CN103192978A - Laminate type sweating and reverse-jetting combined cooling nose cone - Google Patents
Laminate type sweating and reverse-jetting combined cooling nose cone Download PDFInfo
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- CN103192978A CN103192978A CN2013101122957A CN201310112295A CN103192978A CN 103192978 A CN103192978 A CN 103192978A CN 2013101122957 A CN2013101122957 A CN 2013101122957A CN 201310112295 A CN201310112295 A CN 201310112295A CN 103192978 A CN103192978 A CN 103192978A
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Abstract
The invention relates to a laminate type sweating and reverse-jetting combined cooling nose cone of an aircraft. A spherical-conic laminate stacking body is arranged at the top of a circular base frame, and is formed by coaxially stacking a plurality of circular sweating laminates, the radiuses of which are sequentially reduced along the increase of height; a base frame channel is formed in the center of the circular base frame, and a cooling medium is charged in the spherical-conic laminate stacking body through the base frame channel; the center of the circular base frame is provided with a fixing rod which passes through the base frame channel and the spherical-conic laminate stacking body, and the top of the fixing rod is in a circular arc shape and covers the top of the spherical-conic laminate stacking body; and a jetting pipe for charging the cooling medium and a cooling medium flowing inlet are arranged in the fixing rod. The laminate type sweating and reverse-jetting combined cooling nose cone disclosed by the invention realizes a heat resistance design by a manner of combining a laminate type sweating and cooling structure and a reverse-jetting manner so that the thermal protection of a non-stationary point area and the thermal protection of a stationary point area of the head of the hypersonic aircraft can be realized, and the nose cone has the characteristics of small required refrigerant amount, large heat radiation strength and high reliability.
Description
Technical field
The present invention relates to a kind of active temperature barrier that cools off for hypersonic aircraft nose cone and forward position device, be specially the sweating of a kind of aircraft laminated board type and contrary spray combination nose cone.
Background technology
Thermal protection technology is the gordian technique of hypersonic aircraft research.Hypersonic aircraft nose cone and forward position device without any the situation underlaying surface temperature of thermal protection system protection up to 2000～3000 degrees centigrade.Under so high temperature for hypersonic aircraft nose cone and forward position device are not burnt, nose cone and forward position device contour structures are kept perfectly, keep in the hypersonic aircraft cabin normal service conditions being arranged, must adopt thermal protection mode passive or active that it is carried out thermal protection.The thermal protection mode that existing hypersonic aircraft nose cone and forward position device adopt mainly contains ablative thermal protection, sweating cooling solar heat protection.Ablative thermal protection is a kind of solar heat protection form important in the nonrecoverable spacecraft thermal protection structure, belongs to half passive heat control technology.The principle of ablative thermal protection is: ablative material produces series of physical and chemical reaction in heating environment, in these physics and chemical process, consumed ablative material on the one hand, on the other hand also by different way dissipation condition give the heat of material, work under allowable temperature to guarantee inner structure.
Sweating cooling solar heat protection is divided into self start type, compulsory type, self-adapting type and laminated board type sweating according to " disengaging " mode of cooling system conditioner in the nose cone again.Be low-melting-point metal (as copper and silver etc.) to be infiltrated in the stephanoporate framework of refractory material (as tungsten etc.) from the sweating nose cone.When nose cone is subjected to pneumatic heating, come solar heat protection by low-melting-point metal fusing and evaporation.Forcing the sweating nose cone is that fluidised form cooling system conditioner (as water, ammonia, helium etc.) is stored among the container in advance, when needing sweating, utilizes pressure source (high-pressure gas bottle or gas generator etc.) that cooling system conditioner is extruded into porous nose cone surface and finishes solar heat protection.Self adaptation sweating cooling solar heat protection is to adopt loose porous material as shell bulb part, make the thin-wall shell of sweating nose cone with refractory metal (as tungsten alloy), the high volumetric heat capacity solid coolant of high density and high-vapor-pressure solid or liquid driven agent are carried in inside.The principle of self adaptation sweating cooling solar heat protection is: in hypersonic flight course, owing to the pneumatic heating of nose cone and forward position device and the heat transfer by shell are made the cooling system conditioner fusing, the carminative evaporation.Liquid coolant flows on the nose cone surface by skeleton porous or that have passage under the pressure effect of carminative.When cooling system conditioner evaporates, seethes with excitement, just absorbs when absorbing heat heat in the gas boundary-layer, thereby realize solar heat protection to skeleton and closely knit shell.
