Iterative method-based temperature simulation prediction method for heat-proof and heat-insulation oil tank

Abstract

The invention discloses a heat-proof and heat-insulation oil tank temperature simulation prediction method based on an iteration method, and belongs to the technical field of instantaneous oil temperature prediction of oil storage wings and rudder wings. The problem that the instantaneous oil temperature of an aircraft oil storage wing and a rudder wing is difficult to predict is solved. Comprising the following steps: abstracting a wing or a rudder wing with an oil tank into three parts, namely an outer-layer surface, a middle heat insulation layer and an inner-layer oil tank, and establishing an abstracted wing and rudder wing three-dimensional model; performing network division to obtain a three-dimensional model after grid division; and through an iteration method, a curve formed by multiple segments of piecewise functions is obtained, and the curve is a final temperature prediction curve. The method is used for oil tank temperature prediction.

Description

Technical Field

[0001] The invention relates to an iterative method-based method for simulating and predicting the temperature of an anti-insulation oil tank, and belongs to the technical field of instantaneous oil temperature prediction of oil storage wings and rudder wings. Background Art

[0002] With the continuous development of aerospace technology, hypersonic aircraft are also constantly updated, and their flight speed is getting faster and faster. Due to the existence of the "thermal barrier effect", the faster the flight speed, the higher the temperature of its skin, which has a great impact on the safety of the aircraft's fuel tank. Therefore, the fuel tank structure of hypersonic aircraft is generally treated with heat insulation.

[0003] However, different structures, different flight speeds, and different fuel storage capacities will all have an impact on the heat-insulating effect, which greatly affects the design of the fuel tank and heat-insulating structure. Traditional fuel tank temperature measurement generally uses thermocouples, infrared, and other methods, which is not only inconvenient to measure, but also limits the measurable timeline and space area, which is not conducive to mastering the temperature change law. The simulation method can realize the full process analysis on the timeline and space point, which has great advantages, but the current simulation method is still immature and cannot make real-time adjustments to the change in the conduction coefficient. Therefore, the prediction accuracy is not enough. At present, there is an urgent need for an accurate heat-insulating fuel tank prediction method, which is an important part of the design of hypersonic aircraft.

[0004] At present, the oil temperature of the oil storage wings and rudder wings of this type of aircraft is generally measured experimentally using thermocouples, infrared rays, etc., or simply predicted based on production experience. Nowadays, the service environments of various aircraft are different, and the requirements for the oil temperature of the fuel tank at different time periods during the entire flight process are very different. Therefore, when faced with new insulation materials and insulation structures for oil storage wings and rudder wings, there is a lack of an effective means to predict the oil temperature, especially the oil temperature at a certain fixed time. The use of traditional design experiments to measure the temperature of the oil temperature not only greatly increases the research and development cost of new aircraft, but also seriously slows down the design pace of the aircraft. Therefore, there is an urgent need for an effective method to predict the instantaneous oil temperature of the oil storage wings and rudder wings, so as to detect the oil temperature change law of the oil storage structure in advance. Summary of the invention

[0005] In view of the problem that it is difficult to predict the instantaneous oil temperature of an aircraft oil storage wing and a rudder wing, the present invention provides a temperature simulation prediction method for an anti-insulation oil tank based on an iteration method.

[0006] The invention discloses an iterative method for predicting the temperature of an anti-insulated oil tank, comprising:

[0007] Abstract the wing or rudder with fuel tank into three parts: outer surface, middle insulation layer and inner fuel tank, and establish the abstracted 3D model of wing and rudder;

[0008] Dividing the three-dimensional model of the wing and the rudder into grids based on material properties to obtain a three-dimensional model after grid division;

[0009] The thermodynamic simulation time T is set, the flight ambient temperature is inputted at the outermost side of the outer surface of the three-dimensional model after meshing, the initial forced convection coefficient h0 is inputted at the inner surface of the inner fuel tank, and the initial value of the oil temperature c0 is set, and the initial temperature change curve is calculated; the vertical line corresponding to the time point t1 when the heating rate approaches zero in the initial temperature change curve is used as the convection forced line L0, and the convection forced line L0 divides the initial temperature change curve into two time periods, t0 to t1 and t1 to T; the t0 to t1 time period of the initial temperature change curve is fitted as the first section of the fuel tank heating curve; in the t0 to t1 time period, the oil temperature is heated from c0 to c1 at a fixed heating rate;

