CN110196261A - The test device and method of the outer heat insulation material Burning corrosion resistance energy of solid propellant rocket - Google Patents
The test device and method of the outer heat insulation material Burning corrosion resistance energy of solid propellant rocket Download PDFInfo
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- CN110196261A CN110196261A CN201811468689.5A CN201811468689A CN110196261A CN 110196261 A CN110196261 A CN 110196261A CN 201811468689 A CN201811468689 A CN 201811468689A CN 110196261 A CN110196261 A CN 110196261A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
Abstract
The present invention relates to the test devices and method of heat insulation material Burning corrosion resistance energy outside a kind of solid propellant rocket, including flame flow nozzle, sample system, cooling water recirculation system and back temperature measurement system, sample system includes ablation sample, cooling jacket, specimen holder and temperature thermocouple, the side of ablation sample is fixed by specimen holder, the thermometric face at ablation sample back side liner adjustment specimen height, heat insulating mattress is lined between liner and specimen holder pedestal, middle section lays temperature thermocouple, temperature thermocouple is connect with back temperature measurement system, cooling water recirculation system is installed outside cooling jacket.The present invention uses band water-cooling circulating system cooling to take away sample surrounding waste heat, avoids influence of the waste heat to warm result is carried on the back.Operation of the present invention is easy, at low cost, can effectively eliminate the heat transfer of sample surrounding to the adverse effect of back temperature measurement, quantitatively characterize different-thickness, property, complex method outer heat insulation material anti-ablation and heat-proof quality.
Description
Technical field
It is anti-that the present invention relates to heat insulation materials outside a kind of solid propellant rocket of combination plasma heat source ablation experiments system
Ablation property test device and method belong to aerospace experimental method.
Background technique
Hypersonic solid propellant rocket aerothermal ablation in atmosphere high speed flight is serious.It generallys use outer anti-
The ablative-type protective coatings heat insulation material such as hot coating, polymer matrix composites carries out the pneumatic thermal protection on motor body surface, by being pyrolyzed,
The ablation processes such as fusing, evaporation (distillation), thermal chemical reaction consume Self substances, prevent heat from promptly passing to engine shell
Body surface face achievees the purpose that maintain motor body structural strength.Currently, arc tunnel ablation examines outer heat insulation material performance
It is the maximally efficient section that has, but testing cost is high, the period is long, the curriculum test means of material screening stage should not be used as.Other are such as oxygen-
The common ground simulation ablative test method such as acetylene ablation, plasma ablation, quartz lamp radiant heating, because heat flow density is not easy to adjust
Section, the problems such as sample thickness is non-adjustable, specimen holder is mostly steel or graphite-like Heat Conduction Material influence the accuracy of test result, no
Easily obtain the effective information of material ablation performance.
Summary of the invention
Technical problem to be solved by the invention is to provide heat insulation material Burning corrosion resistance energy outside a kind of solid propellant rocket
Test device, with solve eliminate sample surrounding heat transfer to back temperature measurement adverse effect, in real time obtain ablation process in sample
Carry on the back temperature dynamic change, quantitatively characterize different-thickness, property, complex method outer heat insulation material anti-ablation and heat-proof quality
The problem of.
The present invention includes following technical solution: the test device of the outer heat insulation material Burning corrosion resistance energy of solid propellant rocket,
Including flame flow nozzle, sample system, cooling water recirculation system and back temperature measurement system, the sample system includes ablation examination
The side of sample, cooling jacket, specimen holder and temperature thermocouple, ablation sample is fixed by specimen holder, ablation sample back
The thermometric face in face liner adjustment specimen height, is lined with heat insulating mattress, liner and heat insulating mattress center between liner and specimen holder pedestal
Through-hole is opened up, the middle section of through-hole lays temperature thermocouple, and temperature thermocouple is connect with back temperature measurement system, ablation sample
The center in ablation face keeps coaxial with flame flow nozzle center, and flame ablation angle is 90 °；After specimen holder places ablation sample
It is put into cooling jacket, cooling water recirculation system is installed, cooling water recirculation system is by cooling jacket to burning outside cooling jacket
The side of erosion sample and specimen holder cools down.