Research shows with practice, can play thermal protection effect preferably under the situation that above-mentioned thermal protection mode is not too big in aircraft flight speed and the flight time is relatively shorter.But along with the increase of aircraft flight speed and flight time, above thermal protection mode application limit is just apparent in view.Ablative thermal protection is because the sacrificial section surface material, and makes contour structures be difficult to be kept perfectly., reduce otherwise the intensity meeting is obvious because the diaphoretic volume that this structure can be stored is limited, and bone porous porosity can not be very desirable from sweating cooling solar heat protection; Might can not send out " sweat " when stagnation pressure is higher; Also there is the problem by thermal stress-cracking.Force sweating cooling thermal protection structure complexity, reliability is low, and in addition, weight and volume (especially volume) all is the outstanding shortcoming of this form.The quality that cooling system conditioner and carminative have increased aircraft oneself is carried in self adaptation sweating cooling solar heat protection owing to need, design difficulty is bigger, and alternative cooling system conditioner almost only limits to low-melting-point metal, and all low-melting-point metals all are easy to discharge electronics when high temperature, and this may make communication " black barrier " problem worse.
Summary of the invention
The objective of the invention is to, at the deficiencies in the prior art, provide a kind of laminated board type sweating and contrary spray combination cooling nose cone, realize the thermal protection of the non-stagnation region of hypersonic aircraft head and the thermal protection of stagnation region, the cooling working medium that needs is few, and specific heat load is big, the reliability height.
Technical scheme of the present invention is, a kind of laminated board type sweating and contrary spray combination cooling nose cone, comprise circular base frame, described circular base countertop is provided with ball taper laminate and builds up body, this ball taper laminate build up body by a plurality of with highly increasing coaxial being formed by stacking of circular sweating laminate that radius reduces successively; The center of described circular base frame is established oriented sphere taper laminate and is built up the base frame passage that body feeds cooling working medium, and being provided with that fixed link passes the base frame passage and ball taper laminate builds up body, the top of fixed link is that the main header casing of circular-arc and this fixed link builds up the body top at ball taper laminate; Be provided with the jet pipe and the cooling working medium that feed cooling working medium in the described fixed link and flow into entrance.
Described ball taper laminate builds up body and is formed by stacking by first laminate and second laminate are staggered, described first laminate is provided with the control runner along radial direction, be provided with the distribution runner with the control runner along the first corresponding laminate excircle of the first laminate radial direction, and respectively scatter and leave the interval between runner and the corresponding control runner; Described second laminate is provided with fluid collection chamber, and fluid collection chamber is located between the corresponding control with it of the distribution runner runner of adjacent first laminate.
General mechanical micropore and aerated materials are when the situation of local overheating appears in heating surface, because the increase of the resistance to flow of the sweating cooling working medium at sweating position, sweating working medium sweating flow herein will reduce, and occur expansion and the deterioration at local overheating place then; But this structure is owing to control the resistance to flow of runner much larger than the resistance to flow of distribution runner, so when the situation of local overheating appears in the nose cone surface, because the cooling of the liquid in the fluid collection chamber, make that the temperature rise of scattering cooling working medium in the runner is less, thereby the resistance to flow that increases in scattering runner can be ignored with respect to the flow passage resistance force of waterproof in the control runner, thereby it is constant substantially through the flow passage resistance force of waterproof that scatters runner arrival nose cone surface again to make that cooling working medium flows into fluid collection chamber from the control runner, thereby makes such laminate nose cone can contain expansion and the deterioration of local overheating.
