CN106529096A - Analyzing method for temperature field of integral fuel tank - Google Patents
Analyzing method for temperature field of integral fuel tank Download PDFInfo
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- CN106529096A CN106529096A CN201611176702.0A CN201611176702A CN106529096A CN 106529096 A CN106529096 A CN 106529096A CN 201611176702 A CN201611176702 A CN 201611176702A CN 106529096 A CN106529096 A CN 106529096A
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Abstract
The invention discloses an analyzing method for a temperature field of an integral fuel tank, and belongs to the technical field of aircraft designs. The method includes the following steps: step 1, establishing a simulation model of an integral fuel tank structure, and determining a fuel space area inside the integral fuel tank structure; step 2, filling the fuel space area with simulation fuel so that the fuel space area is full of fuel; step 3, further dividing the simulation fuel in the fuel space area into n layers; step 4, applying aerodynamic heating data, changing along with the time, on the aerodynamic surface of the integral fuel tank structure; step 5, carrying out fuel consumption and filling gas simulation through a ladder simulation method; and step 6, obtaining a change result of the temperature of the integral fuel tank structure along with the time after the fuel consumption simulation through the ladder simulation structure. According to the method, temperature field changes of the structure can be effectively obtained without being limited by test equipment or test environments, the product design period is short, and the design efficiency is improved. The analyzing method is easy to promote and apply, and has great practical values.
Description
Technical field
The invention belongs to airplane design technical field, and in particular to a kind of integral tank temperature field analysis method.
Background technology
Airline carriers of passengers generally adopts integral tank structure at present, due to flying speed relatively low (being less than 2 Mach numbers), is carrying out
Aerodynamic Heating problem can be ignored during structure design.But for High Mach number (being more than 2 Mach numbers) aircraft, it is necessary to
Consider impact of the Aerodynamic Heating to integral tank structure.Generally this impact is reacted all by test simulation, but adopts
The cycle for taking research technique is longer, relatively costly.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
The purpose of the present invention：In order to solve the above problems, the present invention proposes a kind of integral tank temperature field analysis method,
The development time can be effectively saved, reduces cost is easy to structural design scheme iteratively faster to update, can effectively obtain structure
Change of temperature field, and the restriction of be not put to the test equipment, experimental enviroment.
Technical scheme：A kind of integral tank temperature field analysis method, it is characterised in that the integral tank temperature
Degree field analysis method is comprised the following steps：
Step 1：Integral tank structure simulation model is set up, the fuel space region of integral tank inside configuration is determined；
Step 2：Fuel oil is simulated for fuel space area filling, makes fuel space region form full oil condition；
Step 3：Refined for the simulation fuel oil in the fuel space region, be divided into n-layer；
Step 4：Apply the Aerodynamic Heating data of the aerodynamic surface of time dependent integral tank structure；
Step 5：Fuel consumption and filling gas simulation are carried out by ladder analogy method；
Step 6：The integral tank structure temperature after ladder analogy method carries out fuel consumption simulation is obtained with the time
Result of variations.
Preferably, fuel oil is simulated using body unit in the step 2.
Preferably, the step 3 is specially：Refined to simulating fuel oil using body unit, and be divided into the body of the n-layer
Unit.
Preferably, n >=5.
Preferably, the ladder analogy method in the step 5 is specially：Fuel consumption is to reduce linearly over time, and sets
Consumption second total time t is put, each m second consumes the body unit of one layer of fuel oil, while filling the gas of one layer of body unit volume；Its
In, n × m=t.
Preferably, the fuel consumption is to reduce linearly over time, and arranges consumption second total time t, and each m second consumes
The body unit of one layer of fuel oil, while the gas for filling one layer of body unit volume is specially：
Within 0 to the m second calculating times, the convection transfer rate and temperature between fuel oil and integral tank structure is set, is entered
Row heat calculates analysis, obtains the initial integral tank structure temperature distribution of 0 to m seconds；
Within m to the 2m second calculating times, at the m seconds, ground floor body unit attribute is changed to into gas by the attribute of fuel oil
Attribute, the initial integral tank structure temperature distribution is applied in integral tank structure as primary condition, fuel oil is arranged
With convection transfer rate and temperature between integral tank structure, the convection transfer rate between gas and integral tank structure and
Convection transfer rate and temperature between temperature, gas and fuel oil, carries out heat and calculates analysis, and obtain m to the 2m seconds second is overall
Oiltank structure temperature field；
Within nm-2m to the nm-m second calculating times, at the nm-2m seconds, n-2 layer body unit attributes are changed by the attribute of fuel oil
For the attribute of gas, it is applied to the second integral tank structure temperature field as primary condition in integral tank structure, combustion is set
Convection transfer rate and the convection transfer rate between temperature, gas and integral tank structure between oil and integral tank structure
Convection transfer rate and temperature and temperature, gas and fuel oil between, carries out heat and calculates analysis, obtain the 3rd integral tank structure
Temperature field；
Within nm-m to the nm second calculating times, at the nm-m seconds, n-1 layer body unit attributes are changed to into gas by the attribute of fuel oil
The attribute of body, is applied to the 3rd integral tank structure temperature field as primary condition in integral tank structure, arrange fuel oil with
Convection transfer rate and temperature between integral tank structure, the convection transfer rate between gas and integral tank structure and temperature
Degree, the convection transfer rate between gas and fuel oil and temperature, carry out heat and calculate analysis, obtain the 4th integral tank structure temperature
.
Preferably, change of structure temperature of the acquisition after ladder analogy method carries out fuel consumption simulation with the time
Change result to be specially：
By the first integral tank structure temperature field, the second integral tank structure temperature field, the 3rd integral tank structure temperature
And the 4th integral tank structure temperature field carry out Time Continuous arrangement, obtain integral tank structure in t times second at any time
Between change result.
The technique effect of the present invention：A kind of integral tank temperature field analysis method of the present invention, for High Mach number aircraft
Integral tank temperature field analysis technology, can effectively obtain structure temperature field and change, and the equipment that is not put to the test, experimental enviroment
Limit, product design cycle is short, improve design efficiency, it is easy to popularization and application, with larger practical value.
Description of the drawings
Fig. 1 is a kind of schematic flow sheet of a preferred embodiment of integral tank temperature field analysis method of the invention.
Fig. 2 changes over schematic diagram for the fuel consumption of embodiment illustrated in fig. 1.
Fuel consumption change ladder simulation schematic diagrames of the Fig. 3 for embodiment illustrated in fig. 1.
Specific embodiment
To make purpose, technical scheme and the advantage of present invention enforcement clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than the embodiment of whole.It is exemplary below with reference to the embodiment of Description of Drawings, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment obtained under the premise of creative work is not made by member, belongs to the scope of protection of the invention.Under
Face combines accompanying drawing and embodiments of the invention is described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " is based on accompanying drawing institute
The orientation for showing or position relationship, are for only for ease of the description present invention and simplify description, rather than indicate or imply the dress of indication
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The restriction of scope.
As shown in figure 1, a kind of integral tank temperature field analysis method of the invention, comprises the following steps：
Step one, integral tank structure simulation model is set up, determine the fuel space region of integral tank inside configuration；
Step 2, for fuel space area filling simulate fuel oil, make fuel space region form full oil condition；
Step 3, refined for the simulation fuel oil in the fuel space region, be divided into n-layer；
The Aerodynamic Heating data of step 4, the aerodynamic surface of the time dependent integral tank structure of applying；
Step 5, carried out by ladder analogy method fuel consumption and filling gas simulation；
The integral tank structure temperature of step 6, acquisition after ladder analogy method carries out fuel consumption simulation is with the time
Result of variations.
In the present embodiment, fuel oil is simulated using body unit in step 2；
In the present embodiment, step 3 is specially：Refined to simulating fuel oil using body unit, and be divided into the n-layer
Body unit.
In the present embodiment, n >=5.It is understood that the number of plies for dividing is more, its result is more accurate.
In the present embodiment, the ladder analogy method in step 5 is specially：Fuel consumption is to reduce linearly over time, and
Arrange and consume second total time t, each m second consumes the body unit of one layer of fuel oil, while filling the gas of one layer of body unit volume；
Wherein, n × m=t.
In the present embodiment, fuel consumption is to reduce linearly over time, and arranges consumption second total time t, and each m second consumes
Fall the body unit of one layer of fuel oil, while the gas for filling one layer of body unit volume is specially：
Within 0 to the m second calculating times, the convection transfer rate and temperature between fuel oil and integral tank structure is set, is entered
Row heat calculates analysis, obtains the initial integral tank structure temperature distribution of 0 to m seconds；
Within m to the 2m second calculating times, at the m seconds, ground floor body unit attribute is changed to into gas by the attribute of fuel oil
Attribute, the initial integral tank structure temperature distribution is applied in integral tank structure as primary condition, fuel oil is arranged
With convection transfer rate and temperature between integral tank structure, the convection transfer rate between gas and integral tank structure and
Convection transfer rate and temperature between temperature, gas and fuel oil, carries out heat and calculates analysis, and obtain m to the 2m seconds second is overall
Oiltank structure temperature field；
Within nm-2m to the nm-m second calculating times, at the nm-2m seconds, n-2 layer body unit attributes are changed by the attribute of fuel oil
For the attribute of gas, it is applied to the second integral tank structure temperature field as primary condition in integral tank structure, combustion is set
Convection transfer rate and the convection transfer rate between temperature, gas and integral tank structure between oil and integral tank structure
Convection transfer rate and temperature and temperature, gas and fuel oil between, carries out heat and calculates analysis, obtain the 3rd integral tank structure
Temperature field；
Within nm-m to the nm second calculating times, at the nm-m seconds, n-1 layer body unit attributes are changed to into gas by the attribute of fuel oil
The attribute of body, is applied to the 3rd integral tank structure temperature field as primary condition in integral tank structure, arrange fuel oil with
Convection transfer rate and temperature between integral tank structure, the convection transfer rate between gas and integral tank structure and temperature
Degree, the convection transfer rate between gas and fuel oil and temperature, carry out heat and calculate analysis, obtain the 4th integral tank structure temperature
.
In the present embodiment, it is described to obtain the structure temperature after ladder analogy method carries out fuel consumption simulation at any time
Between result of variations be specially：By the first integral tank structure temperature field, the second integral tank structure temperature field, the 3rd overall oil
Box structure temperature field and the 4th integral tank structure temperature field carry out Time Continuous arrangement, obtain the overall oil in t times second
Box structure result over time.
By way of example the integral tank temperature field analysis method of the application is described in detail below.It is appreciated that
, this is illustrated and does not constitute any restriction to the application.
According to Oiltank structure design, fuel tank heat analysis structural model is set up；
As shown in Figure 2 and Figure 3：In fuel space region, fuel oil is simulated using body unit, in the model of beginning, simulate full oil
State；And the body unit of simulation full oil condition is refined, it is divided into 5 layers of body unit, numbering is 1,2,3,4,5 from top to bottom；
Assume that fuel consumption is reduced linearly over time, 10m within the time of 3000 seconds3Fuel oil is all consumed；
Applying changes over the Aerodynamic Heating data of the integral tank regional structure aerodynamic surface of (0～3000 second)；
The simulation of fuel consumption is carried out using ladder analogy method, is often crossed and is consumed within 300 seconds one layer of fuel oil body unit, while
The gas of one layer of body unit volume of filling；
Within 0～600 second calculating time, the convection transfer rate and temperature between fuel oil and structure is set, hot meter is carried out
Point counting is analysed, and obtains the structure temperature distribution of 0～600 second；
Within 600～1200 seconds calculating time, at 600 seconds, by the body unit attribute of numbering in structure 1 by fuel oil attribute
Gas properties are changed to, the Structure Calculation temperature field primary condition the most in (1) when 600 seconds is applied in structure, fuel oil is set
Convection transfer rate and temperature between structure, between gas and structure, between gas and fuel oil, carries out heat and calculates analysis,
Obtain the structure temperature field of 600～1200 seconds；
Within 1200～1800 seconds calculating time, at 1200 seconds, the body unit attribute of numbering in structure 2 is belonged to by fuel oil
Property be changed to gas properties, the Structure Calculation temperature field primary condition the most of 1200 seconds in (2) is applied in structure, arrange fuel oil
Convection transfer rate and temperature between structure, between gas and structure, between gas and fuel oil, carries out heat and calculates analysis,
Obtain the structure temperature field of 1200～1800 seconds；
Within 1800～2400 seconds calculating time, at 1800 seconds, the body unit attribute of numbering in structure 3 is belonged to by fuel oil
Property be changed to gas properties, the Structure Calculation temperature field primary condition the most of 1800 seconds in (3) is applied in structure, arrange fuel oil
Convection transfer rate and temperature between structure, between gas and structure, between gas and fuel oil, carries out heat and calculates analysis,
Obtain the structure temperature field of 1800～2400 seconds；
Within 2400～3000 seconds calculating time, at 2400 seconds, the body unit attribute of numbering in structure 4 is belonged to by fuel oil
Property be changed to gas properties, the calculating temperature field primary condition the most of 2400 seconds in (4) is applied in structure, arrange fuel oil with knot
Convection transfer rate and temperature between structure, between gas and structure, between gas and fuel oil, carries out heat and calculates analysis, obtain
The structure temperature field of 2400～3000 seconds；
The above-mentioned data for changing over (0～3000 second) each time period structure temperature field are carried out into Time Continuous whole
Reason, obtains structure temperature field in 3000 second time result over time.
A kind of integral tank temperature field analysis method of the present invention, is directed to High Mach number aircraft by the way of analogue simulation
Integral tank temperature field analysis, can effectively obtain the change of structure temperature field, and the limit of be not put to the test equipment, experimental enviroment
System, product design cycle is short improve design efficiency, it is easy to popularization and application, with larger practical value.
It is last it is to be noted that：Above example only to illustrate technical scheme, rather than a limitation.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：Which is still
Technical scheme described in foregoing embodiments can be modified, or equivalent is carried out to which part technical characteristic and replace
Change；And these modifications or replacement, do not make the essence of appropriate technical solution depart from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (7)
1. a kind of integral tank temperature field analysis method, it is characterised in that the integral tank temperature field analysis method include with
Lower step：
Step 1：Integral tank structure simulation model is set up, the fuel space region of integral tank inside configuration is determined；
Step 2：Fuel oil is simulated for fuel space area filling, makes fuel space region form full oil condition；
Step 3：Refined for the simulation fuel oil in the fuel space region, be divided into n-layer；
Step 4：Apply the Aerodynamic Heating data of the aerodynamic surface of time dependent integral tank structure；
Step 5：Fuel consumption and filling gas simulation are carried out by ladder analogy method；
Step 6：Obtain change of the integral tank structure temperature after ladder analogy method carries out fuel consumption simulation with the time
Change result.
2. integral tank temperature field analysis method as claimed in claim 1, it is characterised in that body list is adopted in the step 2
Unit's simulation fuel oil.
3. integral tank temperature field analysis method as claimed in claim 2, it is characterised in that the step 3 is specially：Using
Body unit is refined to simulating fuel oil, and is divided into the body unit of the n-layer.
4. integral tank temperature field analysis method as claimed in claim 3, it is characterised in that n >=5.
5. integral tank temperature field analysis method as claimed in claim 4, it is characterised in that the joggle die in the step 5
Plan method is specially：Fuel consumption is to reduce linearly over time, and arranges consumption second total time t, and each m second consumes one layer of combustion
The body unit of oil, while filling the gas of one layer of body unit volume；Wherein, n × m=t.
6. integral tank temperature field analysis method as claimed in claim 5, it is characterised in that the fuel consumption is with the time
It is linear to reduce, and consumption second total time t is set, each m second consumes the body unit of one layer of fuel oil, while filling one layer of body unit
The gas of volume is specially：
Within 0 to the m second calculating times, the convection transfer rate and temperature between fuel oil and integral tank structure is set, heat is carried out
Analysis is calculated, the initial integral tank structure temperature distribution of 0 to m seconds is obtained；
Within m to the 2m second calculating times, at the m seconds, ground floor body unit attribute is changed to into the attribute of gas by the attribute of fuel oil,
The initial integral tank structure temperature distribution is applied in integral tank structure as primary condition, fuel oil and entirety are set
Convection transfer rate and temperature between Oiltank structure, the convection transfer rate between gas and integral tank structure and temperature,
Convection transfer rate and temperature between gas and fuel oil, carries out heat and calculates analysis, obtains the second integral tank knot of m to 2m seconds
Structure temperature field；
Within nm-2m to the nm-m second calculating times, at the nm-2m seconds, n-2 layer body unit attributes are changed to into gas by the attribute of fuel oil
The attribute of body, is applied to the second integral tank structure temperature field as primary condition in integral tank structure, arrange fuel oil with
Convection transfer rate and temperature between integral tank structure, the convection transfer rate between gas and integral tank structure and temperature
Degree, the convection transfer rate between gas and fuel oil and temperature, carry out heat and calculate analysis, obtain the 3rd integral tank structure temperature
；
Within nm-m to the nm second calculating times, at the nm-m seconds, n-1 layer body unit attributes are changed to into gas by the attribute of fuel oil
Attribute, is applied to the 3rd integral tank structure temperature field as primary condition in integral tank structure, arranges fuel oil and entirety
Convection transfer rate and temperature between Oiltank structure, the convection transfer rate between gas and integral tank structure and temperature,
Convection transfer rate and temperature between gas and fuel oil, carries out heat and calculates analysis, obtain the 4th integral tank structure temperature field.
7. integral tank temperature field analysis method as claimed in claim 6, it is characterised in that the acquisition is simulated by ladder
Method carries out the structure temperature after fuel consumption simulation, and result is specially over time：
By the first integral tank structure temperature field, the second integral tank structure temperature field, the 3rd integral tank structure temperature field with
And the 4th integral tank structure temperature field carry out Time Continuous arrangement, obtain the integral tank structure in t times second with the time
The result of change.
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| CN201611176702.0A CN106529096A (en) | 2016-12-19 | 2016-12-19 | Analyzing method for temperature field of integral fuel tank |
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| CN201611176702.0A CN106529096A (en) | 2016-12-19 | 2016-12-19 | Analyzing method for temperature field of integral fuel tank |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109117519A (en) * | 2018-07-18 | 2019-01-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of analogy method of Oiltank structure transient state temperature field |
| CN113353286A (en) * | 2021-06-11 | 2021-09-07 | 南京航空航天大学 | Thermal analysis method for multi-compartment oil tank of helicopter |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103034744A (en) * | 2011-10-08 | 2013-04-10 | 唐文献 | Simulation method of temperature field of cylinder head of low-speed diesel engine |
| CN104834781A (en) * | 2015-05-08 | 2015-08-12 | 国网河南省电力公司电力科学研究院 | Transient temperature field simulation method based on multiple commutation failures of smoothing reactor |
-
2016
- 2016-12-19 CN CN201611176702.0A patent/CN106529096A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103034744A (en) * | 2011-10-08 | 2013-04-10 | 唐文献 | Simulation method of temperature field of cylinder head of low-speed diesel engine |
| CN104834781A (en) * | 2015-05-08 | 2015-08-12 | 国网河南省电力公司电力科学研究院 | Transient temperature field simulation method based on multiple commutation failures of smoothing reactor |
Non-Patent Citations (2)
| Title |
|---|
| 任青梅等: "气动加热与结构温度场耦合分析平台研发技术", 《强度与环境》 * |
| 任青梅等: "飞机整体油箱三维瞬态温度场分析", 《航空科学技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109117519A (en) * | 2018-07-18 | 2019-01-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of analogy method of Oiltank structure transient state temperature field |
| CN113353286A (en) * | 2021-06-11 | 2021-09-07 | 南京航空航天大学 | Thermal analysis method for multi-compartment oil tank of helicopter |
| CN113353286B (en) * | 2021-06-11 | 2022-06-17 | 南京航空航天大学 | Thermal analysis method for multi-compartment oil tank of helicopter |
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Application publication date: 20170322 |