Generally, the diameter and thickness of ablation sample can require to be selected according to actual measurement, for convenient test and survey
Result unified standard is measured, the preferred diameter of ablation sample of the present invention is Φ 50mm, with a thickness of 5 ~ 10 mm.The liner uses
Copper lining, copper lining diameter are Φ 50mm, with a thickness of 1 ~ 5 mm.
The test method of the outer heat insulation material Burning corrosion resistance energy of solid propellant rocket, the steps include:
(1) sample system and back temperature measurement system are installed
Prepare the ablation sample for meeting test request；Cooling jacket is fixed on sample frame, cooling jacket leads to cooling water；It will peace
The specimen holder for putting ablation sample is put into cooling jacket, adjusts ablation specimen height, ablation sample center and flame stream with liner
Nozzle center keeps coaxial, and flame ablation angle is 90 °；Ablation sample back side middle section lays thermocouple；It is pressed from both sides using cooling
Recirculated cooling water in set takes away ablation sample surrounding waste heat, avoids influence of the waste heat to back temperature measurement result, letter
Turn to the one-dimensional ablation perpendicular to thickness direction；Temperature thermocouple real-time measurement and record display ablation sample back temperature variation；
(2) plasma heat source excitation and flame stream heat flow density are adjusted
The argon gas or nitrogen/argon-mixed generation high-temperature plasma heat source of certain flow are ionized with plasma ablation device, and through drawing
Wa Er flame flow nozzle forms flame stream, by regulating gas type, gas flow, ablation distance, arc current intensity, provides different heat
The hot-fluid of current density carries out ablation to ablation sample within the setting time；
(3) ablation of ablation sample, data acquisition and processing
Ablation is carried out respectively to ablation sample according to setup parameter, ablation sample weight, thickness after testing ablation shoot surface
Pattern calculates linear ablative rate, carbonation rate and mass ablative rate, in conjunction with warm data are carried on the back in the ablation period, evaluates material anti-ablation
Performance.
Beneficial effect
Compared with prior art, the present invention having the advantage that
(1) it can provide the high-temperature plasma flame stream of different heat flow densities, thermal ablation condition can quantify to a certain degree, be suitble to outer solar heat protection
Material anti-ablation performance test.
(2) by the fixed sample of the dedicated sample collet with water-cooling circulating system of installation internal diameter Φ 50mm, with cooling
Water takes away sample surrounding waste heat, avoids influence of the waste heat to warm result is carried on the back, is reduced to one perpendicular to thickness direction
Ablation is tieed up, it is higher than conventional test methodologies accuracy.
(3) easy to operate, at low cost, strong applicability, sample thickness is adjustable, is suitble to different-thickness, property, complex method
Outer heat insulation material test.
(4) for oxy-acetylene ablation etc., other ablative methods have reference to ablative method.
Detailed description of the invention
Fig. 1 is the test device schematic diagram of the outer heat proof material ablation performance of solid propellant rocket, including gas source 1, control
System 2, flame flow nozzle 3, sample system 4, cooling water recirculation system 5 and back temperature measurement system 6.
Fig. 2 is ablation specimen size schematic diagram.
Fig. 3 is copper lining scale diagrams.
Fig. 4 is heat insulating mattress scale diagrams.
Fig. 5 is sample system schematic, including: ablation sample 41；Cooling jacket 42；Specimen holder 43；Copper lining
44；Heat insulating mattress 45；Temperature thermocouple 46.
Fig. 6 is cooling water recirculation system schematic diagram, including: cooling jacket outer wall 51；Water inlet 52；In cooling jacket
Wall 53；Water outlet 54.
Fig. 7 is ablation specimen holder schematic diagram.
Specific embodiment
With reference to the accompanying drawing and specific embodiment the present invention is described in further detail.
As shown in Fig. 1, the test device of the outer heat insulation material Burning corrosion resistance energy of a kind of solid propellant rocket, including gas source
1, control system 2, flame flow nozzle 3, sample system 4, cooling water recirculation system 5 and back temperature measurement system 6, gas source 1 pass through control
System 2 processed is that flame flow nozzle 3 provides flame stream,
As shown in Fig. 2,41 diameter of ablation sample is Φ 50mm, with a thickness of 5 ~ 10 mm.
As shown in Fig. 3,44 diameter of copper lining is Φ 50mm, with a thickness of 1 ~ 5 mm, and 44 center of copper lining opens up through-hole.
As shown in Fig. 4,45 diameter of heat insulating mattress is Φ 50mm, 45 center of heat insulating mattress opens up through-hole.
As shown in Fig. 5, sample system 4 include ablation sample 41, cooling jacket 42, specimen holder 43, copper lining 44, every
The side of heat pad 45 and temperature thermocouple 46, ablation sample 41 is fixed by specimen holder 43, the survey at 41 back side of ablation sample
Warm face copper lining 44 adjusts specimen height, and 44 outside of copper lining is thermally shielded with heat insulating mattress 45,41 back side of ablation sample center
Region lays temperature thermocouple 46, and temperature thermocouple 46 is connect with back temperature measurement system 6, the center in the ablation face of ablation sample 41
Keep coaxial with 3 center of flame flow nozzle, flame ablation angle is 90 °；As shown in Fig. 7, specimen holder 43 places ablation examination
It is put into after sample 41 in cooling jacket 42, cooling water recirculation system 5 is installed outside cooling jacket 42, cooling water recirculation system 5 passes through
Cooling jacket 42 cools down the side of ablation sample 41 and specimen holder 43.
As shown in Fig. 6, cooling water recirculation system 5 includes cooling jacket outer wall 51；Water inlet 52；Cooling jacket inner wall
53；Water outlet 54.
The test method of the outer heat insulation material Burning corrosion resistance energy of solid propellant rocket, the steps include:
One, sample system and back temperature measurement system are installed
(1) the ablation sample for meeting test request according to Fig. 2 preparation diameter of phi 50mm, thickness, measures ablation sample by every group 5
Initial mass, thickness shoot ablation specimen surface pattern.
(2) cooling jacket of internal diameter Φ 50mm is fixedly mounted on sample frame according to Fig. 3, cooling water recirculation system into
The mouth of a river, water outlet hose are connect with cooling water circulating pump, open recirculated water.
(3) ablation sample is placed in the groove of specimen holder according to Fig. 5, according to ablation sample thickness copper lining tune
Whole ablation specimen height is lined with heat insulating mattress to prevent back-cooled water-cooled, thermometric thermoelectricity between copper lining and specimen holder pedestal
The even cooling jacket backside vias cloth that passes through is put into ablation sample back side central location, fixed；Temperature thermocouple and back temperature are surveyed
The temperature instrumentation of amount system connects, the back temperature variation of real-time display ablation sample.
(4) mounted specimen holder is placed in cooling jacket, the ablation face and cooling jacket end face of ablation sample
Concordantly, ablation sample center keeps coaxial with flame flow nozzle center, and flame ablation angle is 90 °.
Two, it excites plasma heat source and adjusts flame stream heat flow density
(1) argon gas or nitrogen/argon gas mixing source gas pressure are adjusted to specified range.
(2) plasma ablation device is opened, argon gas is ionized or nitrogen/argon mixture gas generates plasma and through Lavalle flame
Flow nozzle is injected into atmospheric environment and forms flame stream, and the cold wall heat flow density of flame stream different location is demarcated with water card calorimeter.
(3) according to cold wall heat flow density calibration result, by corresponding relationship adjustment gas flow, ablation distance and arc electricity in table
Sample ablated surface heat flow density is adjusted to target value by intensity of flow.
Three, sample ablation, data acquisition and processing
(1) opening device carries out ablation to ablation sample at the appointed time by setting parameter, records in the ablation time burn in real time
Lose sample back temperature.
(2) after ablation, ablation sample is removed, after sample to be ablated is cooling, measures ablation sample final weight, thickness
Degree calculates mass ablative rate and linear ablative rate, shoots the surface topography of sample after ablation.
(3) above step is repeated, completes the ablation of remaining 4 ablation sample, test result takes being averaged for 5 ablation samples
Value evaluates material Burning corrosion resistance energy in conjunction with warm data are carried on the back in the ablation period.
Claims (4)
1. a kind of test device of the outer heat insulation material Burning corrosion resistance energy of solid propellant rocket, including flame flow nozzle (3), sample system
System (4), cooling water recirculation system (5) and back temperature measurement system (6), it is characterised in that: the sample system (4) includes ablation
Sample (41), cooling jacket (42), specimen holder (43) and temperature thermocouple (46), the side of ablation sample (41) is by specimen holder
Tool (43) is fixed, the thermometric face liner adjustment specimen height at ablation sample (41) back side, liner and specimen holder (43)
It is lined between pedestal heat insulating mattress (45), liner and heat insulating mattress (45) center open up through-hole, and the middle section of through-hole lays thermometric thermoelectricity
Even (46), temperature thermocouple (46) are connect with back temperature measurement system (6), and the center in the ablation face of ablation sample (41) and flame stream spray
Mouth (3) center keeps coaxial, and flame ablation angle is 90 °；Specimen holder (43) is put into cooling after placing ablation sample (41)
In collet (42), cooling water recirculation system (5) are installed outside cooling jacket (42), cooling water recirculation system (5) passes through cooling folder
Set (42) cools down the side of ablation sample (41) and specimen holder (43).
2. test device according to claim 1, it is characterised in that: ablation sample (41) diameter is Φ 50mm, thickness
Degree is 5 ~ 10 mm.
3. test device according to claim 2, it is characterised in that: the liner uses copper lining, and copper lining diameter is
Φ 50mm, with a thickness of 1 ~ 5 mm.
4. heat insulation material Burning corrosion resistance energy outside the solid propellant rocket of any test device according to claim 1 ~ 3
Test method the steps include:
(1) sample system and back temperature measurement system are installed
Prepare the ablation sample for meeting test request；Cooling jacket is fixed on sample frame, cooling jacket leads to cooling water；It will peace
The specimen holder for putting ablation sample is put into cooling jacket, adjusts ablation specimen height, ablation sample center and flame stream with liner
Nozzle center keeps coaxial, and flame ablation angle is 90 °；Ablation sample back side middle section lays thermocouple；It is pressed from both sides using cooling
Recirculated cooling water in set takes away ablation sample surrounding waste heat, avoids influence of the waste heat to back temperature measurement result, letter
Turn to the one-dimensional ablation perpendicular to thickness direction；Temperature thermocouple real-time measurement and record display ablation sample back temperature variation；
(2) plasma heat source excitation and flame stream heat flow density are adjusted
The argon gas or nitrogen/argon-mixed generation high-temperature plasma heat source of certain flow are ionized with plasma ablation device, and through drawing
Wa Er flame flow nozzle forms flame stream, by regulating gas type, gas flow, ablation distance, arc current intensity, provides different heat
The hot-fluid of current density carries out ablation to ablation sample within the setting time；
(3) ablation of ablation sample, data acquisition and processing
Ablation is carried out respectively to ablation sample according to setup parameter, ablation sample weight, thickness after testing ablation shoot surface
Pattern calculates linear ablative rate, carbonation rate and mass ablative rate, in conjunction with warm data are carried on the back in the ablation period, evaluates material anti-ablation
Performance.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811468689.5A CN110196261A (en) | 2018-12-03 | 2018-12-03 | The test device and method of the outer heat insulation material Burning corrosion resistance energy of solid propellant rocket |
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| CN201811468689.5A CN110196261A (en) | 2018-12-03 | 2018-12-03 | The test device and method of the outer heat insulation material Burning corrosion resistance energy of solid propellant rocket |
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Cited By (3)
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| CN110596180A (en) * | 2019-08-18 | 2019-12-20 | 南京理工大学 | Ablation simulation fixing device for engine interstage protective material |
| CN111024750A (en) * | 2019-12-04 | 2020-04-17 | 南京航空航天大学 | Device and method for testing ablation of ceramic matrix composite material with controllable gas atmosphere |
| CN112083036A (en) * | 2020-07-28 | 2020-12-15 | 中国航天空气动力技术研究院 | Method for evaluating non-dimensional ablation heat-proof performance of material based on standard reference |
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| CN112083036A (en) * | 2020-07-28 | 2020-12-15 | 中国航天空气动力技术研究院 | Method for evaluating non-dimensional ablation heat-proof performance of material based on standard reference |
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