[0010] Then, the current forced convection coefficient h1 is input into the inner surface of the inner oil tank of the three-dimensional model after meshing, and the current oil temperature is set to c1; the current temperature change curve of the time period t0 to t1 based on the initial temperature change curve is calculated; the vertical line corresponding to the time point t2 of the maximum sudden drop in the heating rate in the current temperature change curve is used as the convection forced line L1, and the convection forced line L1 further divides the time period t1 to T of the current temperature change curve into two time periods t1 to t2 and t2 to T; the time period t1 to t2 of the current temperature change curve is fitted as the second section of the oil tank heating curve; in the time period t1 to t2, the oil temperature is heated from c1 to c2 at a fixed heating rate;

[0011] Continue to iterate until the convection force line Ln corresponding to time T is obtained, the nth segment of the fuel tank temperature rise curve is fitted, the complete fitted fuel tank temperature rise curve is obtained, and the fuel tank temperature value at time T is determined.

[0012] According to the temperature simulation prediction method of the anti-insulated oil tank based on the iteration method of the present invention, the outer surface corresponds to all components of the wing or rudder wing exposed to the outer air and the connection parts with the aircraft;

[0013] The inner oil tank corresponds to the oil storage tank;

[0014] The middle heat-insulating layer corresponds to all components between the outer surface and the inner oil tank.

[0015] According to the anti-insulation oil tank temperature simulation prediction method based on iteration method of the present invention, the three-dimensional model of the wing and the rudder wing is established by using 3D modeling software.

[0016] According to the temperature simulation prediction method of the anti-insulation oil tank based on the iteration method of the present invention, the temperature change curve of the three-dimensional model after meshing is calculated based on the transient thermal analysis of Ansys software.

[0017] According to the anti-insulation oil tank temperature simulation prediction method based on iteration method of the present invention, the current forced convection coefficient h1 is the convection coefficient of the remaining oil and gas in the current oil storage tank after mixing.

[0018] According to the anti-insulation oil tank temperature simulation prediction method based on iteration method of the present invention, the oil is in liquid, gaseous or gas-liquid mixed state.

[0019] According to the anti-insulation oil tank temperature simulation prediction method based on iteration method of the present invention, the oil is in a heat dissipation state of natural convection.

[0020] According to the anti-insulation oil tank temperature simulation prediction method based on iteration method of the present invention, the forced convection coefficient of each section is expressed as h(n-1), h(n-1) is the average convection coefficient in the oil tank during the time period t(n-1) to tn; n is not less than 3.

[0021] According to the anti-insulation oil tank temperature simulation prediction method based on iteration method of the present invention, the thermodynamic simulation time T is not less than 100s.

[0022] According to the anti-insulation oil tank temperature simulation prediction method based on the iteration method of the present invention, the fitting method for obtaining the oil tank temperature rise curve is: selecting no less than 5 points that do not contain obvious anomalies on the corresponding segment of the temperature change curve, using the least squares method to perform linear regression analysis, and obtaining the corresponding fitting segment.

[0023] Beneficial effects of the present invention: The present invention proposes a simulation prediction method that can modify parameters in different time periods to approximate the actual measured temperature of the oil tank by using simulation software and iterative thinking.

[0024] The method of the present invention is used to predict the oil temperature of oil storage wings and rudder wings, and can predict the oil temperature of oil storage wings and rudder wings at any time in a high temperature environment without designing experiments. The predicted segmented temperature curve can not only determine the instantaneous temperature at a certain time point, but also more clearly observe the change law of oil temperature, so as to more simply and conveniently evaluate the thermal insulation material and the thermal insulation effect of the thermal insulation material.

[0025] Compared with the traditional simple and crude simulation method, the present invention uses an iterative method to perform calculations step by step to approximate the real temperature rise curve. While ensuring the accuracy of the final predicted temperature, it also solves the dilemma that traditional thermal simulation cannot predict the instantaneous temperature. The simulated temperature cloud map obtained through iteration can also observe abnormal oil temperature conditions and provide specific structural locations where thermal bridges are formed and the temperature is difficult to control. This greatly reduces the trial and error cost of the insulation structure of the oil storage wing and the rudder wing, and facilitates the optimization of specific inappropriate insulation structures.

