CN104833768B - The analog of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation - Google Patents

The analog of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation Download PDF

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Publication number
CN104833768B
CN104833768B CN201510107391.1A CN201510107391A CN104833768B CN 104833768 B CN104833768 B CN 104833768B CN 201510107391 A CN201510107391 A CN 201510107391A CN 104833768 B CN104833768 B CN 104833768B
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China
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gas generator
insulating layer
phase
thermal insulating
rocket engine
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CN201510107391.1A
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CN104833768A (en
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刘洋
关轶文
何国强
李江
刘佩进
陈剑
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Northwestern Polytechnical University
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Northwestern Polytechnical University
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Abstract

The invention discloses the analog of a kind of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation, including the gas generator for burning solid propellant, one end of gas generator sequentially coaxially connects converging portion, changeover portion, deposition section and jet pipe and forms through cavity, the other end of gas generator seals and arranges, and is provided with propellant and for lighting the igniter pad of propellant inside gas generator.Present configuration is simple, installs, easy to use;Experimental provision is with crossing the deposit depth changing regulation ring diameter with dislodger, thus regulates the ablation phenomen of granule phase concentration and simulation large-sized solid rocket engine submerged nozzle back wall cavity endoparticle phase sedimentary condition lower thermal insulating layer.

Description

The analog of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation
Technical field
The invention belongs to rocket engine technical field, relate to a kind of rocket engine endoparticle and deposit bar mutually The analog of part lower thermal insulating layer ablation.
Background technology
In order to improve specific impulse and shorten electromotor entire length, generally in modern Design of Solid Propellant Rocket Engine In propellant, add metal dust (such as Al, Mg), and submerged nozzle is widely used.But starting In machine work process, along with the passage in combustion face gradually forms a cavity in submerged nozzle back wall region, should There is complicated recirculating zone in cavity, there is bigger inertia due to granule, it is not easy to follow streamline mutually, Therefore easily separate with air-flow in the jet pipe back wall region that air flow deflector is bigger and enter recirculating zone, then sink Amass in cavity, become slag;At the end of large-scale segmented rocket engine horizontal firing, in following table The existence of a large amount of deposition is had on face.
The most domestic and international three below aspect that insulation erosion experimentation technology is concentrated mainly on: (1) Oxidizing gas and the chemical ablation of heat insulation layer;(2) air-flow erosion to heat insulation layer;(3) granule phase Mechanical erosion to heat insulation layer.But alumina particle sedimentary condition lower thermal insulating layer ablation experiments technology is domestic Document rarely has to be mentioned.
Summary of the invention
It is an object of the invention to provide a kind of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation Analog, with fill up in prior art in cavity deposited particles mutually under conditions of, research is not solid The blank of body rocket engine insulation ablation phenomen experimental provision.
The technical solution adopted in the present invention is, rocket engine endoparticle phase sedimentary condition lower thermal insulating layer burns The analog of erosion, including the gas generator for burning solid propellant, one end of gas generator Sequentially coaxially connecting converging portion, changeover portion, deposition section and jet pipe and form through cavity, combustion gas occurs The other end of device seals and arranges, and is provided with propellant and for lighting the igniting of propellant inside gas generator Medicated bag;
The internal diameter of deposition section is less than the internal diameter of gas generator, and converging portion is to deposition section from gas generator The hollow taper cavity of smooth contraction, in converging portion, the one end near changeover portion is installed with for regulating The regulation ring of granule phase concentration in combustion gas, the inside cavity of deposition section is provided with and is deposited by action of gravity The dislodger of grain phase, is placed with heat insulation layer test specimen in dislodger;
The gas-solid mixture produced that burns in gas generator flows through converging portion, in order to regulate wherein granule phase Concentration, passes through changeover portion and arrives deposition section, and wherein, granule deposits mutually to dislodger, and gas phase is by spray Bank of tubes goes out.
Further, the sealed end of gas generator connects the front head top for fixing gas generator Bar.
Further, igniter pad is positioned at by the center of propellant.
Further, regulation ring is the ring-type steel ring that inner wall smooth shrinks.
Further, dislodger is the opening being arranged on deposition section outer wall, and dislodger opening is provided with Dismountable cover plate is in order to seal dislodger.
Further, cover plate is provided with and deposits the heat to heat insulation layer test specimen heat output mutually for measuring granule Galvanic couple.
The invention has the beneficial effects as follows, simple in construction, install, easy to use;Experimental provision is by changing Regulation ring diameter or the deposit depth of dislodger, thus regulate granule phase concentration and simulation large-sized solid rocket The ablation phenomen of engine jet pipe back wall cavity endoparticle phase sedimentary condition lower thermal insulating layer.
Accompanying drawing explanation
Fig. 1 is the analog of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation of the present invention Structural representation;
Fig. 2 is the B-B sectional view of Fig. 1.
In figure, 1. front head push rod, 2. gas generator, 3. propellant, 4. igniter pad, 5. receive The section of holding back, 6. regulation ring, 7. changeover portion, 8. deposition section, 9. dislodger, 10. jet pipe, 11. is adiabatic Layer test specimen, 12. thermocouples, 13. cover plates.
Detailed description of the invention
The present invention is described in detail with detailed description of the invention below in conjunction with the accompanying drawings.
The invention provides the simulation of a kind of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation Device, such as Fig. 1 and Fig. 2, including the gas generator 2 for burning solid propellant, combustion gas occurs One end of device 2 sequentially coaxially connects converging portion 5, changeover portion 7, deposition section 8 and jet pipe 10 and formation is passed through Logical cavity, the other end of gas generator 2 seals and arranges, and gas generator 2 is internal is provided with propellant 3 and for lighting the igniter pad 4 of propellant 3,
The internal diameter of deposition section 8 is less than the internal diameter of gas generator 2, and converging portion 5 is from gas generator 2 To the hollow taper cavity of the deposition smooth contraction of section 8, in converging portion 5, the one end near changeover portion 7 is fixed Being provided with the regulation ring 6 of granule phase concentration in regulating gas, the inside cavity of deposition section 8 is provided with logical Overweight masterpiece is used for the dislodger 9 of deposited particles phase, 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, in order to regulate wherein Grain phase concentration, passes through changeover portion 7 and arrives deposition section 8, and wherein, granule deposits mutually to dislodger 9, Gas phase is discharged by jet pipe 10.
Gas generator 2 is hollow cylinder, and one end of gas generator 2 is airtight and is provided with front head Push rod 1, front head push rod 1 is used for fixing gas generator 2, the other end of gas generator 2 and receipts The arrival end connection of the section of holding back 5.Front head push rod 1 pushes up mutually with thrust block so that gas generator 2 is fixed On its Test Rig.
Propellant 3 it is provided with and for lighting the igniter pad 4 of propellant 3, point in gas generator 2 Gunpowder bag 4 is positioned at by the center of propellant 3.Igniter pad 4 is connected to be arranged on gas generator Priming supply on 2 outer walls, can light propellant 3 to produce fuel gas flow by igniter pad 4.
The fuel gas inlet end size of converging portion 5 is more than its gas outlet end size, it is ensured that deposition section 8 Internal diameter is less than the internal diameter of gas generator 2, and the gas outlet end of converging portion 5 is installed with for regulating The regulation ring 6 of granule phase concentration in combustion gas.The ring-type steel ring that regulation ring 6 shrinks for inner wall smooth.Regulation The external diameter fixed dimension of ring, internal diameter size is designed as multiple, selects suitable inner diameter size in real work Regulation ring 6 is arranged on the end that converging portion 5 is adjacent with changeover portion 7, in order to adjust in flammable mixture The concentration of grain phase, is increased and regulation from numerical computations and result of the test, particle erosion speed and concentration Ring 6 diameter increase is not simple linear relationship, thus according to the duty of realistic simulation device, logical Often can arrange the regulation ring 6 that multiple internal diameter size is different, such as diameter is respectively 40mm, 45mm, 50mm, 60mm and 80mm.
