CN104833768A - Simulation device of thermal insulation layer ablation under condition of particle phase deposition in rocket engine - Google Patents
Simulation device of thermal insulation layer ablation under condition of particle phase deposition in rocket engine Download PDFInfo
- Publication number
- CN104833768A CN104833768A CN201510107391.1A CN201510107391A CN104833768A CN 104833768 A CN104833768 A CN 104833768A CN 201510107391 A CN201510107391 A CN 201510107391A CN 104833768 A CN104833768 A CN 104833768A
- Authority
- CN
- China
- Prior art keywords
- deposition
- gas generator
- rocket engine
- phase
- section
- 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.)
- Granted
Links
Abstract
The invention discloses a simulation device of thermal insulation layer ablation under the condition of particle phase deposition in a rocket engine, wherein the simulation device includes a fuel gas generator for combusting a solid propellant, a convergence section, a transition section, a deposition section and a spray tube are successively and coaxially connected to one end of the fuel gas generator to form a penetrated chamber body. The other end of the fuel gas generator is sealed. The solid propellant and an ignition powder bag are arranged inside the fuel gas generator. The simulation device is simple in structure and is convenient to install and use. By means of changing the diameter of an adjustment ring and deposition depth of a deposition trough, the concentration of a particle phase can be adjusted and further the thermal insulation layer ablation under the condition of the particle phase deposition at a back wall concave chamber of a submerged nozzle in a large-scale solid rocket engine can be simulated.
Description
Technical field
The invention belongs to rocket engine technical field, relate to the analogue means of a kind of rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation.
Background technology
In order to improve specific impulse and shorten overall engine length in modern Design of Solid Propellant Rocket Engine, in propellant, usually add metal powder (as Al, Mg), and widely use submerged nozzle.But in engine working process, along with the passing in combustion face forms a cavity gradually in submerged nozzle back wall region, complicated recirculating zone is there is in this cavity, because Particle Phase has larger inertia, be not easy to follow streamline, therefore easily enter recirculating zone with burbling in the jet pipe back wall region that air flow deflector is larger, being then deposited in cavity becomes slag; At the end of large-scale segmented rocket engine horizontal firing, there is the existence of a large amount of deposition on the lower surface.
Domestic and international at present following three aspects are mainly concentrated on to insulation erosion experimental study technology: the chemical ablation of (1) oxidizing gas and heat insulation layer; (2) air-flow is to the erosion of heat insulation layer; (3) Particle Phase is to the mechanical erosion of heat insulation layer.But alumina particle mode of deposition lower thermal insulating layer ablation experiments technology domestic literature rarely has and mentions.
Summary of the invention
The object of this invention is to provide the analogue means of a kind of rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation, with under the condition filling up deposited particles phase in cavity in prior art, do not study the blank of solid propellant rocket insulation erosion phenomenon experimental provision.
The technical solution adopted in the present invention is, the analogue means of rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation, comprise the gas generator for burning solid propellant, one end of gas generator coaxially connects converging portion, transition section, deposition section and jet pipe successively and forms through cavity, the other end sealing of gas generator is arranged, and gas generator inside is provided with propellant and the igniter pad for lighting propellant;
The internal diameter of deposition section is less than the internal diameter of gas generator, converging portion is the hollow taper cavity from gas generator to the smooth contraction of deposition section, the regulating ring for Particle Phase concentration in regulating gas is installed with near one end of transition section in converging portion, the inside cavity of deposition section is provided with the dislodger being carried out deposited particles phase by Action of Gravity Field, is placed with heat insulation layer test specimen in dislodger;
The gas-solid mixture produced that burns in gas generator flows through converging portion, and in order to regulate wherein Particle Phase concentration, then flow through transition section arrival deposition section, wherein, Particle Phase is deposited into dislodger, and gas phase is discharged by jet pipe.
Further, the sealed end of gas generator is connected with the front head push rod for fixing gas generator.
Further, igniter pad is positioned at by the center of propellant.
Further, regulating ring is the ring-type steel ring that inner wall smooth shrinks.
Further, dislodger is be arranged on the opening on deposition section outer wall, and dislodger openend is provided with dismountable cover plate in order to seal dislodger.
Further, cover plate is provided with for measuring the thermopair of Particle Phase deposition to heat insulation layer test specimen heat transfer capacity.
The invention has the beneficial effects as follows, structure is simple, installs, easy to use; Experimental provision by changing the deposit depth of regulating ring diameter or dislodger, thus regulates Particle Phase concentration and the ablation phenomen simulating large-sized solid rocket tube back wall cavity endoparticle phase mode of deposition lower thermal insulating layer.
Accompanying drawing explanation
Fig. 1 is the structural representation of the analogue means of rocket engine endoparticle phase mode of deposition lower thermal insulating layer of the present invention ablation;
Fig. 2 is the B-B cut-open view of Fig. 1.
In figure, 1. front head push rod, 2. gas generator, 3. propellant, 4. igniter pad, 5. converging portion, 6. regulating ring, 7. transition section, 8. deposits section, 9. dislodger, 10. jet pipe, 11. heat insulation layer test specimens, 12. thermopairs, 13. cover plates.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.
The invention provides the analogue means of a kind of rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation, as Fig. 1 and Fig. 2, comprise the gas generator 2 for burning solid propellant, one end of gas generator 2 coaxially connects converging portion 5, transition section 7, deposition section 8 and jet pipe 10 successively and forms through cavity, the other end sealing of gas generator 2 is arranged, gas generator 2 inside is provided with propellant 3 and the igniter pad 4 for lighting propellant 3
The internal diameter of deposition section 8 is less than the internal diameter of gas generator 2, converging portion 5 is the hollow taper cavity from gas generator 2 to the smooth contraction of deposition section 8, the regulating ring 6 for Particle Phase concentration in regulating gas is installed with near one end of transition section 7 in converging portion 5, the inside cavity of deposition section 8 is provided with the dislodger 9 being carried out deposited particles phase by Action of Gravity Field, is placed with heat insulation layer test specimen 11 in dislodger 9;
The gas-solid mixture produced that burns in gas generator 2 flows through converging portion 5, and in order to regulate wherein Particle Phase concentration, then flow through transition section 7 arrival deposition section 8, wherein, Particle Phase is deposited into dislodger 9, and gas phase is discharged by jet pipe 10.
Gas generator 2 is hollow cylinder, and one end of gas generator 2 is airtight and be provided with front head push rod 1, and front head push rod 1 is used for fixing gas generator 2, and the other end of gas generator 2 is communicated with the inlet end of converging portion 5.Front head push rod 1 pushes up mutually with thrust block, and gas generator 2 is fixed on its Test Rig.
Be provided with propellant 3 and the igniter pad 4 for lighting propellant 3 in gas generator 2, igniter pad 4 is positioned at by the center of propellant 3.Igniter pad 4 is connected to the priming supply be arranged on gas generator 2 outer wall, can light propellant 3 to produce fuel gas flow by igniter pad 4.
The fuel gas inlet end size of converging portion 5 is greater than its gas outlet end size, and ensure that the internal diameter of deposition section 8 is less than the internal diameter of gas generator 2, the gas outlet end of converging portion 5 is installed with the regulating ring 6 for Particle Phase concentration in regulating gas.The ring-type steel ring that regulating ring 6 shrinks for inner wall smooth.The external diameter fixed measure of regulating ring, internal diameter size is designed to multiple, the regulating ring 6 of suitable inner diameter size is selected to be arranged on converging portion 5 end adjacent with transition section 7 in real work, in order to adjust the concentration of Particle Phase in combustible mixture, from numerical evaluation and test findings, it is not simple linear relationship that particle erosion speed and concentration increase with the increase of regulating ring 6 diameter, thus according to the duty of realistic simulation device, the different regulating ring of multiple internal diameter size 6 can be set usually, such as diameter is respectively 40mm, 45mm, 50mm, 60mm and 80mm.
Dislodger 9 is for being arranged on the opening on deposition section 8 outer wall, and dislodger 9 openend is provided with dismountable cover plate 13 in order to seal dislodger 9, and dismountable cover plate 13 is placed with heat insulation layer test specimen 11.Cover plate 13 is provided with for measuring the thermopair 12 of Particle Phase deposition to heat insulation layer test specimen 11 heat transfer capacity.
