CN108460217A - A kind of unstable state three-dimensional icing method for numerical simulation - Google Patents
A kind of unstable state three-dimensional icing method for numerical simulation Download PDFInfo
- Publication number
- CN108460217A CN108460217A CN201810206121.XA CN201810206121A CN108460217A CN 108460217 A CN108460217 A CN 108460217A CN 201810206121 A CN201810206121 A CN 201810206121A CN 108460217 A CN108460217 A CN 108460217A
- Authority
- CN
- China
- Prior art keywords
- icing
- water
- computing unit
- overflow water
- numerical simulation
- 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
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Computer Hardware Design (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computational Mathematics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention discloses a kind of unstable state three-dimensional icing method for numerical simulation, belong to Flight Safety design field.The movement locus of water droplet is calculated using N S equation calculation air field, Lagrangian method, icing amount is calculated according to the conservation of mass and the conservation of energy and overflow water, the flow direction of overflow water and the assignment of traffic of different directions are calculated by the position vector of the velocity vector of local air, active cell and adjacent cells.Using non-steady calculation method, in each time step, it freezes and calculates since stagnation unit group, thermal equilibrium calculation is carried out to each grid cell therein, obtain next grid cell number of icing amount, overflow water and overflow water flow direction, calculating promotes backward according to the flow direction of overflow water, until all grid cells of traversal frozen surface, enters the calculating of future time step later.It is compared by example and the prior art, it was demonstrated that unstable state three-dimensional icing method for numerical simulation proposed by the present invention is effective.
Description
Technical field
The present invention relates to Flight Safety design field, especially a kind of unstable state three-dimensional icing numerical simulation side
Method.
Background technology
It freezes and seriously threatens the flight safety of aircraft.Experiment and calculating such two may be used to the research of ice formation issues
Kind mode.The experiment icing tunnel cost used that freezes and operating cost are high, and the icing tunnel that China comes into operation at present is all
It is small-sized icing tunnel, is limited by its size, certain operating modes can not tests, therefore using the technique study ice formation issues of experiment
There is many difficulties and obstacle.And with the development of numerical computation method and computer technology, numerical simulation increasingly at
For an important means of the research that freezes.Numerical simulation can be carried out with lower cost, faster speed to studying a question
Qualitative or quantitative analysis.Foreign countries develop calculating that is more early, and having had some more mature to the numerical simulation of icing
Software.The country in recent years also gradually increases the numerical simulation of icing, and two dimension icing calculates research and carries out more comprehensive, three-dimensional icing
Calculating is also gradually spread out, and there are three significant difficult points during three-dimensional icing calculates：The determination of stagnation unit, the flow direction of overflow water and
Frozen surface trellis traversal.In addition it is current it is three-dimensional freeze that calculate carried out by pseudo steady method, often using freezing process as
One time step, this has certain difference with true freezing process, results in clear ice, the result of calculation of mixing ice is often missed with experiment
Difference is larger.
Invention content
Therefore, for the above problem of the prior art, the present invention in order to overcome the deficiencies of the prior art, proposes a kind of unstable state
The computational methods that three-dimensional freezes, can more truly describe freezing process, obtain icing ice shape.
Specifically, the method specifically includes：
Step 1, which determines, calculates the time；
Step 2 starts outer circulation, searches for current computing unit group, is stagnation unit group when calculating for the first time；
Step 3 starts interior cycle, and current computing unit is determined in computing unit group；
Step 4 sets current computing unit equilibrium temperature；
Step 5 calculates the icing amount of current computing unit, overflow water, equilibrium temperature, freezing fraction；
Step 6 carries out icing calculation of thermodynamics to current computing unit, judges whether to reach thermodynamic equilibrium；If reaching heat
Dynamic balance then enters step 7, otherwise return to step 4；
The element number that step 7 search overflow water will flow to, calculates and flows into water and water temperature；
Step 8 judges whether to traverse all units in current computing unit group, if the judgment is Yes, terminates interior cycle, into
Enter step 9, otherwise return to step 3, carries out cycle in next time；
Step 9 judges whether traversal all grid cells of frozen surface, if the judgment is Yes, terminates outer circulation, into step
Rapid 10, otherwise return to step 2, carry out outer circulation next time and using the element number that step 7 searches as current computing unit
Group.
