CN104925269B - The assay device of a kind of high hypervelocity aircraft cabin section thermal environment and method - Google Patents
The assay device of a kind of high hypervelocity aircraft cabin section thermal environment and method Download PDFInfo
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- CN104925269B CN104925269B CN201510232948.4A CN201510232948A CN104925269B CN 104925269 B CN104925269 B CN 104925269B CN 201510232948 A CN201510232948 A CN 201510232948A CN 104925269 B CN104925269 B CN 104925269B
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Abstract
The invention discloses assay device and the method for a kind of high hypervelocity aircraft cabin section thermal environment, wherein, system includes test tool assembly, cabin section assembly and cabin inner assembly, described test tool assembly includes that heating membrane, described heating membrane are fitted in outside the section assembly of cabin, described heating membrane has multiple and according to cabin section assembly outside wall surface and makes, the cladding that described heat shield is completely fitted by multiple described heating membrane.Detection method includes preparing detection platform step, coating inner insulating layer step, cladding heating membrane step, measuring process.In system and method for the present invention, use the thermal environment in heating membrane heating, the preferably complicated cabin section of simulation super speed vehicle, and then thermal design in its cabin can be detected.
Description
Technical field
The invention belongs to high hypervelocity aircraft thermal protection technology field, relate to the examination of thermal environment in a kind of cabin
Experiment device and method, when complex appearance cabin segment length is navigated in cabin the accurate simulation of thermal environment to carry out
The detection of hot property.
Background technology
Hypersonic jump glide class aircraft refers generally to flight speed and exceedes more than Ma5, flight time
The aircraft of more than 1200s.Such vehicle flight speeds is high, and jump glide maneuver flight, has
Stronger mobility and penetration ability, have huge military value and potential economic worth, at present
Become the Main way of domestic and international weapon and spacecraft development.
Hypersonic aircraft flies in endoatmosphere sustained maneuver, and aircraft is carried out continuing by air-flow
Aerodynamic Heating, stationary point hot-fluid peak value reaches 5MW/m2, always adding heat is 2 × 103MJ/m2, the flight time
Up to 1200s, aircraft local and cabin section large area face serious Aerodynamic Heating, always add heat relatively big,
In cabin, thermal environment is harsher.
For the trouble free service of stand-alone device in guarantee hypersonic aircraft cabin, need carrying out heat in cabin
Design.But different model high hypervelocity aircraft profile is different, and thermal protection structure varies, outside the section of cabin
Shape is complicated, and in the section of cabin, part is hundreds and thousands of, and in cabin, stand-alone device comes in every shape, and layout is ever-changing,
Material mixes, and cabin self-energy available sources is more, and energy transfer mode is varied so that heat
Design is a system and complicated engineering, and the reasonability of inspection thermal design is also the important of thermal design link
Work.Theoretical method is to being difficult in cabin carry out Accurate Prediction, and in cabin, the research of thermal environment relies primarily on ground
Interview is tested and is carried out.In the section of cabin, thermal environment simulation is the inspection rational important means of thermal design.Only accurate
Really simulate thermal environment in the section of cabin, be only possible to prepare detection thermal design the most reasonable.
In cabin, thermal environment simulation refers to: use heater to heat it outside the section of cabin, and in survey room
Temperature, pressure and other parameters, to judge temperature, whether the measured value of pressure meets design requirement.Cabin
In interior thermal environment simulation, conventional heater is quartz burner radiation heating.Employing quartz ampoule heats
There is more problem: quartz ampoule can only be processed into linear type, causing quartz ampoule heater can only be tool
Regular shape, the heater of such as column type, or plate heater, such
Heater may be only available for the inside thermal environment simulation of regular shape cabin section, for having complex appearance
Cabin section, it has local protuberance or a depression, uses the heater of conventional quartzy cast to carry out
In cabin during thermal environment simulation, differ bigger with thermal environment in true cabin.Accordingly, there exist exploitation can simulate
The technical need of detection of complex cabin section thermal environment.
Summary of the invention
For disadvantages described above or the Improvement requirement of prior art, the invention provides a kind of high hypervelocity flight
The assay device of device cabin section thermal environment and method, its object is to by arranging heating membrane, described in add
Film has multiple, and multiple heating membrane are completely fitted and are coated on the section outer wall of cabin so that in the section of cabin
Thermal environment and true environment close, the detection of thermal design in the section of cabin should be able to be carried out mutually, overcome existing
In technology due to quartz ampoule heating cause cannot the technical problem of thermal design in the section of detection of complex cabin.
For achieving the above object, according to one aspect of the present invention, it is provided that a kind of detection high hypervelocity flies
The assay device of thermal design in the section of row device cabin, it is characterised in that include
Test tool assembly, cabin section assembly and cabin inner assembly, wherein
Described cabin section assembly includes heat shield, outer thermal insulation layer, cabin section bearing layer and inner insulating layer, institute
State outer thermal insulation layer and described inner insulating layer lays respectively at cabin section bearing layer outside wall surface and internal face, described anti-
Thermosphere is positioned on outer thermal insulation layer；
Described test tool assembly includes heating membrane, upper end cover and frock, and described frock is for propping up
Supportting described cabin section assembly and make an end face of this cabin section assembly close, described upper end cover is used for closing institute
Stating cabin another end face of section assembly, described heating membrane is fitted in outside described heat shield, described heating film
Sheet has multiple and makes according to cabin section bearing layer outside wall surface shape, and multiple described heating membrane are by described
The cladding that heat shield is completely fitted；
Described cabin inner assembly includes unit and unit support in cabin, and described unit support is fixed on described cabin
On section bearing layer, it is used for supporting unit in cabin.
By above inventive concept, (1) arranges heating membrane, and heating membrane has multiple, multiple heating
Diaphragm makes according to cabin section bearing layer outside wall surface shape, and heating membrane can be curved surface or plane,
Can be arbitrary shape, the cladding that described heat shield is completely fitted by described heating membrane should be able to be made mutually,
When heating, the thermal environment in the section of cabin, Jin Erneng when preferable simulated flight device flight could be realized
Thermal design in detection cabin, it is thus achieved that rationally due to data, with judge thermal design in the section of cabin reasonability,
And can instruct further and improve thermal design.(2) further, inner insulating layer is set in the section of cabin, interior
Thermal insulation layer can be heat conductivity and the less aerogel material of thermal diffusion coefficient or the honeybee for multiple structure
Nest structural material, or thermal control coating and the heat-barrier material of multilamellar, be used for reducing radiation coefficient and changing
Hot coefficient, it is achieved that present system preferably imitates high hypervelocity aircraft cabin section inner structure, it is ensured that be
Unite preferable simulating actual conditions.
Further, described heating membrane includes outer layer, nexine and intermediate layer, and described intermediate layer is for adding
Hot water radiation wire.As preferably, resistance wire is flexible, deformable, it is simple to according to outside the section bearing layer of cabin
The shape of wall is prepared as variously-shaped heating membrane, in order to fit tightly.
According to the second aspect of the invention, also provide for a kind of detection high hypervelocity aircraft cabin section interior-heat and set
The method of meter, it is characterised in that comprise the steps:
Preparing detection platform step, the cabin section bearing layer that outer wall has heat shield and outer thermal insulation layer is fixed
In frock；
Coating inner insulating layer step, in cabin section bearing layer inwall coating thermal control coating and heat-barrier material, institute
State thermal control coating for changing radiation coefficient and the absorptance on surface, to reduce the heat of radiation transmission；
Described heat-barrier material is used for reducing surface thermal conductivity and surface convection transfer rate, to reduce heat exchange；
Cladding heating membrane step, outside the heat shield of cabin section assembly, laminating is coated with multiple heating membrane,
Described heating membrane makes according to the outside wall surface shape of cabin section assembly, can completely be pasted by described heat shield
The cladding closed；
Measuring process, enclosure section two ends, open heating membrane, measure and obtain temperature, pressure in the section of cabin
Power and speed.
By above inventive concept, (1) coats thermal control coating and heat-barrier material at cabin section bearing layer inwall,
Described thermal control coating is for changing radiation coefficient and the absorptance on surface, to reduce the heat of radiation transmission
Amount；Described heat-barrier material is used for reducing surface thermal conductivity and surface convection transfer rate, changes to reduce
Heat.Reduce radiation coefficient and the coefficient of heat transfer, it is achieved that present system preferably imitates high hypervelocity aircraft
Practical situation in the section of cabin, it is ensured that the preferable simulating actual conditions of system.(2) cladding heating membrane, heating
Diaphragm has multiple, and multiple heating membrane make according to cabin section bearing layer outside wall surface, and heating membrane is permissible
It is curved surface or plane, can be arbitrary shape, described heating membrane should be able to be made mutually by described anti-
The cladding that thermosphere is completely fitted, when heating, could realize cabin when preferable simulated flight device flight
Thermal environment in Duan, and then can accurately detect the reasonability of thermal design in cabin.
Further, between described heat shield and described heating membrane, fill heat-conducting silicone grease, be used for reducing
The thermal resistance of contact, and then improve the efficiency of heating surface of heating membrane.
Further, described heating membrane includes outer layer, nexine and intermediate layer, and described intermediate layer is for adding
Hot water radiation wire.
In general, by the contemplated above technical scheme of the present invention compared with prior art, it is possible to
Obtain following beneficial effect:
(1) arranging heating membrane, multiple heating membrane make according to cabin section bearing layer outside wall surface, specifically
, heating membrane can be curved surface or plane, can be arbitrary shape, should be able to make described mutually
The cladding that described heat shield is completely fitted by heating membrane, it is achieved preferably when simulated flight device flight
Thermal environment in the section of cabin, and then the reasonability of thermal design in cabin can be detected, it is ensured that the accuracy of detection.
Further, inner insulating layer is set in the section of cabin, in the field of aircraft cabin piece housing, interior heat insulation
Layer is used for reducing radiation coefficient and the coefficient of heat transfer, it is achieved that present system preferably imitates high hypervelocity flight
Device cabin section inner structure, it is ensured that the preferable simulating actual conditions of system.
(2) system and method for the present invention use heating membrane heating, especially can effectively solve to jump for a long time
A thermal environmental test difficult problem in symmetry complex appearance aircraft cabin, the glide class that jumps face, cabin interior-heat ring of accurately knowing the real situation
Border, the reliability of thermal design and reasonability in checking thermal protection and cabin.
Accompanying drawing explanation
Fig. 1 is the cabin interior-heat environment test device longitudinal section sectional view of the embodiment of the present invention；
Fig. 2 is the cabin interior-heat environment test device cross section view of the embodiment of the present invention；
Fig. 3 be the embodiment of the present invention cabin in stand-alone device and unit supporting structure schematic diagram.
In all of the figs, identical reference represents same feature, specifically, 1-frock,
2-heating membrane, the outer thermal insulation layer of 3-heat shield, 4-, 5-upper end cover, unit in 6-cabin, 7-
Cabin section bearing layer, 8-inner insulating layer, 9-unit support.
Detailed description of the invention
In order to make the purpose of the present invention, technical scheme and advantage clearer, below in conjunction with accompanying drawing
And embodiment, the present invention is further elaborated.Should be appreciated that described herein specifically
Embodiment only in order to explain the present invention, is not intended to limit the present invention.Additionally, it is disclosed below
Just may be used as long as technical characteristic involved in each embodiment of the present invention does not constitutes conflict each other
To be mutually combined.
Fig. 1 is the cabin interior-heat environment test device longitudinal section sectional view of the preferred embodiment of the present invention；Fig. 2
Cabin interior-heat environment test device horizontal cross-section sectional view for the preferred embodiment of the present invention；Fig. 3 is this
Stand-alone device and unit supporting structure schematic diagram in the cabin of bright preferred embodiment.
From above figure, in the present invention, detection high hypervelocity aircraft cabin section interior-heat designed system includes
Test tool assembly, cabin section assembly and cabin inner assembly.Wherein, described cabin section assembly include heat shield 3,
Outer thermal insulation layer 4, cabin section bearing layer 7 and inner insulating layer 8, described outer thermal insulation layer 4 and described interior heat insulation
Layer 8 lays respectively at cabin section bearing layer 7 outside wall surface and internal face, and described heat shield is positioned at outer thermal insulation layer 4
On；Described test tool assembly includes heating membrane 2, upper end cover 5 and frock 1, described frock 1
For supporting described cabin section assembly and making an end face of this cabin section assembly close, described upper end cover is used for
Closing described cabin another end face of section assembly, described heating membrane 2 is fitted in outside described heat shield, institute
State heating membrane have multiple and make according to cabin section bearing layer 7 outside wall surface, multiple described heating membrane
The cladding that described heat shield is completely fitted；Described cabin inner assembly includes unit 6 and unit support 9 in cabin,
Described unit support is fixed on the section bearing layer of described cabin, is used for supporting unit in cabin.
Concrete, the size dimension for whole system, frock and heating membrane can be according to the reality of cabin section
Border profile and size calculate and determine.Especially for heating membrane, multiple heating membrane are according to cabin Duan Cheng
Power layer outside wall surface makes, and heating membrane can be curved surface or plane, can be arbitrary shape,
The cladding that described heat shield is completely fitted by described heating membrane should be able to be made mutually.Heating membrane is relatively thin, and one
As thickness be 2mm～5mm.Those skilled in the art find in substantial amounts of engineering practice, this thickness model
The heating membrane enclosed, the outside wall surface of cabin section of relatively fitting, and manufacturing cost is the most economical, cost performance
Optimal with availability.
In cabin, heat test heating system is diaphragm heating system, and diaphragm heating system has stronger setting
Meter property, is particularly suited for complicated symmetric profile cabin, face section, outside diaphragm heating system may be designed to cabin section
Shape is consistent, and inner surface keeps consistent with the outer surface of heat shield, closely pastes with cabin section heat shield during installation
Close, to reduce the thermal resistance of contact, improve diaphragm type heating system heats efficiency.Generally, heat shield can
To be fiberglass or carbon carbon composite.
In the present invention, heating membrane includes outer layer, nexine and intermediate layer, and described intermediate layer is for preferably to add
Hot water radiation wire.Resistance wire is flexible, deformable, it is simple to according to the apperance of cabin section bearing layer 7 outside wall surface
It is prepared as variously-shaped heating membrane, in order to fit tightly.
In the present invention, the test method of thermal environment in the section of a kind of high hypervelocity aircraft cabin, comprises the steps:
Preparing detection platform step, the cabin section bearing layer 7 that outer wall has heat shield and outer thermal insulation layer is solid
It is scheduled in frock；
Coating inner insulating layer step, in cabin section bearing layer inwall coating thermal control coating and heat-barrier material, institute
State thermal control coating for changing radiation coefficient and the absorptance on surface, to reduce the heat of radiation transmission；
Described heat-barrier material is used for reducing surface thermal conductivity and surface convection transfer rate, to reduce heat exchange；
Cladding heating membrane step, the fixing multiple heating membrane of laminating outside the heat shield of cabin section assembly,
Described heating membrane customizes according to the outside wall surface shape of cabin section assembly, can completely be pasted by described heat shield
The cladding closed.As preferably, heat conduction can be filled between described heat shield and described heating membrane internal face
Silicone grease, for reducing the thermal resistance of contact, and then improves the efficiency of heating surface of heating membrane.The most excellent
Choosing, described heating membrane includes that outer layer, nexine and intermediate layer, described intermediate layer are resistive heater.
Resistance wire is flexible, deformable, it is simple to be prepared as various shape according to the apperance of cabin section bearing layer outside wall surface
The heating membrane of shape, in order to fit tightly.
Measuring process, enclosure section two ends, open heating membrane, measure and obtain temperature, pressure in the section of cabin
Power and speed.
Wherein, coating inner insulating layer step and cladding heating membrane step can be carried out simultaneously, or not
Successively order is carried out.
Concrete, the maximum temperature that heating membrane can reach is about 400 DEG C, in order in the section of accurate simulation cabin
Thermal environment, need the thickness to heat shield to carry out thinning, i.e. the thickness of the heat shield in present system
Degree is less than the thickness of actual high hypervelocity aircraft heat shield.Obtain and the equivalence of actual heat shield by calculating
Heat shield thickness, conventional equivalent way is: carries out in cabin before thermal design detection, carries out gas
Dynamic theory of heat computational analysis, show that heating membrane needs the thermal boundary condition controlled.Long for ultrahigh speed
Time aircraft cabin section heat shield outer wall peak temperature generally individually at about 2000 DEG C, calculate heat shield and
Temperature at outer thermal insulation layer different-thickness, choose the heating efficiency meeting heating membrane heat shield and every
The thickness of thermosphere.When preparing detection platform step, the thickness of heat shield and thermal insulation layer enters according to this thickness
Row processing.
Cabin section thermal environmental test is based on section two ends, cabin dynamic thermal balance principle, i.e. experimental cabin section and two ends
Cabin section heat transmission reaches dynamic equilibrium, and hot-fluid is approximately zero.Need during test section two ends, cabin are entered
Row insulation, this just requires that two ends end cover selects heat insulation and sealing effectiveness relatively good material, to subtract
Cludy section boundary effect is on the impact of thermal environment in cabin.
In cabin thermal environmental test simulation hypersonic aircraft flight time cabin in temperature, pressure, speed (temperature
The change of degree causes the change of atmospheric density, and variable density causes pressure to change, and then causes air stream
Dynamic, create velocity) the regularity of distribution, temperature, pressure and the VELOCITY DISTRIBUTION in cabin and flight
The flight attitude of device and overload size are closely bound up, accordingly, it would be desirable to the flight attitude of aircraft and mistake
It is loaded into the comprehensive analysis of row, but during ground simulation, overload is definite value G.Can cover accordingly, it would be desirable to choose
Installation posture during lid flight is tested.
Section Aerodynamic Heating harsher height in hypersonic aircraft cabin is below 70km, and in cabin, unit sets
Standby omnidistance work spontaneous heating, in cabin, the heat convection of air and stand-alone device is closely bound up with atmospheric density,
Therefore, during temperature, pressure and speed distribution regularities in ground simulation cabin, need to consider the cabin in high-altitude
Interior atmospheric density, needs cabin section is carried out evacuation process if desired.When simulation low latitude, just it is not required to
Evacuation is wanted to process the size of the most corresponding air pressure of simulated flight.
In cabin, thermal environmental test is for the temperature in boiler-plate, pressure and speed distribution regularities, therefore,
Need, in significant points, temperature, speed and pressure transducer are installed when testing and carry out data acquisition.
The present invention is explained below by by more specifically embodiment, in the present embodiment, test
Cabin section is external diameter194mm, highly 170mm annular compartment section, cabin section outside wall surface has recess and protrusion,
Wall thickness 3mm, material is titanium alloy；In cabin, unit uses aluminum mass shell body to add as simulating piece, test employing
Film.Test uses temperature rise curve to control, and keeps fixing temperature rise rate, and temperature control curve is from 308s
Room temperature 25 DEG C starts to control, 1067s temperature rise to 250 DEG C.In result of the test, unit outside wall temperature 88 DEG C～
Between 102 DEG C, at distance bulkhead stage casing about 10mm, air themperature is between 158 DEG C～164 DEG C；Unit
Outer wall or cabin section inwall use thermal control coating and the thermal control mode of multilayer insulation material, can be by unit temperature
It is reduced to 60 DEG C from 93 DEG C.Increase thermal insulation layer or similar also can be used in cabin section and unit housing inside and outside wall
Effective thermal control means, reduce thermal environment in cabin.
As it will be easily appreciated by one skilled in the art that and the foregoing is only presently preferred embodiments of the present invention,
Not in order to limit the present invention, all made within the spirit and principles in the present invention any amendment, etc.
With replacement and improvement etc., should be included within the scope of the present invention.
Claims (5)
1. the assay device of one kind high hypervelocity aircraft cabin section thermal environment, it is characterised in that include
Test tool assembly, cabin section assembly and cabin inner assembly, wherein
Described cabin section assembly include heat shield (3), outer thermal insulation layer (4), cabin section bearing layer (7) with
And inner insulating layer (8), described outer thermal insulation layer (4) and described inner insulating layer (8) lay respectively at cabin section
Bearing layer (7) outside wall surface and internal face, described heat shield is positioned on outer thermal insulation layer (4)；
Described test tool assembly includes heating membrane (2), upper end cover (5) and frock (1),
Described frock (1) is for supporting described cabin section assembly and making an end face closing of this cabin section assembly, institute
Stating upper end cover for closing described cabin another end face of section assembly, described heating membrane (2) is fitted in institute
Stating outside heat shield, described heating membrane has multiple and makes according to cabin section bearing layer (7) outside wall surface,
The cladding that described heat shield is completely fitted by multiple described heating membrane；
Described cabin inner assembly includes unit (6) and unit support (9) in cabin, and described unit support is solid
It is scheduled on the section bearing layer of described cabin, is used for supporting unit in cabin.
The assay device of a kind of high hypervelocity aircraft cabin the most as claimed in claim 1 section thermal environment, its
Being characterised by, described heating membrane includes outer layer, nexine and intermediate layer, and described intermediate layer is for adding thermoelectricity
Resistance silk.
3. the test method of one kind high hypervelocity aircraft cabin section thermal environment, it is characterised in that include as follows
Step:
Prepare detection platform step, outer wall is had heat shield (3) and the cabin section of outer thermal insulation layer (4)
Bearing layer (7) is fixed in frock；
Coating inner insulating layer step, at cabin section bearing layer (7) inwall coating thermal control coating and heat-barrier material
To obtain inner insulating layer (8), described thermal control coating is used for changing radiation coefficient and the absorptance on surface,
To reduce the heat of radiation transmission；Described heat-barrier material is used for reducing surface thermal conductivity and surface convection current
The coefficient of heat transfer, to reduce heat exchange；
Cladding heating membrane step, the fixing multiple heating membrane (2) of laminating outside the heat shield of cabin section assembly,
Described heating membrane makes according to the outside wall surface shape of cabin section assembly, can completely be pasted by described heat shield
The cladding closed；
Measuring process, enclosure section two ends, open heating membrane, measure and obtain temperature, pressure in the section of cabin
Power and speed.
The test method of a kind of high hypervelocity aircraft cabin the most as claimed in claim 3 section thermal environment, its
It is characterised by, between described heat shield and described heating membrane, fills heat-conducting silicone grease, be used for reducing contact
Thermal resistance, and then improve heating membrane the efficiency of heating surface.
5. the test method of a kind of high hypervelocity aircraft cabin section thermal environment as described in claim 3 or 4,
It is characterized in that, described heating membrane includes outer layer, nexine and intermediate layer, and described intermediate layer is heating
Resistance wire.
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