CN109823510A - Hypersonic aircraft and its thermal protection structure and coolant circulating system - Google Patents
Hypersonic aircraft and its thermal protection structure and coolant circulating system Download PDFInfo
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- CN109823510A CN109823510A CN201910166313.7A CN201910166313A CN109823510A CN 109823510 A CN109823510 A CN 109823510A CN 201910166313 A CN201910166313 A CN 201910166313A CN 109823510 A CN109823510 A CN 109823510A
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Abstract
The present invention provides a kind of pneumatic integrated thermal protection struc ture of rudder leading edge of hypersonic aircraft, the thermal protection structure is the integrated design, it include: solar heat protection covering, heat pipe, heat sink and thermal insulation layer, the solar heat protection covering is set to pneumatic rudder leading edge outer surface, heat sink is set to the inner surface of solar heat protection covering, heat pipe is fixedly connected with heat sink, and the heat pipe is set to the inner surface of heat sink, and thermal insulation layer is fixedly installed on the inner surface of heat pipe.The present invention also provides a kind of coolant circulating system and hypersonic aircrafts.The present invention can make the up-front deformation of flight vehicle aerodynamic rudder small small with heat flow density, keep the aerodynamic characteristic of aircraft high lift-drag ratio and the operability of pneumatic rudder, solves the problems, such as the problem that the big bring material failure of flight vehicle aerodynamic rudder leading edge hot-fluid and flying speed cause to bear aerodynamic loading ability difference fastly, the extreme distribution for avoiding pneumatic rudder leading edge temperature, it is heat-insulated for a long time to realize aircraft.
Description
Technical field
The present invention relates to hypersonic aircraft thermal protection fields, and in particular to a kind of up-front heat of flight vehicle aerodynamic rudder is anti-
Protection structure and coolant circulating system.
Background technique
Hypersonic aircraft in classical meaning refers to using airbreathing motor and combinations thereof engine as power, big
The aircraft to be flown in gas-bearing formation or across atmosphere with the speed long cruise of 5 or more Mach number.Ma=5 is not stringent herein
Boundary, but a region, i.e., the flow behavior of hypersonic air-flow can occur significantly to change in the range.Fly with tradition
Row device is compared, and hypersonic aircraft has great advantage, and high flying speed can ensure that it is reached in 2-3 hours
Any position in the whole world, effectively shortens the goal response time, promotes the penetration ability and survival ability of aircraft.
The hypersonic aircraft of long range maneuvering flight is carried out in endoatmosphere, is generally used pneumatic control rudder to control
The track of flight and the posture of aircraft are made, such as the body wing flap, flaperon, the ruddevator that are widely adopted at present (are referred to as
Pneumatic control rudder).The common trait of these pneumatic control rudders is nose of wing point, wing thickness is thin, aspect ratio is small.They need to be subjected to height
Harsh Aerodynamic Heating environment under Mach air-flow, while the mechanical load of great aerodynamic load and operating mechanism is born,
Its shape and rigidity are also kept at very high temperatures.The leading edge of pneumatic control rudder and the panel of two sides all have special gas
Dynamic thermal environment.
In hypersonic aircraft configuration design, the sharp leading edge of lower resistance replaces passivation leading edge that will become necessarily to become
Gesture.For aircraft in hypersonic flight, since air viscosity acts on, the air-flow in object plane boundary layer produces strong rub
It wipes, result makes the kinetic energy of gas be irreversibly transformed into thermal energy, in addition leading-edge radius very little, generates at leading edge position very strong
Aerodynamic Heating.Sharp leading edge shape aircraft has greater advantage on aeroperformance, but can bring that heat flow density is big, solar heat protection
Difficult problem.Influence of the radius of nose of wing to hot-fluid is very big, and when radius increases, hot-fluid reduces；Radius reduces, and hot-fluid is significant
Increase.
