CN109139301A - A kind of integrated solid rocket motor nozzle of thermal protection structure - Google Patents
A kind of integrated solid rocket motor nozzle of thermal protection structure Download PDFInfo
- Publication number
- CN109139301A CN109139301A CN201811043213.7A CN201811043213A CN109139301A CN 109139301 A CN109139301 A CN 109139301A CN 201811043213 A CN201811043213 A CN 201811043213A CN 109139301 A CN109139301 A CN 109139301A
- Authority
- CN
- China
- Prior art keywords
- larynx
- section
- insulation
- converging portion
- thermal protection
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- 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
- F02K9/97—Rocket nozzles
-
- 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
- F02K9/97—Rocket nozzles
- F02K9/974—Nozzle- linings; Ablative coatings
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Thermal Insulation (AREA)
Abstract
A kind of integrated solid rocket motor nozzle of thermal protection structure, blanking cover are fixed in solid propellant rocket, and are located at the expansion segment conical surface of insulation.Larynx lining inner mold face be made of converging portion inclined-plane, larynx diameter and expansion segment inclined-plane, and make converging portion inclined-plane and expansion segment inclined-plane respectively with two end surfaces arc transitions of larynx diameter.The inner mold face of insulation includes converging portion, larynx lining construction section and expanding section.The conical surface that the inner surface of converging portion is 45 °；Larynx lining construction section is made of the conical surface, cylindrical surface and positioning surface.The present invention realizes the integrated design of investigation on thermal protection for nozzle structure, reduces jet pipe and wears windburn danger in engine working process；Investigation on thermal protection for nozzle structure interface is reduced, engine jet pipe inner mold face ablation situation is reduced, improves investigation on thermal protection for nozzle reliability, and the stress for serving as a contrast larynx is more reasonable, larynx lining fragmentation risk is reduced, improves structural reliability.
Description
Technical field
The invention belongs to Solid Rocket Motor Technology fields, are related to the application in terms of solid rocket motor nozzle, use
In reduction solid rocket motor nozzle manufacturing cost and improve engine jet pipe functional reliability.
Background technique
The jet pipe of solid propellant rocket is the energy conversion device of engine, is usually located at engine chamber tail portion.
Conventional solid rocket tube by jet pipe shell, converging portion insulation, larynx lining, expansion segment insulation, throat's backing and
The composition such as blanking cover.Its main function is: 1) according to the burning area of powder column, being protected by controlling the size of nozzle throat area
Demonstrate,proving combustion chamber has certain operating pressure, makes powder column normal combustion；2) thermal energy by the combustion gas that powder column burning generates is converted into
Kinetic energy, combustion gas constantly accelerate when flowing through jet pipe, are finally discharged with high speed from nozzle exit, generate the reaction for promoting body to advance
Power --- thrust；3) change thrust direction, control the flight attitude of aircraft.
As solid propellant rocket is widely used in the multiple fields such as guided missile, rocket, rocket sledge boost motor, solid-rocket
The design of engine jet pipe is also sufficiently improved.Different from the jet pipe of liquid-propellant rocket engine, solid rocket motor nozzle
It is a kind of jet pipe of non-cooled structure, more precisely a kind of ablation cooling spray pipe.
Three are generally divided into according to the overall Nozzle Design requirement and restrictive condition, Nozzle Design totally given with engine of bullet
Major part, i.e. pneumatic design, structure design and heat protection design.The pneumatic design of jet pipe include quasi spline, it is smooth calculate and
Other calculating in relation to parameter.The quasi spline of jet pipe is the form parameter for selecting converging portion, throat and expansion segment three parts, with
Just make designed jet pipe that there is highest efficiency.Nozzle structure can be divided into two parts, respectively support construction and insulation, ablation
Structure.The main function of support construction is support converging portion heat insulation layer, ablation layer, larynx lining component, expansion segment heat insulation layer and ablation
Layer, and they are organized into integral, the whole load born in addition to thermal force, in addition, support construction also acts as jet pipe and combustion chamber
The effect of connection.Insulation, ablation structure main function be constitute jet pipe continuous inner mold face, do not change as far as possible or change less
The type face of pneumatic design guarantees that the temperature of support construction controls in allowed limits, to ensure engine health, reliably work
Make.
