CN104373296A - Novel hypersonic missile outer-layer wind turbine blade heat preventing and cooling technology - Google Patents
Novel hypersonic missile outer-layer wind turbine blade heat preventing and cooling technology Download PDFInfo
- Publication number
- CN104373296A CN104373296A CN201410526272.5A CN201410526272A CN104373296A CN 104373296 A CN104373296 A CN 104373296A CN 201410526272 A CN201410526272 A CN 201410526272A CN 104373296 A CN104373296 A CN 104373296A
- Authority
- CN
- China
- Prior art keywords
- missile
- blade
- guided missile
- wind wheel
- cooling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/34—Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
Abstract
The invention provides a novel aircraft and missile wind turbine blade heat preventing and cooling technology, and particularly relates to a novel hypersonic missile outer-layer wind turbine blade heat preventing and cooling technology. Wind turbine blades are arranged on the outer layer of a hypersonic missile, high-speed airflow is converted into acting kinetic energy, the high-speed airflow blows the blades to move, the blades drive wind turbines to rotate, the blades rotate at high speed to blow cold air to the outer layer of the missile, the cold air blows to the outer layer of the missile for cooling, meanwhile, hot air emitted by the missile is blown out to be exhausted to the rear portion of the missile, no shock wave or viscous friction is generated by the outer layer of the missile any more, and no pneumatic heating or thermal barrier is generated any more. No infrared radiation is generated, no directional echoes are generated, and an American antimissile system and a radar cannot carry out infrared tracking imaging. The pneumatic heating problem of the hypersonic missile of six times to 23 times is solved through the technology, and the technology can be suitable for various hypersonic aircrafts.
Description
Technical field
This technology relates to the kinetic energy that high velocity air is changed into work done by the outer wind wheel blade installed of a kind of hypersonic missile, blows fan cold wind and reduces guided missile temperature, the solar heat protection cooling new technology of fan-out guided missile hot gas.
Background technique
The difficult problem run in hypersonic aircraft R&D process is Aerodynamic Heating problem, namely so-called
thermal boundary.Overcoming the main means of thermal boundary is carry out thermal protection to aircraft, and thermo-lag method divides by solar heat protection mechanism to be had: heat sink solar heat protection; Radiative thermal protection; Sweat coolling solar heat protection and ablative heat protection.
Heat sink solar heat protection mainly utilizes the thermal capacity of material to absorb heat.Any material has thermal capacity, but first will go large specific heat, and the material of such unit mass could absorb more heat; It is secondary high heat conductivity, wants to absorb a large amount of heat, just must roll up the quality of heat sink material, form heavier heat-protection system.
Radiative thermal protection mainly utilizes the radiation characteristic of material.Exactly the Aerodynamic Heating on its surface is distributed in the form of radiation again.Because radiant heat flux is directly proportional to the biquadratic of surface temperature, therefore, the radiative thermal protection material selected not only will have outside high radiation character, but also must have low heat conductivity and high-temperature stability.
Sweat coolling solar heat protection is by reaching the object of solar heat protection from porous surface exuded fluid.The main mechanism by thermal chokes effect or quality injection effect carrys out solar heat protection.
Film cooling solar heat protection relies on aperture ejection liquid or the gas of aircraft surface, the very thin liquid film of one deck or air film is formed on surface, aircraft surface and high-temperature gas are separated, then liquid evaporation endothermic, gas inject boundary layer, produce thermal chokes effect, reduce the heat transfer by convection entering aircraft.
Ablative heat protection is outer by burning-off, reaches the object of protection internal layer.Now research and develop multiple ablative material, selected for the aircraft of different purposes or the different parts of aircraft.Ablative heat protection applies a kind of the most successful method in current hypersonic aircraft thermal protection.The major defect of ablative heat protection is single use and the aerodynamic configuration change due to ablation generation.The latter, will affect stability, the impact accuracy of Reentry vehicle and reenter maneuvering flight, and cruise vehicle rise resistance, stability and control.
These technology all cannot solve 6 to 23 times of hypersonic aircraft Aerodynamic Heating problems.
Summary of the invention
This technology provides the wind wheel blade solar heat protection cooling new technology of a kind of hypersonic vehicle and guided missile.And it is outer at hypersonic missile, wind wheel blade is installed, high velocity air is changed into the kinetic energy of work done, high velocity air blows blade movement, and blade drives wind wheel to rotate, and blade high speed rotating fan cold wind blows guided missile skin, to blow a cold wind over cooling to guided missile skin, the hot gas fan-out simultaneously given out by guided missile is discharged to guided missile rear, and guided missile skin no longer produces shock wave and viscous friction, no longer produces Aerodynamic Heating and thermal boundary.Also do not produce infrared radiation, do not produce directed echo, U.S.'s anti-missile system and radar cannot infrared track imagings.This technology solves 6 times of Aerodynamic Heating problems to 23 times of hypersonic missiles, and is applicable to various sonic flight device.
Accompanying drawing explanation
Fig. 1: the wind wheel frame schematic diagram of this technology.
The schematic rear view of Fig. 2: Fig. 1 wind wheel frame.
Fig. 3: the wind wheel blade schematic diagram of this technology.
Schematic diagram is looked on a wind wheel blade left side of Fig. 4: this technology Fig. 3.
Embodiment;
In figure, 1 blade, 2 wind wheels, 3 wheel carriers, 4 wheel shafts, 5 bullets, 6 Missile Bodies, 7 outer blade diameter, 8 take turns lattice.