[0026] When the method of the present invention is used for new thermal insulation materials and thermal insulation structures of oil storage wings and rudder wings, its iterative method can accurately predict the oil temperature distribution state of oil storage wings and rudder wings at different time points, and can also simply and quickly predict the change law of oil temperature over time of complex oil storage structures. It greatly reduces the time and practical cost of verifying the rationality of rudder wing oil storage structure or thermal insulation results, and provides more detailed optimization suggestions. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of a rudder wing with a fuel tank;

[0028] Figure 2 Yes Figure 1 Schematic diagram of the split after abstract processing; in the figure, 11 is the outer surface, 12 is the middle insulation layer, and 13 is the inner oil tank;

[0029] Figure 3 This is a schematic diagram of mesh division of the 3D model of the rudder wing with fuel tank;

[0030] Figure 4 It is a schematic diagram of the initial temperature change curve obtained by a simulation using the method of the present invention; in the figure, c represents the oil temperature;

[0031] Figure 5 It is a predicted temperature change diagram after the present invention finally completes the iteration;

[0032] Figure 6 is a schematic diagram of a rudder wing with a fuel tank in Embodiment 1;

[0033] Figure 7 yes Figure 6 Schematic diagram of the split after abstract processing;

[0034] Figure 8 is a schematic diagram of mesh division of the oil storage rudder wing after abstract processing in the first embodiment;

[0035] Fig. 9 is a schematic diagram of an initial temperature change curve in a simulation in Example 1;

[0036] Fig.10 is a schematic diagram of a linear curve of oil tank temperature rise after complete fitting in Example 1;

[0037] Fig.11 This is a temperature change curve result diagram of the final prediction of Example 1;

[0038] Fig.12 is a temperature distribution cloud diagram of the final temperature prediction of the first embodiment;

[0039] Fig.13 This is a physical picture of the temperature measurement experimental design in the comparative experiment;

[0040] Fig.14 It is a temperature curve chart after actual testing in the comparative experiment. DETAILED DESCRIPTION

[0041] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0042] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0043] The present invention will be further described below in conjunction with the accompanying drawings, but is not intended to be a limitation of the present invention.

[0044] Specific implementation method 1. Combination Figures 1 to 5 As shown, the present invention provides a temperature simulation prediction method for an anti-insulation oil tank based on an iteration method, comprising:

[0045] Abstract the wing or rudder with fuel tank into three parts: outer surface, middle insulation layer and inner fuel tank, and establish the abstracted 3D model of wing and rudder;

[0046] According to the basic properties of materials of different components of the wing or rudder wing, the three-dimensional model of the wing and rudder wing is meshed to obtain a three-dimensional model after meshing;

[0047] The thermodynamic simulation time T is set, the flight ambient temperature is inputted at the outermost side of the outer surface of the three-dimensional model after meshing, the initial forced convection coefficient h0 is inputted at the inner surface of the inner fuel tank, and the initial value of the oil temperature c0 is set, and the initial temperature change curve is calculated; the vertical line corresponding to the time point t1 when the heating rate approaches zero in the initial temperature change curve is used as the convection forced line L0, and the convection forced line L0 divides the initial temperature change curve into two time periods, t0 to t1 and t1 to T; the t0 to t1 time period of the initial temperature change curve is fitted as the first section of the fuel tank heating curve; in the t0 to t1 time period, the oil temperature is heated from c0 to c1 at a fixed heating rate;

[0048] Then, the current forced convection coefficient h1 is input into the inner surface of the inner oil tank of the three-dimensional model after meshing, and the current oil temperature is set to c1; the current temperature change curve of the time period t0 to t1 based on the initial temperature change curve is calculated; the vertical line corresponding to the time point t2 of the maximum sudden drop in the heating rate in the current temperature change curve is used as the convection forced line L1, and the convection forced line L1 further divides the time period t1 to T of the current temperature change curve into two time periods t1 to t2 and t2 to T; the time period t1 to t2 of the current temperature change curve is fitted as the second section of the oil tank heating curve; in the time period t1 to t2, the oil temperature is heated from c1 to c2 at a fixed heating rate;

[0049] Continue to iterate until the convection force line Ln corresponding to time T is obtained, the nth segment of the fuel tank temperature rise curve is fitted, the complete fitted fuel tank temperature rise curve is obtained, and the fuel tank temperature value at time T is determined.