Through retrieving, specially application No. is in 200910124936.4 innovation and creation, a kind of solid propellant rocket is disclosed
Nozzle divergence cone composite wound structure.The innovation and creation propose new nozzle divergence cone thermal protection structure and processing technology, mention
The high thermal protection reliability of nozzle divergence cone, but there are higher costs, and improve only solid rocket motor nozzle expansion
Open the deficiency of the thermal protection reliability of section.
Summary of the invention
To overcome the shortcomings of thermal protection poor reliability at high cost, whole existing in the prior art, the invention proposes one
The kind integrated solid rocket motor nozzle of thermal protection structure.
The present invention includes jet pipe shell, larynx lining, insulation and blanking cover.Wherein, in the jet pipe shell inner surface cylindrical section
With cone section sticking adiabatic part, larynx lining is pasted in the cylinder section surface and cone section surface of insulation inner surface.The blanking cover is fixed
In solid propellant rocket, and it is located at the expansion segment conical surface of the insulation, the divergence ratio of the blanking cover front end face is 3.5.
The larynx lining inner mold face be made of converging portion inclined-plane, larynx diameter and expansion segment inclined-plane, and make the converging portion inclined-plane and
Expansion segment inclined-plane respectively with two end surfaces arc transitions of larynx diameter.
The inner hole of the jet pipe shell is divided into entrance, converging portion and supporting section, and supporting section inner mold face is cylindrical surface,
There is radial positioning convex platform at the aperture of the supporting section.
The internal diameter of the jet pipe housing inlet port section is 120mm, and the convergence half-angle of converging portion is 45 °, and the internal diameter of supporting section is
81mm.The height of the positioning convex platform is 3mm, width 5mm.
The inner mold face of the insulation includes converging portion, larynx lining construction section and expanding section.The inner surface of the converging portion is
45 ° of the conical surface；The larynx lining construction section is made of the conical surface, cylindrical surface and positioning surface, and the conical surface therein is connected with the converging portion,
Since different inner diameters difference is formed by end face as positioning surface between cylindrical surface and expanding section.External peripheral surface at the expanding section
Port at have with the positioning convex platform cooperation positioning spigot.
The external peripheral surface of the larynx lining is pasted on the larynx lining construction section of the insulation, and the inner face for serving as a contrast the larynx
It is bonded with the positioning surface on the insulation.The outer surface of the larynx lining and the type face of insulation larynx lining construction section are adapted.
This project is by improving engine jet pipe structure, in the case where not changing jet pipe total coating process, realizes
Investigation on thermal protection for nozzle structure (including converging portion insulation, backing and expansion segment insulation etc.) integrated design.It is of the present invention
Jet pipe development it is as follows:
1) jet pipe shell expansion segment is changed to cylindrical surface by tapered surface, adjusts cylindrical section diameter, guarantee expansion segment insulation
Size surplus；
2) by jet area contraction section insulation, backing, expansion segment insulation design be structure as a whole, by converging portion insulation with
Larynx serves as a contrast mating surface and is changed to radial mating surface by axis mating surface；
3) graphite larynx lining external surface is improved as after improvement with insulation mating surface, jet pipe entirety inner mold face is kept not
Become.
Compared with available engine jet pipe, the invention has the following advantages that
1) investigation on thermal protection for nozzle structure proposed by the present invention is realized including converging portion insulation, backing and expansion segment insulation
The equal structure-integrated design of investigation on thermal protection for nozzle, reduces amount of parts and manufacturing procedure, reduces jet pipe manufacturing cost；
2) investigation on thermal protection for nozzle structure of the invention is an entirety, and the interface between the existing multiple insulations of jet pipe is being sent out
Airflow channel easy to form in the motivation course of work and cause jet pipe to wear fire, the investigation on thermal protection for nozzle structure of integrated design does not have then
Fiery channel is worn, jet pipe is reduced and wears windburn danger in engine working process；
3) The present invention reduces investigation on thermal protection for nozzle structure interfaces, reduce engine jet pipe inner mold face ablation situation, mention
High investigation on thermal protection for nozzle reliability；
4) jet pipe throat lining external surface proposed by the present invention is made of the conical surface and cylindrical surface, when the engine is working, larynx lining by
It can be axially expanded after high-temperature heating, the stress for serving as a contrast larynx is more reasonable, reduces larynx lining fragmentation risk；
5) jet pipe shell proposed by the present invention tail portion design has positioning convex platform, and it is fixed that investigation on thermal protection for nozzle structure is effectively performed
Position, compared with existing nozzle divergence cone is bonded to jet pipe shell, improves structural reliability.
The present invention then proposes a kind of thermal protection knot of the integrated designs such as jet area contraction section, expansion segment and throat's backing
Structure reduces jet pipe cost and improves investigation on thermal protection for nozzle reliability.
By taking certain h type engine h as an example.Improving front engine jet pipe is traditional Nozzle Design structure, as shown in Figure 1.After improvement
Engine jet pipe use thermal protection structure integrated design jet pipe, as shown in Figure 2.Improved 1 expanding section of jet pipe shell
External surface is cylindrical surface, realizes insulation 7 and installs and paste and jet pipe shell inner mold face from jet pipe shell converging portion；After improvement
The external surface of insulation 7 matched with 1 inner mold face of shell, interior shape face eliminates converging portion confined planes, realizes the one of insulation 7
Bodyization design.Improved larynx serves as a contrast 3 external surfaces and matches with 7 inner mold face of insulation, and inner mold face is made of the conical surface and cylindrical surface, realizes
Larynx lining 3 is installed from insulation converging portion and affixes to inner mold face；.
To verify effect of the invention, improved engine jet pipe insulation erosion is measured by ground experiment
And assessment, and counted jet pipe manufacture processing cost, the results showed that, present invention significantly reduces engine manufacturing cost and improve
Engine jet pipe functional reliability.It is in particular in:
1) using thermal protection structure integrated design jet pipe inner mold face ablation concave point with interface quantity by 3 reduce to
At 2.Ablation is more serious at general jet pipe interface, and mainly since different materials ablating rate is different, air-flow is at interface
Vortex is easily formed, is caused serious compared with other position ablations at interface.It improves rear jet inner mold face and is averaged ablating rate by 0.2mm/s
It is decreased to 0.18mm/s, reduces engine jet pipe inner mold face ablation situation, improve jet pipe functional reliability；
2) engine jet pipe number of parts is reduced by 6 to 4, and investigation on thermal protection for nozzle structure includes converging portion insulation before improving
Part 2, throat's backing 4 and expansion segment insulation 5 improve the insulation 7 that rear jet thermal protection structure is the integrated design.Simultaneously
Main manufacturing procedure is reduced by 9 to 5, and main manufacturing procedure comparison is shown in Table 1.It is counted through cost accounting, engine jet pipe system
It causes originally to reduce about 30%.
Table 1
| Process serial number | Before improvement | After improvement | Remarks |
| 1 | Shell processing | Shell processing | |
| 2 | The processing of converging portion insulation | Insulation processing | |
| 3 | Converging portion insulation bonding | Insulation bonding | |
| 4 | Larynx lining processing | Larynx lining processing | |
| 5 | Larynx lining bonding | Larynx lining bonding | |
| 6 | The processing of throat's backing | ||
| 7 | Throat's backing bonding | ||
| 8 | The processing of expansion segment insulation | ||
| 9 | Expansion segment insulation bonding |
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the prior art.
Fig. 2 is structural schematic diagram of the invention.
In figure:
1. jet pipe shell；2. converging portion insulation；3. larynx serves as a contrast；4. throat's backing；5. expansion segment insulation；6. blanking cover；7.
Insulation.
Specific embodiment
The present embodiment is a kind of certain integrated model solid rocket motor nozzle of thermal protection structure, including jet pipe shell
1, larynx lining 3, insulation 7 and blanking cover 6.Wherein, in the jet pipe shell inner surface cylindrical section and cone section sticking adiabatic part 7, exhausted
The cylindrical section and cone section of 7 inner surface of warmware are pasted with larynx lining 3.The blanking cover 6 is fixed in solid propellant rocket, and is located at institute
It states at the expansion segment conical surface of insulation 7, the divergence ratio of the blanking cover front end face is 3.5.
The inner hole of the jet pipe shell 1 is divided into entrance, converging portion and supporting section, has diameter at the aperture of the supporting section
To positioning convex platform.In the present embodiment, the internal diameter of entrance is 120mm, and the convergence half-angle of converging portion is 45 °, supporting section it is interior
Diameter is 81mm.The height of the positioning convex platform is 3mm, width 5mm.
The type face of the outer mold surface of the insulation 7 and 1 inner hole of jet pipe shell is adapted.The inner mold of the insulation 7
Face includes converging portion, larynx lining construction section and expanding section.The conical surface that the inner surface of the converging portion is 45 °；The larynx serves as a contrast construction section
It is made of the conical surface, cylindrical surface and positioning surface, the conical surface therein is connected with the converging portion, due to not between cylindrical surface and expanding section
Being formed by end face with difference in internal diameters is positioning surface.Have at the port of external peripheral surface at the expanding section and the positioning convex platform
The positioning spigot of cooperation.
The external peripheral surface of the larynx lining 3 is pasted on the larynx lining construction section of the insulation 7, and the inner end for serving as a contrast the larynx
Face is bonded with the positioning surface.The outer surface of the larynx lining 3 and the type face of insulation larynx lining construction section are adapted.The larynx serves as a contrast interior
Type face is made of converging portion inclined-plane, larynx diameter and expansion segment inclined-plane, and make the converging portion inclined-plane and expansion segment inclined-plane respectively with larynx
Two end surfaces arc transitions of diameter.
The blanking cover 6 uses the prior art.
In the present embodiment, engine work in every parameter is shown in Table 2.
Table 2
| Serial number | Parameter name | Unit | Numerical value | Remarks |
| 1 | Propellant mass | kg | 8.45 | |
| 2 | Working time | s | 4.9 | +20℃ |
| 3 | Average thrust | kN | 4.12 | +20℃ |
| 4 | Average pressure | MPa | 9.1 | +20℃ |
| 5 | Average second flow | kg/s | 1.72 | +20℃ |
| 6 | Nozzle throat | mm | Φ23 | |
| 7 | Exit inside diameter | mm | Φ65 | |
| 8 | Divergence ratio | - | 8.0 |
Claims (5)
1. a kind of integrated solid rocket motor nozzle of thermal protection structure, which is characterized in that served as a contrast including jet pipe shell, larynx,
Insulation and blanking cover；Wherein, in the jet pipe shell inner surface cylindrical section and cone section sticking adiabatic part, in insulation inner surface
Cylinder section surface and cone section surface are pasted with larynx lining；The blanking cover is fixed in solid propellant rocket, and is located at the insulation
At the expansion segment conical surface of part, the divergence ratio of the blanking cover front end face is 3.5；
The inner mold face of larynx lining is made of converging portion inclined-plane, larynx diameter and expansion segment inclined-plane, and makes the converging portion inclined-plane and expansion
Section inclined-plane respectively with two end surfaces arc transitions of larynx diameter.
2. the integrated solid rocket motor nozzle of thermal protection structure as described in claim 1, which is characterized in that the jet pipe
The inner hole of shell is divided into entrance, converging portion and supporting section, and supporting section inner mold face is cylindrical surface, in the hole of the supporting section
There is radial positioning convex platform at mouthful.
3. the integrated solid rocket motor nozzle of thermal protection structure as claimed in claim 2, which is characterized in that the jet pipe
The internal diameter of housing inlet port section is 120mm, and the convergence half-angle of converging portion is 45 °, and the internal diameter of supporting section is 81mm；The positioning convex platform
Height be 3mm, width 5mm.
4. the integrated solid rocket motor nozzle of thermal protection structure as described in claim 1, which is characterized in that the insulation
The inner mold face of part includes converging portion, larynx lining construction section and expanding section；The conical surface that the inner surface of the converging portion is 45 °；The larynx
Lining construction section is made of the conical surface, cylindrical surface and positioning surface, and the conical surface therein is connected with the converging portion, cylindrical surface and expanding section it
Between due to different inner diameters difference be formed by end face be positioning surface；Have at the port of external peripheral surface at the expanding section with it is described
The positioning spigot of positioning convex platform cooperation.
5. the integrated solid rocket motor nozzle of thermal protection structure as described in claim 1, which is characterized in that the larynx lining
External peripheral surface be pasted onto the insulation larynx lining construction section on, and make the larynx serve as a contrast inner face and the insulation on
Positioning surface fitting；The outer surface of the larynx lining and the type face of insulation larynx lining construction section are adapted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811043213.7A CN109139301A (en) | 2018-09-07 | 2018-09-07 | A kind of integrated solid rocket motor nozzle of thermal protection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811043213.7A CN109139301A (en) | 2018-09-07 | 2018-09-07 | A kind of integrated solid rocket motor nozzle of thermal protection structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109139301A true CN109139301A (en) | 2019-01-04 |
Family
ID=64823683
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811043213.7A Pending CN109139301A (en) | 2018-09-07 | 2018-09-07 | A kind of integrated solid rocket motor nozzle of thermal protection structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109139301A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112128023A (en) * | 2020-09-03 | 2020-12-25 | 湖北航天化学技术研究所 | Small solid rocket engine nozzle blocking cover and manufacturing method thereof |
| CN112483282A (en) * | 2020-12-08 | 2021-03-12 | 晋西工业集团有限责任公司 | High-reliability multilayer composite material spray pipe |
| CN112523902A (en) * | 2020-11-30 | 2021-03-19 | 内蒙动力机械研究所 | 3D printing-based composite material fixing shell for spray pipe |
| CN113339157A (en) * | 2021-06-16 | 2021-09-03 | 西安交通大学 | Variable thrust's miniature solid rocket engine flexible nozzle system |
| CN113505442A (en) * | 2021-08-02 | 2021-10-15 | 北京理工大学 | Design method of secondary flow throat plug engine |
| CN114876673A (en) * | 2022-04-12 | 2022-08-09 | 西安零壹空间科技有限公司 | Low-cost ablation-resistant embedded spray pipe and machining method thereof |
| CN115450798A (en) * | 2022-10-31 | 2022-12-09 | 北京中科宇航技术有限公司 | Long-time working solid rocket engine and long tail jet pipe thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202360245U (en) * | 2011-11-21 | 2012-08-01 | 湖北航天技术研究院总体设计所 | Simplified combined nozzle structure of engine |
| CN102943719A (en) * | 2012-11-06 | 2013-02-27 | 北京航空航天大学 | Turbulence device for postcombustion chamber of hybrid rocket engine |
| CN103061919A (en) * | 2012-12-25 | 2013-04-24 | 北京航空航天大学 | Airtight testing device of solid-liquid rocket engine combustor |
| CN106837611A (en) * | 2017-01-26 | 2017-06-13 | 北京航空航天大学 | A kind of airtight check device of solid-liquid rocket jet pipe |
| CN107091169A (en) * | 2017-06-29 | 2017-08-25 | 湖北三江航天江河化工科技有限公司 | A kind of rocket engine |
-
2018
- 2018-09-07 CN CN201811043213.7A patent/CN109139301A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202360245U (en) * | 2011-11-21 | 2012-08-01 | 湖北航天技术研究院总体设计所 | Simplified combined nozzle structure of engine |
| CN102943719A (en) * | 2012-11-06 | 2013-02-27 | 北京航空航天大学 | Turbulence device for postcombustion chamber of hybrid rocket engine |
| CN103061919A (en) * | 2012-12-25 | 2013-04-24 | 北京航空航天大学 | Airtight testing device of solid-liquid rocket engine combustor |
| CN106837611A (en) * | 2017-01-26 | 2017-06-13 | 北京航空航天大学 | A kind of airtight check device of solid-liquid rocket jet pipe |
| CN107091169A (en) * | 2017-06-29 | 2017-08-25 | 湖北三江航天江河化工科技有限公司 | A kind of rocket engine |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112128023A (en) * | 2020-09-03 | 2020-12-25 | 湖北航天化学技术研究所 | Small solid rocket engine nozzle blocking cover and manufacturing method thereof |
| CN112128023B (en) * | 2020-09-03 | 2021-06-22 | 湖北航天化学技术研究所 | Small solid rocket engine nozzle blocking cover and manufacturing method thereof |
| CN112523902A (en) * | 2020-11-30 | 2021-03-19 | 内蒙动力机械研究所 | 3D printing-based composite material fixing shell for spray pipe |
| CN112483282A (en) * | 2020-12-08 | 2021-03-12 | 晋西工业集团有限责任公司 | High-reliability multilayer composite material spray pipe |
| CN113339157A (en) * | 2021-06-16 | 2021-09-03 | 西安交通大学 | Variable thrust's miniature solid rocket engine flexible nozzle system |
| CN113505442A (en) * | 2021-08-02 | 2021-10-15 | 北京理工大学 | Design method of secondary flow throat plug engine |
| CN113505442B (en) * | 2021-08-02 | 2023-12-01 | 北京理工大学 | Design method of secondary throat plug engine |
| CN114876673A (en) * | 2022-04-12 | 2022-08-09 | 西安零壹空间科技有限公司 | Low-cost ablation-resistant embedded spray pipe and machining method thereof |
| CN114876673B (en) * | 2022-04-12 | 2024-03-29 | 西安零壹空间科技有限公司 | Low-cost ablation-resistant embedded spray pipe and processing method thereof |
| CN115450798A (en) * | 2022-10-31 | 2022-12-09 | 北京中科宇航技术有限公司 | Long-time working solid rocket engine and long tail jet pipe thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109139301A (en) | A kind of integrated solid rocket motor nozzle of thermal protection structure | |
| CN106930865B (en) | A kind of high-energy solid rocket engine that width temperature uses | |
| US8061145B2 (en) | Arrangement for propelling an aircraft, aircraft and outlet nozzle for a jet engine | |
| CN109339975A (en) | A kind of stealthy exhaust pipe of the adjustable cone-shaped cavity of band | |
| CN109723573A (en) | A kind of dipulse engine and production method with medicine winding integral structure | |
| CN202360245U (en) | Simplified combined nozzle structure of engine | |
| US20120087787A1 (en) | Turbofan jet engine | |
| CN103521404B (en) | A kind of Portable low-pressure cold spray apparatus | |
| CN112682219B (en) | Wide-speed-range engine based on tail confluence rocket of annular supercharging central body | |
| CN108843462B (en) | It is classified pressurized combustion solid propellant rocket | |
| CN109139298A (en) | A kind of space double elements precise tracking based on two-way single injector centrifugation ejector filler | |
| CN109630315A (en) | Solid rocket scramjet engine, arc-shaped gas generator and central injection device | |
| CN108825405A (en) | A kind of full runner of axially symmetric structure RBCC using multistep rocket | |
| CN102748775B (en) | Streamline flame stabilizer with built-in ignition sources | |
| CN210455240U (en) | Ventilation, heat insulation and heat dissipation mechanism for turbojet power unmanned aerial vehicle | |
| US20160090174A1 (en) | Reaction drive blade tip with turning vanes | |
| CN201143468Y (en) | Laval nozzle for cold spraying | |
| CN114251196A (en) | Variable expansion ratio spray pipe of single-chamber double-thrust solid rocket engine | |
| CN106014688A (en) | Flow control device and method | |
| CN214533288U (en) | Long tail nozzle structure of segmentation of solid rocket engine | |
| CN107091169A (en) | A kind of rocket engine | |
| CN108757221A (en) | A kind of liquid Asia burning ramjet | |
| CN113898496B (en) | Rocket engine and carrier rocket | |
| CN115434827A (en) | Special-shaped micro-thrust eccentric spray pipe | |
| CN208887490U (en) | A kind of steering engine thermal protection struc ture |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190104 |