The passivation of aircraft leading edge and ablating heat shield are the common thermal protection methods of hypersonic aircraft, but leading edge is passivated
It is to reduce Aerodynamic Heating to sacrifice the aeroperformance of aircraft, the lift resistance ratio of aircraft can be reduced in this way and increase the resistance of aircraft
Power, to put forward higher requirement to the thrust of hypersonic aircraft engine；Ablating heat shield causes big profile variation
Also aerodynamic characteristics of vehicle will be seriously affected, it is right since the pneumatic rudder of hypersonic aircraft has the particular/special requirement of " conformal "
The variable quantity of pneumatic rudder has lesser requirement, when the deflection of pneumatic rudder is excessive, will lead to the control of hypersonic aircraft
Thrashing.The pneumatic rudder leading edge of hypersonic aircraft will not only consider that thermal protection is also contemplated that the bearing capacity of pneumatic rudder, because
Great aerodynamic loading can be born during flight for hypersonic aircraft, and the up-front deflection of pneumatic rudder should
It is smaller, it needs to keep pneumatic rudder structure completely indeformable.The design of most of hypersonic aircraft is all air-cooled structure at this stage
Design, by bearing structure design in the inside of thermal protection struc ture, this greatly increases the quality of flight vehicle aerodynamic rudder, give steering engine
Design increase difficulty.
Hypersonic aircraft is to improve lift resistance ratio, and pneumatic rudder need to have sharp leading edge, and pneumatic rudder leading edge is required to possess
Certain bearing capacity and the good aerodynamic configuration of holding, this proposes more stringent requirement to the solar heat protection of aircraft, and tradition is anti-
Heat and bearing mode have been unable to satisfy the anti-heat demand of tipping leading edge, so it is up-front to need a kind of pneumatic rudder of hypersonic aircraft
Integrated thermal protection structure, for solving the problems, such as that pneumatic rudder leading edge heat flow density is big, deformation is big and bearing capacity is small.
Summary of the invention
The object of the present invention is to provide a kind of up-front thermal protection structures of flight vehicle aerodynamic rudder, are provided in particular in a kind of superb
The up-front integrated thermal protection struc ture of velocity of sound flight vehicle aerodynamic rudder, can make the small and heat flow density of the up-front deformation of flight vehicle aerodynamic rudder
It is small, the aerodynamic characteristic of aircraft high lift-drag ratio and the operability of pneumatic rudder are kept, it is big to solve flight vehicle aerodynamic rudder leading edge hot-fluid
Bring material failure problem and flying speed lead to the problem for bearing aerodynamic loading ability difference fastly, avoid pneumatic rudder leading edge temperature
The extreme distribution of degree, it is heat-insulated for a long time to realize aircraft.
The technical solution adopted by the present invention is that: the present invention provides a kind of pneumatic rudder of hypersonic aircraft up-front integration
Thermal protection structure, the thermal protection structure are the integrated design, comprising: solar heat protection covering, heat pipe, heat sink and thermal insulation layer, institute
It states solar heat protection covering and is set to pneumatic rudder leading edge outer surface, heat sink is set to the inner surface of solar heat protection covering, and heat pipe and heat absorption fill
It sets and is fixedly connected, and the heat pipe is set to the inner surface of heat sink, and thermal insulation layer is fixedly installed on the inner surface of heat pipe.
Further, the solar heat protection covering is fabricated by heat insulation material, solar heat protection covering with a thickness of 8-10mm.
Further, the shape of the heat pipe is triangle, and the triangle of heat pipe is two rows arranged opposite.
Further, heat sink with a thickness of 5mm or more, and the thickness of heat sink along close to pneumatic rudder leading edge direction by
It is cumulative big.
Further, the heat sink is the metal foil to match with the solar heat protection covering of flight vehicle aerodynamic rudder outer surface
Plate, and heat sink is fixedly mounted on the inner surface of solar heat protection covering.
Further, thermal insulation layer is fabricated by heat-barrier material.
Another aspect of the present invention provides a kind of coolant circulating system, including coolant reservoir；Coolant delivery pump,
Heat-exchanger rig and thermal protection structure described above；
The coolant delivery pump is mounted on aircraft on the end frame of pneumatic rudder, and heat-exchanger rig is mounted on aircraft
At fuel delivery pipe road, the leading edge of flight vehicle aerodynamic rudder is arranged in thermal protection structure；
The coolant reservoir is connected with the coolant delivery pump, the coolant delivery pump and thermal protection structure phase
Even, the thermal protection structure is connected with heat-exchanger rig, and the heat-exchanger rig is connected with coolant reservoir, the coolant storage
Case, coolant delivery pump, thermal protection structure and heat-exchanger rig mutually form coolant circulating system.
Another aspect of the present invention provides a kind of hypersonic aircraft, including the above-mentioned thermal protection structure,
The edge of flight vehicle aerodynamic rudder is arranged in the thermal protection structure.
The present invention also provides a kind of hypersonic aircrafts, including coolant circulating system described above.
Compared with the prior art, the invention has the advantages that:
1) present invention provides a kind of pneumatic rudder of hypersonic aircraft up-front integrated thermal protection struc ture, can make aircraft
The pneumatic up-front deformation of rudder is small and heat flow density is small, keeps the aerodynamic characteristic of aircraft high lift-drag ratio and the operability of pneumatic rudder,
Solve the problems, such as that the big bring material failure of flight vehicle aerodynamic rudder leading edge hot-fluid and flying speed cause to bear aerodynamic loading energy fastly
The problem of power difference avoids the extreme distribution of pneumatic rudder leading edge temperature, it is heat-insulated for a long time to realize aircraft.
2) present invention combines solar heat protection covering with heat sink, as flight vehicle aerodynamic rudder leading edge thermal protection structure, inhales
Thermal absorbs the heat of flight vehicle aerodynamic rudder leading edge solar heat protection covering, reduces the ablation of surface thermal protection covering or ablation does not occur, make
The aerodynamic configuration variation of the pneumatic rudder of hypersonic aircraft is small, keeps the preferable aerodynamic characteristic of pneumatic rudder and operating characteristic, convenient
The calculating of aerodynamic force and the accurate control of aircraft, are better achieved the control function of aircraft.
3) present invention, can will be before pneumatic rudder in the heat sink of the high heat sink heat-absorbing material of inner surface installation of solar heat protection covering
The low-temperature space to two sides is dredged in the high-temperature region of edge, can be substantially reduced temperature difference, eliminates flight vehicle aerodynamic rudder edge
Localized hyperthermia, the heat for avoiding the absorption of edge heat sink is less than the heat of Aerodynamic Heating, close so as to cause leading edge hot-fluid
Spend situation that is very big and making leading edge thermal deformation big.And it since heat sink and solar heat protection covering are fixed together, also solves
Pneumatic rudder leading edge is more sharp, and general thermal protection structure cannot absorb sharp leading edge leading edge heat problem.
4) present invention installs heat pipe in the inner surface of heat sink, so that heat pipe is exchanged heat with heat sink, is dropped with this
The temperature of low heat sink enables heat sink continual and absorbs heat from the leading edge of pneumatic rudder.
5) the heat pipe shape that uses of the present invention is for triangle, and material of its manufacture is high heat sink material, and the three of heat pipe
Angular is two rows arranged opposite (as shown in Figure 1), so that the efficiency of the heat exchange of heat pipe increases, and the heat pipe energy of triangle
Enough play support, increases the bearing capacity and stability of pneumatic rudder, reduce the deflection of pneumatic rudder.
6) present invention is using thermal protection structure as solar heat protection covering, heat sink, heat pipe and thermal insulation layer, will carrying lotus and
Heat protection design is integration, can mitigate so that such thermal protection structure can either protect also be able to bear it is higher pneumatic
Load avoids the air-cooled structure design of pneumatic rudder, reduces the quality of pneumatic rudder thermal protection structure, improves the liter resistance of aircraft
Than and aeroperformance.
7) coolant in heat pipe of the present invention selects the helium of liquid, since the helium temperature of liquid is low, good effect of heat exchange,
And since the physicochemical properties of helium are stablized, use is safe.High temperature helium after cooling heat sink by pipeline and flies
The fuel of row device liquid carries out heat exchange in heat-exchanger rig, so that the helium gas cooling of high temperature is then proceeded at liquid by cold
But cooling heat sink is removed in delivery pump conveying.
Detailed description of the invention
Fig. 1 is a kind of up-front thermal protection structure schematic diagram of the pneumatic rudder of hypersonic aircraft provided by the invention；
Fig. 2 is that A goes out partial enlargement diagram in Fig. 1, shows the company of solar heat protection covering, heat pipe, heat sink and thermal insulation layer
Connect relationship；
Fig. 3 is a kind of structural schematic block diagram of coolant circulating system provided by the invention；
Fig. 4 is the diagrammatic cross-section of heat-exchanger rig in a kind of coolant circulating system provided by the invention；
Fig. 5 is the schematic front view of heat-exchanger rig in a kind of coolant circulating system provided by the invention；
Fig. 6 is the left view schematic diagram of heat-exchanger rig in a kind of coolant circulating system provided by the invention.
Appended drawing reference: 1 coolant reservoir；2 coolant delivery pumps；3 thermal protection structures；30 solar heat protection coverings；31 heat pipes；32
Heat sink；33 thermal insulation layers；4 heat-exchanger rigs；40 fuel inlets；41 fuel outlets；42 coolant entrances；43 coolant outlets.
Specific embodiment
Hypersonic aircraft be future aircraft development important directions, hypersonic aircraft require high lift-drag ratio and
The leading edge of wing and pneumatic rudder is sharp, so hypersonic aircraft will bear continuing for the high hot-fluid of long-time in flight course
Heating also suffers local superelevation hot-fluid heating in the sharp leading edge of pneumatic rudder, causes the temperature point of pneumatic rudder different parts
Cloth and its uneven, this harsh thermal environment puts forward stern challenge to traditional thermal protection struc ture.And it is hypersonic to fly
Row device also still suffers from biggish aerodynamic loading in flight course, and current design is all largely air-cooled structure design, does not have
By thermal protection struc ture and bearing structure comprehensive design, the quality of flight vehicle aerodynamic rudder thermal protection structure is considerably increased in this way, is reduced
The aerodynamic characteristic and operability of aircraft.
The embodiment of the present invention devises a kind of pneumatic integrated thermal protection structure of rudder leading edge of hypersonic aircraft, will be high
The heat sink of heat sink material is matched with heat pipe, and leading edge heat flow density that this thermal protection structure is arranged in pneumatic rudder is big
Place can effectively improve pneumatic rudder leading edge thermal protection effect, reduce the ablation of edge and because of Aerodynamic Heating bring shape
Variation, solves the problems, such as the thermal protection of pneumatic rudder sharp leading edge, for the pneumatic rudder leading edge of the following high lift-drag ratio hypersonic aircraft
Anti- thermal design provides a kind of new approaches and method.
The present invention will be further explained below with reference to the attached drawings.A specific embodiment of the invention to protection of the invention not
It provides constraints.Protection scope of the present invention is subject to the claims.
The embodiment of the present invention provides a kind of pneumatic rudder of hypersonic aircraft up-front integrated thermal protection structure, such as Fig. 1
Shown, the thermal protection structure 3 is the integrated design, comprising: solar heat protection covering 30, heat pipe 31, heat sink 32 and thermal insulation layer 33,
The solar heat protection covering 30 is set to pneumatic rudder leading edge outer surface, and heat sink 32 is set to the inner surface of solar heat protection covering 30, heat pipe
31 are fixedly connected with heat sink 32, and the heat pipe 31 is set to the inner surface of heat sink 32, and thermal insulation layer 33 is fixedly installed
In the inner surface of heat pipe 31.
The pneumatic rudder leading edge of hypersonic aircraft generates a large amount of Aerodynamic Heating in flight course, is that solar heat protection is covered first
Skin 1 radiates certain heat, carries out the solar heat protection of the first step, the high heat sink heat absorption being then just mounted in inside solar heat protection covering 1
Device 3 absorbs the heat of pneumatic rudder skins front edges, and by the high temperature at the big sharp leading edge of heat flow density toward pneumatic rudder two sides
It is dredged at low temperature, avoids the temperature of the part of pneumatic rudder edge excessively high, be finally just mounted in the heat of 3 inner surface of heat sink
Pipe 2 is exchanged with 3 row heat of heat sink, is reduced by 3 heat of heat sink, is enabled heat sink 3 constantly from pneumatic
Rudder leading edge absorbs and dredges heat.There are also thermal insulation layers 4 for most the inside, can be every living external Aerodynamic Heating, so that inside pneumatic rudder
Temperature is normal, and internal instrument and equipment can normally work.
First protection of the solar heat protection covering as thermal protection struc ture, can radiate the heat of a part；By heat sink 3 and heat
Pipe 2 matches, and the second as thermal protection protects.The leading edge heat flow density that this thermal protection structure is arranged in pneumatic rudder is big
Place, can effectively improve pneumatic rudder leading edge thermal protection effect, reduce edge ablation and because of Aerodynamic Heating bring outside
Deformation solves the problems, such as the thermal protection of pneumatic rudder sharp leading edge, makes the small and heat flow density of the up-front deformation of flight vehicle aerodynamic rudder
It is small, the aerodynamic characteristic of aircraft high lift-drag ratio and the operability of pneumatic rudder are kept, it is big to solve flight vehicle aerodynamic rudder leading edge hot-fluid
Bring material failure problem and flying speed lead to the problem for bearing aerodynamic loading ability difference fastly, avoid pneumatic rudder leading edge temperature
The extreme distribution of degree, it is heat-insulated for a long time to realize aircraft.
Preferably, the solar heat protection covering 30 is fabricated by heat insulation material, solar heat protection covering 30 with a thickness of 8-10mm, prevent
The too thick quality that will increase flight vehicle aerodynamic rudder of hot covering, reduces the operability of aircraft, and solar heat protection covering on the contrary is excessively thin to be reduced
The bearing capacity of flight vehicle aerodynamic rudder increases the up-front heat distortion amount of flight vehicle aerodynamic rudder, sets 8-10mm for solar heat protection covering
It can overcome too thick and too thin defect solar heat protection covering can be using resistance to ablation and the heat insulation material of lightweight, such as: solar heat protection covering
Outer layer enhancing C/C, SiC/SiC, C/SiC or ceramic matric composite can be used, these materials have high thermal stability,
Chemical inertness, heat resistanceheat resistant vibration, high-intensitive and low-gravity feature, and internal layer internal layer uses porous bulk material, specific stiffness is big, can
To resist thermal stress caused by outer layer dense surface layer is sharply increased as temperature, entire thermal protection system or even entire gas are kept
Dynamic shape relatively high stability under the high temperature conditions.
Preferably, the shape of the heat pipe 31 is triangle, and the triangle of heat pipe is two rows arranged opposite.Heat pipe
Wall surface is fabricated by high heat sink material, and such as: metallic copper, Cu-base composites and graphene are mainly characterized in that thermal conductivity
Rate is high, can absorb certain heat.
Refer to Fig. 2, the shape of heat pipe 31 is triangle, two rows arranged opposite, and such design greatly increases heat
The heat exchange efficiency of pipe, and since the shape of heat pipe is triangle, the bearing capacity and stability of pneumatic rudder can be enhanced, so that
Pneumatic rudder is able to bear more aerodynamic loadings, and thermal protection struc ture and bearing structure are combined design, reduce pneumatic rudder thermal protection
The quality of structure.
Preferably, heat sink 32 with a thickness of 5mm or more, and the thickness of heat sink 32 is along close to pneumatic rudder leading edge side
To being gradually increased.The material of heat sink is that high heat sink material can be absorbed a part of heat on solar heat protection covering, and due to
The heat flow density of flight vehicle aerodynamic rudder leading edge sharp parts is larger, therefore close to edge, and the thickness of heat sink should be compared with
Greatly a bit, enable heat sink to absorb more heats and up-front heat is dredged to the two sides of pneumatic rudder, reduce gas
The dynamic up-front heat flow density of rudder.And, thickness biggish heat sink also maximum in the aerodynamic loading that the sharp place of leading edge is born
It is fixed thereto, the rigidity that leading edge is sharply located can be enhanced, reduce the up-front deflection of pneumatic rudder.
Preferably, the heat-absorbing material that the heat sink 32 can be heat sink using height, such as: Cu-base composites and stone
Black alkene.The metal foil that heat sink of the embodiment of the present invention 32 is matched using the solar heat protection covering 30 with flight vehicle aerodynamic rudder outer surface
Plate, and heat sink is fixedly mounted on the inner surface of solar heat protection covering 30.Heat sink can be absorbed and dredge pneumatic rudder leading edge
Heat, the heat that can sharply locate to avoid leading edge excessively concentrates, and causes leading edge ablation and heat distortion amount big.
Preferably, thermal insulation layer 33 is fabricated by heat-barrier material, for remaining by above-mentioned thermal protection structure every living
Heat guarantees the normal work of pneumatic rudder interior instrument equipment.
Another embodiment of the present invention provides a kind of coolant circulating systems, including coolant reservoir 1；Coolant delivery pump
2, heat-exchanger rig 4 and any one thermal protection structure 3 described above；
The coolant delivery pump 2 is mounted on aircraft on the end frame of pneumatic rudder, and heat-exchanger rig 4 is mounted on fuel
At output channel, the leading edge that flight vehicle aerodynamic rudder is arranged in thermal protection structure 3 is sharply located；
The coolant reservoir 1 is connected with the coolant delivery pump 2, the coolant delivery pump 2 and thermal protection knot
Structure 3 is connected, and the thermal protection structure 3 is connected with heat-exchanger rig 4, and the heat-exchanger rig 4 is connected with coolant reservoir 1, described
Coolant reservoir 1, coolant delivery pump 2, thermal protection structure 3 and heat-exchanger rig 4 mutually form coolant circulating system, institute
Coolant delivery pump is stated coolant to be delivered in heat pipe, so that the coolant in heat pipe and heat sink carry out heat friendship
It changes, to keep heat sink cooling.
Fig. 3 is referred to, the circulatory system of coolant includes coolant reservoir 1, coolant delivery pump 2, heat pipe 3 and heat exchange
Device 4.When heat sink reaches certain temperature, (mounting temperature sensor, temperature can be by artificially setting in heat sink
The temperature set, but be artificially arranged will be more than certain temperature by the temperature limiting of solar heat protection skin material, the temperature of solar heat protection covering,
It will be oxidized or ablation, therefore temperature should be lower than the limit temperature of solar heat protection covering, the general solar heat protection covering of C/C material exist
500-600 can be aoxidized when spending, so the temperature of setting is 800k), coolant delivery pump 2 starts from coolant reservoir 1 to heat
Coolant is conveyed in pipe 31, the coolant in heat pipe carries out heat with heat sink and exchanges, and to reduce the temperature of heat sink, makes
Obtaining heat sink can continue working, and the coolant after heat exchange becomes high temperature coolant, high temperature cold-zone by cryogenic coolant
Between continue through pipeline to heat-exchanger rig, in heat-exchanger rig, low temp fuel exchanges heat with high temperature coolant, after heat exchange
Fuel high-temperature fuel is become by low temp fuel, and the agent of high temperature cold-zone becomes cryogenic coolant, then by pipeline by low temperature cold-zone
Between be delivered to coolant reservoir, then cryogenic coolant is delivered to by heat pipe by coolant delivery pump and heat sink carries out heat
Amount exchange, to realize the circulation of coolant.In Fig. 3, low temp fuel from fuel inlet 5 enter heat-exchanger rig 4, by with it is cold
But after agent heat exchange, the high-temperature fuel after heat exchange is discharged through fuel outlet 6, and the high-temperature fuel after heat exchange is through 6 row of fuel outlet
After out, into burning in the combustion chamber inside aircraft engine, thrust is provided for aircraft.Coolant can select liquid
The helium of state, because hydraulic helium temperature is low, exchange capability of heat is strong, and physicochemical properties are stablized, and is not susceptible to safety accident.With
High temperature helium after heat sink exchanges heat enters heat-exchanger rig 4, and the helium of high temperature carries out heat with the fuel of low temperature and exchanges, most
Cooling helium is transported in coolant reservoir 1 afterwards, to constitute coolant circulating system.The combustion of the embodiment of the present invention
The fuel that material can use aircraft self-contained.Fig. 4-6 is the schematic diagram of heat-exchanger rig, the heat-exchanger rig, to make high temperature
The fuel of helium and low temperature carry out heat and exchange.Its working principle is that: the fuel of low temperature enters heat-exchanger rig, passes through one section of spiral shell
The pipeline (helical pipe is as shown in Figure 4) of rotation, is passed through the helium of high temperature in the pipeline of spiral, and fuel and helium flowing
Contrary, the flow direction of fuel is left (as shown in Figure 5) from right direction, and helium flows from left to right in helical pipe, so that low
The helium of warm fuel and high temperature in helical pipe comes into full contact with, and the fuel of low temperature can carry out heat with the helium of high temperature and exchange, cold
But the helium of high temperature greatly improves the cooling efficiency of coolant so that helium can continue to exchange with heat sink progress heat.
Helical pipe can make its heat transfer effect more preferable, it is to be understood that the pipeline in heat-exchanger rig of the embodiment of the present invention is not limited to
Helical pipe.
Another embodiment of the present invention provides a kind of hypersonic aircraft, including coolant circulation system described above
System.
Claims (8)
1. a kind of up-front integrated thermal protection structure of pneumatic rudder of hypersonic aircraft, which is characterized in that the thermal protection knot
Structure is the integrated design, comprising: solar heat protection covering (30), heat pipe (31), heat sink (32) and thermal insulation layer (33), the solar heat protection are covered
Skin (30) is set to pneumatic rudder leading edge outer surface, and heat sink (32) is set to the inner surface of solar heat protection covering (30), heat pipe (31)
It is fixedly connected with heat sink (32), and the heat pipe (31) is set to the inner surface of heat sink (32), and thermal insulation layer (33) is solid
Surely it is set to the inner surface of heat pipe (31).
2. thermal protection structure according to claim 1, which is characterized in that the solar heat protection covering (30) is by heat insulation material system
Make, solar heat protection covering (30) with a thickness of 8-10mm.
3. thermal protection structure according to claim 1, which is characterized in that the shape of the heat pipe (31) is triangle, heat
The triangle for managing (31) is two rows arranged opposite.
4. thermal protection structure according to claim 1, which is characterized in that heat sink (32) with a thickness of 5mm or more, and
The thickness of heat sink (32) is gradually increased along close to pneumatic rudder leading edge direction.
5. thermal protection structure according to claim 1, which is characterized in that the heat sink (32) be and aircraft gas
The sheet metal that the solar heat protection covering (30) of dynamic rudder outer surface matches, and heat sink is fixedly mounted on solar heat protection covering (30)
Inner surface.
6. a kind of coolant circulating system, which is characterized in that including coolant reservoir (1)；Coolant delivery pump (2), heat exchange
Thermal protection structure (3) described in device (4) and claim 1-5 any one；
The coolant delivery pump (2) is mounted on aircraft on the end frame of pneumatic rudder, and heat-exchanger rig (4) is mounted on fuel
At output channel, the leading edge of flight vehicle aerodynamic rudder is arranged in thermal protection structure (3)；
The coolant reservoir (1) is connected with the coolant delivery pump (2), the coolant delivery pump (2) and thermal protection
Structure (3) is connected, and the thermal protection structure (3) is connected with heat-exchanger rig (4), the heat-exchanger rig (4) and coolant reservoir
(1) it is connected, the coolant reservoir (1), coolant delivery pump (2), thermal protection structure (3) and heat-exchanger rig (4) are mutual
Form coolant circulating system.
7. a kind of hypersonic aircraft, including any thermal protection structure of claim 1-5, the thermal protection structure is set
Set the leading edge in flight vehicle aerodynamic rudder.
8. a kind of hypersonic aircraft, including coolant circulating system as claimed in claim 6.
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| CN110524974A (en) * | 2019-09-30 | 2019-12-03 | 湖北航天技术研究院总体设计所 | A kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape |
| CN110553554A (en) * | 2019-09-03 | 2019-12-10 | 中国空空导弹研究院 | Light thermal protection structure for hypersonic missile |
| EP3750810A1 (en) * | 2019-06-14 | 2020-12-16 | Rosemount Aerospace Inc. | Friction energy savers |
| CN112193402A (en) * | 2020-09-16 | 2021-01-08 | 北京宇航系统工程研究所 | Constant-temperature heat shield structure capable of being stored for long time |
| CN113306697A (en) * | 2021-07-08 | 2021-08-27 | 南京航空航天大学 | Novel hypersonic aircraft wing |
| CN113619769A (en) * | 2021-07-28 | 2021-11-09 | 哈尔滨工业大学 | Reusable heat protection structure combining phase change heat absorption and decomposition heat absorption of aircraft |
| CN113978046A (en) * | 2021-11-09 | 2022-01-28 | 厦门大学 | Thermal protection structure and preparation method thereof |
| CN117429629A (en) * | 2023-12-21 | 2024-01-23 | 中国人民解放军国防科技大学 | Infrared optical type heat protection auxiliary heat radiation device for hypersonic aircraft |
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