CN106828887A - A kind of Vehicle nose's self adaptation thermal protection method - Google Patents
A kind of Vehicle nose's self adaptation thermal protection method Download PDFInfo
- Publication number
- CN106828887A CN106828887A CN201611029621.8A CN201611029621A CN106828887A CN 106828887 A CN106828887 A CN 106828887A CN 201611029621 A CN201611029621 A CN 201611029621A CN 106828887 A CN106828887 A CN 106828887A
- Authority
- CN
- China
- Prior art keywords
- temperature
- shock wave
- thermal protection
- gas
- self adaptation
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
A kind of Vehicle nose's self adaptation thermal protection method, is related to high speed pneumatic thermal protection field, high-speed aerodynamics field；Vehicle nose's self adaptation thermal protection method includes：Determine the elevated position of head temperature, thermocouple is installed, and the in-flight required shock wave pin of pre-set flight device sprays the flow and pressure of gas；Adjustment shock wave pin sprays the flow and pressure of gas in time, this process constantly circulates regulation, until reducing surface temperature, prevent surface thermal ablation, the present invention can experience the elevated position installation thermocouple of head temperature using in supersonic speed or hypersonic aircraft internal face, according to the temperature that thermocouple measurement is obtained, the aperture of control valve, while by the gas pressure for controlling shock wave pin to spray, can finally change to flow the flow-disturbing situation in Vehicle nose, surface temperature is reduced, thermal ablation is prevented, so as to play a part of thermal protection to Vehicle nose.
Description
Technical field
The present invention relates to a kind of high speed pneumatic thermal protection field, high-speed aerodynamics field, particularly a kind of aircraft
Head self adaptation thermal protection method.
Background technology
Especially blunt body aircraft can form one arch attached shock to aircraft during high-speed flight in bullet,
To giving birth to strong compression to miscarry, while head causes air themperature drastically to raise with come the violent friction of life of miscarrying, because
This bullet experience high speed, high pressure, environment of high temperature in flight course, there is very serious ablation to bullet surface material, destroy
Flight Vehicle Structure causes aircraft interior temperature rise, and the safety analysis to aircraft constitutes a threat to.
To prevent Vehicle nose to be burned out, it is necessary to using thermal protection measure, current existing method mainly includes following
Three aspects：First aircraft exterior increase it is anti-insulating surface, prevent structure ablative degradation, completely cut off external heat, but should
Method increases aircraft weight, reduces the capacity of aircraft, and heat-barrier material cost is higher, it is impossible to secondary utilization；Second side
Method is to install shock wave pin in Vehicle nose, and shock wave is pushed away into bullet, while forming low-pressure area in bullet surface, reduces surface temperature
Degree, but shock wave is attached to shock wave pin front portion in flight course, causes the easily ablated damage of shock wave pin, reduces thermal protection effect
Otherwise can also there is Vehicle nose's thermal ablation, it is necessary to change in time in fruit；The third method is used in projectile nose
Energy delivers (such as shock wave, low-light), and shock wave is pushed away into bullet, but the research is still underway, also immature.
The content of the invention
A kind of above-mentioned deficiency it is an object of the invention to overcome prior art, there is provided Vehicle nose's self adaptation thermal protection
Method, the present invention can experience the elevated position installation thermocouple of head temperature using in supersonic speed or aircraft internal face,
According to the temperature that thermocouple measurement is obtained, the aperture of control valve, while by the gas pressure for controlling shock wave pin to spray, final energy
It is enough to change to flow the flow-disturbing situation in Vehicle nose, surface temperature is reduced, thermal ablation is prevented, so as to be played to Vehicle nose
The effect of thermal protection.
Above-mentioned purpose of the invention is achieved by following technical solution：
A kind of Vehicle nose's self adaptation thermal protection method, Vehicle nose self adaptation temperature barrier include shock wave pin,
The elevated position of valve, head temperature, thermocouple, aircraft, air accumulator and measuring instrument；Self adaptation thermal protection method includes as follows
Step：
Step (1), by shock wave pin, air accumulator after ground assembles, be installed to the head of aircraft, preset shock wave pin
Initial length；
Step (2), determine the elevated position of head temperature, thermocouple is installed；Thermocouple welding to head temperature is raised
Position inwall, thermocouple is numbered, and thermocouple is connected on measuring instrument, temperature is obtained according to measuring instrument measurement
Highest position；
The in-flight required shock wave pin of step (3), pre-set flight device sprays the flow and pressure of gas；Treat aircraft
After taking off, according to the control of flow and pressure valve opening of default gas, the gas flow that regulation shock wave pin sprays；Ensure to fly
During row device Automatic adjusument surface temperature, Vehicle nose's wall surface temperature that thermocouple is surveyed is necessary less than temperature is required
When need to supplement the gas of air accumulator.
Step (4), reading real-time judge aircraft surface temperature in-flight according to measuring instrument, and shock wave is adjusted in time
Pin sprays the flow and pressure of gas, and this process constantly circulates regulation, until reducing surface temperature, prevents surface thermal ablation.
In a kind of above-mentioned Vehicle nose's self adaptation thermal protection method, in described step (), the aircraft head
Portion is arc-shaped, and arc radius are r, and the initial length of shock wave pin is 1-3 times of r.
In a kind of above-mentioned Vehicle nose's self adaptation thermal protection method, in described step (two), according to bowshock
Determine that the elevated position of head temperature, i.e. bowshock attached shock are sprayed by shock wave pin in the position attached again on body surface
After gas pushes away bullet, the position that body is attached to again is exactly the elevated position of head temperature.
In a kind of above-mentioned Vehicle nose's self adaptation thermal protection method, in described step (two), such as head temperature liter
Position high is annular, then accordingly in the circle arrangement thermocouple of annular location one；If the elevated position of head temperature is several concentrations
Region, then accordingly arrange several thermocouples in corresponding region.
In a kind of above-mentioned Vehicle nose's self adaptation thermal protection method, in described step (three), shock wave pin is default
The flow and pressure of gas are sprayed, shock wave pin ejection gas is met and attached body bowshock is pushed away into aircraft surface.
It is described to require temperature in described step (three) in a kind of above-mentioned Vehicle nose's self adaptation thermal protection method
Meet Vehicle nose's wall surface material and do not produce thermal ablation.
In a kind of above-mentioned Vehicle nose's self adaptation thermal protection method, in described step (three), the air accumulator
Gas can carry out increase adjustment according to actually used situation.
In a kind of above-mentioned Vehicle nose's self adaptation thermal protection method, in described step (four), Vehicle nose's wall
The increase of shock wave pin sprays gas flow when face temperature is raised, otherwise reduces.
The present invention has the following advantages that compared with prior art：
(1) present invention can be by Active Control Method, and real-time monitoring aircraft surface temperature, adaptive in flight course
Aircraft surface temperature should be adjusted, prevents aircraft surface thermal ablation situation from occurring, jet pressures and flow are actual according to flight
Thermal environment carries out Self Adaptive Control, is conducive to the consumption of saving spray current mass flow, reduces the requirement to volume of gas storage tank；
(2) bowshock is pushed away Vehicle nose by the present invention by the way of shock wave pin increases pressure gas stream, while arch
Also away from shock wave pin, shock wave pin is easily burned out ripple when solving the problems, such as single use shock wave pin, reduces aircraft surface heat and burns
The risk of erosion；
(3) complete equipment of the present invention can be utilized repeatedly, and with strong applicability, can be arranged on any aircraft.
Brief description of the drawings
Fig. 1 is Vehicle nose's self adaptation thermal protection schematic diagram of the present invention.
Specific embodiment
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings：
It is as shown in Figure 1 Vehicle nose's self adaptation thermal protection schematic diagram, as seen from the figure, a kind of Vehicle nose's self adaptation
Thermal protection method, Vehicle nose's self adaptation temperature barrier includes shock wave pin 1, the elevated position 3 of valve 2, head temperature, heat
Galvanic couple 4, aircraft 5, air accumulator 6 and measuring instrument 7；Self adaptation thermal protection method comprises the following steps：
Step (1), by shock wave pin 1, air accumulator 6 after ground assembles, be installed to the head of aircraft 5, preset shock wave
The initial length of pin 1, the head of aircraft 5 is arc-shaped, and arc radius are r, and the initial length of shock wave pin 1 is 1-3 times of r；
Step (2), determine the elevated position 3 of head temperature, the determination method at the elevated position 3 of head temperature is：According to
Bowshock determines the elevated position 3 of head temperature in the position attached again on body surface, i.e. bowshock attached shock is swashed
After the gas that ripple pin sprays pushes away bullet, the position that body is attached to again is exactly the elevated position 3 of head temperature, according to head
Thermocouple 4 is installed at the elevated position 3 of temperature, and such as elevated position 3 of head temperature is annular, then accordingly enclose cloth in annular location one
Put thermocouple 4；If the elevated position 3 of head temperature is several concentrated areas, then accordingly several thermocouples are arranged in corresponding region
4；Thermocouple 4 is welded to the inwall at the elevated position 3 of head temperature, the installation site of thermocouple 4 can neither be too near to described
Aircraft wall, prevents thermal ablation from being damaged, can not be too remote apart from the aircraft wall, prevents measurement from larger mistake occur
Difference, while the thermocouple is arranged in the installation site of the whole head of the aircraft according to actual flight state, can arrange one
Circle is several, it is ensured that can be measured that maximum temperature position in all flight conditions；Thermocouple 4 is numbered, and by thermoelectricity
Even 4 are connected on measuring instrument 7, and temperature highest position is obtained according to the measurement of measuring instrument 7；
The in-flight required shock wave pin 1 of step (3), pre-set flight device 5 sprays the flow and pressure of gas, shock wave pin 1
The default flow and pressure for spraying gas, should meet the ejection gas of shock wave pin 1 and attached body bowshock is pushed away into the table of aircraft 5
Face；After aircraft 5 takes off, according to the aperture of control of flow and pressure valve 2 of default gas, what regulation shock wave pin 1 sprayed
Gas flow；During ensureing the Automatic adjusument surface temperature of aircraft 5, the head wall surface temperature of aircraft 5 that thermocouple 4 is surveyed
Less than requiring temperature, it is desirable to which temperature meets the head wall surface material of aircraft 5 and do not produce thermal ablation；Needed to gas storage when necessary
The gas of tank 6 is supplemented, and the gas of air accumulator 6 can carry out increase adjustment according to actually used situation.
Step (4), reading real-time judge aircraft surface temperature in-flight according to measuring instrument 7, and shock wave is adjusted in time
Pin 1 sprays the flow and pressure of gas, and shock wave pin 1 increases ejection gas flow when the head wall surface temperature of aircraft 5 is raised, otherwise
Reduce, the distance of Automatic adjusument detached shock wave and projectile nose, realization carries out jet flow self adaptation according to the degree of Aerodynamic Heating
Control；This process constantly circulates regulation, until reducing surface temperature, prevents surface thermal ablation.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (8)
1. a kind of Vehicle nose's self adaptation thermal protection method, it is characterised in that：Vehicle nose's self adaptation temperature barrier bag
Include shock wave pin (1), valve (2), the elevated position of head temperature (3), thermocouple (4), aircraft (5), air accumulator (6) and measurement
Instrument (7)；Self adaptation thermal protection method comprises the following steps：
Step (1), by shock wave pin (1), air accumulator (6) after ground assembles, be installed to the head of aircraft (5), preset swash
The initial length of ripple pin (1)；
Step (2), determine the elevated position of head temperature (3), thermocouple (4) is installed；Thermocouple (4) is welded to head temperature
The inwall of elevated position (3) is spent, thermocouple (4) is numbered, and thermocouple (4) is connected on measuring instrument (7), according to
Measuring instrument (7) measurement obtains temperature highest position；
The in-flight required shock wave pin (1) of step (3), pre-set flight device (5) sprays the flow and pressure of gas；Wait to fly
After device (5) takes off, according to the gas that control of flow and pressure valve (2) aperture of default gas, regulation shock wave pin (1) spray
Flow；During ensureing aircraft (5) Automatic adjusument surface temperature, aircraft (5) head wall temperature that thermocouple (4) is surveyed
Degree needs to supplement the gas of air accumulator (6) less than temperature is required when necessary.
Step (4), reading real-time judge aircraft surface temperature in-flight according to measuring instrument (7), and shock wave pin is adjusted in time
(1) flow and pressure of gas are sprayed, this process constantly circulates regulation, until reducing surface temperature, prevents surface thermal ablation.
2. a kind of Vehicle nose's self adaptation thermal protection method according to claim 1, it is characterised in that：Described step
(1) in, aircraft (5) head is arc-shaped, and arc radius are r, and the initial length of shock wave pin (1) is 1-3 times of r.
3. a kind of Vehicle nose's self adaptation thermal protection method according to claim 1, it is characterised in that：Described step
(2) in, the elevated position of head temperature (3), i.e. bowshock are determined in the position attached again on body surface according to bowshock
After attached shock pushes away bullet by the gas that shock wave pin sprays, the position that body is attached to again is exactly the elevated portion of head temperature
Position (3).
4. a kind of Vehicle nose's self adaptation thermal protection method according to claim 1, it is characterised in that：Described step
(2) in, such as elevated position of head temperature (3) is annular, then accordingly in circle arrangement thermocouple of annular location one (4)；Such as head
The elevated position of temperature (3) is several concentrated areas, then accordingly arrange several thermocouples (4) in corresponding region.
5. a kind of Vehicle nose's self adaptation thermal protection method according to claim 1, it is characterised in that：Described step
(3) in, the default flow and pressure for spraying gas of shock wave pin (1) meets shock wave pin (1) ejection gas and swashs attached body arch
Ripple pushes away aircraft (5) surface.
6. a kind of Vehicle nose's self adaptation thermal protection method according to claim 1, it is characterised in that：Described step
(3) it is described to require that temperature meets aircraft (5) head wall surface material and do not produce thermal ablation in.
7. a kind of Vehicle nose's self adaptation thermal protection method according to claim 1, it is characterised in that：Described step
(3) in, the gas of the air accumulator (6) can carry out increase adjustment according to actually used situation.
8. a kind of Vehicle nose's self adaptation thermal protection method according to claim 1, it is characterised in that：Described step
(4) in, shock wave pin (1) increase sprays gas flow when aircraft (5) head wall surface temperature is raised, otherwise reduces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611029621.8A CN106828887B (en) | 2016-11-14 | 2016-11-14 | A kind of adaptive thermal protection method of Vehicle nose |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611029621.8A CN106828887B (en) | 2016-11-14 | 2016-11-14 | A kind of adaptive thermal protection method of Vehicle nose |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106828887A true CN106828887A (en) | 2017-06-13 |
| CN106828887B CN106828887B (en) | 2018-11-23 |
Family
ID=59145893
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611029621.8A Active CN106828887B (en) | 2016-11-14 | 2016-11-14 | A kind of adaptive thermal protection method of Vehicle nose |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106828887B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107352042A (en) * | 2017-07-10 | 2017-11-17 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of drag reduction method in supersonic turbulent boundary layer |
| CN107515053A (en) * | 2017-09-20 | 2017-12-26 | 湖北三江航天红阳机电有限公司 | A kind of pneumatic heat detecting device and its manufacture method |
| CN110641727A (en) * | 2019-11-06 | 2020-01-03 | 北京空间技术研制试验中心 | Design method of shock wave rod device mounted on head of supersonic aircraft |
| CN111392026A (en) * | 2020-03-23 | 2020-07-10 | 南京航空航天大学 | Hypersonic aircraft nose cone active thermal protection system |
| CN112158362A (en) * | 2020-09-30 | 2021-01-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Resistance-reducing and heat-reducing device and method for spacecraft |
| CN112193401A (en) * | 2020-04-07 | 2021-01-08 | 北京空天技术研究所 | Thermal protection method for front edge of hypersonic aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0570239A2 (en) * | 1992-05-14 | 1993-11-18 | Lucas Industries Public Limited Company | Thermocouple |
| CN1994823A (en) * | 2006-12-27 | 2007-07-11 | 中国科学院力学研究所 | Ablation-free self-adaptive heat-resistant and damping system for high supersonic aerocraft |
| CN1994824A (en) * | 2006-12-27 | 2007-07-11 | 中国科学院力学研究所 | Reverse pulse explosion heat-resistant and damping method for high supersonic aerocraft |
| CN103592046A (en) * | 2013-10-22 | 2014-02-19 | 中国科学院力学研究所 | Integral type thermocouple |
| CN104608942A (en) * | 2015-02-13 | 2015-05-13 | 中国科学院宁波材料技术与工程研究所 | Ultra-high speed aircraft thermal protection and drag reduction method and system |
| CN104859835A (en) * | 2015-04-27 | 2015-08-26 | 清华大学 | Hypersonic aircraft head cone based on composite cooling mode |
-
2016
- 2016-11-14 CN CN201611029621.8A patent/CN106828887B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0570239A2 (en) * | 1992-05-14 | 1993-11-18 | Lucas Industries Public Limited Company | Thermocouple |
| CN1994823A (en) * | 2006-12-27 | 2007-07-11 | 中国科学院力学研究所 | Ablation-free self-adaptive heat-resistant and damping system for high supersonic aerocraft |
| CN1994824A (en) * | 2006-12-27 | 2007-07-11 | 中国科学院力学研究所 | Reverse pulse explosion heat-resistant and damping method for high supersonic aerocraft |
| CN103592046A (en) * | 2013-10-22 | 2014-02-19 | 中国科学院力学研究所 | Integral type thermocouple |
| CN104608942A (en) * | 2015-02-13 | 2015-05-13 | 中国科学院宁波材料技术与工程研究所 | Ultra-high speed aircraft thermal protection and drag reduction method and system |
| CN104859835A (en) * | 2015-04-27 | 2015-08-26 | 清华大学 | Hypersonic aircraft head cone based on composite cooling mode |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107352042A (en) * | 2017-07-10 | 2017-11-17 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of drag reduction method in supersonic turbulent boundary layer |
| CN107352042B (en) * | 2017-07-10 | 2020-03-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Drag reduction method for supersonic turbulent boundary layer |
| CN107515053A (en) * | 2017-09-20 | 2017-12-26 | 湖北三江航天红阳机电有限公司 | A kind of pneumatic heat detecting device and its manufacture method |
| CN107515053B (en) * | 2017-09-20 | 2019-05-21 | 湖北三江航天红阳机电有限公司 | A kind of pneumatic heat detecting device and its manufacturing method |
| CN110641727A (en) * | 2019-11-06 | 2020-01-03 | 北京空间技术研制试验中心 | Design method of shock wave rod device mounted on head of supersonic aircraft |
| CN111392026A (en) * | 2020-03-23 | 2020-07-10 | 南京航空航天大学 | Hypersonic aircraft nose cone active thermal protection system |
| CN112193401A (en) * | 2020-04-07 | 2021-01-08 | 北京空天技术研究所 | Thermal protection method for front edge of hypersonic aircraft |
| CN112193401B (en) * | 2020-04-07 | 2022-05-20 | 北京空天技术研究所 | Thermal protection method for front edge of hypersonic aircraft |
| CN112158362A (en) * | 2020-09-30 | 2021-01-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Resistance-reducing and heat-reducing device and method for spacecraft |
| CN112158362B (en) * | 2020-09-30 | 2021-04-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Resistance-reducing and heat-reducing device and method for spacecraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106828887B (en) | 2018-11-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106828887A (en) | A kind of Vehicle nose's self adaptation thermal protection method | |
| EP3257756B1 (en) | Thermal protection and drag reduction method and system for ultra high-speed aircraft | |
| CN105691620B (en) | Utilize the ultrasonic combined anti-icing and de-icing device of the heat pipe of aircraft engine waste heat and method | |
| CN105626204B (en) | Air assists hybrid gas drive urea injection system and method | |
| KR20160112308A (en) | Fuel injection system and control method thereof | |
| US20180339766A1 (en) | Landing gear bogie pitch trimmer | |
| CN114261523A (en) | Novel combined ice preventing and removing system | |
| CN108058832A (en) | A kind of combined type anti-freeze fluid-anti-deicing system of air bag | |
| CN102190084A (en) | De-icing system comprising detection means for detecting an air leak in the hot air supply | |
| CN105508054B (en) | A kind of engine inlets anti-icing system and aero-engine | |
| CN108969950A (en) | A kind of sea floating heap containment high pressure water spraying fire fighting system | |
| CN108100273B (en) | Aircraft fuel cooling system | |
| CN104326079A (en) | Adaptive active thermal protection device and aircraft | |
| CN109720582B (en) | Composite electric heating-anti-icing liquid ice prevention and removal system | |
| CN115230969B (en) | Aircraft environmental control system and method adopting vortex tube for preventing ice and cooling electronic equipment | |
| CN104406147B (en) | A kind of steam generator | |
| CN110979693A (en) | Anti-icing and deicing system, unmanned aerial vehicle and control method | |
| CN110589026B (en) | Ground test device of closed-loop aircraft electric anti-icing system | |
| CN208092570U (en) | adjacent tank temperature control system | |
| CN205717329U (en) | Flameholder with novel cooling structure integrated design | |
| CN210718856U (en) | Infrared seeker refrigerating system | |
| CN103776122B (en) | A kind of icing tunnel humidity control method and special humidification system thereof | |
| CN207745436U (en) | Frequency conversion tank flames of anger fire extinguishing cooling system | |
| CN217409610U (en) | Wisdom fire-fighting robot with remote control | |
| CN219355163U (en) | Overheat protection system for vehicle and fire engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |