemented
It burns；When Modality work is fired in Asia, incoming flow is preferably compressed by reducing the realization of inlet throat area, the small flow of booster-missile combination
The efficient burning of second level supporting plate and three-level supporting plate spray fuel is realized in work；In super burn Modality work, by further decreasing
Inlet throat area realizes the compression to High Mach number incoming flow, is realized by level-one supporting plate and second level supporting plate spray fuel efficient
Burning.
(4) wide 0~8 range of Mach number Ma work may be implemented in the axially symmetric structure RBCC full tunnel of multistep rocket.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of the full runner of axially symmetric structure RBCC using multistep rocket of the present invention.
Fig. 2 is a kind of main view of the full runner of axially symmetric structure RBCC using multistep rocket of the present invention.
Fig. 3 is the structural schematic diagram of cone in the present invention.
Wherein a. air intake duct；B. distance piece；C. combustion chamber；D. jet pipe；1. conical inner body；2. first order branch board group；3.
One-stage rocket；4. second level branch board group；5. booster-missile combination；6. third level branch board group；7. three-stage rocket；8. shell；9. the first circle
Column casing body；10 second cylindrical tubes；11. cone；11-1. conical section；11-2. waiting straight sections；11-3. inverted round stage section.
Specific embodiment
A kind of full runner of axially symmetric structure RBCC using multistep rocket of the present invention, as illustrated in fig. 1 and 2, including shell 8,
A conical inner body 1 is axially arranged in shell 8, one section of the front end of conical inner body 1 is pierced by shell 8, be pierced by the part of shell 8 with
The external compression section of air inlet section a is formed between the entrance of shell 8；Circular passage is formed between shell 8 and conical inner body 1, the annular is logical
Road sequentially forms interior compression section, distance piece b and the combustion section c of air inlet section a from front to back, and the rear end of shell 8 and jet pipe d are sliding
Dynamic connection, and jet pipe d is connected with circular passage；It is slidably connected between shell 8 and conical inner body 1, in different rocket mode
Under, shell 8 can slide back and forth relative to conical inner body 1.As shown in figure 3, conical inner body 1 includes being sequentially connected to connect from front to back
Cone 11, the first cylindrical tube 9 and the second cylindrical tube 10；Cone 11 from front to back including integrally connected conical section 11-1,
Equal straight sections 11-2, inverted round stage section 11-3；Wherein, conical section 11-1 is located at outside shell 8, the first cylindrical tube 9 and the second cylindrical drum
Body 10 is located at combustion section c；The shape of shell 8 and the shape of the conical inner body 1 of position in the inner are adapted, and are waited straight sections 11-2 and are fallen
The corresponding interior compression section for forming air inlet section a and distance piece b between rotary table section 11-3 and shell 8.The shape of shell 8 and position are in the inner
Conical inner body 1 shape be adapted, with guarantee air intake duct a shrinkage ratio be greater than combustion section c burning area.Shell 8
Some is protruded into jet pipe d for rear end, can be by opening up track in the upper surface of deep part, while in jet pipe d and its
Contact portion is set to the sliding rail that track matches, to realize the sliding of shell 8.
In the present invention, it is provided with multistep rocket, it is specific as follows：Rear end in cone 11 and around the company of the first cylindrical tube 9
It is provided within one week multiple one-stage rockets 3；Rear end in first cylindrical tube 9 and more around being provided with for one week for the second cylindrical tube 1
A booster-missile combination 5；The nozzle hole of one-stage rocket 3 and booster-missile combination 5 is connected with combustion section c.Second cylindrical tube 10
Rear end is axially provided with three-stage rocket 7, and the nozzle hole of three-stage rocket 7 is connected with jet pipe d.To be easy to implement the multistage fire of setting
Arrow, the diameter of 11 rear end of cone are greater than the diameter of the first cylindrical tube 9, and the diameter of the first cylindrical tube 9 is greater than the second cylindrical drum
The diameter of body 10.It is aspirated in Ejector Mode using multistep rocket injection, increases the contact area of rocket plume and air, it can be with
Increase injection air mass flow, promotes rocket plume to the acting ability of air using multistep rocket, promote the stagnation pressure of air, realize
Ejector Mode performance boost；Using the three-stage rocket of channel tail portion, the demand that realization is taken off and low-speed stage accelerates and climbs, together
When three-stage rocket can big flow work, can assist forming aerothermodynamic and be jammed, reduce Ejector Mode jet pipe and cross degrees of expansion；
By opening the rocket of different location in different modalities, the effect of combustion-supporting steady flame is realized.The one-stage rocket 3 and booster-missile combination 5 are
Rocket ejector, three-stage rocket 7 are booster rocket.