The sectional area of described fluid collection chamber from inside to outside increases successively along the radial direction of second laminate.
The cross section of described fluid collection chamber is equicrural triangle, and the drift angle of equicrural triangle near the control runner of adjacent first laminate and the base of equicrural triangle near corresponding distribution runner.
The thickness of described first laminate is 0.1～1mm.
The thickness of described second laminate is 0.1～1mm.
During work, cooling working medium flows into ball taper laminate respectively from the bottom of base frame passage and jet pipe and builds up body and jet pipe.The cooling working medium that inflow ball taper laminate builds up body is through first laminate and second laminate, and final cooling working medium arrives at the distribution runner of the first sweating laminate, forms the thermal protection function to nose cone.The cooling working medium that flows into jet pipe flows out through accelerating the back, forms reverse spray, to the stagnation region of nose cone and near carry out thermal protection.The distribution flow diameter is 0.5～3mm.Above-mentioned each fluid outlet all makes fluid accelerate through design, and particularly reverse spout place fluid is with ejection at a high speed.The fluid of ejection evaporates in high velocity air, seethes with excitement and absorbs heat, thereby reaches thermo-lag purpose.The jet flow of reverse jet pipe can reduce pneumatic heating, thereby makes the stagnation region of serious heating reach thermo-lag purpose.
The present invention is with the liquid-propellant rocket engine gas generator, platelet injector, the laminated board type fluid mixer, laminate is that the latest Progress of high speed ship thruster and the staggered sweating spray of laminate is background, a kind of laminated board type sweating cooling nose cone of novel pneumatic layout is proposed, sweating cooling nose cone different from the past utilizes aerated materials to carry out sweating and is subjected to various limitations, but utilize the self-contained fuel of aircraft as cooling system conditioner, produce the high speed jet air-flow of multilayered state by the distributed slit jet pipe of veneer structure, the good runner configuration that utilizes the laminate self structure to have, the fluid that solves various complexity flows to problem, accurate shunting characteristics can make coolant flow different and different with the resistance to flow in the laminate sheet in the laminate, guarantee in different cooling requirement place of wall, ensure strong the stablizing of generating surface sweating stream, overcome the defective that local overheating may appear in general aerated materials sweating cooling structure, reached the reusable purpose of heating part.
The invention has the beneficial effects as follows, the mode that this nose cone adopts laminated board type sweating cooling structure and reverse jet flow to combine is prevented thermal design, can realize the thermal protection of the non-stagnation region of hypersonic aircraft head and the thermal protection of stagnation region, it is little to have the amount of coolant that needs again, specific heat load is big, the characteristic that reliability is high, last this nose cone can realize that reusable purpose for the design of the reusable aircraft of the next generation provides a kind of outstanding effects such as solar heat protection design, is a kind of high efficiency, high reliability, the novel hypersonic thermal protection system of high practicability.
Description of drawings
Fig. 1 is first block diagram of cooling nose cone of the present invention;
Fig. 2 is second block diagram of cooling nose cone of the present invention;
Fig. 3 is the structural representation of first laminate;
Fig. 4 is the structural representation of second laminate;
Fig. 5 is the structural representation of first laminate and the stack of second laminate;
Fig. 6 is the scheme drawing of fixed link.
The specific embodiment
As Fig. 1, Fig. 2, shown in Figure 6, a kind of laminated board type sweating cooling nose cone, comprise circular base frame 1, circular base frame 1 end face is provided with ball taper laminate and builds up body, this ball taper laminate build up body by a plurality of with highly increasing circular sweating laminate 2,3 coaxial being formed by stacking that radius reduces successively; The center of circular base frame 1 is established oriented sphere taper laminate and is built up the base frame passage 7 that body feeds cooling working medium, and being provided with that fixed link 4 passes base frame passage 7 and ball taper laminate builds up body, the top of fixed link is that the main header casing of circular-arc and this fixed link builds up the body top at ball taper laminate; Be provided with the jet pipe 5 and the cooling working medium that feed cooling working medium in the fixed link 4 and flow into entrance 8.
As shown in Figure 3-Figure 5, ball taper laminate builds up body by first laminate 2 and second laminate, 3 staggered being formed by stacking, first laminate 2 is provided with control runner 9 along radial direction, be provided with along corresponding first laminate, 2 excircles of first laminate, 2 radial directions with control runner 9 and scatter runner 6, and respectively scatter between runner 6 and the corresponding control runner 9 and leave the interval; Described second laminate is provided with fluid collection chamber 10, and fluid collection chamber 10 is located between the corresponding control with it of distribution runner 6 runner 9 of adjacent first laminate.
The cross section of fluid collection chamber 10 is equicrural triangle, and the drift angle of equicrural triangle near the control runner 9 of adjacent first laminate 2 and the base of equicrural triangle near corresponding distribution runner 6.
The thickness of first laminate 2 is 0.1～1mm, and the thickness of second laminate 3 is 0.1～1mm.
Base frame and fixed link adopt heat-resistance stainless steel tubing, between each parts by the diffusion welding welding forming.
Claims (6)
1. nose cone is cooled off in a laminated board type sweating and contrary spray combination, comprise circular base frame (1), it is characterized in that, described circular base frame (1) end face is provided with ball taper laminate and builds up body, this ball taper laminate build up body by a plurality of with highly increasing coaxial being formed by stacking of circular sweating laminate (2,3) that radius reduces successively; The center of described circular base frame (1) is established oriented sphere taper laminate and is built up the base frame passage (7) that body feeds cooling working medium, and being provided with that fixed link (4) passes base frame passage (7) and ball taper laminate builds up body, the top of fixed link is that the main header casing of circular-arc and this fixed link builds up the body top at ball taper laminate; Be provided with the jet pipe (5) and the cooling working medium that feed cooling working medium in the described fixed link (4) and flow into entrance (8).
2. according to the described laminated board type sweating of claim 1 and contrary spray combination cooling nose cone, it is characterized in that, described ball taper laminate builds up body and is formed by stacking by first laminate (2) and second laminate (3) are staggered, described first laminate (2) is provided with control runner (9) along radial direction, be provided with along corresponding first laminate (2) excircle of first laminate (2) radial direction with control runner (9) and scatter runner (6), and respectively scatter between runner (6) and the corresponding control runner (9) and leave the interval; Described second laminate is provided with fluid collection chamber (10), and fluid collection chamber (10) is located between distribution runner (6) runner of corresponding control with it (9) of adjacent first laminate.
3. according to the described laminated board type sweating of claim 2 and contrary spray combination cooling nose cone, it is characterized in that the sectional area of described fluid collection chamber (10) from inside to outside increases successively along the radial direction of second laminate (3).
4. according to the described laminated board type sweating of claim 3 and contrary spray combination cooling nose cone, it is characterized in that, the cross section of described fluid collection chamber (10) is equicrural triangle, and the drift angle of equicrural triangle near the control runner (9) of adjacent first laminate (2) and the base of equicrural triangle near corresponding distribution runner (6).
5. according to the described laminated board type sweating of claim 2 and contrary spray combination cooling nose cone, it is characterized in that the thickness of described first laminate (2) is 0.1～1mm.
6. according to the described laminated board type sweating of claim 2 and contrary spray combination cooling nose cone, it is characterized in that the thickness of described second laminate (3) is 0.1～1mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201310112295.7A CN103192978B (en) | 2013-04-02 | 2013-04-02 | Laminate type sweating and reverse-jetting combined cooling nose cone |
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| CN201310112295.7A CN103192978B (en) | 2013-04-02 | 2013-04-02 | Laminate type sweating and reverse-jetting combined cooling nose cone |
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| CN103192978A true CN103192978A (en) | 2013-07-10 |
| CN103192978B CN103192978B (en) | 2015-04-15 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103662094A (en) * | 2014-01-03 | 2014-03-26 | 中国人民解放军国防科学技术大学 | Inlaid type laminate side-spraying nose cone |
| CN103723269A (en) * | 2013-09-11 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Thermal protection structure |
| CN104859835A (en) * | 2015-04-27 | 2015-08-26 | 清华大学 | Hypersonic aircraft head cone based on composite cooling mode |
| CN107719630A (en) * | 2017-09-25 | 2018-02-23 | 中国人民解放军国防科技大学 | Laminate type gas sweating nose cone |
| CN106516072B (en) * | 2016-11-10 | 2018-06-29 | 清华大学 | A kind of thermal protection structure at the leading edge position of hypersonic vehicle |
| CN109334974A (en) * | 2018-10-29 | 2019-02-15 | 北京临近空间飞行器系统工程研究所 | A kind of flow control type impact Sweat coolling nose cone |
| CN109812352A (en) * | 2019-03-06 | 2019-05-28 | 中南大学 | Rocket ejector and its thermal protection structure and thermal protection method |
| CN113588199A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Reverse jet flow blockage degree test device and test method for hypersonic wind tunnel |
| CN113911315A (en) * | 2021-12-14 | 2022-01-11 | 清华大学 | Aircraft nose cone cooling structure |
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Patent Citations (5)
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| US20040245389A1 (en) * | 2003-06-05 | 2004-12-09 | Behrens William W. | Cooled insulation surface temperature control system |
| CN2744599Y (en) * | 2004-07-27 | 2005-12-07 | 南京师范大学 | Heat protection device for pneumatic heating heated-surface of superhigh speed aircraft |
| US20080290218A1 (en) * | 2007-05-25 | 2008-11-27 | Schwimley Scott L | Plasma actuator system and method for use with a weapons bay on a high speed mobile platform |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103723269A (en) * | 2013-09-11 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Thermal protection structure |
| CN103723269B (en) * | 2013-09-11 | 2018-01-30 | 太仓派欧技术咨询服务有限公司 | A kind of thermal protection structure |
| CN103662094A (en) * | 2014-01-03 | 2014-03-26 | 中国人民解放军国防科学技术大学 | Inlaid type laminate side-spraying nose cone |
| CN104859835A (en) * | 2015-04-27 | 2015-08-26 | 清华大学 | Hypersonic aircraft head cone based on composite cooling mode |
| CN106516072B (en) * | 2016-11-10 | 2018-06-29 | 清华大学 | A kind of thermal protection structure at the leading edge position of hypersonic vehicle |
| CN107719630A (en) * | 2017-09-25 | 2018-02-23 | 中国人民解放军国防科技大学 | Laminate type gas sweating nose cone |
| CN107719630B (en) * | 2017-09-25 | 2019-08-16 | 中国人民解放军国防科技大学 | Laminate type gas sweating nose cone |
| CN109334974A (en) * | 2018-10-29 | 2019-02-15 | 北京临近空间飞行器系统工程研究所 | A kind of flow control type impact Sweat coolling nose cone |
| CN109334974B (en) * | 2018-10-29 | 2020-09-18 | 北京临近空间飞行器系统工程研究所 | Flow control type impact sweating cooling nose cone |
| CN109812352A (en) * | 2019-03-06 | 2019-05-28 | 中南大学 | Rocket ejector and its thermal protection structure and thermal protection method |
| CN113588199A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Reverse jet flow blockage degree test device and test method for hypersonic wind tunnel |
| CN113911315A (en) * | 2021-12-14 | 2022-01-11 | 清华大学 | Aircraft nose cone cooling structure |
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