[0050] The parameter input of the three-dimensional model after meshing can be realized by using Transient Thermal of Ansys software. In the temperature rise curve of the oil tank after fitting, the section from t0 to t1 is a linear temperature rise curve. In the time period of t1, the oil temperature rises from c0 to c1 at a fixed temperature rise rate. Using the secondary command of Ansys software, the current fitting curve is input into the new thermal simulation. At this time, the internal oil temperature will rise from c0 to c1 from 0 to t1, and c1 will remain unchanged from t1 to T. The convection coefficient in the time period from 0 to t1 is h0, and the convection coefficient in the time period from t1 to T is h1. h1 is the new convection coefficient after the oil volume is reduced and the remaining oil tank is a mixture of oil and gas. After recalculation, a new temperature change curve is obtained. At this time, the temperature change curve is divided into three parts from t0 to t1, t1 to t2, and t2 to T by the convection force lines L1 and L0. L1 is the vertical line where the temperature change curve has the maximum point of sudden drop in the temperature rise rate.

[0051] Then, the temperature change curve is constructed based on the iteration results and the final temperature prediction value is output:

[0052] Repeat the above iteration process to the nth iteration. At this time, the oil temperature in each section of 0~t1, t1~t2...t(n-1)~T increases linearly at its own constant heating rate, and the oil temperature is finally raised to cn. The obtained curve composed of multiple segmented functions is the final temperature prediction curve. The final oil temperature cn is the predicted final oil temperature of the wing or rudder wing oil storage tank at the specified time point. The oil temperature prediction at other time points can also be observed based on the prediction curve.

[0053] Combination Figure 2 As shown, the outer surface corresponds to all components of the wing or rudder wing exposed to the outer air and the connection parts with the aircraft;

[0054] The inner oil tank corresponds to the oil storage tank;

[0055] The middle thermal insulation layer corresponds to all components between the outer surface and the inner oil tank, such as thermal insulation filling materials, structural support skeletons, etc.

[0056] In this implementation, when meshing the outer surface, the middle insulation layer, and the inner oil tank, the meshing of each abstract component needs to remain independent of each other.

[0057] Furthermore, the three-dimensional model of the wing and the rudder wing is established using any 3D modeling software.

[0058] As an example, according to the required model size, the wing and rudder 3D model is established using Solidworks software.

[0059] As an example, the temperature variation curve of the three-dimensional model after meshing is calculated based on transient thermal analysis of Ansys software.

[0060] In this embodiment, the current forced convection coefficient h1 is the convection coefficient of the remaining oil in the current oil storage tank after mixing with the gas.

[0061] The oil needs to be kept in a liquid, gaseous or gas-liquid mixed state at all times.

[0062] The oil is in a state of heat dissipation by natural convection, without any additional heat dissipation device.

[0063] As an example, the thermodynamic simulation time T is not less than 100 s.

[0064] As an example, 300°C≦ambient temperature C≦900°C.

[0065] In this embodiment, the ambient temperature C and the initial value of the oil temperature c0 can both be given by actual flight service conditions.

[0066] All convection coefficients can be calculated or given based on experience according to the aircraft's state, the fuel storage material, and specific fuel consumption conditions.

[0067] Furthermore, the fitting method for obtaining the fuel tank temperature rise curve is: selecting no less than 5 points without obvious anomalies on the corresponding segment of the temperature change curve, using the least squares method or other statistical tools and programming tools to perform linear regression analysis, and obtaining the corresponding fitting segment.

[0068] In this embodiment, the forced convection coefficient of each section is expressed as h(n-1), where h(n-1) is the average convection coefficient in the fuel tank during the time period t(n-1) to tn; n is not less than 3.

[0069] In this embodiment, the temperature change curve obtained by iteration is not necessarily equal in each time period. The curve obtained by each iteration is fitted into a linear curve before entering the next iteration. The final temperature prediction curve is a piecewise composite function composed of multiple linear functions.

[0070] The technical solution of the method of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention.