By offering dislodger 9 at test section, the deposition of Particle Phase in flow field can be realized, later stage can obtain heat insulation layer mass ablative rate by the means such as thicknessmeter and electron microscope and observe the microscopic appearances such as charring layer, facilitates the research for Particle Phase mode of deposition lower thermal insulating layer ablation situation.
The course of work of the present invention is: push up mutually with thrust block with front head push rod 1, makes gas generator 2 be fixed on its Test Rig; Propellant 3 and igniter pad 4 are loaded on one end away from converging portion 5, gas generator 2 inside, notice that igniter pad 4 should hang on the powder center of propellant 3; Propellant 3 ignites by igniter pad 4 after the excitation of 24V priming supply; The gas-solid two-phase mixture produced by propellant 4 after igniting flows through converging portion 5 and regulating ring 6, at converging portion 5 with under the acting in conjunction of both regulating rings 6, and can the random concentration of Particle Phase in regulating gas potpourri; Particle Phase and combustion gas, after transition section 7, enter deposition section 8; Owing to being provided with dislodger 9 in deposition section 8, so a recirculating zone can be formed, because Particle Phase has larger inertia, be not easy to follow streamline, therefore mutually easy with gas phase separation and then enter recirculating zone at dislodger 9 regions particulate that air flow deflector is larger, under gravity, partial particulate phase and gas phase separation is made; Criterion is caught according to different, the Particle Phase had within the scope of certain size is deposited on the heat insulation layer test specimen 11 placed in dislodger 9, measure the heat transfer capacity of gained particle deposition to heat insulation layer test specimen 11 by thermopair 12, under reaching simulated rocket engine full-scale condition, alumina particle is to the object of heat insulation layer test specimen ablation.
In test, gas generator 2, converging portion 5, transition section 7, deposition section 8, all adopt butt-end packing between cover plate 13 and noxxle closure and use bolt to connect.
In this experiment, key job parameter is propellant charge aluminum content, stress loading, deformation quantity and deformation course etc.The analogue means of rocket engine endoparticle phase mode of deposition lower thermal insulating layer of the present invention ablation, finally can simulate alumina particle and deposit and study mode of deposition lower thermal insulating layer ablation problem.
Embodiment:
Assembled according to shown in Fig. 1 by experimental provision of the present invention in experiment, wherein front head push rod 1, gas generator 2, converging portion 5, transition section 7, deposition section 8, cover plate 13 and jet pipe 10 are 45# steel.The selection in propellant 3, regulating ring 6 diameter, heat insulation layer test specimen 11, jet pipe 10 larynx footpath determines by experiment condition.
Front head push rod 1 is length-adjustable two-part structure, and adopts M16*1.5 to be threaded with gas generator 2; Gas generator 2 is hollow cylinder, and its length is 195mm, and external diameter is 220mm, and internal diameter is 200mm, and its surface-welding has igniter head seat and pressure transducer seat, for connecting the igniter pad 4 being positioned at gas generator 2 and arranging; Equidistant perforate 20 on the ring flange at gas generator 2 two ends, aperture is Φ 13; Converging portion 5 total length 217mm, convergent angle 40 °, wall thickness is 10mm, the equidistant perforate of converging portion 5 front end flange 20, the equidistant perforate of rear end flanges 12, and aperture is Φ 13; Transition section 7 is hollow cylinder, and long is 100mm, and wall thickness is that all the other wall wall thickness of 25mm are 10mm, all equidistant perforate 12 of front and back end flange, and aperture is Φ 13; Depositor 8 housing total length 200mm, the analogue means 110mm form of 110mm rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation is opened in bottom, bottom wall thickness 25mm, and all the other face the wall and meditate thick is 10mm, all equidistant perforate 12 of front and back end flange, and aperture is Φ 13; Cover plate 13 is the steel plate of the analogue means 10mm of the analogue means 110mm rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation of 110mm rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation, the wide 50mm of its end face draw-in groove height 10mm can by long 60mm, wide 50mm, high 10mm test specimen inserts wherein, cover plate 13 bottom welding has thermopair seat, the linear perforate in edge along cover plate 13 16, aperture is Φ 6.5, is threaded for adopting with the housing of depositor 8.Thermopair 12 experimentally requires temperature range, and measuring accuracy has K type, Type B thermopair available.After experimental provision installs, tie point live wire and thermometric, load cell; After all detections are errorless, experimental provision is opened in countdown igniting.After experiment terminates, treat that experimental provision is cooled to room temperature, and give Particle Phase deposition to after the thermal insulation material 20min ablation time, more carefully dismantle experimental provision and do relevant cleaning.
In later stage work, service precision is the thicknessmeter of 0.01mm, measures the thickness after the ablation of heat insulation layer test specimen 11, by with early stage thickness contrast can calculate heat insulation layer mass ablative rate; Use Electronic Speculum or x-ray 3 Dimension Image Technique observe the microscopic appearances such as charring layer thus grasp ablation rule, obtain ablation characteristics.
Following table for respectively to tripropellant and three constituent elements change propellant test measured by data:
| Maximum linear ablating rate | Average thickness before ablation | Average thickness after ablation | |
| Tripropellant | 0.14mm/s | 9.83mm | 9.12mm |
| Three constituent elements change propellant | 0.204mm/s | 9.52mm | 8.61mm |
Claims (6)
1. the analogue means of rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation, it is characterized in that, comprise the gas generator (2) for burning solid propellant, one end of described gas generator (2) coaxially connects converging portion (5), transition section (7), deposition section (8) and jet pipe (10) successively and forms through cavity, the other end sealing of described gas generator (2) is arranged, described gas generator (2) inside is provided with propellant (3) and the igniter pad (4) for lighting propellant (3)
The internal diameter of described deposition section (8) is less than the internal diameter of gas generator (2), described converging portion (5) is the hollow taper cavity from gas generator (2) to deposition section (8) smooth contraction, the regulating ring (6) for Particle Phase concentration in regulating gas is installed with near one end of transition section (7) in described converging portion (5), the inside cavity of described deposition section (8) is provided with the dislodger (9) being carried out deposited particles phase by Action of Gravity Field, is placed with heat insulation layer test specimen (11) in described dislodger (9);
The gas-solid mixture that in described gas generator (2), burning produces flows through converging portion (5), in order to regulate wherein Particle Phase concentration, flow through transition section (7) again and arrive deposition section (8), wherein, Particle Phase is deposited into dislodger (9), and gas phase is discharged by jet pipe (10).
2. the analogue means of rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation as claimed in claim 1, it is characterized in that, the sealed end of described gas generator (2) is connected with the front head push rod (1) for fixing gas generator (2).
3. the analogue means of rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation as claimed in claim 2, it is characterized in that, described igniter pad (4) is positioned at by the center of propellant (3).
4. the analogue means of rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation as claimed in claim 3, is characterized in that, the ring-type steel ring that described regulating ring (6) shrinks for inner wall smooth.
5. the analogue means of rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation as claimed in claim 4, it is characterized in that, described dislodger (9) is for being arranged on the opening on described deposition section (8) outer wall, and described dislodger (9) openend is provided with dismountable cover plate (13) in order to seal dislodger (9).
6. the analogue means of rocket engine endoparticle phase mode of deposition lower thermal insulating layer ablation as claimed in claim 5, it is characterized in that, described cover plate (13) being provided with for measuring the thermopair (12) of Particle Phase deposition to heat insulation layer test specimen (11) heat transfer capacity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510107391.1A CN104833768B (en) | 2015-03-11 | 2015-03-11 | The analog of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510107391.1A CN104833768B (en) | 2015-03-11 | 2015-03-11 | The analog of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104833768A true CN104833768A (en) | 2015-08-12 |
| CN104833768B CN104833768B (en) | 2016-08-17 |
Family
ID=53811781
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510107391.1A Expired - Fee Related CN104833768B (en) | 2015-03-11 | 2015-03-11 | The analog of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104833768B (en) |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105388248A (en) * | 2015-12-31 | 2016-03-09 | 中国人民解放军国防科学技术大学 | Micrometer order solid particle ignition burning test device under jet stream condition |
| CN105527370A (en) * | 2015-11-03 | 2016-04-27 | 西北工业大学 | Apparatus for simulating insulation ablation under condition of particle deposition in cavity in back wall of submerged nozzle |
| CN105547505A (en) * | 2016-01-05 | 2016-05-04 | 西安航天动力技术研究所 | Apparatus for simulating and monitoring temperature field of missile enclosed stern compartment |
| CN106053711A (en) * | 2016-05-20 | 2016-10-26 | 湖北三江航天江河化工科技有限公司 | Ablation rate testing device and testing method |
| CN108644031A (en) * | 2018-05-08 | 2018-10-12 | 江西航天经纬化工有限公司 | A kind of solid propellant rocket insulation erosion rate test method |
| CN108982747A (en) * | 2018-08-28 | 2018-12-11 | 西安近代化学研究所 | A kind of hypervelocity projectile larynx lining ablation property testing experiment kettle |
| CN109163906A (en) * | 2018-09-21 | 2019-01-08 | 西北工业大学 | The Multi-functional analog engine of insulation erosion test |
| CN110005547A (en) * | 2019-04-30 | 2019-07-12 | 西北工业大学 | Experimental rig and method based on solid propellant rocket high-temperature particle sedimentation state |
| CN110388284A (en) * | 2019-05-27 | 2019-10-29 | 西北工业大学 | Multisection type rocket engine experimental provision and its collecting material method |
| CN110702565A (en) * | 2019-08-09 | 2020-01-17 | 西北工业大学 | Simulation device for metal particle flow-following combustion in high-temperature multi-component environment and use method |
| CN110749536A (en) * | 2019-10-16 | 2020-02-04 | 南京理工大学 | Solid rocket engine thermal protection material ablation experimental device |
| CN110953090A (en) * | 2019-10-17 | 2020-04-03 | 西北工业大学 | Test device for simulating two-phase flow ablation environment in isobaric multichannel rocket engine |
| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
| CN111751486A (en) * | 2020-06-28 | 2020-10-09 | 西北工业大学 | Diagnosis method and device for ignition combustion process and details of metal particles along with flow |
| CN112326868A (en) * | 2020-11-09 | 2021-02-05 | 北京航天发射技术研究所 | Temperature measurement method and temperature measurement device based on integral metal structure |
| CN112943484A (en) * | 2021-01-19 | 2021-06-11 | 西北工业大学 | Experimental device for researching heat transfer influence of roughness on wall surface of spray pipe |
| CN113669451A (en) * | 2021-08-31 | 2021-11-19 | 湖北三江航天红林探控有限公司 | Sealing structure and application thereof in high-temperature and high-pressure system |
| CN113847168A (en) * | 2021-09-28 | 2021-12-28 | 西北工业大学 | Experimental device for measuring chemical non-equilibrium parameters in spray pipe of solid rocket engine |
| CN114137143A (en) * | 2021-11-02 | 2022-03-04 | 星河动力(北京)空间科技有限公司 | Multilateral multi-outlet testing device for heat insulation layer of rocket engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0792159A (en) * | 1993-09-21 | 1995-04-07 | Hitachi Ltd | Method and equipment for evaluating firing/combustion characteristics of solid fuel and combustion method thereof |
| DE4425958B4 (en) * | 1993-07-22 | 2006-06-14 | Sumitomo Chemical Co., Ltd. | The thermal analysis apparatus |
| CN102854284A (en) * | 2012-09-11 | 2013-01-02 | 西北工业大学 | Solid fuel regression rate test device |