Step 10 judges whether the time for reaching setting, if the judgment is Yes, completes to calculate, otherwise return to step 1 is opened
Future time step calculates.
Further, the traversal of frozen surface grid is made of interior cycle and outer circulation in the method, and outer circulation will
Computing unit group promotes from front to back, and interior cycle is to complete the traversal of grid in computing unit group.
Further, the determination method of stagnation unit is in the method, is sweared according to the normal vector of unit and stroke speed
The angle of amount, if it is less than some numerical value, then the unit is stagnation unit.
Further, the determination method for the unit that step 7 overflow water will flow in the method is, with active cell
The central point of central point and adjacent cells forms vector, and the velocity vector of dot product air obtains the angle between two vectors, such as
Fruit angle is less than 90 degree, then judges that overflow water can flow to the adjacent cells.
Further, step 7 calculates the angle between two vectors according to the method for flowing into water in the method
Size distributes, and angle is smaller, and it is bigger to flow into water.
The present invention is for three-dimensional three difficult points present in calculating that freeze：The determination of stagnation unit, freezes at overflow water flow direction
Surface mesh traverses, it is proposed that following solution：The traversal of frozen surface grid uses two cyclic processes, interior cycle and outer
Cycle.Interior cycle is responsible for the trellis traversal in current grid unit group, and the continuous propulsion from leading edge backward is responsible in outer circulation.Respectively
It calculates the mixing ice of three-dimensional NACA0012 aerofoil profiles, clear ice example and is compared with experimental result, the results showed that the present invention
The unstable state three-dimensional icing computational methods of proposition are effective.
Description of the drawings：
Fig. 1 is the three-dimensional icing computational methods flow chart of the present invention；
Fig. 2 is the mass balance figure of micro unit；
Fig. 3 is the energy balance figure of micro unit；
Fig. 4 is the adjacent net trrellis diagram of active cell；
Fig. 5 is air velocity and grid element center point vector angle figure；
Fig. 6 is the schematic diagram for determining current computing unit；
Fig. 7 is -4.4 DEG C of ice shapes (operating mode 1) of temperature；
Fig. 8 is -28.3 DEG C of ice shapes (operating mode 2) of temperature；
Fig. 9 is -2.2 DEG C of ice shapes (operating mode 3) of temperature；
Figure 10 is -3.89 DEG C of ice shapes of temperature (4 section A of operating mode)；
Figure 11 is -3.89 DEG C of ice shapes of temperature (4 section B of operating mode)
Figure 12 is -3.89 DEG C of ice shapes of temperature (4 section C of operating mode).
Specific implementation mode
Description of specific embodiments of the present invention below：
Unstable state three-dimensional icing computational methods proposed by the present invention are formed by being recycled in one with an outer circulation.Exist first
Stagnation one-element group is chosen according to the angle between the crash direction of water droplet and computing unit method direction on frozen surface, it is stagnant by these
Stop element (initial calculation unit) sets out, and icing thermodynamics meter is carried out to each grid cell using the conservation of mass and the conservation of energy
It calculates, obtains icing amount, the overflow water of active cell.Overflow water is determined according to the flow direction of air in current grid unit
Flow direction and flow, and the water for recycling that calculative grid cell and each grid cell flow into next time is marked, in Fig. 1
Interior cycle, all units have been traversed interior cycle in current computing unit group when completing, subsequently into active cell group next time
Calculating so constantly promoted backward such as the outer circulation in Fig. 1, until all grid cell on traversal frozen surface, until
This, the icing for completing all grid cells of a time step calculates, and then enters the cycle of next time step.When up to
When to setting time, calculates and complete.
Gas-liquid two-phase stream calculation
Flow Field Calculation under the conditions of icing meteorology is the two-phase stream calculation that air, water droplet coexist.The present invention uses Euler-
Lagrangian method carries out air-liquid water droplets two-phase stream calculation.It is empty in Euler-Lagrange two-phase flow calculation methodologies
Gas phase is continuous phase, when direct solution equal N-S equations, turbulence model uses standard k-ε turbulence model；Water droplet is mutually discrete phase,
The Movement Locus Equation of water droplet in air flow field is calculated by Lagrangian method.Before two-phase stream calculation, water drop motion is done as follows
Assuming that：A. air-flow does not influence the flow field that air-flow flows through type face due to containing super-cooling waterdrop；B. water droplet is during the motion, neither solidifying
Poly- not also to be crushed, the size of water droplet remains unchanged；C. the medium parameters such as temperature, viscosity, density are kept during water drop motion
It is constant.When water droplet passes through air movement, the track of water droplet is by local air effect in the various counteracting forces on water droplet
To be calculated.
Icing thermodynamical model
The processes such as shock, merging, migration of the water droplet on wall surface are sufficiently complex, calculate, simplified as follows for convenience：
1. the water droplet temperature struck on wall surface is equal with wall peripheral gas temperature, due to super-cooling waterdrop diameter very little,
It is believed that it is rapid to exchange heat between water droplet and air-flow, keep temperature equal；
2. the water droplet struck on wall surface all rests on wall surface, that is, ignore the liquid quality splashed when shock from wall surface；
3. air-flow has not carried liquid when flowing through wall surface；
4. liquid is sprawled in wall surface along grain direction, until freezing or evaporating；
5. freezing process is in quasi-steady state, any time enters water droplet gross mass and icing, evaporation and the outflow of wall surface
Liquid quality it is equal；
6. the heat exchange amount of wall surface and ice is disregarded, i.e., wall surface is adiabatic wall；
The water collected to frozen surface using the volume control technique of Messinge establishes the conservation of mass and energy conservation equation.
The mass balance of micro unit is as shown in Fig. 2, corresponding mass-conservation equation can be determined by following formula：
For the shock amount of water droplet,Quality for the water flowed into from upstream,For flow into downstream water quality,For the icing amount of water,For the evaporation capacity of water.
Freezing fraction is introduced for description icing amount, that is, characterize the icing amount of each unit and enters all liquid waters of the unit
Mass ratio can be expressed as：
The energy balance of micro unit is as shown in figure 3, corresponding energy conservation equation can be determined by following formula：
WhereinFor the interior energy of the water of inflow micro unit；For the interior energy of the water of outflow micro unit；To hit wall surface
The energy brought into of water,To evaporate taken away heat,The latent heat discharged by water freezing,For convection current heat waste
It loses；For the heating amount for anti-icing system, the present invention without reference to anti-ice problem, so
Simultaneous equations (1), (2), (3), and assume surface temperature, the icing amount of micro unit can be obtained by iterative solutionAnd overflow water
The distribution of overflow water
It mixes in ice, clear ice calculating, since water does not freeze completely on a certain grid cell of wall surface, the water not freezed is in sky
It is entered under the action of gas in adjacent grid, here it is flooding problems.For two dimension calculate, flow to next unit be
It is very specific.For three-dimensional computations, Major Difficulties are which grid the water not freezed on current grid unit flows on earth
How unit determines the grid cell.This to freeze calculate bring key problem that great difficulty and the present invention study it
One.
The power of water flowing is mainly the drag generated close to the hollow flow of air of wall surface fluid domain unit, therefore of the invention
The flow direction and the air-flow direction of near wall unit for thinking water are consistent.It is flowed from a certain grid cell (surface grids)
The water of the water operation gone out to meshes unit (surface grids) is mainly obtained according to geometrical analysis.In three-dimension unstructure net
In lattice, grid on face is triangle, such as Fig. 4, and the unit for having side adjacent therewith has 3 (being two on boundary), it is assumed here that
Overflow water only flows to and the current grid unit unit that have side adjacent.The drag that water overflow direction is given birth to air stream movable property has
It closes, therefore the overflow direction of water is determined by the directional velocity of air.Such as Fig. 5, the central point O and list adjacent thereto of active cell
The central point O of member1Form vectorThe velocity vector of dot product airThe angle between two vectors can be obtainedWith work as
The unit that front unit has side adjacent have altogether there are three, therefore such angle also there are three, compare these three (if grid cell exists
On boundary then there are two) size of angle, if angle is more than 90 °, it is believed that water will not flow to the unit, if angle is less than 90 °
Think that water is possible to flow into the unit, the size of influx is distributed according to the size of angle, and angle is smaller, flows into water
Amount is bigger.
The selection of stagnation unit
It freezes to calculate and first has to find stagnation unit, then begin stepping through all grids of frozen surface from stagnation unit.It is stagnant
The problem of stop element is initial calculation unit, therefore there is no the inflows of upstream overflow water, you can think that it is zero to flow into water.If
Two dimension calculates, and there are one stagnation units, is easier to determine, but there is much stagnation unit in three-dimensional computations, such as Fig. 6, unit
1,3,5,7,9 be all stagnation unit, how to find in a program, determines that these units are a more difficult problems, if logical
It crosses coordinate and finds the versatility that will limit this method.
The determination of stagnation unit of the present invention is based on following thought：First according to the vector of the normal vector of unit and stroke speed
Angle between the two is less than some angle, determines that a part of grid cell is stagnation unit, such as Fig. 6,1-20 may be taken as
Stagnation unit, and these grids are not necessarily all real stagnation units, some units have overflow water inflow, therefore we claim these
Unit is active cell.The icing amount that water is hit on these active cells, the list that determines discharge and will flow into are calculated first
The element number of member, the active cell that the unit that overflow water flows into as recycles next time.
Above procedure can be seen that in initial calculation, need not be accurately known which stagnation unit has, it is only necessary to
Some grid cells are roughly selected as initial calculation unit, but these selected grid cells must include all
Real stagnation unit.
The traversal of frozen surface grid
When the t=0 moment, it is first determined current computing unit group, the active cell group calculated for the first time are stagnation unit group, it
Afterwards according to the conservation of energy and the principle of mass conservation, icing calculation of thermodynamics is carried out to each grid cell in active cell group, this
Shi Jinhang's is inner cyclic process, and icing amount, the overflow water of each unit in active cell group are obtained by interior cycle.According to
The distribution method of the above overflow water determines the flow direction and flow of overflow water, and mark flow to grid cell number, namely under
The calculative grid cell of cycle in primary, next time in the cycle grid cell to be calculated constitute working as of calculating next time
Front unit group, after all units have been traversed in current computing unit group, cycle terminates in this.Subsequently into outer circulation, search
Rope active cell group next time, is again introduced into interior cycle, so constantly promotes backward later, until institute on traversal frozen surface
Some grid cells.So far, the icing of all grid cells of a period, which calculates, completes, and then enters following for t=t+ Δs t
Ring is calculated and is completed when reaching setting time.
Contrast experiment verifies
In order to be compared with the analog result of the prior art, the present embodiment interception calculates the straight wings of NACA0012 obtained
Along the two-dimensional section of grain direction, section is located at midspan for ice shape, 30 ° of angle of sweep MS-317 aerofoil profile ice shapes.It is for section
The swept-back wing of GLC-305 has been intercepted perpendicular to up-front section A and section B, and is parallel to tri- sections section C of incoming
Ice shape figure compared with the prior art, operating mode is as shown in table 1.
Table 1
Fig. 7 be temperature be -4.4 DEG C when NACA0012 aerofoil profiles calculate ice shape and the prior art comparison, from figure on can
Go out to calculate ice shape and experimental result substantially conforms to, icing high-low limit, stationary point icing thickness greatest around and experimental result are compared with one
It causes, ice sheet growth tendency is raised to upper left side, is coincide with experimental result.
For the lower rime ice of temperature, it is believed that overflow water zero, the present embodiment calculate temperature be -28.3 DEG C when
NACA0012 aerofoil profile ice shapes, and being compared with experiment, such as Fig. 8, icing Upper-lower Limit and maximum ice layer thickness and experiment
It coincide preferable.
For 30 ° of angle of sweep MS-317 aerofoil profiles, the present embodiment calculates -2.2 DEG C of ice shape, is compared with the prior art such as figure
9, icing limes superiors is more bigger than testing, and icing limit inferior and ice layer thickness are consistent with experiment, growth tendency and the experiment one of ice sheet
It causes.
Section is compared with the prior art such as Figure 10 extremely for the ice shape of the swept-back wing middle section A of GLC-305, section B, section C
Figure 12.In Figure 10, icing Upper-lower Limit is more bigger than experiment value, icing thickness and experiment it is almost the same, the growth tendency of ice sheet with
Experiment is consistent.In Figure 11, icing Upper-lower Limit and maximum icing thickness and experiment are almost the same, but the ice of upper left side protrusion
Angle mould is intended not good enough.In Figure 12, calculates ice shape and experiment is closely similar, coincide preferable.
Find out that the result of calculation of analogy method of the present invention and experimental result are almost the same by comparing above, result of calculation energy
The growth tendency and icing maximum gauge for enough reflecting ice sheet, illustrate that analogy method three-dimensional icing computational methods of the present invention are effective
's.
It is the preferred embodiment of the present invention above, it is noted that for those skilled in the art,
Various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications also should be regarded as this
The protection domain of invention.
Claims (6)
1. a kind of unstable state three-dimensional icing method for numerical simulation, which is characterized in that the method specifically includes：
Step 1, it determines and calculates the time；
Step 2, start outer circulation, search for current computing unit group, be stagnation unit group when calculating for the first time；
Step 3, start interior cycle, current computing unit is determined in computing unit group；
Step 4, current computing unit equilibrium temperature is set；
Step 5, the icing amount of current computing unit, overflow water, equilibrium temperature, freezing fraction are calculated；
Step 6, icing calculation of thermodynamics is carried out to current computing unit, judges whether to reach thermodynamic equilibrium；If reaching heating power
Balance, then enter step 7, otherwise return to step 5；
Step 7, the element number that search overflow water will flow to, calculates and flows into water and water temperature；
Step 8, judge whether to traverse all units in current computing unit group, if the judgment is Yes, terminate interior cycle, into step
Rapid 9, otherwise return to step 3, carry out cycle in next time；
Step 9, judge whether to traverse all grid cells of frozen surface, if the judgment is Yes, terminate outer circulation, enter step
10, otherwise return to step 2, carry out outer circulation next time and using the element number that step 7 searches as current computing unit group.
2. step 10 judges whether the time for reaching setting, if the judgment is Yes, complete to calculate, otherwise return to step 1 is opened
Future time step calculates.
3. unstable state three-dimensional icing method for numerical simulation as described in claim 1, which is characterized in that freeze table in the method
The traversal of surface grids is made of interior cycle and outer circulation, and outer circulation promotes computing unit group from front to back, and interior cycle has been
At the traversal of grid in computing unit group.
4. unstable state three-dimensional icing method for numerical simulation as described in claim 1, which is characterized in that stagnation list in the method
The determination method of member is, according to the angle of the normal vector of unit and stroke speed vector, if it is less than some numerical value, then and the unit
For stagnation unit.
5. unstable state three-dimensional icing method for numerical simulation as described in claim 1, which is characterized in that step 7 in the method
The determination method for the unit that overflow water will flow to is to be formed and sweared with the central point of the central point of active cell and adjacent cells
Amount, the velocity vector of dot product air obtain the angle between two vectors, if angle is less than 90 degree, judge overflow water meeting
Flow to the adjacent cells.
6. unstable state three-dimensional icing method for numerical simulation as claimed in claim 4, which is characterized in that step 7 in the method
The size distribution of angle according to the method for calculating inflow water between two vectors, angle is smaller, flows into water and gets over
Greatly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810206121.XA CN108460217B (en) | 2018-03-13 | 2018-03-13 | Unsteady three-dimensional icing numerical simulation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810206121.XA CN108460217B (en) | 2018-03-13 | 2018-03-13 | Unsteady three-dimensional icing numerical simulation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108460217A true CN108460217A (en) | 2018-08-28 |
| CN108460217B CN108460217B (en) | 2021-10-01 |
Family
ID=63216906
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810206121.XA Expired - Fee Related CN108460217B (en) | 2018-03-13 | 2018-03-13 | Unsteady three-dimensional icing numerical simulation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108460217B (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109376403A (en) * | 2018-09-29 | 2019-02-22 | 南京航空航天大学 | A kind of two-dimentional icing method for numerical simulation based on Descartes's self-adapting reconstruction technology |
| CN111307406A (en) * | 2020-05-06 | 2020-06-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing wind tunnel liquid water content measuring method |
| CN112729762A (en) * | 2021-03-29 | 2021-04-30 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring uniformity of icing grid and cloud and mist field |
| CN112989725A (en) * | 2021-04-19 | 2021-06-18 | 江苏普旭科技股份有限公司 | Simulation method for aircraft icing environment simulation |
| CN113112568A (en) * | 2021-06-08 | 2021-07-13 | 中国空气动力研究与发展中心低速空气动力研究所 | Two-dimensional ice shape simplification method based on arc fitting |
| CN113779904A (en) * | 2021-06-09 | 2021-12-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing phase change calculation method based on coupling of continuous liquid film and discrete liquid film |
| CN113959593A (en) * | 2021-10-22 | 2022-01-21 | 中国航发沈阳发动机研究所 | Method for solving surface temperature of anti-icing component |
| CN115659517A (en) * | 2022-11-10 | 2023-01-31 | 南京航空航天大学 | Rotor blade icing quasi-unsteady numerical simulation method and system |
| CN116562192A (en) * | 2023-07-06 | 2023-08-08 | 中国空气动力研究与发展中心计算空气动力研究所 | Method, device, equipment and storage medium for predicting icing ice shape of airplane |
| CN116611266A (en) * | 2023-07-19 | 2023-08-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Unsteady state electric heating anti-icing system simulation method |
| CN118070694A (en) * | 2024-01-23 | 2024-05-24 | 清华大学 | Method and device for determining icing data of overhead platform, electronic equipment and storage medium |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080086907A1 (en) * | 2004-03-08 | 2008-04-17 | Quasar Group, Inc. | System and method for creating orthotics |
| CN101872373A (en) * | 2010-05-14 | 2010-10-27 | 南京航空航天大学 | Wing-tip grid reconstruction method of iced three-dimensional wing |
| CN102522026A (en) * | 2011-11-29 | 2012-06-27 | 天津空中代码工程应用软件开发有限公司 | Flight icing simulator |
| CN102682145A (en) * | 2011-11-30 | 2012-09-19 | 天津空中代码工程应用软件开发有限公司 | Numerical simulation method of flight icing |
| CN102682144A (en) * | 2011-11-30 | 2012-09-19 | 天津空中代码工程应用软件开发有限公司 | Flight icing numerical value simulation method of helicopter rotor wing |
| CN104298886A (en) * | 2014-10-20 | 2015-01-21 | 上海电机学院 | Icing 3-D numerical simulation method of aeroengine rotating part |
| CN205408046U (en) * | 2016-03-11 | 2016-07-27 | 陕西科技大学 | Road detection device that freezes based on image is three -dimensional to be handled |
| CN106248340A (en) * | 2016-07-08 | 2016-12-21 | 西南科技大学 | A kind of wind tunnel model 3D ice shape On-line Measuring Method based on 3-D supersonic imaging technology |
| WO2017049136A1 (en) * | 2015-09-18 | 2017-03-23 | President And Fellows Of Harvard College | Nucleic acid frameworks for structural determination |
-
2018
- 2018-03-13 CN CN201810206121.XA patent/CN108460217B/en not_active Expired - Fee Related
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080086907A1 (en) * | 2004-03-08 | 2008-04-17 | Quasar Group, Inc. | System and method for creating orthotics |
| CN101872373A (en) * | 2010-05-14 | 2010-10-27 | 南京航空航天大学 | Wing-tip grid reconstruction method of iced three-dimensional wing |
| CN102522026A (en) * | 2011-11-29 | 2012-06-27 | 天津空中代码工程应用软件开发有限公司 | Flight icing simulator |
| CN102682145A (en) * | 2011-11-30 | 2012-09-19 | 天津空中代码工程应用软件开发有限公司 | Numerical simulation method of flight icing |
| CN102682144A (en) * | 2011-11-30 | 2012-09-19 | 天津空中代码工程应用软件开发有限公司 | Flight icing numerical value simulation method of helicopter rotor wing |
| CN104298886A (en) * | 2014-10-20 | 2015-01-21 | 上海电机学院 | Icing 3-D numerical simulation method of aeroengine rotating part |
| WO2017049136A1 (en) * | 2015-09-18 | 2017-03-23 | President And Fellows Of Harvard College | Nucleic acid frameworks for structural determination |
| CN205408046U (en) * | 2016-03-11 | 2016-07-27 | 陕西科技大学 | Road detection device that freezes based on image is three -dimensional to be handled |
| CN106248340A (en) * | 2016-07-08 | 2016-12-21 | 西南科技大学 | A kind of wind tunnel model 3D ice shape On-line Measuring Method based on 3-D supersonic imaging technology |
Non-Patent Citations (2)
| Title |
|---|
| 张丽芬等: ""机翼三维结冰数值模拟"", 《航空计算技术》 * |
| 李静: ""发动机进口静止/旋转部件结冰及结冰试验的相似研究"", 《中国博士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109376403B (en) * | 2018-09-29 | 2023-06-23 | 南京航空航天大学 | Two-dimensional icing numerical simulation method based on Cartesian self-adaptive reconstruction technology |
| CN109376403A (en) * | 2018-09-29 | 2019-02-22 | 南京航空航天大学 | A kind of two-dimentional icing method for numerical simulation based on Descartes's self-adapting reconstruction technology |
| CN111307406A (en) * | 2020-05-06 | 2020-06-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing wind tunnel liquid water content measuring method |
| CN112729762A (en) * | 2021-03-29 | 2021-04-30 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring uniformity of icing grid and cloud and mist field |
| CN112729762B (en) * | 2021-03-29 | 2021-07-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring uniformity of icing grid and cloud and mist field |
| CN112989725A (en) * | 2021-04-19 | 2021-06-18 | 江苏普旭科技股份有限公司 | Simulation method for aircraft icing environment simulation |
| CN113112568A (en) * | 2021-06-08 | 2021-07-13 | 中国空气动力研究与发展中心低速空气动力研究所 | Two-dimensional ice shape simplification method based on arc fitting |
| CN113112568B (en) * | 2021-06-08 | 2021-09-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Two-dimensional ice shape simplification method based on arc fitting |
| CN113779904A (en) * | 2021-06-09 | 2021-12-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing phase change calculation method based on coupling of continuous liquid film and discrete liquid film |
| CN113959593A (en) * | 2021-10-22 | 2022-01-21 | 中国航发沈阳发动机研究所 | Method for solving surface temperature of anti-icing component |
| CN113959593B (en) * | 2021-10-22 | 2023-07-07 | 中国航发沈阳发动机研究所 | Method for solving surface temperature of anti-icing component |
| CN115659517B (en) * | 2022-11-10 | 2023-02-28 | 南京航空航天大学 | Rotor blade icing quasi-unsteady numerical simulation method and system |
| CN115659517A (en) * | 2022-11-10 | 2023-01-31 | 南京航空航天大学 | Rotor blade icing quasi-unsteady numerical simulation method and system |
| CN116562192A (en) * | 2023-07-06 | 2023-08-08 | 中国空气动力研究与发展中心计算空气动力研究所 | Method, device, equipment and storage medium for predicting icing ice shape of airplane |
| CN116562192B (en) * | 2023-07-06 | 2023-09-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Method, device, equipment and storage medium for predicting icing ice shape of airplane |
| CN116611266A (en) * | 2023-07-19 | 2023-08-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Unsteady state electric heating anti-icing system simulation method |
| CN116611266B (en) * | 2023-07-19 | 2023-09-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Unsteady state electric heating anti-icing system simulation method |
| CN118070694A (en) * | 2024-01-23 | 2024-05-24 | 清华大学 | Method and device for determining icing data of overhead platform, electronic equipment and storage medium |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108460217B (en) | 2021-10-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108460217A (en) | A kind of unstable state three-dimensional icing method for numerical simulation | |
| Zhang et al. | Shape variation and unique tip formation of a sessile water droplet during freezing | |
| Cao et al. | Numerical simulation of three-dimensional ice accretion on an aircraft wing | |
| Trontin et al. | Description and assessment of the new ONERA 2D icing suite IGLOO2D | |
| Jin et al. | Study of ice accretion and icing effects on aerodynamic characteristics of DU96 wind turbine blade profile | |
| Croce et al. | FENSAP-ICE: Analytical model for spatial and temporal evolution of in-flight icing roughness | |
| CN102682145A (en) | Numerical simulation method of flight icing | |
| CN104298886A (en) | Icing 3-D numerical simulation method of aeroengine rotating part | |
| Alekseyenko et al. | Numerical simulation of icing of a cylinder and an airfoil: model review and computational results | |
| Cao et al. | Extension to the Myers model for calculation of three-dimensional glaze icing | |
| Alekseenko et al. | Mathematical modeling of ice body formation on the wing airfoil surface | |
| CN106508020B (en) | A kind of complex aircraft calculation of aerodynamic heating method that can be used for engineering design | |
| Vahab et al. | An adaptive coupled level set and moment-of-fluid method for simulating droplet impact and solidification on solid surfaces with application to aircraft icing | |
| Lian et al. | A modified spongy icing model considering the effect of droplets retention on the ice accretion process | |
| Cao et al. | Insight into rime ice accretion on an aircraft wing and corresponding effects on aerodynamic performance | |
| Özgen et al. | In-flight ice formation simulation on finite wings and air intakes | |
| Lian et al. | Experimental and numerical investigation of icing process of a liquid droplet | |
| Norde et al. | Splashing model for impact of supercooled large droplets on a thin liquid film | |
| Szilder et al. | Three-dimensional numerical simulation of ice accretion using a discrete morphogenetic approach | |
| Cao et al. | Numerical simulation of ice accretion in supercooled large droplet conditions | |
| Porter | Predicted Ice Shape Formations on a Boundary Layer Ingesting Engine Inlet | |
| Chang et al. | Numerical investigation of airfoil ice accumulation: Ice shape and ice crack propagation | |
| Li et al. | Methods and criterion for adaptive ICE accretion simulation: mesh boundary merge and reconstruction | |
| Ferdous et al. | Prediction of ice accretion and aerodynamic performance analysis of NACA 2412 aerofoil | |
| Yanxiang et al. | Numerical Evaluation of the Effect of Icing Accretion on an Airship |
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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20211001 |