It is slidably connected between the shell 8 and conical inner body 1 by three-level branch board group, respectively first order branch board group 2, the second level
Branch board group 4 and third level branch board group 6, first order branch board group 2, second level branch board group 4 and third level branch board group 6 are correspondingly arranged at cone
The outer wall of body 11, the first cylindrical tube 9 and the second cylindrical tube 10 one week, and it is axially disposed；Branch in same branch board group
Plate is uniformly arranged, and the position of the supporting plate in adjacent branch board group is staggered and supporting plate and one-stage rocket 3 and booster-missile combination 5
Position is staggered；Supporting plate in branch board group is connected with fuel, for the spray fuel into corresponding channel.The branch of branch board group
It is axial on plate side wall to be provided with sliding rail, the track matched with sliding rail is mutually provided with along axis on the corresponding position of 8 inner wall of shell.
Multiple groups supporting plate can be also used for the spray of fuel in different operating mode, supporting plate in addition to playing the role of structural support and sliding rail
It is in interlaced arrangement with multistep rocket, avoids multistep rocket high-temperature heat flux from directly washing away supporting plate, while realizing rocket plume combustion zone
Interlock with supporting plate spray fuel combustion zone, promotes fuel combustion efficiency.
To match with channel, it is horn-like that jet pipe d is that rear end extends out, and can extend out or shrink.Jet pipe d design
It is inside and outside two layers, is all made of heat-resisting material, the heat-resisting material in each layer is disposed as multiple long fish scale-shapeds, ectonexine
The refractory material position of long fish scale-shaped is staggered, is connected with hydraulic device on each long flap, is pulled using hydraulic stem, adjusts
The angle that flap opens.Above-mentioned is by the way of using in technology.Long flap can also be realized using other modes
Opening angle.In the prior art, there is such mode for realizing expansion and contraction.
A kind of working method of above-mentioned full runner of axially symmetric structure RBCC using multistep rocket is as follows：
When engine operation is in Ejector Mode, shell 8 is slided towards direction of flow, and the shrinkage ratio of air intake duct is 4, air inlet
Road throat area is in maximum position, and one-stage rocket 3 and booster-missile combination 5 start, and third level branch board group 6 is sprayed towards combustion section c
Fuel is infused, is mixed and burned with incoming flow, three-stage rocket 7 starts work, and jet pipe is adjusted to expansion ratio 1.2；On the one hand low speed is realized
The demand that takeoff phase quickly accelerates, on the other hand can form pneumatic boundary in jet pipe d, and auxiliary injection stage heating power is stopped up
Plug, jet pipe d are adjusted to small expansion ratio form；
When engine operation is when mode is fired in Asia, shell 8 is slided towards direction of flow, is reduced inlet throat area, is mentioned
The compression effectiveness to incoming flow is risen, the shrinkage ratio of air intake duct is 5.5, closes one-stage rocket 3 and three-stage rocket 7, and booster-missile combination 5 is normal
Work, realizes the effect of combustion-supporting steady flame, the 4 spray fuel combustion of first order branch board group 2 and second level branch board group, and jet pipe is adjusted to
Expansion ratio is 1.8；
When engine operation is in super burn mode, shell 8 is slided towards direction of flow, and the shrinkage ratio of air flue is 6.5, into one
Step reduces inlet throat area, guarantees to the compression effectiveness compared with High Mach number incoming flow, one-stage rocket 3, booster-missile combination 5 and three-level
Rocket 7 is turned off, first order branch board group 2,4 spray fuel of second level branch board group, is blended and is burnt with incoming air, and jet pipe is adjusted
It is 2.4 for expansion ratio.
In addition, air is flowed towards the front end of conical inner body 1, here it is above-mentioned described incoming flow, opposite with incoming flow is
It is direction of flow, is exactly the direction opposite with incoming flow towards direction of flow, is shell 8 towards front slide in the application.
Claims (9)
1. a kind of full runner of axially symmetric structure RBCC using multistep rocket, which is characterized in that including shell (8), the shell
(8) it is axially arranged in a conical inner body (1), one section of the front end of the conical inner body (1) is pierced by shell (8), is pierced by shell
(8) the external compression section of air inlet section (a) is formed between part and the entrance of shell (8)；
Circular passage is formed between the shell (8) and conical inner body (1), which sequentially forms air inlet section from front to back
(a) interior compression section, distance piece (b) and combustion section (c), the rear end of the shell (8) are slidably connected with jet pipe (d), and
Jet pipe (d) is connected with circular passage；
It is slidably connected between the shell (8) and conical inner body (1), under different rocket mode, the shell (8) can be relative to
Conical inner body (1) slides back and forth.
2. a kind of full runner of axially symmetric structure RBCC using multistep rocket according to claim 1, which is characterized in that institute
State conical inner body (1) includes being sequentially connected the cone (11) connect, the first cylindrical tube (9) and the second cylindrical tube from front to back
(10)；The cone (11) from front to back including integrally connected conical section (11-1), etc. straight sections (11-2), inverted round stage section (11-
3)；Wherein, the conical section (11-1) is located at shell (8) outside, first cylindrical tube (9) and the second cylindrical tube (10) position
In combustion section (c)；The shape of the shell (8) and the shape of the conical inner body (1) of position in the inner are adapted, described to wait straight sections
The corresponding interior compression section for forming air inlet section (a) and distance piece (b) between (11-2) and inverted round stage section (11-3) and shell (8).
3. a kind of full runner of axially symmetric structure RBCC using multistep rocket according to claim 2, which is characterized in that institute
It states the rear end in cone (11) and is provided with multiple one-stage rockets (3) within (9) one weeks around the first cylindrical tube；First circle
Rear end and circular second cylindrical tube in column casing body (9) are provided with multiple booster-missile combinations (5) in (10) one weeks；The level-one fire
The nozzle hole of arrow (3) and booster-missile combination (5) is connected with combustion section (c).
4. a kind of full runner of axially symmetric structure RBCC using multistep rocket according to claim 3, which is characterized in that institute
The rear end for stating the second cylindrical tube (10) is axially provided with three-stage rocket (7), the nozzle hole and jet pipe of the three-stage rocket (7)
(d) it is connected.
5. a kind of full runner of axially symmetric structure RBCC using multistep rocket according to claim 3 or 4, feature exist
In the diameter of cone (11) rear end is greater than the diameter of the first cylindrical tube (9), the diameter of first cylindrical tube (9)
Greater than the diameter of the second cylindrical tube (10).
6. a kind of full runner of axially symmetric structure RBCC using multistep rocket according to any one of claim 2-5,
It is characterized in that, is slidably connected between the shell (8) and conical inner body (1) by three-level branch board group, respectively first order branch board group
(2), second level branch board group (4) and third level branch board group (6), the first order branch board group (2), second level branch board group (4) and
Three-level branch board group (6) is correspondingly arranged at outer wall one week of cone (11), the first cylindrical tube (9) and the second cylindrical tube (10),
And it is axially disposed；The position of supporting plate in adjacent branch board group is staggered and supporting plate and the one-stage rocket (3) and two
The position of grade rocket (5) is staggered；Supporting plate in the branch board group is connected with fuel, is used for the spray into corresponding channel
Fuel.
7. a kind of full runner of axially symmetric structure RBCC using multistep rocket according to any one of claim 2-5,
It is characterized in that, it is axial on the supporting plate side wall of the branch board group to be provided with sliding rail, edge on the corresponding position of shell (8) inner wall
Axis is mutually provided with the track matched with sliding rail.
8. a kind of full runner of axially symmetric structure RBCC using multistep rocket according to claim 1, which is characterized in that institute
Stating jet pipe (d), to be that rear end extends out horn-like, and can extend out or shrink.
9. a kind of work of full runner of axially symmetric structure RBCC using multistep rocket according to claim 1 to 8
Make mode, which is characterized in which is as follows：
Engine operation in Ejector Mode, slide towards direction of flow by the shell (8), and the shrinkage ratio of air intake duct is 4, described
One-stage rocket (3) and booster-missile combination (5) starting, the third level branch board group (6) and are come towards combustion section (c) spray fuel
Stream is mixed and burned, and the three-stage rocket (7) starts work, and jet pipe is adjusted to expansion ratio 1.2；
Engine operation when mode is fired in Asia, slide towards direction of flow by the shell (8), and the shrinkage ratio of air intake duct is 5.5, closes
Close the one-stage rocket (3) and three-stage rocket (7), the booster-missile combination (5) works normally, the first order branch board group (2) and
The second level branch board group (4) spray fuel combustion, it is 1.8 that jet pipe, which is adjusted to expansion ratio,；
Engine operation in super burn mode, slide towards direction of flow by the shell (8), and the shrinkage ratio of air flue is 6.5, described
One-stage rocket (3), booster-missile combination (5) and three-stage rocket (7) are turned off, the first order branch board group (2), second level branch board group
(4) spray fuel is blended with incoming air and is burnt, and it is 2.4 that jet pipe, which is adjusted to expansion ratio,.
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| CN112228246A (en) * | 2020-10-30 | 2021-01-15 | 华中科技大学 | Rocket-based detonation and stamping combined cycle engine and use method and application thereof |
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| CN111594344A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Small-scale two-stage rocket combined ramjet engine |
| CN111594346A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Mesoscale rocket-based combined cycle engine |
| CN111594347A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Large-scale multi-stage rocket-based combined cycle engine |
| CN112228246A (en) * | 2020-10-30 | 2021-01-15 | 华中科技大学 | Rocket-based detonation and stamping combined cycle engine and use method and application thereof |
| CN112228246B (en) * | 2020-10-30 | 2021-11-02 | 华中科技大学 | Rocket-based detonation and stamping combined cycle engine and use method and application thereof |
| CN113153577A (en) * | 2021-04-21 | 2021-07-23 | 华中科技大学 | Multistage rotary detonation rocket stamping combined engine |
| CN113153577B (en) * | 2021-04-21 | 2023-02-10 | 华中科技大学 | Multistage rotary detonation rocket stamping combined engine |
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| Publication number | Publication date |
|---|---|
| CN108825405B (en) | 2020-09-08 |
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