1 blade, oblique angle is fixed on the cylindrical body of 2 wind wheels, meets high velocity air and impacts rotation.2 wind wheels, by cylindrical shell, 4 wheel shafts are formed, and above have 1 blade, diameter several centimeters, Tong Ti Long degree N centimetre, and load 8 and take turns in lattice, blade rotates work done windward, blow the cooling of fan cold wind, discharge the hot gas that guided missile sheds to guided missile skin.3 wheel carriers, are fixed on guided missile skin, have numerous 8 to take turns lattice, and each lattice of taking turns install multiple 2 wind wheels.4 wheel shafts, at center, cylindrical shell two ends, insert 8 and take turns in the hole of lattice, rotate.5 bullets, guided missile warhead.6 Missile Bodies, interior mounted engine, motor fuel, sensor.7 outer blade diameter, after wind power blade loaded onto by guided missile, the peripheral diameter that blade top is formed.8 take turns lattice, are fixed on guided missile skin, form sash in length and breadth, have the hole of slotting 4 wheel shafts in wheel lattice, install 2 wind wheels and use.
The solar heat protection cooling object of this technology is achieved in that
After hypersonic missile is launched, high velocity air impacts guided missile head, impacts on all blade periphery blade faces, blade by wind is moved, and drives the work done of wind wheel high speed rotating, blade high speed rotating, fan to guided missile skin cooling of blowing a cold wind over, the hot gas fan-out simultaneously given out by guided missile is discharged to guided missile rear.High velocity air cannot produce shock wave and viscosity, no longer produces Aerodynamic Heating and thermal boundary.
Realize solar heat protection cooling object.
Claims (3)
1. outer at guided missile, wind wheel blade solar heat protection cooling is installed, wind wheel blade is made up of cylindrical shell blade wheel shaft etc., high velocity air impacts blade movement, blade drives wind wheel high speed rotating, and blade high speed rotating blows the cooling of fan cold wind to guided missile skin, and the hot gas fan-out that guided missile gives out by blade high speed rotating is discharged to guided missile rear, high velocity air is changed into the kinetic energy of work done by wind wheel blade, and guided missile skin no longer produces Aerodynamic Heating and thermal boundary.
2. outer at guided missile as claimed in claim 1, wind wheel blade solar heat protection cooling is installed, it is characterized in that, guided missile skin no longer produces shock wave and viscous friction, also do not produce infrared radiation, do not produce directed echo, U.S.'s anti-missile system and radar cannot infrared track imagings.
3. outer at guided missile as claimed in claim 1, wind wheel blade solar heat protection cooling is installed, it is characterized in that, be widely used in various aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410526272.5A CN104373296A (en) | 2014-10-09 | 2014-10-09 | Novel hypersonic missile outer-layer wind turbine blade heat preventing and cooling technology |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410526272.5A CN104373296A (en) | 2014-10-09 | 2014-10-09 | Novel hypersonic missile outer-layer wind turbine blade heat preventing and cooling technology |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104373296A true CN104373296A (en) | 2015-02-25 |
Family
ID=52552408
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410526272.5A Pending CN104373296A (en) | 2014-10-09 | 2014-10-09 | Novel hypersonic missile outer-layer wind turbine blade heat preventing and cooling technology |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104373296A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113792508A (en) * | 2021-11-10 | 2021-12-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Aerodynamic heat calculation method considering surface quality injection effect |
Citations (6)
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|---|---|---|---|---|
| CN2092224U (en) * | 1991-03-26 | 1992-01-08 | 周春飞 | Bicycle topee |
| CN2128050Y (en) * | 1992-08-07 | 1993-03-17 | 张之屏 | Knight's sun Helmet |
| CN2744895Y (en) * | 2004-10-29 | 2005-12-07 | 杜大森 | Heat radiation structure for high speed rotation gears |
| CN201013516Y (en) * | 2007-02-09 | 2008-01-30 | 傅传明 | Rotor of forced cooling ignition apparatus for motorcycle |
| US20100005572A1 (en) * | 2008-07-10 | 2010-01-14 | David Vern Chaplin | Thermoelectric crash helmet cooling system with no mechanically moving components or fluids |
| CN103538732A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Circumferential thermal protection device of axial-symmetry hypersonic aircraft |
-
2014
- 2014-10-09 CN CN201410526272.5A patent/CN104373296A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2092224U (en) * | 1991-03-26 | 1992-01-08 | 周春飞 | Bicycle topee |
| CN2128050Y (en) * | 1992-08-07 | 1993-03-17 | 张之屏 | Knight's sun Helmet |
| CN2744895Y (en) * | 2004-10-29 | 2005-12-07 | 杜大森 | Heat radiation structure for high speed rotation gears |
| CN201013516Y (en) * | 2007-02-09 | 2008-01-30 | 傅传明 | Rotor of forced cooling ignition apparatus for motorcycle |
| US20100005572A1 (en) * | 2008-07-10 | 2010-01-14 | David Vern Chaplin | Thermoelectric crash helmet cooling system with no mechanically moving components or fluids |
| CN103538732A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Circumferential thermal protection device of axial-symmetry hypersonic aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113792508A (en) * | 2021-11-10 | 2021-12-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Aerodynamic heat calculation method considering surface quality injection effect |
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| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150225 |
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| RJ01 | Rejection of invention patent application after publication |