Dislodger 9 is the opening being arranged on deposition section 8 outer wall, and dislodger 9 opening is provided with removable The cover plate 13 unloaded, in order to seal dislodger 9, dismountable cover plate 13 is placed with heat insulation layer test specimen 11. It is provided with on cover plate 13 and deposits the thermocouple 12 to heat insulation layer test specimen 11 heat output mutually for measuring granule.
By offering dislodger 9 at test section, can realize granule deposition in flow field, the later stage passes through Calibrator and the means such as ultramicroscope can get heat insulation layer mass ablative rate with to observe charring layer etc. micro- See pattern, facilitate the research for granule phase sedimentary condition lower thermal insulating layer ablation situation.
The work process of the present invention is: push up mutually with thrust block with front head push rod 1 so that gas generator 2 are fixed on its Test Rig;It is internal away from convergence that propellant 3 and igniter pad 4 are loaded on gas generator 2 One end of section 5, notices that igniter pad 4 should hang on the powder center of propellant 3;Igniter pad 4 warp After the excitation of 24V priming supply, propellant 3 is ignited;The gas-particle two-phase produced by propellant 4 after igniting mixes Compound flows through converging portion 5 and regulation ring 6, under the common effect of converging portion 5 and regulation both rings 6, Can the random concentration of granule phase in regulating gas mixture;Granule phase and combustion gas after changeover portion 7, Enter deposition section 8;Owing to deposition section 8 being provided with dislodger 9, a recirculating zone then can be formed, There is bigger inertia due to granule, it is not easy to follow streamline mutually, therefore in the deposition that air flow deflector is bigger Groove 9 regions particulate easily separates and then enters recirculating zone mutually with gas phase, under gravity so that portion Granule is divided to separate with gas phase;According to different capture criterions, have the granule phase in the range of certain size It is deposited in dislodger 9 on the heat insulation layer test specimen 11 placed, measures gained granule by thermocouple 12 The deposition heat output to heat insulation layer test specimen 11, reaches aluminium oxide granule under simulated rocket electromotor full-scale condition The grain purpose to heat insulation layer test specimen ablation.
In test, gas generator 2, converging portion 5, changeover portion 7, deposition section 8, cover plate 13 and spray All use end face seal between lid and make to be connected with.
In this tests, key job parameter is propellant charge aluminum content, stress loading, deformation quantity And deformation course etc..The mould of the rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation of the present invention Intend device, finally can simulate alumina particle and deposit and study sedimentary condition lower thermal insulating layer ablation problem.
Embodiment:
The experimental provision of the present invention is assembled shown in Fig. 1 by experiment, wherein front head push rod 1, Gas generator 2, converging portion 5, changeover portion 7, deposition section 8, cover plate 13 and jet pipe 10 are 45# Steel.Propellant 3, regulation ring 6 diameter, heat insulation layer test specimen 11, jet pipe 10 larynx footpath selection by reality Test operating mode to determine.
Front head push rod 1 is length-adjustable two-part structure, and uses M16*1.5 with gas generator 2 Threaded;Gas generator 2 is hollow cylinder, its a length of 195mm, and external diameter is 220mm, Internal diameter is 200mm, and its surface soldered has igniter head seat and pressure transducer seat, is positioned at combustion for connection The igniter pad 4 arranged in gas generator 2;Equidistant perforate 20 on the ring flange at gas generator 2 two ends Individual, 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, aperture is Φ 13; Changeover portion 7 is hollow cylinder, a length of 100mm, and wall thickness is that remaining wall wall thickness of 25mm is 10mm, all equidistant perforate 12 of front and back end flange, aperture is Φ 13;Depositor 8 housing total length 200mm, The analog of 110mm rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation is driven in bottom 110mm form, bottom wall thickness 25mm, remaining faces the wall and meditates thick is 10mm, and front and back end flange is the most equidistantly opened 12, hole, aperture is Φ 13;Cover plate 13 is under 110mm rocket engine endoparticle phase sedimentary condition The analog 110mm rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation of insulation erosion The steel plate of analog 10mm, its end face draw-in groove height 10mm width 50mm can be wide by long 60mm 50mm, high 10mm test specimen is inserted, and cover plate 13 bottom welding has thermocouple seat, along cover plate 13 The linear perforate in edge 16, aperture is Φ 6.5, threadeds for using with the housing of depositor 8. Thermocouple 12 is then according to requirement of experiment temperature range, and certainty of measurement has K-type, Type B thermocouple to be available for choosing Select.After experimental provision installs, junction point live wire and thermometric, load cell;All detections are errorless After, experimental provision is opened in countdown igniting.After experiment terminates, treat that experimental provision is cooled to room temperature, and compose Give after granule deposits mutually to the adiabator 20min ablation time, more carefully dismounting experimental provision being correlated with Cleaning.
In later stage work, service precision is the calibrator of 0.01mm, after measuring heat insulation layer test specimen 11 ablation Thickness, by heat insulation layer mass ablative rate can be calculated with the contrast of early stage thickness;Use Electronic Speculum or x Ray 3 Dimension Image Technique is observed the microscopic appearances such as charring layer thus is grasped ablation rule, it is thus achieved that ablation is special Property.
Following table is tripropellant and three constituent elements to change propellant respectively test measured 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 analog of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation, it is characterised in that Including the gas generator (2) for burning solid propellant, one end of described gas generator (2) Sequentially coaxially connect converging portion (5), changeover portion (7), deposition section (8) and jet pipe (10) and formed Through cavity, the other end of described gas generator (2) seals and arranges, described gas generator (2) Inside is provided with propellant (3) and is used for lighting the igniter pad (4) of propellant (3),
The internal diameter of described deposition section (8) is less than the internal diameter of gas generator (2), described converging portion (5) For from gas generator (2) to deposition section (8) smooth contraction hollow taper cavity, described convergence In section (5), the one end near changeover portion (7) is installed with granule phase concentration in regulating gas Regulation ring (6), the inside cavity of described deposition section (8) is provided with carrys out deposited particles phase by action of gravity Dislodger (9), be 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 granule phase concentration, pass through changeover portion (7) and arrive deposition section (8), wherein, granule phase Depositing to dislodger (9), gas phase is discharged by jet pipe (10).
2. as claimed in claim 1 rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation Analog, it is characterised in that the sealed end of described gas generator (2) connects to be had for fixing combustion The front head push rod (1) of gas generator (2).
3. as claimed in claim 2 rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation Analog, it is characterised in that described igniter pad (4) is positioned at by the center of propellant (3).
4. as claimed in claim 3 rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation Analog, it is characterised in that described regulation ring (6) is the ring-type steel ring that inner wall smooth shrinks.
5. as claimed in claim 4 rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation Analog, it is characterised in that described dislodger (9) is for be arranged on described deposition section (8) outward Opening on wall, described dislodger (9) opening is provided with dismountable cover plate (13) in order to close Envelope dislodger (9).
6. as claimed in claim 5 rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation Analog, it is characterised in that be provided with on described cover plate (13) and deposit mutually absolutely for measuring granule The thermocouple (12) of thermosphere test specimen (11) heat output.
CN201510107391.1A 2015-03-11 2015-03-11 The analog of rocket engine endoparticle phase sedimentary condition lower thermal insulating layer ablation Expired - Fee Related CN104833768B (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
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
CN106053711B (en) * 2016-05-20 2017-11-10 湖北三江航天江河化工科技有限公司 A kind of ablating rate test device and method of testing
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
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
CN110702565B (en) * 2019-08-09 2020-11-03 西北工业大学 Simulation device for metal particle flow-following combustion in high-temperature multi-component environment and use method
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

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5588746A (en) * 1993-07-22 1996-12-31 Sumitomo Chemical Company, Limited Apparatus for thermal analysis
JP2927154B2 (en) * 1993-09-21 1999-07-28 株式会社日立製作所 Apparatus and method for evaluating ignition and combustion characteristics of solid fuel and method for combustion of solid fuel
CN102854284B (en) * 2012-09-11 2015-06-24 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
CN103967653B (en) * 2014-04-28 2016-06-08 北京航空航天大学 A kind of axially injection end combustion solid-liquid rocket structure
CN104330519B (en) * 2014-10-30 2016-05-18 西北工业大学 A kind of particle pneumatic floating laser ignition experimental provision

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