| CN103867339A (en) * | 2012-12-14 | 2014-06-18 | 上海新力动力设备研究所 | Ablation-proof structure of solid rocket engine |
| CN103967653A (en) * | 2014-04-28 | 2014-08-06 | 北京航空航天大学 | Axial injection end combustion solid-liquid rocket engine structure |
| CN104330519A (en) * | 2014-10-30 | 2015-02-04 | 西北工业大学 | Particle airflow suspension laser ignition experiment device |
-
2015
- 2015-03-11 CN CN201510107391.1A patent/CN104833768B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4425958B4 (en) * | 1993-07-22 | 2006-06-14 | Sumitomo Chemical Co., Ltd. | The thermal analysis apparatus |
| JPH0792159A (en) * | 1993-09-21 | 1995-04-07 | Hitachi Ltd | Method and equipment for evaluating firing/combustion characteristics of solid fuel and combustion method thereof |
| CN102854284A (en) * | 2012-09-11 | 2013-01-02 | 西北工业大学 | Solid fuel regression rate test device |
| CN103867339A (en) * | 2012-12-14 | 2014-06-18 | 上海新力动力设备研究所 | Ablation-proof structure of solid rocket engine |
| CN103967653A (en) * | 2014-04-28 | 2014-08-06 | 北京航空航天大学 | Axial injection end combustion solid-liquid rocket engine structure |
| CN104330519A (en) * | 2014-10-30 | 2015-02-04 | 西北工业大学 | Particle airflow suspension laser ignition experiment device |
Non-Patent Citations (1)
| Title |
|---|
| 杨昀等: "分段装药固体火箭发动机限燃层烧蚀实验方法", 《固体火箭技术》 * |
Cited By (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105527370A (en) * | 2015-11-03 | 2016-04-27 | 西北工业大学 | Apparatus for simulating insulation ablation under condition of particle deposition in cavity in back wall of submerged nozzle |
| CN105527370B (en) * | 2015-11-03 | 2017-07-28 | 西北工业大学 | Submerged nozzle back wall cavity endoparticle sedimentary condition lower thermal insulating layer ablation analogue means |
| CN105388248B (en) * | 2015-12-31 | 2017-03-29 | 中国人民解放军国防科学技术大学 | Micron order solid particle ignition assay device under the conditions of a kind of high velocity air |
| CN105388248A (en) * | 2015-12-31 | 2016-03-09 | 中国人民解放军国防科学技术大学 | Micrometer order solid particle ignition burning test device under jet stream condition |
| CN105547505A (en) * | 2016-01-05 | 2016-05-04 | 西安航天动力技术研究所 | Apparatus for simulating and monitoring temperature field of missile enclosed stern compartment |
| CN105547505B (en) * | 2016-01-05 | 2018-02-16 | 西安航天动力技术研究所 | A kind of device for simulating the closed deck store temperature field of monitoring guided missile |
| CN106053711A (en) * | 2016-05-20 | 2016-10-26 | 湖北三江航天江河化工科技有限公司 | Ablation rate testing device and testing method |
| CN108644031B (en) * | 2018-05-08 | 2020-05-12 | 江西航天经纬化工有限公司 | Method for testing ablation rate of heat insulation layer of solid rocket engine |
| CN108644031A (en) * | 2018-05-08 | 2018-10-12 | 江西航天经纬化工有限公司 | A kind of solid propellant rocket insulation erosion rate test method |
| CN108982747B (en) * | 2018-08-28 | 2021-06-15 | 西安近代化学研究所 | Superspeed ammunition throat liner ablation performance test kettle |
| CN108982747A (en) * | 2018-08-28 | 2018-12-11 | 西安近代化学研究所 | A kind of hypervelocity projectile larynx lining ablation property testing experiment kettle |
| CN109163906A (en) * | 2018-09-21 | 2019-01-08 | 西北工业大学 | The Multi-functional analog engine of insulation erosion test |
| CN110005547A (en) * | 2019-04-30 | 2019-07-12 | 西北工业大学 | Experimental rig and method based on solid propellant rocket high-temperature particle sedimentation state |
| CN110388284B (en) * | 2019-05-27 | 2020-10-27 | 西北工业大学 | Multi-section rocket engine experimental device and substance collection method thereof |
| CN110388284A (en) * | 2019-05-27 | 2019-10-29 | 西北工业大学 | Multisection type rocket engine experimental provision and its collecting material method |
| CN110702565A (en) * | 2019-08-09 | 2020-01-17 | 西北工业大学 | Simulation device for metal particle flow-following combustion in high-temperature multi-component environment and use method |
| CN110749536A (en) * | 2019-10-16 | 2020-02-04 | 南京理工大学 | Solid rocket engine thermal protection material ablation experimental device |
| CN110749536B (en) * | 2019-10-16 | 2022-04-01 | 南京理工大学 | Solid rocket engine thermal protection material ablation experimental device |
| CN110953090A (en) * | 2019-10-17 | 2020-04-03 | 西北工业大学 | Test device for simulating two-phase flow ablation environment in isobaric multichannel rocket engine |
| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
| CN111751486A (en) * | 2020-06-28 | 2020-10-09 | 西北工业大学 | Diagnosis method and device for ignition combustion process and details of metal particles along with flow |
| CN111751486B (en) * | 2020-06-28 | 2021-09-21 | 西北工业大学 | Diagnosis method and device for ignition combustion process and details of metal particles along with flow |
| CN112326868A (en) * | 2020-11-09 | 2021-02-05 | 北京航天发射技术研究所 | Temperature measurement method and temperature measurement device based on integral metal structure |
| CN112943484A (en) * | 2021-01-19 | 2021-06-11 | 西北工业大学 | Experimental device for researching heat transfer influence of roughness on wall surface of spray pipe |
| CN113669451A (en) * | 2021-08-31 | 2021-11-19 | 湖北三江航天红林探控有限公司 | Sealing structure and application thereof in high-temperature and high-pressure system |
| CN113847168A (en) * | 2021-09-28 | 2021-12-28 | 西北工业大学 | Experimental device for measuring chemical non-equilibrium parameters in spray pipe of solid rocket engine |
| CN113847168B (en) * | 2021-09-28 | 2023-06-09 | 西北工业大学 | Experimental device for measuring chemical unbalance parameters in jet pipe of solid rocket engine |
| CN114137143A (en) * | 2021-11-02 | 2022-03-04 | 星河动力(北京)空间科技有限公司 | Multilateral multi-outlet testing device for heat insulation layer of rocket engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104833768B (en) | 2016-08-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104833768A (en) | Simulation device of thermal insulation layer ablation under condition of particle phase deposition in rocket engine | |
| CN105448177B (en) | Double venturi analogue means for exploration rocket engine internal insulation ablation phenomen | |
| CN105527370B (en) | Submerged nozzle back wall cavity endoparticle sedimentary condition lower thermal insulating layer ablation analogue means | |
| CN104330519B (en) | A kind of particle pneumatic floating laser ignition experimental provision | |
| CN101975125B (en) | Device for measuring linear burning rate of liquid propellant in high pressure environment | |
| CN105388248A (en) | Micrometer order solid particle ignition burning test device under jet stream condition | |
| CN104568631A (en) | Gas-solid two-phase erosion wear testing device | |
| CN202854103U (en) | Testing device for regression rate of solid fuel | |
| CN112098100B (en) | Solid engine heat insulation layer ablation performance parallel examination test device | |
| CN113417760B (en) | Solid propellant oxygen combustion split charging coupling combustion transparent window experimental device and experimental method | |
| CN109404166B (en) | Wide-working-condition liquid hydrogen-liquid oxygen torch type electric ignition device | |
| CN101393098A (en) | Material ablation detection device and method in high-temperature gas | |
| CN109163906A (en) | The Multi-functional analog engine of insulation erosion test | |
| CN113915029A (en) | Test device for nozzle throat lining of rocket engine | |
| CN107703030A (en) | A kind of Visualizing Test System that can meet extreme condition measurement needs | |
| CN109277556B (en) | Dual-purpose tundish roaster burner | |
| CN104390215A (en) | Cone-shaped flame burner applicable for researching combustion characteristics of liquid fuel and method thereof | |
| CN103743571B (en) | For the air heating apparatus of long-time supersonic combustion | |
| CN110388284B (en) | Multi-section rocket engine experimental device and substance collection method thereof | |
| CN204422361U (en) | A kind of gas-particle two-phase erosion abrasion test device | |
| CN216198530U (en) | Test device for checking efficiency of solid rocket engine jet pipe | |
| Dahiya et al. | Improvement of the domestic LPG cooking stoves: a review | |
| CN104456553A (en) | Conical flame combustor suitable for researching combustion characteristics of liquid fuel and method thereof | |
| CN103134899A (en) | Combustion performance test method of nanometer aluminum powder | |
| CN206361685U (en) | A kind of tiny-oil ignition and smooth combustion apparatus with coal dust flow velocity and concentration monitor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160817 Termination date: 20170311 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |