CN106908174B - The heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density - Google Patents
The heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density Download PDFInfo
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- CN106908174B CN106908174B CN201710050405.XA CN201710050405A CN106908174B CN 106908174 B CN106908174 B CN 106908174B CN 201710050405 A CN201710050405 A CN 201710050405A CN 106908174 B CN106908174 B CN 106908174B
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- heat
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- flow meter
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K17/00—Measuring quantity of heat
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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Abstract
The invention discloses a kind of heat-flow meters of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density, including heat-flow meter, heat-flow meter includes the heat sink copper of column and constantan piece of coaxial placement, the top coaxial placement of constantan piece has for reducing the thermal insulation ceramics disk of constantan piece surface high-temp hot-fluid, thermal insulation ceramics disk, the outside tight of constantan piece and heat sink copper has beryllium oxide ceramic shell, and thermal insulation ceramics disk is fixed on to the top of constantan piece by beryllium oxide ceramics shell, beryllium oxide ceramics shell is also used to a part of hot-fluid being directed directly towards heat sink Copper substrate, heat sink copper hole is offered along its axis direction inside heat sink copper, thermocouple for measuring heat sink copper head temperature is installed at the position of constantan piece in heat sink copper hole.To overcome the problems, such as not washing away or deposit Heat flux calculation to condensed-phase particle under the conditions of high temperature, high pressure, high hot-fluid in solid propellant rocket.
Description
[technical field]
The invention belongs to Solid Rocket Motor Technology fields, and in particular to a kind of dynamic real-time measurement solid-rocket starts
The heat-flow meter of machine internal oxidition aluminothermy current density.
[background technique]
During the work time, the vigorous combustion of propellant will generate high temperature, the height of 2500-3900K to solid propellant rocket
Quick burning air-flow, high-temperature fuel gas generate the serious ablation of hot-fluid the thermally protective materials of engine.Meanwhile the condensed-phase in combustion product
Particle will slip into section to jet pipe and converging portion causes serious erosion and washes away, so that the heat for increasing considerably engine carries
Lotus.It is able to maintain that normal work and spacecraft in the ascent stage to guarantee rocket engine under the conditions of severe thermal environment
Will not be burnt due to external heating environment during with reentry stage, it is therefore desirable to absorbed using various thermally protective materials with
Dissipate various heat effects.One of root cause problems as solid propellant rocket thermal protection, heat-flow measurement are to grasp wall surface heat
The conventional means of environment.
It is that current heat-flow measurement technology often uses one dimensional heat transfer it is assumed that heat is transmitted along wall surface normal direction or face direction.Root
According to Fourier law, when heat is transmitted along wall direction, there can be temperature gradient in wall surface, therefore wall surface temperature pair can not be studied
The influence of hot-fluid.Heat-flow measurement technology along normal direction transmitting includes instantaneous measurement technology and steady state measurement technology.For for a long time,
The test measurement of high hot-fluid, instantaneous measurement technology cannot be applicable in.
Steady-state heat-flux measurement technique along normal direction transmitting is divided into two classes: 1) the water card calorimeter based on principle of energy balance,
Its response time takes usually from several seconds to tens second, is not able to satisfy the requirement of quick response.2) thermal resistance heat flow transducer, usually
Thermal cross is formed in nonmetal heating resistance layer two sides, while measuring surface temperature and hot-fluid.But nonmetal heating resistance layer and metal
Water cooling or heat sink structure can have obvious thermal contact resistance when connecting, in long-time test when measurement megawatt square meter level hot-fluid,
It is unsuitable for megawatt square meter level hot-fluid and prolonged test.
Domestic some researchers, are based on thermal resistance heat flux measurement principle, to the temperature and hot-fluid survey in long-time test
Amount is explored.Harbin Institute of Technology Liu Linhua [1] etc. is to radiation, the coupling pair of thermally conductive and boundary in one-dimensional translucent plate
Stream heat transfer process is studied, and is proposed a kind of by another lateral boundaries incident radiation heat of side boundary emergent radiation intensity inverting
The method of current density.Shuai Y [2] etc. grinds the radiant heat attribute of spherical heat-absorbing chamber using MCM (Monte Carlo Method)
Study carefully, gives the regularity of distribution of focal plane heat flow density.Chen Zeshao [3] etc. describes lump hot melten type Research On The Transient Radiant Heat Flow Meter, and one
As radiant type heat-flow meter using heat balance method of design, cannot be used in measurement variation hot-fluid, lump hot type heat-flow meter is by surface
The scale copper of blacking makees the side head of heat-flow meter, and the insulation of the copper sheet back side is influenced, dynamic response characteristic also compares by gauge head hot melt
Difference, therefore thermal transient radiant heat flux density can be surveyed.
Northwestern Polytechnical University Zhang Xiangyu [4] has carried out the heat under particle scouring state for simulation overload compression ratio engine
Current density test job has obtained total conductive heat flow density of two phase combustion, has established a set of hot-fluid calculation method.But due to
Its heat-flow measurement device is persistently cooled down using cooling water heat exchanging test specimen, causes heat exchange test specimen nearby there are biggish temperature ladder,
After this increases combustion gas heat convection heat flow density to a certain extent, and low temperature wall surface will affect condensed-phase particle shock wall surface
Physical state, this, which will lead to, is transmitted to total heat of the total heat current density of heat-flow measurement device greater than actual engine wall surface and heat insulation layer
Current density.
In conclusion carried out correlative study work in terms of the design of heat-flow meter and the measurement of hot-fluid both at home and abroad, but
The harsh environments such as high temperature and pressure in solid propellant rocket are related to less, and means of testing differs greatly, and influence factor is examined
Consider less, conclusion is caused to differ greatly.
[summary of the invention]
The object of the present invention is to provide the heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density,
To overcome heat flow density can not be washed away or deposited to condensed-phase particle under the conditions of high temperature, high pressure, high hot-fluid in solid propellant rocket
The problem of measurement.
The invention adopts the following technical scheme: the heat of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density
Flowmeter, including heat-flow meter, heat-flow meter include the heat sink copper of column and constantan piece of coaxial placement, and the top coaxial placement of constantan piece has
For reducing the thermal insulation ceramics disk of constantan piece surface high-temp hot-fluid, the outside of thermal insulation ceramics disk, constantan piece and heat sink copper is closely wrapped
It is wrapped with beryllium oxide ceramics shell, and thermal insulation ceramics disk is fixed on to the top of constantan piece, beryllium oxide by beryllium oxide ceramics shell
Ceramic shell is also used to for a part of hot-fluid being directed directly towards heat sink Copper substrate, offers inside heat sink copper along its axis direction heat sink
Copper hole is equipped with the thermocouple for measuring heat sink copper head temperature in heat sink copper hole at the position of constantan piece.
Further, it is provided on the outer wall of heat sink copper for reducing the water-cooling channel of heat-flow meter temperature, water-cooling channel is
The groove opened up around heat sink copper surface.
Further, the diameter of thermal insulation ceramics disk is identical as the diameter of constantan piece.
Further, thermocouple is connected with the copper wire for connecting temperature acquisition system.
Further, heat sink copper is installed in the test section of rocket engine by ring flange.
Further, the center perforation of heat sink copper offers cavity.
It is used to measure in the solid propellant rocket course of work the beneficial effects of the present invention are: the present invention devises one kind,
Fused alumina particles wash away the experimental provision with heat flow density under sedimentation state, in order to measure solid propellant rocket particle stream
High hot-fluid under dynamic state, makes up the vacancy to Heat flux calculation method under engine high-temperature environment, in existing Gordan heat
On the basis of flowmeter, by numerical simulation means and the selection to a variety of ceramic physical property, it is final determine use beryllium oxide ceramics as
Thermally insulating housing realizes the purpose accurately measured to particle heat flow density to meet simultaneously under the high hot-fluid souring of particle.
[Detailed description of the invention]
Fig. 1 is that the structure of the heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density of the present invention is shown
It is intended to；
Fig. 2 is that the assembly of the heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density of the present invention is shown
It is intended to.
Wherein, 1. thermal insulation ceramics disk, 2. constantan pieces, 3. beryllium oxide ceramics shells, 4. water-cooling channels, 5. thermocouples, 6. heat
Heavy copper, 7. copper wire, 9. ring flanges, 10. heat sink copper holes, 11. converging portions, 12. test section test specimens, 13. jet pipes.
[specific embodiment]
Below by drawings and examples, technical scheme of the present invention will be described in further detail.
The present invention provides a kind of heat-flow meters of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density, such as
Shown in Fig. 1, including heat-flow meter, heat-flow meter include the heat sink copper 6 of column and constantan piece 2 of coaxial arrangement, the center perforation of heat sink copper 6
Opening up hole, the top coaxial placement of constantan piece 2 has for reducing the thermal insulation ceramics disk 1 of 2 surface high-temp hot-fluid of constantan piece, every
The outside tight of thermal Ceramics disk 1, constantan piece 2 and heat sink copper 6 has beryllium oxide ceramic shell 3 and fixes thermal insulation ceramics disk 1
On the top of constantan piece 2, beryllium oxide ceramics shell 3 is used to a part of hot-fluid being directed directly towards heat sink 6 matrix of copper, in heat sink copper 6
Portion offers heat sink copper hole 10 along its axis direction, in heat sink copper hole 10 close to constantan piece 2 position at be equipped with one or
The more than one thermocouple 5 for being used to measure heat sink 6 head temperature of copper, each thermocouple 5 is respectively connected with to be adopted for connecting temperature
The copper wire 7 of collecting system, every 7 end later period of copper wire with test macro for connecting.
Wherein, the water-cooling channel 4 for reducing heat-flow meter temperature is provided on the outer wall of heat sink copper 6, water-cooling channel 4 is to enclose
The square groove opened up around heat sink 6 surface of copper is passed through cooling water from one section of lower end import of heat sink copper 6 in later experiments, to reach
To the purpose cooling to heat sink copper 6.
The diameter of thermal insulation ceramics disk 1 is identical as the diameter of constantan piece 2, can guarantee the leakproofness of assembly in this way.
There is different thermal conductivity, and high-temperature erosion-resistant on original 2 surface of Gordan heat-flow meter constantan piece and outer surface installation
The thermal insulation ceramics disk 1 and beryllium oxide ceramics shell 3 of characteristic, to measure in the solid propellant rocket course of work, particle washes away
Or its heat flow density for acting on adiabatic wall in engine under sedimentation state.
Due to thermal environment very severe in Solid Rocket Motor combustion chamber, such as high temperature, big hot-fluid, strong particle erosion, work
Make time length etc., for conventional Gordan heat-flow meter, there is the danger that can not work normally with burn at any time, this hairs
The high temperature resistant attribute of bright sensitivity and ceramic material based on Gordan heat-flow meter thermometric, cleverly devise a kind of high temperature resistant,
The heat-flow meter of antiscour.
In engine working process, condensed-phase particle washes away under engine runner convergence effect in thermal insulation ceramics disk 1
Surface and beryllium oxide ceramics shell 3, particle bring hot-fluid are divided into rapidly two paths on heat-flow meter head: a part of hot-fluid warp
Cross thermal insulation ceramics disk 1, constantan piece 2 enters heat sink 6 matrix of copper；Another part hot-fluid enters matrix by beryllium oxide ceramics shell 3.
Wherein heat sink 6 intrinsic silicon of copper of hollow cylinder is embedded with installation thermocouple 5, for measuring copper-based temperature, while matrix surface
Cooling-water duct 4 is offered, the huge hot-fluid of bring is washed away or deposit to take away particle, to guarantee the normal work of heat-flow meter
Make, when heat-flow meter is processed, need to guarantee combining closely between beryllium oxide ceramics shell 3 and heat sink copper 6, avoid due to processing technology
And the interval station introduced, so that the measurement accuracy to hot-fluid impacts.
The heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density of the present invention passes through in solid fire
Arrow engine particle wash away or deposition position at install heat-flow meter, can measure condensed-phase particle in heat-insulating material surface bring
Heat gain achievees the purpose that measure particle hot-fluid and wall surface temperature, solves existing heat-flow meter under superhigh temperature heat-flux conditions
Destructible problem is solved to heat flow density and wall surface temperature under the conditions of high temperature, high hot-fluid in solid propellant rocket simultaneously
The problem of measurement, finally in the available solid propellant rocket course of work, washing away or deposit to sending out by condensed-phase particle
Motivation inner surface bring heat gain.And then the foundation for thermal boundary condition in numerical value calculating provides experimental basis, thus side
Insulation erosion mechanism research.
Embodiment:
Thermal insulation ceramics disk 1 is thickness 2mm, the cylindrical body of internal diameter 10mm；The dimensional parameters of beryllium oxide ceramics shell 3 are as follows: wall thickness
3mm, outer diameter 20mm, top internal diameter 10mm, inner major diameter 16mm；Heat sink copper 6 is outer diameter 16mm, the cylindrical sleeves knot of internal diameter 4mm
Structure；Heat sink 6 outer surface of copper offers the continuous water-cooling channel 4 of wide 2mm, depth 2mm, is equipped with thermocouple 5 inside heat sink copper 6.
Wherein, the selection of heat sink 6 outer diameter of copper is determined by the internal diameter of beryllium oxide ceramics shell 3, the selection gist processing of internal diameter
Accuracy determines.
Thermal insulation ceramics disk 1 have low heat conductivity aluminium oxide ceramics, for reducing 2 surface temperature of constantan piece, play every
Effect hot and resistant to high temperature；The beryllium oxide with high-melting-point, high thermal conductivity characteristic is increased in the outside of thermal insulation ceramics disk 1
Ceramic shell 3, it acts as a part of hot-fluid is directed directly towards heat sink 6 matrix of copper, and the design of 6 intrinsic silicon of heat sink copper has cooling
Aquaporin-4 and thermocouple 5, to realize the cooling purpose with the copper-based temperature of real time monitoring.
As shown in Fig. 2, by dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density of the present invention in test
Heat-flow meter is assemblied in engine test section by ring flange 9, and the test section is mainly by converging portion 11, test section test specimen 12, spray
Pipe 13 forms.It is opened up at the first respectively 48mm and 117mm in the test section test specimen 12 in engine test section along airflow direction
The mounting hole of two diameter phi 20mm, to cooperate dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density of the present invention
Heat-flow meter installation.In later stage work, first heat-flow meter can be demarcated using tungsten lamp, then be installed on engine test section such as
Fig. 2, to be measured to the heat flow density of particle phase under engine behavior.Dynamic real-time measurement solid-rocket of the present invention
The heat-flow meter of engine internal oxidition aluminothermy current density and engine test section are assembled using end face seal mode, bolts and nuts by
GB/T5781-2000 hexagon-headed bolt-- C grades of M8 and GB/T41-2000 hex-head nut of C grades of full thread M8 is constituted.
Since the working environment of solid propellant rocket is related to high temperature, high pressure, high heat flow problem, especially in condensed-phase particle
It washes away and under sedimentary condition, will cause huge heat transfer and corrode.Currently, the country there is no in solid propellant rocket
Grain washes away the laboratory facilities with heat flow density real-time measurement under sedimentary condition.Therefore, herein by theory analysis and numerical simulation
The means combined, the method for analyzing real-time measurement particle hot-fluid.It has finally determined to be sent out based on thermal resistance parallel method rocket
Hot-fluid in motivation carries out test experiments.However, in order to overcome the difficulties such as the ultra-high temperature, the superelevation hot-fluid that measure environment, simultaneously
The respective rate of heat-flow meter is improved, choosing thermally protective materials is key factor.The present invention considers the resistance to height of thermally insulating housing in fusion
After the various aspects factors such as temperature, resistance to erosion and thermal conductivity, finally determine outside using beryllium oxide ceramics as original Gordan heat-flow meter
Shell mutually washes away heat-flow meter with heat flow density under sedimentary condition to be configured to real-time measurement solid propellant rocket endoparticle,
It is intended to fill the blank in this field, contributes for later experiments numerical analysis.
The present invention makes up to measure the high hot-fluid under solid propellant rocket particle flow state to engine high-temperature ring
The vacancy of Heat flux calculation method under border, on the basis of existing Gordan heat-flow meter, by numerical simulation means with to a variety of
The selection of ceramic physical property, final determine uses beryllium oxide ceramics as thermally insulating housing, to meet in the high hot-fluid souring of particle
The purpose that lower while realization accurately measures particle heat flow density.Condensed-phase particle acts on insulation in measurement solid propellant rocket
The heat flow density of layer surface, this has important meaning for the research for carrying out heat-insulating material ablation characteristics in dense plasmas two phase flow
Justice, the foundation for thermal boundary condition in numerical value calculating provide experimental basis, are to carry out insulation erosion mechanism study and burn
Lose the important component of model buildings.
Claims (5)
1. the heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density, including heat-flow meter, the hot-fluid
Meter includes the heat sink copper of column (6) and constantan piece (2) of coaxial placement, which is characterized in that is coaxially put on the top of the constantan piece (2)
It is equipped with for reducing the thermal insulation ceramics disk (1) of constantan piece (2) surface high-temp hot-fluid, the thermal insulation ceramics disk (1), the constantan piece
(2) have beryllium oxide ceramic shell (3) with the outside tight of the heat sink copper (6), and passing through beryllium oxide ceramics shell (3) will
The thermal insulation ceramics disk (1) is fixed on the top of the constantan piece (2), and the beryllium oxide ceramics shell (3) is also used to one
Hot-fluid is divided to be directed directly towards heat sink copper (6) matrix, the heat sink copper (6) is internal to offer heat sink copper hole (10) along its axis direction,
It is equipped at the position of the constantan piece (2) for measuring at the top of the heat sink copper (6) in the heat sink copper hole (10)
The center perforation of the thermocouple (5) of temperature, the heat sink copper (6) opens up hole.
2. the heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density as described in claim 1,
It is characterized in that, the water-cooling channel (4) for reducing heat-flow meter temperature, the water cooling is provided on the outer wall of the heat sink copper (6)
Channel (4) is the groove opened up around heat sink copper (6) surface.
3. the heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density as claimed in claim 1 or 2,
It is characterized in that, the diameter of the thermal insulation ceramics disk (1) is identical as the diameter of the constantan piece (2).
4. the heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density as claimed in claim 1 or 2,
It is characterized in that, the thermocouple (5) is connected with the copper wire (7) for connecting temperature acquisition system.
5. the heat-flow meter of dynamic real-time measurement solid propellant rocket internal oxidition aluminothermy current density as claimed in claim 1 or 2,
It is characterized in that, the heat sink copper (6) is installed in the test section of rocket engine by ring flange (9).
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108344521B (en) * | 2018-03-14 | 2024-04-16 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient heat flow sensor |
| CN110836725B (en) * | 2018-08-16 | 2021-02-12 | 哈尔滨工业大学 | Double-probe heat flow meter in high heat flow coupling environment and method for measuring heat flow density thereof |
| CN111829694A (en) * | 2019-04-23 | 2020-10-27 | 北京振兴计量测试研究所 | Heat flow sensing element for heat flow sensor and heat flow sensor with same |
| CN113566993A (en) * | 2020-04-28 | 2021-10-29 | 中国航发商用航空发动机有限责任公司 | Engine temperature measuring device and heat insulation lining thereof |
| CN111879443A (en) * | 2020-07-14 | 2020-11-03 | 西安近代化学研究所 | Tool for measuring density of gas-liquid two-phase heat flow in rocket engine |
| CN112065602A (en) * | 2020-08-27 | 2020-12-11 | 西安石大能源股份有限公司 | Heat recycling device for vented combustible gas |
| CN114659677B (en) * | 2022-05-25 | 2022-08-23 | 中国飞机强度研究所 | Circular foil type heat flow sensor for aerospace plane test experiment and design method thereof |
| CN116380402B (en) * | 2023-05-26 | 2023-08-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for installing and manufacturing transient radiation heat flow sensor for high enthalpy expansion wind tunnel |
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| CN101571428A (en) * | 2009-05-21 | 2009-11-04 | 中国科学院力学研究所 | Multi-function sensor and heat current and temperature measuring method under high temperature |
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