[0071] Embodiment 1, combined with Figures 6 to 12 Specific instructions:

[0072] A temperature simulation prediction method for an anti-insulation oil tank based on an iteration method is carried out in the following steps:

[0073] Step 1: Abstract processing and modeling of the wings and rudders with fuel tanks;

[0074] Will Figure 6 The rudder wing with fuel tank is abstractly composed of three parts: outer surface 11, middle insulation layer 12, and inner fuel tank 13. The outer surface includes all components of the rudder wing exposed to the outer air and the connection part with the aircraft; the inner fuel tank refers to the fuel storage tank; the middle insulation layer includes insulation filling materials and structural support frame. The abstracted rudder wing three-dimensional model is established using Solidworks software, as shown in the figure. Figure 7 As shown;

[0075] Step 2: Preliminary thermal simulation of fuel tank temperature:

[0076] According to the basic material properties of different components of the wing or rudder wing, the three-dimensional model is divided into grids. Figure 8 As shown in the figure, the transient thermal function of Ansys software is used to input the thermodynamic simulation time of 1000s, the temperature encountered during flight is input as 650°C on the outermost side of the outer layer surface 11, and the forced convection is input on the inner surface of the inner layer tank 13, with a convection coefficient of 5×10 5 W / mm·℃, the initial temperature of the internal oil temperature is constant at 22℃. After calculating the results, the temperature change curve 21 is obtained, such as Fig. 9 shown.

[0077] Step 3: Post-processing and iterative process of simulation results:

[0078] According to the temperature change curve 21 of the initial simulation result, it is divided into two parts, 0-249s and 249s-1000s, by the convection force line L0. L0 is the vertical line at the time point when the heating rate of the temperature change curve 21 approaches zero. The 0-249s segment curve is fitted into a linear heating curve, as shown in Fig.10As shown, it means that in the time period from 0 to 249s, the oil temperature rises from 22℃ to 30.22℃ at a heating rate of 0.032℃ / s. Using the secondary command of Ansys software, the result is input into the new thermal simulation. At this time, the internal oil temperature will rise from 22℃ to 30.22℃ from 0 to 249s, and remain at 30.22℃ from 249s to 1000s. The convection coefficient from 0 to 249s is 5×105W / mm·℃, and the convection coefficient from 249s to 1000s is 4.8×10 5 W / mm·℃. After calculating the result again, the temperature change curve 22 is obtained. At this time, the temperature change curve 22 is divided into three parts of 0-249s, 249-529s, and 529s-1000s by the convection force lines L1 and L0. L1 is the vertical line where the maximum point of the sudden drop in the heating rate of the temperature change curve 22 is located.

[0079] Step 4: Construct the temperature change curve based on the iteration results and output the final temperature prediction value:

[0080] Repeat the above iteration process to the third iteration. At this time, the oil temperature is linearly increased at a constant heating rate of 0.032℃ / s, 0.035℃ / s, 0.036℃ / s, and 0.038℃ / s in 0~249s, 249~529s, 529s~768s, and 768s~1000s, and the oil temperature is finally raised to 61.2℃. The obtained curve composed of multiple segmented functions, that is, the final temperature prediction curve is as follows Fig.11 As shown, the final oil temperature c4 is the predicted final oil temperature of the wing or rudder oil storage tank at a specified time point. The oil temperature prediction at other time points can also be observed based on the prediction curve. And further obtain Fig.12 The temperature distribution cloud diagram shown can be used to observe abnormal oil temperature conditions and provide specific structural locations where thermal bridges are formed and the temperature is difficult to control.

[0081] Comparative experiment: Combination Fig.13 Specifically, this experiment adopts the traditional actual test measurement method, designs and carries out the actual measurement test of the thermal insulation of the simulated rudder wing under the same parameters as the embodiment, and its various parameters are the same as the embodiment 1. At the same time, for the safety of the experiment, a large-sized heating chamber is selected instead of a small heating furnace to simulate the high temperature of 650°C outside. Finally, the actual temperature rise curve is obtained as follows Fig.14 It is not difficult to find that the results of the traditional design actual test are basically consistent with the prediction results of Example 1. However, the method of the present invention greatly simplifies the process of predicting the thermal insulation of the rudder and wing structure, greatly reduces the cost of evaluating and predicting the thermal insulation performance under different structures, thereby accelerating the design and optimization of the thermal insulation of the rudder and wing structure.

[0082] In addition to aerospace vehicles, other fields such as rockets or missiles can also adopt the solution ideas and solutions of the method of the present invention when facing the problem of instantaneous temperature prediction of heat-insulated oil tanks. Similar methods and solutions for solving temperature prediction problems using iterative methods are all within the protection scope of this patent.

[0083] The present application has been described in detail above in conjunction with specific implementation methods and exemplary embodiments, and these descriptions are not to be construed as limitations on the present application. Those skilled in the art will appreciate that, without departing from the spirit and scope of the present application, a variety of equivalent replacements, modifications or improvements may be made to the technical solution of the present application and its implementation methods, all of which fall within the scope of the present application. The scope of protection of the present application shall be subject to the attached claims.

Claims

1. A temperature simulation prediction method for an anti-insulation oil tank based on an iteration method, characterized in that: include, Abstract the wing or rudder with fuel tank into three parts: outer surface, middle insulation layer and inner fuel tank, and establish the abstracted three-dimensional model of the wing and rudder; Dividing the three-dimensional model of the wing and the rudder into grids based on material properties to obtain a three-dimensional model after grid division; The thermodynamic simulation time T is set, the flight ambient temperature is inputted at the outermost side of the outer surface of the three-dimensional model after meshing, the initial forced convection coefficient h0 is inputted at the inner surface of the inner fuel tank, and the initial value of the oil temperature c0 is set, and the initial temperature change curve is calculated; the vertical line corresponding to the time point t1 when the heating rate approaches zero in the initial temperature change curve is used as the convection forced line L0, and the convection forced line L0 divides the initial temperature change curve into two time periods, t0 to t1 and t1 to T; the t0 to t1 time period of the initial temperature change curve is fitted as the first section of the fuel tank heating curve; in the t0 to t1 time period, the oil temperature is heated from c0 to c1 at a fixed heating rate; Then, the current forced convection coefficient h1 is input into the inner surface of the inner oil tank of the three-dimensional model after meshing, and the current oil temperature is set to c1; the current temperature change curve of the time period t0 to t1 based on the initial temperature change curve is calculated; the vertical line corresponding to the time point t2 of the maximum sudden drop in the heating rate in the current temperature change curve is used as the convection forced line L1, and the convection forced line L1 further divides the time period t1 to T of the current temperature change curve into two time periods t1 to t2 and t2 to T; the time period t1 to t2 of the current temperature change curve is fitted as the second section of the oil tank heating curve; in the time period t1 to t2, the oil temperature is heated from c1 to c2 at a fixed heating rate; Continue to iterate until the convection force line Ln corresponding to time T is obtained, the nth segment of the fuel tank temperature rise curve is fitted, the complete fitted fuel tank temperature rise curve is obtained, and the fuel tank temperature value at time T is determined.

2. The method for simulating and predicting the temperature of an anti-insulated oil tank based on an iteration method according to claim 1 is characterized in that: The outer surface corresponds to all components of the wing or rudder exposed to the outer air and the connection parts with the aircraft; The inner oil tank corresponds to the oil storage tank; The middle heat-insulating layer corresponds to all components between the outer surface and the inner oil tank.

3. The temperature simulation prediction method of the anti-insulation oil tank based on the iteration method according to claim 1 is characterized in that: The three-dimensional models of the wing and the rudder wing are established using 3D modeling software.

4. The method for simulating and predicting the temperature of an anti-insulated oil tank based on an iteration method according to claim 1 is characterized in that: The temperature variation curve of the three-dimensional model after meshing is calculated based on transient thermal analysis of Ansys software.

5. The temperature simulation prediction method of the anti-insulation oil tank based on the iteration method according to claim 1 is characterized in that: The current forced convection coefficient h1 is the convection coefficient of the remaining oil and gas in the current oil storage tank after mixing.

6. The method for simulating and predicting the temperature of an anti-insulated oil tank based on an iteration method according to claim 5 is characterized in that: The oil is in a liquid state, a gaseous state or a gas-liquid mixed state.

7. The method for simulating and predicting the temperature of an anti-insulated oil tank based on an iteration method according to claim 5 is characterized in that: The oil is in a heat dissipation state of natural convection.

8. The method for simulating and predicting the temperature of an anti-insulated oil tank based on an iteration method according to claim 1 is characterized in that: The forced convection coefficient of each section is expressed as h(n-1), where h(n-1) is the average convection coefficient in the fuel tank during the time period t(n-1) to tn; n is not less than 3.

9. The method for simulating and predicting the temperature of an anti-insulated oil tank based on an iteration method according to claim 1, characterized in that: The thermodynamic simulation time T is not less than 100s.

10. The temperature simulation prediction method of the anti-insulation oil tank based on the iteration method according to claim 1 is characterized in that: The fitting method for obtaining the fuel tank temperature rise curve is as follows: selecting no less than 5 points without obvious anomalies on the corresponding segment of the temperature change curve, performing linear regression analysis using the least squares method, and obtaining the corresponding fitting segment.

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