CN107792392A - A kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge and method - Google Patents
A kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge and method Download PDFInfo
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Abstract
The present invention relates to a kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge and method, in particular for the active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge and method of Na-K alloy working medium, belong to the thermal protection technology field of flying vehicles control rudder.The system includes heater, temperature measurement system, temperature control system, wind cooling temperature lowering equipment and power supply.The active complement heat conduction guaranteed performance test of flying vehicles control rudder tipping leading edge based on Na-K alloy working medium is successfully carried out using the active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge and method, long-time high temperature, the continual and steady loading problem of high hot-fluid for solving special aerodynamic configuration product.The system and method may extend to the active complement heat conduction properties of product certification test of all kinds of working medium, various profiles, have preferable versatility.
Description
Technical field
The present invention relates to a kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge and method, especially pin
To the active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge and method of Na-K alloy working medium, belong to flying vehicles control
The thermal protection technology field of rudder.
Background technology
Aircraft with hypersonic flight, high vehicle out-driving and capability of fast response is in the long endurance high speed of near space
When flight or atmospheric reentry, the pneumatic thermal environment that the regional area such as rudder, nose of wing and nose cone is subjected to is compared with other positions more
Badly, the airvane particular on aircraft outer surface is to adjust flight attitude and the important component of flight path, it is necessary to assure
Its safety of pneumatic dimension shape and structure during flying for long time.The it is proposed of active complement heat conduction concept, can be fast and effective
Heat is transported to the large area low temperature of aircraft lee face by ground from the serious high-temperature region of the Aerodynamic Heatings such as rudder, nose of wing and nose cone
Area, on this basis by solar heat protection, thermal control and structure-integrated design, height can be alleviated while low-temperature space radiating effect is improved
The heat carrying burden of warm area material and structure, is expected to the reusable structure solar heat protection integrated technique of hypersonic aircraft
It is achieved.
Depend on shock tunnel for the test method of flying vehicles control (air) rudder tipping leading edge both at home and abroad at present more, its
Feature is can to simulate high speed, Gao Han, high reynolds number and High Mach number, but test period is very short, and typically only several milliseconds to several
Ten milliseconds.And for the Na-K alloy working medium with active complement heat conduction function, it absorbs heat by liquid from heating section
It is changed into gaseous state, the list for becoming liquid again is cooled down by heat loss through radiation or convection current after radiating segment is flow under the promotion of saturated vapor pressure
Secondary circulation time is far longer than the test period of shock tunnel, it is impossible to meet the special aerodynamic configuration of control flaps point leading edge and it is long when
Between the particularity tested.
The content of the invention
Present invention solves the technical problem that it is：A kind of overcome the deficiencies in the prior art, it is proposed that flying vehicles control rudder tipping
The active complement heat conduction pilot system of leading edge and method, this method can solve the problem that the sharp leading edge test model with high thermal conductivity
Complement heat conduction Performance Evaluation test problem, for the active complement heat conduction technology with higher engineering application value and existing ripe flight
The design that device thermal protection system is combined provides reliable test data support.
The present invention technical solution be：
A kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge, before described flying vehicles control rudder tipping
The test model of the active complement heat conduction of edge includes endotherm section and radiating segment, and the system includes heater, temperature measurement system, temperature
Control system, wind cooling temperature lowering equipment and power supply；
Described heater is used to heat test model；
Described temperature measurement system is used to carry out temperature survey to test model；
Described temperature control system is used to carry out temperature control to test model；
Described wind cooling temperature lowering equipment is used to cool to test model；
Described power supply is used to provide real-time voltage to heater.
Described heater is profiling quartz lamp heater, and heater includes lamp array, water cooling reflector and bottom plate；Bottom plate
The profile of the endotherm section of inner surface configuration and test model matches, and lamp array is embedded into the inner surface of bottom plate, and water cooling reflector is embedding
Enter the outer surface to bottom plate.
When the rated power of power supply is 100kW, when the arrangement spacing of fluorescent tube in lamp array is 1-2mm, while water cooling is reflective
When the spacing of plate and lamp array is 3-5mm, the loading energy of the heat flow density of the sharp leading edge center position of endotherm section on test model
Power is not less than 1000kW/m2, the load capability of the temperature of the sharp leading edge center position of endotherm section is not less than on test model
1500℃；
When the rated power of power supply is 100kW, when the arrangement spacing of fluorescent tube in lamp array is 3-5mm, while water cooling is reflective
When the spacing of plate and lamp array is 6-9mm, the loading energy of the heat flow density of the sharp leading edge center position of endotherm section on test model
Power is not less than 750kW/m2, the load capability of the temperature of the sharp leading edge center position of endotherm section is not less than 1100 on test model
℃。
The arrangement spacing d of fluorescent tube and water cooling reflector and the spacing h of lamp array determination method are in described lamp array：
Utilize the Radiant exothermicity computational methods between the heat radiation of quartzy lamp array and each heating surface of test model, wherein parameter
Ai, Ti, ε i, α i and ρ i are respectively area, temperature, blackness, absorptivity and the reflectivity on each surface；
To establish the computation model that quartzy lamp array is radiated test model, it is assumed that quartzy filament temperature is uniform, quartz glass
Transmitance is 100%, that is, ignores the absorption to radiant heat, and each surface is diffusion-gray surface, and Net long wave radiation J and projection radiation G are
It is uniform, when each surface carries out radiation heat transfer in cavity, its Net long wave radiation is own radiation and antiradiation sum, i.e.,：
Ji=Ei+ρiGi=εiEbi+(1-αi)Gi (1)
Radiant exothermicity in i surfaces and cavity between other surfaces, i.e. its clear the or net heat flow Ф i lost, should
Receive, the difference of branch radiation energy, be expressed as within the unit interval equal to the surface：
φi=Ai(Ji-Gi) (2)
In formula, projection radiation Gi is solved by Net long wave radiation Ji expression formulas above, i.e.,：
Gi=(Ji-εEbi)/(1-εi) (3)
Therefore
Formula (4) provides a formula to calculate a surface net radiation heat exchange amount, and calculated value is timing, net radiation hot-fluid
Spread out of from the surface, the on the contrary then incoming surface；
G is that total projection on i surfaces radiates, and it is equal to radiation sum of all n surfaces to i surfaces in system, i.e.,：
Therefore
For this formula, using relational expression AiFi-j=AiFj-iAi is eliminated, obtains following formula：
For the closed system being made up of n surface, the equation group of following n equation is obtained：
Formula (7) can be organized into the form of matrix：
Obtain the Net long wave radiation J on each surface1、J2、J3、···、Jn, the net radiation heat exchange on i surfaces and each surface in system
Amount, obtained according to formula (2) and formula (4)：
Described temperature measurement system is used to measure the temperature of endotherm section and radiating segment in test model, is additionally operable to measurement and inhales
Radiant heat flux density on hot arc, and the real time temperature for measuring sharp leading edge center on obtained endotherm section is sent to temperature
Control system.
Described temperature control system receives the real time temperature for the sharp leading edge center that temperature measurement system is sent, and will
The real time temperature of the sharp leading edge center received and the target temperature of the sharp leading edge center of test model requirement are carried out
Compare, when target temperature is higher than real time temperature, temperature control system sends the control letter for raising real-time output voltage to power supply
Number, when target temperature is less than real time temperature, temperature control system sends the control signal for reducing real-time output voltage to power supply,
When target temperature is identical with real time temperature, temperature control system sends the control signal for maintaining real-time output voltage to power supply.
Described wind cooling temperature lowering equipment is electric fan, for carrying out forced convertion cooling to the radiating segment of test model；Electricity
The numerical values recited for the real-time voltage that source is provided heater is controlled by temperature control system.
The profile of described endotherm section is leading-edge radius R=5mm wedge profile, and the material of endotherm section is code name GH3128
Tungsten, molybdenum solution strengthening nickel-base alloy；Radiating segment is the fin tube structure that 316 stainless steels make, and endotherm section and radiating segment pass through
Welding manner connects, and the inside of endotherm section and the inside of radiating segment are heat-transfer working medium runner, and heat-transfer working medium closes for sodium potassium liquid
Gold.
A kind of active complement heat conduction test method of flying vehicles control rudder tipping leading edge, include the step of this method：
(1) test model is positioned in heater, enables lamp array in heater to the endotherm section of test model
Sharp leading edge is uniformly heated；
(2) turn on the power, temperature measurement system, temperature control system and wind cooling temperature lowering equipment；
(3) temperature measurement system gathers the spoke in the temperature and endotherm section of endotherm section and radiating segment in test model in real time
Heat flow density is penetrated, and the real time temperature for measuring sharp leading edge center on obtained endotherm section is sent to temperature control system；
(4) the real-time temperature for the sharp leading edge center that temperature control system is sent according to the temperature measurement system received
Degree, compared with the target temperature of the sharp leading edge center of test model requirement, when target temperature is higher than real time temperature,
Temperature control system sends the control signal for raising real-time output voltage to power supply, when target temperature is less than real time temperature, temperature
Spend control system and the control signal for reducing real-time output voltage is sent to power supply, when target temperature is identical with real time temperature, temperature
Spend control system and the control signal for maintaining real-time output voltage is sent to power supply.
Normal thermal starting test and long-time stability test are carried out to test model；
Normally thermal starting method of testing is：Absorbed heat in the test model gathered in real time according to step (3) temperature measurement system
The real time temperature T of sharp leading edge center in sectionCenterWith the real time temperature T of radiating segment apical positionTopIt is compared, judges sodium potassium
Whether alloy working medium reaches thermal starting state, and records and work as TCenterWith TTopDifference required time t when being not more than 100 DEG C；
Work as TCenterWith TTopDifference be not more than 100 DEG C when think that Na-K alloy working medium is in complete thermal starting state；
Long-time stability method of testing is：It is further continued for after Na-K alloy working medium is in complete thermal starting state using temperature
Spend the real time temperature T of sharp leading edge center on endotherm section in the test model that measuring system gathers in real timeCenterWith radiating segment top
The real time temperature T of positionTop, the time gathered in real time is not less than 1000s, works as TCenterChanging value be not more than 50 DEG C, and TTopChange
Change value is not more than 150 DEG C；
When test model can either meet normal thermal starting test and disclosure satisfy that long-time stability test, it is believed that examination
Test model and disclosure satisfy that thermal design requirement.
The present invention compared with prior art the advantages of be：
(1) it is directed to the flying vehicles control rudder tipping leading edge test model with high thermal conductivity and devises a kind of active heat
Guaranteed performance test system is dredged, the system has stronger heating efficiency, disclosure satisfy that sharp leading edge temperature is not less than 1200 DEG C,
Sharp leading edge heat flow density is not less than 1000kW/m2, thermal design test requirements document of the test period more than 1000s；
(2) in active complement heat conduction guaranteed performance test system nucleus equipment --- profiling quartz lamp heater being capable of pin
Heating efficiency is adjusted for different tests requirement, temperature regulating range be room temperature to 1500 DEG C, heat flow density adjustable range
For 0 to 1000kW/m2；
(3) successfully carried out using the active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge and method and be based on
The active complement heat conduction guaranteed performance test of flying vehicles control rudder tipping leading edge of Na-K alloy working medium, solves special aerodynamic configuration
Long-time high temperature, the continual and steady loading problem of high hot-fluid of product.The system and method may extend to all kinds of working medium, various profiles
Active complement heat conduction properties of product certification test, there is preferable versatility.
Brief description of the drawings
Fig. 1 is the structural representation of test model；
Fig. 2 is the structural representation of heater；
Fig. 3 is the system composition schematic diagram of the present invention；
Fig. 4 is the test curve figure of the normal thermal starting of test model；
Fig. 5 is the test curve figure of long-time stable；
Fig. 6 is quartz lamp profiling heater design of Structural Parameters schematic diagram.
Embodiment
A kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge, the system includes heater 9, temperature is surveyed
Amount system 11, temperature control system 12, wind cooling temperature lowering equipment 13 and power supply 14, as shown in Figure 3；
As shown in figure 1, the test model 10 of the described active complement heat conduction of flying vehicles control rudder tipping leading edge includes heat absorption
Section 1 and radiating segment 2, the profile of endotherm section 1 are leading-edge radius R=5mm wedge profile, and the material of endotherm section 1 is code name
GH3128 tungsten, molybdenum solution strengthening nickel-base alloy；Radiating segment 2 is the fin tube structure that 316 stainless steels make, as shown in Figure 1.Inhale
Hot arc 1 is connected with radiating segment 2 by welding manner, and the inside of endotherm section 1 and the inside of radiating segment 2 are heat-transfer working medium runner,
Heat-transfer working medium is sodium potassium liquid alloy；
As shown in Fig. 2 described heater 9 is profiling quartz lamp heater, heater 9 includes lamp array 3, water cooling reflector
4 and bottom plate 5；The profile of the inner surface configuration of bottom plate 5 and the endotherm section 1 of test model 10 matches, and lamp array 3 is embedded into bottom plate 5
Inner surface, water cooling reflector 4 is embedded into the outer surface of bottom plate 5；
The described heat flow density of heater 9 and the load capability of temperature in by lamp array 3 the arrangement spacing of fluorescent tube influenceed,
Also influenceed by water cooling reflector 4 and the spacing of lamp array 3；
When the rated power of power supply 14 is 100kW, when the arrangement spacing of fluorescent tube in lamp array 3 is 1-2mm, while water cooling is anti-
When tabula rasa 4 and the spacing of lamp array 3 are 3-5mm, the heat flow density of the sharp leading edge center position of endotherm section 1 on test model 10
Load capability is not less than 1000kW/m2, the load capability of the temperature of the sharp leading edge center position of endotherm section 1 on test model 10
Not less than 1500 DEG C；
When the rated power of power supply 14 is 100kW, when the arrangement spacing of fluorescent tube in lamp array 3 is 3-5mm, while water cooling is anti-
When tabula rasa 4 and the spacing of lamp array 3 are 6-9mm, the heat flow density of the sharp leading edge center position of endotherm section 1 on test model 10
Load capability is not less than 750kW/m2, the load capability of the temperature of the sharp leading edge center position of endotherm section 1 on test model 10
Not less than 1100 DEG C；
Described temperature measurement system 11 is used to measure the Temperature Distribution of endotherm section 1 and radiating segment 2 in test model 10, also
For measuring the radiant heat flux density on endotherm section 1, and the real-time temperature that sharp leading edge center on obtained endotherm section 1 will be measured
Degree is sent to temperature control system 12；
Described temperature control system 12 receives the real time temperature for the sharp leading edge center that temperature measurement system 11 is sent,
And the target temperature for the sharp leading edge center for requiring the real time temperature of the sharp leading edge center received and test model 10
Degree is compared, and when target temperature is higher than real time temperature, temperature control system 12 sends rise output electricity in real time to power supply 14
The control signal of pressure, when target temperature is less than real time temperature, temperature control system 12 is sent to power supply 14 reduces output in real time
The control signal of voltage, when target temperature is identical with real time temperature, temperature control system 12 is sent to power supply 14 remains real-time
The control signal of output voltage；
Described wind cooling temperature lowering equipment 13 is electric fan, cold for carrying out forced convertion to the radiating segment 2 of test model 10
But；
Described power supply 14 is used to provide real-time voltage to heater 10, and the rated power of power supply 14 is 100kW；Power supply 14
The numerical values recited of the real-time voltage provided heater 10 is controlled by temperature control system 12.
A kind of active complement heat conduction test method of flying vehicles control rudder tipping leading edge, include the step of this method：
(1) test model 10 is positioned in heater 9, enables suction of the lamp array 3 to test model 10 in heater 9
The sharp leading edge of hot arc 1 is uniformly heated；
(2) 14, temperature measurement system 11, temperature control system 12 and wind cooling temperature lowering equipment 13 are turned on the power；
(3) temperature measurement system 11 gathers the temperature and endotherm section of endotherm section 1 and radiating segment 2 in test model 10 in real time
Radiant heat flux density on 1, and the real time temperature for measuring sharp leading edge center on obtained endotherm section 1 is sent to temperature control
System 12 processed；
(4) the sharp leading edge center that temperature control system 12 is sent according to the temperature measurement system 11 received is real-time
Temperature, compared with the target temperature of the sharp leading edge center of the requirement of test model 10, when target temperature is higher than temperature in real time
When spending, temperature control system 12 sends the control signal for raising real-time output voltage to power supply 14, when target temperature is less than real-time
During temperature, temperature control system 12 sends the control signal for reducing real-time output voltage to power supply 14, when target temperature and in real time
When temperature is identical, temperature control system 12 sends the control signal for maintaining real-time output voltage to power supply 14；
Normal thermal starting test：Endotherm section 1 in the test model 10 gathered in real time according to step (3) temperature measurement system 11
The real time temperature T of upper sharp leading edge centerCenterWith the real time temperature T of the apical position of radiating segment 2TopIt is compared, judges sodium potassium
Whether alloy working medium reaches thermal starting state, and records and work as TCenterWith TTopDifference required time t when being not more than 100 DEG C；
Work as TCenterWith TTopDifference be not more than 100 DEG C when think that Na-K alloy working medium is in complete thermal starting state；
Long-time stability is tested：Temperature in use measurement is further continued for after Na-K alloy working medium is in complete thermal starting state
In the test model 10 that system 11 gathers in real time on endotherm section 1 sharp leading edge center real time temperature TCenterWith the top of radiating segment 2
The real time temperature T of positionTop, the time gathered in real time is not less than 1000s, works as TCenterChanging value be not more than 50 DEG C, and TTopChange
Change value is not more than 150 DEG C.
When test model 10 can either meet normal thermal starting test and disclosure satisfy that long-time stability test, it is believed that
Test model 10 disclosure satisfy that thermal design requirement.
The present invention will be further described with reference to the accompanying drawings and examples.
Embodiment
It is required that the thermal design requirement that test model 10 meets is：The temperature of sharp leading edge is not less than 1200 DEG C, the heat of sharp leading edge
Current density is not less than 1000kW/m2；And in 10s can normal heat start, stable work time is not less than 1000s；
System and method below by the present invention comes whether testing experiment model disclosure satisfy that requirement.
According to the above-mentioned thermal design test requirements document proposed for test model 10, design and made a kind of for flying
The pilot system of device control flaps tipping leading edge active complement heat conduction experiment, the system include heater 9, temperature measurement system 11,
Temperature control system 12, wind cooling temperature lowering equipment 13 and power supply 14；
The test model 10 of the described active complement heat conduction of flying vehicles control rudder tipping leading edge includes endotherm section 1 and radiating segment
2, the profile of endotherm section 1 is leading-edge radius R=5mm wedge profile, and tungsten, the molybdenum that the material of endotherm section 1 is code name GH3128 are solid
Molten reinforcing nickel-base alloy；Radiating segment 2 is the fin tube structure that 316 stainless steels make, as shown in Figure 1.Endotherm section 1 and radiating segment 2
Connected by welding manner, the inside of endotherm section 1 and the inside of radiating segment 2 are heat-transfer working medium runner, and heat-transfer working medium is sodium potassium
Liquid alloy；
Described heater 9 is profiling quartz lamp heater, and heater 9 includes lamp array 3, water cooling reflector 4 and bottom plate 5；
The profile of the inner surface configuration of bottom plate 5 and the endotherm section 1 of test model 10 matches, and lamp array 3 is embedded into the inner surface of bottom plate 5,
Water cooling reflector 4 is embedded into the outer surface of bottom plate 5；
The described heat flow density of heater 9 and the load capability of temperature in by lamp array 3 the arrangement spacing of fluorescent tube influenceed,
Also influenceed by water cooling reflector 4 and the spacing of lamp array 3；
Under conditions of the rated power of power supply 14 is 100kW, it is not less than 1200 DEG C according to the temperature of sharp leading edge, sharp leading edge
Heat flow density be not less than 1000kW/m2Specific test requirements document, the arrangement spacing of fluorescent tube in the lamp array 3 of the heater 9 of design
For 2mm, while water cooling reflector 4 and the spacing of lamp array 3 are 4mm.
Described temperature measurement system 11 is used to measure the temperature of endotherm section 1 and radiating segment 2 in test model 10, is additionally operable to
The radiant heat flux density on endotherm section 1 is measured, and the real time temperature for measuring sharp leading edge center on obtained endotherm section 1 is sent out
Give temperature control system 12；
Described temperature control system 12 receives the real time temperature for the sharp leading edge center that temperature measurement system 11 is sent,
And the target temperature for the sharp leading edge center for requiring the real time temperature of the sharp leading edge center received and test model 10
Degree is compared, and when target temperature is higher than real time temperature, temperature control system 12 sends rise output electricity in real time to power supply 14
The control signal of pressure, when target temperature is less than real time temperature, temperature control system 12 is sent to power supply 14 reduces output in real time
The control signal of voltage, when target temperature is identical with real time temperature, temperature control system 12 is sent to power supply 14 remains real-time
The control signal of output voltage；
Described wind cooling temperature lowering equipment 13 is electric fan, cold for carrying out forced convertion to the radiating segment 2 of test model 10
But；
Described power supply 14 is used to provide real-time voltage to heater 10, and the rated power of power supply 14 is 100kW；Power supply 14
The numerical values recited of the real-time voltage provided heater 10 is controlled by temperature control system 12.
First test model 10 is positioned in heater 9 during experiment, enables the lamp array 3 in heater 9 to test model
The sharp leading edge of 10 endotherm section 1 is uniformly heated；Turn on the power 14, temperature measurement system 11, temperature control system 12 and wind
Cold cooling system 13；
Ensure system worked well afterwards, temperature measurement system 11 gathers in real time in the course of work absorbs heat in test model 10
Radiant heat flux density in section 1 and the temperature and endotherm section 1 of radiating segment 2, and will measure on obtained endotherm section 1 in sharp leading edge
The real time temperature of heart position is sent to temperature control system 12；Temperature control system 12 is according to the temperature measurement system 11 received
The real time temperature of the sharp leading edge center of transmission, carried out with the target temperature of the sharp leading edge center of the requirement of test model 10
Compare, when target temperature is higher than real time temperature, temperature control system 12 sends the control for raising real-time output voltage to power supply 14
Signal processed, when target temperature is less than real time temperature, temperature control system 12 is sent to power supply 14 reduces real-time output voltage
Control signal, when target temperature is identical with real time temperature, temperature control system 12 is sent to power supply 14 maintains output electricity in real time
The control signal of pressure；
The measuring point temperature paid close attention to during system testing is sharp leading edge center on endotherm section 1 in test model 10
Real time temperature TCenterWith the real time temperature T of the apical position of radiating segment 2Top, and TCenterWith TTopDifference no more than 100 DEG C when institute
The time t needed.T during this experimentCenterWith TTopDifference required time t=1s when being not more than 100 DEG C, illustrate sodium
Potassium-sodium alloy working medium can normal thermal starting, test data in the 1s in 203s to 204s after on-test as shown in figure 4, by reaching
To thermal starting state.
As seen from Figure 5, out of, the 250s to 1260s after on-test the 1010s times, TCenterWith TTopDifference
Value is not more than 150 DEG C, illustrates temperature T of the test model 10 in sharp leading edgeCenterNot less than 1200 DEG C, the heat flow density of sharp leading edge
1000kW/m2Experimental condition under can long-time stable work.
For profiling heater design structural representation as shown in fig. 6, wherein：D distances between fluorescent tube in lamp array；h
The vertical range between water cooling reflector and lamp array.
Using the Radiant exothermicity computational methods between the heat radiation of quartzy lamp array and each heating surface of test model, d is extrapolated
With two design parameters of h, calculating parameter Ai, Ti in figure and formula, ε i, α i and ρ i be respectively the area on each surface, temperature, black
Degree, absorptivity and reflectivity.
To establish the computation model that quartzy lamp array is radiated test model, following physical simplifications are proposed it is assumed that quartzy filament
Temperature is uniform, and quartz glass transmitance is 100%, that is, ignores the absorption to radiant heat, each surface is diffusion-gray surface, effectively
Radiation J and projection radiation G is uniform, and when each surface carries out radiation heat transfer in cavity, its Net long wave radiation is spoke itself
Penetrate and antiradiation sum, i.e.,：
Ji=Ei+ρiGi=εiEbi+(1-αi)Gi (1)
Radiant exothermicity in i surfaces and cavity between other surfaces, i.e. its clear the or net heat flow Ф i lost, should
Receive, the difference of branch radiation energy, be expressed as within the unit interval equal to the surface：
φi=Ai(Ji-Gi) (2)
In formula, projection radiation Gi can be solved by Net long wave radiation Ji expression formulas above, i.e.,：
Gi=(Ji-εEbi)/(1-εi) (3)
Therefore
Formula (4) provides a formula to calculate a surface net radiation heat exchange amount, and calculated value is timing, net radiation hot-fluid
Spread out of from the surface, the on the contrary then incoming surface.
G is that total projection on i surfaces radiates, and it is equal to radiation sum of all n surfaces to i surfaces in system, i.e.,：
Therefore
For this formula, using relational expression AiFi-j=AiFj-iAi is eliminated, obtains following formula：
For the closed system being made up of n surface, the equation group of following n equation can be obtained：
Formula (7) can be organized into the form of matrix：
The usable computer program of above-mentioned matrix solves the Net long wave radiation J on each surface1、J2、J3、···、Jn.I surfaces with
The net radiation heat exchange amount on each surface in system, obtained according to formula (2) and formula (4)：
Drawn by above-mentioned relation formula：Distance h=between distance d=2mm, cooled plate and lamp array between fluorescent tube in heater lamp array
4mm。
Claims (10)
1. a kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge, described flying vehicles control rudder tipping leading edge
The test model of active complement heat conduction includes endotherm section and radiating segment, it is characterised in that：The system includes heater, temperature survey
System, temperature control system, wind cooling temperature lowering equipment and power supply；
Described heater is used to heat test model；
Described temperature measurement system is used to carry out temperature survey to test model；
Described temperature control system is used to carry out temperature control to test model；
Described wind cooling temperature lowering equipment is used to cool to test model；
Described power supply is used to provide real-time voltage to heater.
2. a kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge according to claim 1, its feature
It is：Described heater is profiling quartz lamp heater, and heater includes lamp array, water cooling reflector and bottom plate；Bottom plate it is interior
The profile of the endotherm section of surface configuration and test model matches, and lamp array is embedded into the inner surface of bottom plate, the insertion of water cooling reflector
To the outer surface of bottom plate.
3. a kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge according to claim 2, its feature
It is：When the rated power of power supply is 100kW, when the arrangement spacing of fluorescent tube in lamp array is 1-2mm, while water cooling reflector with
The load capability of the heat flow density of the sharp leading edge center position of endotherm section is not when the spacing of lamp array is 3-5mm, on test model
Less than 1000kW/m2, the load capability of the temperature of the sharp leading edge center position of endotherm section is not less than 1500 DEG C on test model；
When the rated power of power supply is 100kW, when the arrangement spacing of fluorescent tube in lamp array is 3-5mm, while water cooling reflector with
The load capability of the heat flow density of the sharp leading edge center position of endotherm section is not when the spacing of lamp array is 6-9mm, on test model
Less than 750kW/m2, the load capability of the temperature of the sharp leading edge center position of endotherm section is not less than 1100 DEG C on test model.
4. a kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge according to claim 3, its feature
It is：The arrangement spacing d of fluorescent tube and water cooling reflector and the spacing h of lamp array determination method are in described lamp array：
Using the Radiant exothermicity computational methods between the heat radiation of quartzy lamp array and each heating surface of test model, wherein parameter Ai,
Ti, ε i, α i and ρ i are respectively area, temperature, blackness, absorptivity and the reflectivity on each surface；
To establish the computation model that quartzy lamp array is radiated test model, it is assumed that quartzy filament temperature is uniform, and quartz glass passes through
Rate is 100%, that is, ignores the absorption to radiant heat, and each surface is diffusion-gray surface, and Net long wave radiation J and projection radiation G are equal
Even, when each surface carries out radiation heat transfer in cavity, its Net long wave radiation is own radiation and antiradiation sum, i.e.,：
Ji=Ei+ρiGi=εiEbi+(1-αi)Gi (1)
Radiant exothermicity in i surfaces and cavity between other surfaces, i.e. its clear the or net heat flow Ф i lost, should be equal to
The surface is received within the unit interval, the difference of branch radiation energy, is expressed as：
φi=Ai(Ji-Gi) (2)
In formula, projection radiation Gi is solved by Net long wave radiation Ji expression formulas above, i.e.,：
Gi=(Ji-εEbi)/(1-εi) (3)
Therefore
<mrow>
<msub>
<mi>&phi;</mi>
<mi>i</mi>
</msub>
<mo>=</mo>
<mfrac>
<mrow>
<msub>
<mi>E</mi>
<mrow>
<mi>b</mi>
<mi>i</mi>
</mrow>
</msub>
<mo>-</mo>
<msub>
<mi>J</mi>
<mi>i</mi>
</msub>
</mrow>
<mrow>
<mo>(</mo>
<mn>1</mn>
<mo>-</mo>
<msub>
<mi>&epsiv;</mi>
<mi>i</mi>
</msub>
<mo>)</mo>
<mo>/</mo>
<msub>
<mi>A</mi>
<mi>i</mi>
</msub>
<msub>
<mi>&epsiv;</mi>
<mi>i</mi>
</msub>
</mrow>
</mfrac>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>4</mn>
<mo>)</mo>
</mrow>
</mrow>
Formula (4) provides a formula to calculate a surface net radiation heat exchange amount, and calculated value is timing, net radiation hot-fluid from this
Surface is spread out of, the on the contrary then incoming surface；
G is that total projection on i surfaces radiates, and it is equal to radiation sum of all n surfaces to i surfaces in system, i.e.,：
<mrow>
<msub>
<mi>G</mi>
<mi>i</mi>
</msub>
<mo>=</mo>
<munderover>
<mo>&Sigma;</mo>
<mrow>
<mi>j</mi>
<mo>=</mo>
<mn>1</mn>
</mrow>
<mi>n</mi>
</munderover>
<msub>
<mi>F</mi>
<mrow>
<mi>j</mi>
<mo>-</mo>
<mi>i</mi>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mi>i</mi>
</msub>
<msub>
<mi>A</mi>
<mi>j</mi>
</msub>
<mo>/</mo>
<msub>
<mi>A</mi>
<mi>i</mi>
</msub>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>4</mn>
<mo>)</mo>
</mrow>
</mrow>
Therefore
For this formula, using relational expression AiFi-j=AiFj-iAi is eliminated, obtains following formula：
<mrow>
<munderover>
<mo>&Sigma;</mo>
<mrow>
<mi>j</mi>
<mo>=</mo>
<mn>1</mn>
</mrow>
<mi>n</mi>
</munderover>
<msub>
<mi>F</mi>
<mrow>
<mi>i</mi>
<mo>-</mo>
<mi>j</mi>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mi>j</mi>
</msub>
<mo>-</mo>
<mfrac>
<msub>
<mi>J</mi>
<mi>i</mi>
</msub>
<mrow>
<mn>1</mn>
<mo>-</mo>
<msub>
<mi>&epsiv;</mi>
<mi>i</mi>
</msub>
</mrow>
</mfrac>
<mo>=</mo>
<mfrac>
<msub>
<mi>&epsiv;</mi>
<mi>i</mi>
</msub>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mi>i</mi>
</msub>
<mo>-</mo>
<mn>1</mn>
</mrow>
</mfrac>
<msub>
<mi>&sigma;</mi>
<mi>b</mi>
</msub>
<msubsup>
<mi>T</mi>
<mi>i</mi>
<mn>4</mn>
</msubsup>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>6</mn>
<mo>)</mo>
</mrow>
</mrow>
For the closed system being made up of n surface, the equation group of following n equation is obtained：
<mrow>
<mfenced open = "" close = "|">
<mtable>
<mtr>
<mtd>
<mrow>
<msub>
<mi>F</mi>
<mrow>
<mn>1</mn>
<mo>-</mo>
<mn>1</mn>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mn>1</mn>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mn>1</mn>
<mo>-</mo>
<mn>2</mn>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mn>2</mn>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mn>1</mn>
<mo>-</mo>
<mn>3</mn>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mn>3</mn>
</msub>
<mo>+</mo>
<mn>...</mn>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mn>1</mn>
<mo>-</mo>
<mi>n</mi>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mi>n</mi>
</msub>
<mo>-</mo>
<mfrac>
<msub>
<mi>J</mi>
<mn>1</mn>
</msub>
<mrow>
<mn>1</mn>
<mo>-</mo>
<msub>
<mi>&epsiv;</mi>
<mn>1</mn>
</msub>
</mrow>
</mfrac>
<mo>=</mo>
<mfrac>
<msub>
<mi>&epsiv;</mi>
<mn>1</mn>
</msub>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mn>1</mn>
</msub>
<mo>-</mo>
<mn>1</mn>
</mrow>
</mfrac>
<msub>
<mi>&sigma;</mi>
<mi>b</mi>
</msub>
<msubsup>
<mi>T</mi>
<mn>1</mn>
<mn>4</mn>
</msubsup>
</mrow>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<msub>
<mi>F</mi>
<mrow>
<mn>2</mn>
<mo>-</mo>
<mn>1</mn>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mn>1</mn>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mn>2</mn>
<mo>-</mo>
<mn>2</mn>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mn>2</mn>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mn>2</mn>
<mo>-</mo>
<mn>3</mn>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mn>3</mn>
</msub>
<mo>+</mo>
<mn>...</mn>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mn>2</mn>
<mo>-</mo>
<mi>n</mi>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mi>n</mi>
</msub>
<mo>-</mo>
<mfrac>
<msub>
<mi>J</mi>
<mn>2</mn>
</msub>
<mrow>
<mn>1</mn>
<mo>-</mo>
<msub>
<mi>&epsiv;</mi>
<mn>2</mn>
</msub>
</mrow>
</mfrac>
<mo>=</mo>
<mfrac>
<msub>
<mi>&epsiv;</mi>
<mn>2</mn>
</msub>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mn>2</mn>
</msub>
<mo>-</mo>
<mn>1</mn>
</mrow>
</mfrac>
<msub>
<mi>&sigma;</mi>
<mi>b</mi>
</msub>
<msubsup>
<mi>T</mi>
<mn>2</mn>
<mn>4</mn>
</msubsup>
</mrow>
</mtd>
</mtr>
<mtr>
<mtd>
<mo>.</mo>
</mtd>
</mtr>
<mtr>
<mtd>
<mo>.</mo>
</mtd>
</mtr>
<mtr>
<mtd>
<mo>.</mo>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<msub>
<mi>F</mi>
<mrow>
<mi>n</mi>
<mo>-</mo>
<mn>1</mn>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mn>1</mn>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mi>n</mi>
<mo>-</mo>
<mn>2</mn>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mn>2</mn>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mi>n</mi>
<mo>-</mo>
<mn>3</mn>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mn>3</mn>
</msub>
<mo>+</mo>
<mn>...</mn>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mi>n</mi>
<mo>-</mo>
<mi>n</mi>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mi>n</mi>
</msub>
<mo>-</mo>
<mfrac>
<msub>
<mi>J</mi>
<mi>n</mi>
</msub>
<mrow>
<mn>1</mn>
<mo>-</mo>
<msub>
<mi>&epsiv;</mi>
<mi>n</mi>
</msub>
</mrow>
</mfrac>
<mo>=</mo>
<mfrac>
<msub>
<mi>&epsiv;</mi>
<mi>n</mi>
</msub>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mi>n</mi>
</msub>
<mo>-</mo>
<mn>1</mn>
</mrow>
</mfrac>
<msub>
<mi>&sigma;</mi>
<mi>b</mi>
</msub>
<msubsup>
<mi>T</mi>
<mi>n</mi>
<mn>4</mn>
</msubsup>
</mrow>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>7</mn>
<mo>)</mo>
</mrow>
</mrow>
Formula (7) can be organized into the form of matrix：
<mrow>
<mfenced open = "[" close = "]">
<mtable>
<mtr>
<mtd>
<mrow>
<msub>
<mi>F</mi>
<mrow>
<mn>1</mn>
<mo>-</mo>
<mn>1</mn>
</mrow>
</msub>
<mo>-</mo>
<mfrac>
<mn>1</mn>
<mrow>
<mn>1</mn>
<mo>-</mo>
<msub>
<mi>&epsiv;</mi>
<mn>1</mn>
</msub>
</mrow>
</mfrac>
</mrow>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mn>1</mn>
<mo>-</mo>
<mn>2</mn>
</mrow>
</msub>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mn>1</mn>
<mo>-</mo>
<mn>3</mn>
</mrow>
</msub>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mn>1</mn>
<mo>-</mo>
<mi>n</mi>
</mrow>
</msub>
</mtd>
</mtr>
<mtr>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mn>2</mn>
<mo>-</mo>
<mn>1</mn>
</mrow>
</msub>
</mtd>
<mtd>
<mrow>
<msub>
<mi>F</mi>
<mrow>
<mn>2</mn>
<mo>-</mo>
<mn>2</mn>
</mrow>
</msub>
<mo>-</mo>
<mfrac>
<mn>1</mn>
<mrow>
<mn>1</mn>
<mo>-</mo>
<msub>
<mi>&epsiv;</mi>
<mn>2</mn>
</msub>
</mrow>
</mfrac>
</mrow>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mn>2</mn>
<mo>-</mo>
<mn>3</mn>
</mrow>
</msub>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mn>2</mn>
<mo>-</mo>
<mi>n</mi>
</mrow>
</msub>
</mtd>
</mtr>
<mtr>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mn>3</mn>
<mo>-</mo>
<mn>1</mn>
</mrow>
</msub>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mn>3</mn>
<mo>-</mo>
<mn>2</mn>
</mrow>
</msub>
</mtd>
<mtd>
<mrow>
<msub>
<mi>F</mi>
<mrow>
<mn>3</mn>
<mo>-</mo>
<mn>2</mn>
</mrow>
</msub>
<mo>-</mo>
<mfrac>
<mn>1</mn>
<mrow>
<mn>1</mn>
<mo>-</mo>
<msub>
<mi>&epsiv;</mi>
<mn>3</mn>
</msub>
</mrow>
</mfrac>
</mrow>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mn>3</mn>
<mo>-</mo>
<mi>n</mi>
</mrow>
</msub>
</mtd>
</mtr>
<mtr>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
</mtr>
<mtr>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mi>n</mi>
<mo>-</mo>
<mn>1</mn>
</mrow>
</msub>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mi>n</mi>
<mo>-</mo>
<mn>2</mn>
</mrow>
</msub>
</mtd>
<mtd>
<msub>
<mi>F</mi>
<mrow>
<mi>n</mi>
<mo>-</mo>
<mn>3</mn>
</mrow>
</msub>
</mtd>
<mtd>
<mn>...</mn>
</mtd>
<mtd>
<mrow>
<msub>
<mi>F</mi>
<mrow>
<mi>n</mi>
<mo>-</mo>
<mi>n</mi>
</mrow>
</msub>
<mo>-</mo>
<mfrac>
<mn>1</mn>
<mrow>
<mn>1</mn>
<mo>-</mo>
<msub>
<mi>&epsiv;</mi>
<mi>n</mi>
</msub>
</mrow>
</mfrac>
</mrow>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>&times;</mo>
<mfenced open = "[" close = "]">
<mtable>
<mtr>
<mtd>
<msub>
<mi>J</mi>
<mn>1</mn>
</msub>
</mtd>
</mtr>
<mtr>
<mtd>
<msub>
<mi>J</mi>
<mn>2</mn>
</msub>
</mtd>
</mtr>
<mtr>
<mtd>
<msub>
<mi>J</mi>
<mn>3</mn>
</msub>
</mtd>
</mtr>
<mtr>
<mtd>
<mo>.</mo>
</mtd>
</mtr>
<mtr>
<mtd>
<msub>
<mi>J</mi>
<mi>n</mi>
</msub>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>=</mo>
<mfenced open = "[" close = "]">
<mtable>
<mtr>
<mtd>
<mfrac>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mn>1</mn>
</msub>
<msub>
<mi>&sigma;</mi>
<mi>b</mi>
</msub>
<msubsup>
<mi>T</mi>
<mn>1</mn>
<mn>4</mn>
</msubsup>
</mrow>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mn>1</mn>
</msub>
<mo>-</mo>
<mn>1</mn>
</mrow>
</mfrac>
</mtd>
</mtr>
<mtr>
<mtd>
<mfrac>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mi>2</mi>
</msub>
<msub>
<mi>&sigma;</mi>
<mi>b</mi>
</msub>
<msubsup>
<mi>T</mi>
<mi>2</mi>
<mn>4</mn>
</msubsup>
</mrow>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mi>2</mi>
</msub>
<mo>-</mo>
<mn>1</mn>
</mrow>
</mfrac>
</mtd>
</mtr>
<mtr>
<mtd>
<mfrac>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mi>3</mi>
</msub>
<msub>
<mi>&sigma;</mi>
<mi>b</mi>
</msub>
<msubsup>
<mi>T</mi>
<mi>3</mi>
<mn>4</mn>
</msubsup>
</mrow>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mi>3</mi>
</msub>
<mo>-</mo>
<mn>1</mn>
</mrow>
</mfrac>
</mtd>
</mtr>
<mtr>
<mtd>
<mo>.</mo>
</mtd>
</mtr>
<mtr>
<mtd>
<mfrac>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mi>n</mi>
</msub>
<msub>
<mi>&sigma;</mi>
<mi>b</mi>
</msub>
<msubsup>
<mi>T</mi>
<mi>n</mi>
<mn>4</mn>
</msubsup>
</mrow>
<mrow>
<msub>
<mi>&epsiv;</mi>
<mi>n</mi>
</msub>
<mo>-</mo>
<mn>1</mn>
</mrow>
</mfrac>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>-</mo>
<mo>-</mo>
<mo>-</mo>
<mrow>
<mo>(</mo>
<mn>8</mn>
<mo>)</mo>
</mrow>
</mrow>
Obtain the Net long wave radiation J on each surface1、J2、J3、…、Jn, the net radiation heat exchange amount on i surfaces and each surface in system, according to formula
(2) obtained with formula (4)：
<mrow>
<msub>
<mi>&phi;</mi>
<mi>i</mi>
</msub>
<mo>=</mo>
<msub>
<mi>A</mi>
<mi>i</mi>
</msub>
<mrow>
<mo>(</mo>
<msub>
<mi>J</mi>
<mi>i</mi>
</msub>
<mo>-</mo>
<munderover>
<mo>&Sigma;</mo>
<mrow>
<mi>j</mi>
<mo>-</mo>
<mn>1</mn>
</mrow>
<mi>n</mi>
</munderover>
<msub>
<mi>F</mi>
<mrow>
<mi>i</mi>
<mo>-</mo>
<mi>j</mi>
</mrow>
</msub>
<msub>
<mi>J</mi>
<mi>j</mi>
</msub>
<mo>)</mo>
</mrow>
<mo>.</mo>
</mrow>
5. a kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge according to claim 1, its feature
It is：Described temperature measurement system is used to measure the temperature of endotherm section and radiating segment in test model, is additionally operable to measurement heat absorption
Radiant heat flux density in section, and the real time temperature for measuring sharp leading edge center on obtained endotherm section is sent to temperature control
System processed.
6. a kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge according to claim 1, its feature
It is：Described temperature control system receives the real time temperature for the sharp leading edge center that temperature measurement system is sent, and will connect
The real time temperature of the sharp leading edge center received and the target temperature of the sharp leading edge center of test model requirement are compared
Compared with, when target temperature is higher than real time temperature, temperature control system sends the control signal for raising real-time output voltage to power supply,
When target temperature is less than real time temperature, temperature control system sends the control signal for reducing real-time output voltage to power supply, when
When target temperature is identical with real time temperature, temperature control system sends the control signal for maintaining real-time output voltage to power supply.
7. a kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge according to claim 1, its feature
It is：Described wind cooling temperature lowering equipment is electric fan, for carrying out forced convertion cooling to the radiating segment of test model；Power supply pair
The numerical values recited for the real-time voltage that heater provides is controlled by temperature control system.
8. a kind of active complement heat conduction pilot system of flying vehicles control rudder tipping leading edge according to claim 1, its feature
It is：The profile of described endotherm section is leading-edge radius R=5mm wedge profile, and the material of endotherm section is code name GH3128's
Tungsten, molybdenum solution strengthening nickel-base alloy；Radiating segment is the fin tube structure that 316 stainless steels make, and endotherm section and radiating segment pass through weldering
The mode of connecing connects, and the inside of endotherm section and the inside of radiating segment are heat-transfer working medium runner, and heat-transfer working medium is sodium potassium liquid alloy.
9. a kind of active complement heat conduction test method of flying vehicles control rudder tipping leading edge, it is characterised in that wrap the step of this method
Include：
(1) test model is positioned in heater, before enabling the lamp array in heater to the point of the endotherm section of test model
Edge is uniformly heated；
(2) turn on the power, temperature measurement system, temperature control system and wind cooling temperature lowering equipment；
(3) temperature measurement system gathers the radiant heat in the temperature and endotherm section of endotherm section and radiating segment in test model in real time
Current density, and the real time temperature for measuring sharp leading edge center on obtained endotherm section is sent to temperature control system；
(4) real time temperature for the sharp leading edge center that temperature control system is sent according to the temperature measurement system received, with
The target temperature of the sharp leading edge center of test model requirement is compared, when target temperature is higher than real time temperature, temperature
Control system sends the control signal for raising real-time output voltage, when target temperature is less than real time temperature, temperature control to power supply
System processed sends the control signal for reducing real-time output voltage, when target temperature is identical with real time temperature, temperature control to power supply
System processed sends the control signal for maintaining real-time output voltage to power supply.
10. a kind of active complement heat conduction test method of flying vehicles control rudder tipping leading edge according to claim 9, its feature
It is：Normal thermal starting test and long-time stability test are carried out to test model；
Normally thermal starting method of testing is：In the test model gathered in real time according to step (3) temperature measurement system on endotherm section
The real time temperature T of sharp leading edge centerCenterWith the real time temperature T of radiating segment apical positionTopIt is compared, judges Na-K alloy
Whether working medium reaches thermal starting state, and records and work as TCenterWith TTopDifference required time t when being not more than 100 DEG C；
Work as TCenterWith TTopDifference be not more than 100 DEG C when think that Na-K alloy working medium is in complete thermal starting state；
Long-time stability method of testing is：Temperature in use survey is further continued for after Na-K alloy working medium is in complete thermal starting state
In the test model that amount system gathers in real time on endotherm section sharp leading edge center real time temperature TCenterWith radiating segment apical position
Real time temperature TTop, the time gathered in real time is not less than 1000s, works as TCenterChanging value be not more than 50 DEG C, and TTopChanging value
No more than 150 DEG C；
When test model can either meet normal thermal starting test and disclosure satisfy that long-time stability test, test model energy
Enough meet thermal design requirement.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109960878A (en) * | 2019-03-25 | 2019-07-02 | 西北工业大学 | A kind of active/passive thermal protection system coupling design method towards hypersonic aircraft totality |
| CN113155895A (en) * | 2021-03-31 | 2021-07-23 | 中国飞机强度研究所 | Thermal contact resistance measuring structure and measuring method thereof |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102609017A (en) * | 2012-03-01 | 2012-07-25 | 大连理工大学 | Heating device and method capable of producing controllable temperature gradient field on metal wing structure |
| US20140299712A1 (en) * | 2009-12-01 | 2014-10-09 | The Boeing Company | Thermal Barrier Coated RF Radomes |
| CN104859835A (en) * | 2015-04-27 | 2015-08-26 | 清华大学 | Hypersonic aircraft head cone based on composite cooling mode |
| CN105277227A (en) * | 2015-10-13 | 2016-01-27 | 北京航天长征飞行器研究所 | Infrared protective cover with integrated dual-layer structure for heat insulation and force bearing |
| CN205067051U (en) * | 2015-10-30 | 2016-03-02 | 北京科技大学 | Hypersonic wind tunnel temperature measurement structure |
| CN106572546A (en) * | 2016-10-26 | 2017-04-19 | 北京航天长征飞行器研究所 | Adjustable integral flat-plate quartz lamp heater structure |
| CN106809375A (en) * | 2016-12-19 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of hypersonic aircraft leading-type rudderpost thermal protection struc ture |
| CN106841288A (en) * | 2017-03-23 | 2017-06-13 | 北京临近空间飞行器系统工程研究所 | Comprehensive analysis method based on the various thermally protective materials of flight |
| CN107103117A (en) * | 2017-03-27 | 2017-08-29 | 北京临近空间飞行器系统工程研究所 | A kind of thermal environment design method in hypersonic aircraft control flaps gap |
-
2017
- 2017-09-26 CN CN201710879526.5A patent/CN107792392B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140299712A1 (en) * | 2009-12-01 | 2014-10-09 | The Boeing Company | Thermal Barrier Coated RF Radomes |
| CN102609017A (en) * | 2012-03-01 | 2012-07-25 | 大连理工大学 | Heating device and method capable of producing controllable temperature gradient field on metal wing structure |
| CN104859835A (en) * | 2015-04-27 | 2015-08-26 | 清华大学 | Hypersonic aircraft head cone based on composite cooling mode |
| CN105277227A (en) * | 2015-10-13 | 2016-01-27 | 北京航天长征飞行器研究所 | Infrared protective cover with integrated dual-layer structure for heat insulation and force bearing |
| CN205067051U (en) * | 2015-10-30 | 2016-03-02 | 北京科技大学 | Hypersonic wind tunnel temperature measurement structure |
| CN106572546A (en) * | 2016-10-26 | 2017-04-19 | 北京航天长征飞行器研究所 | Adjustable integral flat-plate quartz lamp heater structure |
| CN106809375A (en) * | 2016-12-19 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of hypersonic aircraft leading-type rudderpost thermal protection struc ture |
| CN106841288A (en) * | 2017-03-23 | 2017-06-13 | 北京临近空间飞行器系统工程研究所 | Comprehensive analysis method based on the various thermally protective materials of flight |
| CN107103117A (en) * | 2017-03-27 | 2017-08-29 | 北京临近空间飞行器系统工程研究所 | A kind of thermal environment design method in hypersonic aircraft control flaps gap |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109960878A (en) * | 2019-03-25 | 2019-07-02 | 西北工业大学 | A kind of active/passive thermal protection system coupling design method towards hypersonic aircraft totality |
| CN109960878B (en) * | 2019-03-25 | 2022-07-05 | 西北工业大学 | Hypersonic aircraft-oriented overall active/passive thermal protection system coupling design method |
| CN113155895A (en) * | 2021-03-31 | 2021-07-23 | 中国飞机强度研究所 | Thermal contact resistance measuring structure and measuring method thereof |
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|---|---|
| CN107792392B (en) | 2019-07-12 |
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