CN114662369B - Method for evaluating large-gradient extremely-high-temperature thermal strength of complex curved surface structure of aerospace plane - Google Patents
Method for evaluating large-gradient extremely-high-temperature thermal strength of complex curved surface structure of aerospace plane Download PDFInfo
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Abstract
The invention discloses a method for evaluating the large-gradient ultrahigh-temperature thermal strength of a complex curved surface structure of an aerospace plane, which relates to the technical field of plane design and comprises the following steps: s1, intercepting the actual characteristic data; s2, performing a heat strength experiment; s3, constructing a thermal intensity calculation model; s4, comparing the data; s5, performing secondary hot strength experiment; s6, secondarily constructing a thermal strength calculation model; s7, carrying out secondary data comparison; s8, performing weighted calculation on the final strain value; and S9, performing weighted calculation on the displacement final value. The invention discloses a large-gradient extremely-high-temperature heat intensity evaluation method for a complex curved surface structure of an aerospace plane, and provides an accurate and comprehensive heat intensity evaluation method for the complex curved surface structure of the aerospace plane under the environment of large gradient, rapid time change and extremely high temperature, so that theoretical support is provided for development of the aerospace plane.
Description
Technical Field
The invention relates to the technical field of airplane design, in particular to a method for evaluating the large-gradient extremely-high-temperature thermal strength of a complex curved surface structure of an aerospace airplane.
Background
In the aerospace field, with strong military requirements and advanced technical promotion, hypersonic aerospace planes become tip weaponry researched and developed by countries in the world of twenty-first century. In the technical field of aircraft design, accurate thermal strength evaluation is carried out on key structural components of the aerospace aircraft, and the method is an indispensable link in the aerospace aircraft development process.
The nose cone is a key structural component of the aerospace plane, generally has a complex curved surface appearance, and is called as a complex curved surface structure in the invention. In the flight process of the aerospace plane, the complex curved surface structure is in a large-gradient fast-time-varying extremely high-temperature environment, namely: the surface temperature gradient value of the complex curved surface structure is large, for example, the temperature difference of each centimeter can reach more than 100 ℃; the surface temperature of the complex curved surface structure has the characteristic of quick time change, for example, the temperature of the same position of the surface of the structure changes with time and can reach about 200 ℃/s; local areas of complex curved structures are at extremely high temperatures, for example around 1800 c is possible in the apex region. The large-gradient fast-time-varying extreme high-temperature environment is combined with the complex curved surface appearance of the nose cone, so that the corresponding accurate heat intensity evaluation is full of challenges.
Aiming at the nose cone of the aerospace plane, namely a complex curved surface structure, the thermal strength evaluation under the large-gradient fast-time-varying extremely high-temperature environment is developed, and at present, two main means are provided: firstly, the heat intensity evaluation is completed through numerical calculation, and secondly, the heat intensity evaluation is completed through ground experiments. Based on numerically calculated heat strength assessment, there are major problems: the heat intensity calculation model of the complex curved surface structure in the large-gradient fast-time-varying extremely high-temperature environment cannot completely reflect the real structural state, so that the heat intensity evaluation is inaccurate; based on the heat intensity evaluation of the ground experiment, there are main problems: strain data of a large curvature part (such as a corner/turning edge) and a high-temperature part above 1000 ℃ of the complex curved surface structure in the experimental process are difficult to obtain, so that the thermal strength characteristic of the complex curved surface structure cannot be comprehensively mastered, and the corresponding thermal strength evaluation is not comprehensive.
In view of the main problems of the two evaluation means, which cannot be solved later, how to realize accurate and comprehensive thermal strength evaluation for a complex curved surface structure in a large-gradient rapid-change extremely high-temperature environment becomes one of the key problems in the aerospace plane development process at present, and a corresponding technical invention is urgently needed.
Disclosure of Invention
Aiming at the existing problems, the invention provides a method for evaluating the large-gradient ultrahigh-temperature thermal strength of a complex curved surface structure of an aerospace plane.
The technical scheme of the invention is as follows:
a method for evaluating the large-gradient ultrahigh-temperature thermal strength of a complex curved surface structure of an aerospace plane comprises the following steps:
s1, intercepting actual characteristic data: selecting large-gradient fast-time-varying extreme high-temperature environment actual characteristic data of a complex curved surface structure of the aerospace plane, wherein the selected actual characteristic data are a temperature gradient value, a temperature-time-varying speed rate value and a temperature peak value, multiplying the selected actual characteristic data by 1/3-1/2 respectively to realize equal-proportion adjustment of the large-gradient fast-time-varying extreme high-temperature environment actual characteristic data in an original state, and taking intercepted data as an intercepted state value of the actual characteristic data;
s2, heat strength test: in the thermal intensity laboratory, the intercepted state value of the actual characteristic data obtained in the step S1 is applied to the complex curved surface structure of the aerospace plane, a high-temperature strain sensor and a displacement sensor are arranged on the complex curved surface structure, and the measured value is measuredStrain data L of complex curved surface structure under heat intensity experiment 1 And displacement data M 1 ；
S3, constructing a heat intensity calculation model: importing the intercepted state value of the actual characteristic data obtained in the step S1 into finite element calculation software, constructing a thermal strength calculation model of the complex curved surface structure, and measuring strain data L of the complex curved surface structure under the thermal strength calculation model 2 And displacement data M 2 ；
S4, data comparison: the strain data L obtained in step S2 1 And the strain data L obtained in step S3 2 Comparing the displacement data M obtained in step S2 1 And the displacement data M obtained in step S3 2 Comparing to obtain a relative error C 1 The relative error C 1 The calculation formula of (2) is as follows:
C 1 =（L 2 -L 1 ）/L 1 or C 1 =（M 2 -M 1 ）/M 1 ；
If two sets of relative errors C 1 If any one of the above is more than 5-8%, the heat intensity calculation model in step S3 is corrected to obtain a corrected heat intensity calculation model, and step S3 is repeated to obtain strain data L under the corrected heat intensity calculation model 2 ʹ and displacement data M 2 ʹ, completing a correction cycle;
then the strain data L 2 ʹ and the strain data L 1 Comparing the displacement data M 2 ʹ and the displacement data M 1 Comparing to obtain a relative error C 1 ʹ, the relative error C 1 ʹ is calculated as:
C 1 ʹ=（L 2 ʹ-L 1 ）/L 1 or C 1 ʹ=（M 2 ʹ-M 1 ）/M 1 ；
If two sets of relative errors C 1 If any one of the two groups is more than 5-8%, the correction cycle is carried out again until the two groups of relative errors C 1 n ʹ is less than 5-8%, wherein n is C 1 n ʹ, ʹ, i.e., the number of cycles;
s5, secondary hot strength experiment: in a thermal strength laboratory, the actual characteristic data selected in the step S1 is applied to a complex curved surface structure of the aerospace plane, a high-temperature strain sensor and a displacement sensor are arranged on the complex curved surface structure, and strain data L of the complex curved surface structure under a thermal strength secondary experiment is measured 3 And displacement data M 3 ；
S6, secondary construction of a thermal strength calculation model: importing the actual characteristic data selected in the step S1 into the thermal intensity calculation model corrected in the step S4, and measuring strain data L of the complex curved surface structure under the corrected thermal intensity calculation model 4 And displacement data M 4 ；
S7, secondary data comparison: the strain data L obtained in step S5 3 And the strain data L obtained in step S6 4 Comparing the displacement data M obtained in step S5 3 And the displacement data M obtained in step S6 4 Comparing to obtain a relative error C 2 The relative error C 2 The calculation formula of (2) is as follows:
C 2 =（L 4 -L 3 ）/L 3 or C 2 =（M 4 -M 3 ）/M 3 ；
If two sets of relative errors C 2 If any one of the two is greater than 10-15%, performing secondary correction on the heat intensity calculation model in the step S6 to obtain a secondarily corrected heat intensity calculation model, and repeating the step S6 to obtain strain data L under the secondarily corrected heat intensity calculation model 4 ʹ and displacement data M 4 ʹ, completing a secondary correction cycle;
then the strain data L 4 ʹ and the strain data L 3 Comparing the displacement data M 4 ʹ and the displacement data M 3 Comparing to obtain a relative error C 2 ʹ, the relative error C 2 ʹ is calculated as:
C 2 ʹ=（L 4 ʹ-L 3 ）/L 3 or C 2 ʹ=（M 4 ʹ-M 3 ）/M 3 ；
If two sets of relative errors C 2 ʹ is greater than 10-15%, the above two correction cycles are carried out until the relative errors C are equal to each other 2 n ʹ are all less than 10-15%, and strain data L is obtained correspondingly 4 n ʹ and displacement data M 4 n ʹ, wherein n is the number ʹ, namely the cycle number;
s8, strain final value weighting calculation: the strain data L obtained in step S5 3 Given a weight A 1 The strain data L obtained in step S7 4 n ʹ to give weight A 2 The weighted average value of the two is the final strain value L in the corresponding temperature range, and L = L 3 ×A 1 +L 4 n ʹ×A 2 ；
S9, displacement final value weighting calculation: the displacement data M obtained in step S5 3 Given a weight B 1 The displacement data M obtained in step S7 4 n ʹ to give weight B 2 The weighted average value of the two is the displacement final value M in the corresponding temperature range, M = M 3 ×B 1 +M 4 n ʹ×B 2 。
Further, the complex curved surface structure in the step S1 is a nose cone of an aerospace plane. The nose cone of the aerospace plane is the most representative complex curved surface structure.
Further, in the step S2, the clipped state values of the actual feature data obtained in the step S1 are applied to the complex curved surface structure of the aerospace plane by means of heat radiation. The heat radiation can provide a complex curved surface structure temperature rise closest to the real condition.
Further, in step S5, the actual characteristic data obtained in step S1 is applied to the complex curved surface structure of the aerospace plane by means of heat radiation, and in step S5, if the temperature peak value in the actual characteristic data exceeds the maximum temperature that can be tested by the strain sensor, the maximum temperature that can be tested by the strain sensor is taken when the strain data is tested, the original temperature peak value is kept when the displacement data is tested, and the maximum temperature that can be tested by the strain sensor is also taken when the strain data is tested in step S6, under this condition, the method further includes step S10:
s10, calculating a theoretical final value: importing the actual characteristic data selected in the step S1 into the thermal intensity calculation model corrected in the step S7, and measuring theoretical final strain data L of the complex curved surface structure under the thermal intensity calculation model subjected to secondary correction 5 。
For example, if the actual extreme high temperature reaches 1800 ℃, the used strain sensor can only allow the test of the strain data below 900 ℃, and only the strain data below 900 ℃ can be acquired.
Further, in the step S2, the number of the high-temperature strain sensors is 28 to 33, 9 to 11 high-temperature regions are arranged, the rest high-temperature strain sensors are uniformly distributed in non-extreme high-temperature regions of the complex curved surface structure, the number of the displacement sensors is 3, and one displacement sensor is arranged at each of an extreme high temperature position, a large temperature gradient value position and a position 50cm to 1m away from a constraint point of the complex curved surface structure experimental part. The high-temperature strain sensor is mainly used for high-temperature strain sensors which need to be arranged at extremely high temperature.
Further, in the step S5, the number of the high-temperature strain sensors is 30 to 35, 10 to 12 high-temperature regions are arranged, the rest high-temperature strain sensors are uniformly distributed in non-extreme high-temperature regions of the complex curved surface structure, the number of the displacement sensors is 4, and one displacement sensor is respectively arranged at an extreme high temperature position, a large temperature gradient value position, a position 50cm to 1m away from a constraint point of the complex curved surface structure experimental piece and a position 80cm to 1.2m away from the constraint point of the complex curved surface structure experimental piece. More high temperature strain sensors and displacement sensors are required than in step S2.
Further, the step of correcting the heat intensity calculation model in step S4 and the step of secondarily correcting the heat intensity calculation model in step S7 each include: adjusting the type of a computing unit in the heat intensity computing model, subdividing a unit grid of the heat intensity computing model, adjusting the contact state among components in the heat intensity computing model, and adjusting the basic thermodynamic performance parameters of materials in the heat intensity computing model. The corrected heat intensity calculation model is more accurate.
Further, the stepsIn step S8A 1 A value of 50%, A 2 The value is 50%. The weight coefficient value is obtained according to calculation, experimental state and result reliability.
Further, B in the step S9 1 Value of 70%, B 2 The value is 30%. The weight coefficient value is obtained according to calculation, experimental state and result reliability.
The method for evaluating the large-gradient extremely-high-temperature thermal strength of the aerospace plane complex curved surface structure can also be suitable for complex curved surface structures of other aircrafts, such as hypersonic-speed repeatedly-usable air and ground shuttle aircrafts, hypersonic-speed missiles and other aircraft nose cones.
The invention has the beneficial effects that:
(1) the invention relates to a method for evaluating large-gradient extremely high-temperature thermal strength of a complex curved surface structure of an aerospace plane, which is an accurate and comprehensive thermal strength evaluation method aiming at the complex curved surface structure of the aerospace plane under the environment of large gradient, fast time change and extreme high temperature, and provides theoretical support for development of the aerospace plane;
(2) the method for evaluating the large-gradient extremely-high-temperature thermal strength of the complex curved surface structure of the aerospace plane disclosed by the invention has the advantages of exerting respective calculation and experiment means, skillfully and comprehensively applying calculation results and experiment results in different states, acquiring accurate and comprehensive thermal strength characteristic data of the complex curved surface structure through multiple rounds of interactive iterative verification and correction, making up for the defect of a single means, establishing a principle based on differential weight, realizing the combined application of the calculation results and the experiment results, and finishing the accurate and comprehensive characterization evaluation of the structural thermal strength.
Drawings
FIG. 1 is a process flow chart of a method for evaluating the large-gradient extreme high-temperature thermal strength of a complex curved surface structure of an aerospace plane in embodiment 1 of the invention;
fig. 2 is a process flow chart of a large-gradient extremely high-temperature thermal strength evaluation method for a complex curved surface structure of an aerospace plane in embodiment 2 of the invention.
Detailed Description
Example 1
A method for evaluating the large-gradient ultrahigh-temperature thermal strength of a complex curved surface structure of an aerospace plane comprises the following steps as shown in figure 1:
s1, intercepting actual characteristic data: selecting large-gradient fast-time-varying extreme high-temperature environment actual characteristic data of a complex curved surface structure of the aerospace plane, wherein the complex curved surface structure is a nose cone of the aerospace plane, the selected actual characteristic data are a temperature gradient value, a temperature time-varying speed value and a temperature peak value, multiplying the selected actual characteristic data by 1/2 respectively to realize equal-proportion adjustment of the large-gradient fast-time-varying extreme high-temperature environment actual characteristic data in an original state, and the intercepted data are intercepted state values of the actual characteristic data;
s2, heat strength test: in the heat intensity laboratory, the intercepted state values of the actual feature data obtained in step S1 are applied to the complex curved surface structure of the aerospace plane by means of heat radiation, high-temperature strain sensors and displacement sensors are arranged on a complex curved surface structure, the high-temperature strain sensors and the displacement sensors are all products sold in the market, the high-temperature strain sensors are ZC-NC-G1265-120 strain gages sold by the Weak precision measurement trade (Shanghai) Limited company, the arrangement number of the high-temperature strain sensors is 30, wherein, 10 displacement sensors are distributed in the extreme high temperature area, the rest displacement sensors are uniformly distributed in the non-extreme high temperature area with the complex curved surface structure, the distribution number of the displacement sensors is 3, the strain data L of the complex curved surface structure under the thermal strength experiment is measured by arranging one strain data L at an extremely high temperature position, a large temperature gradient value position and a position 75cm away from a constraint point of the complex curved surface structure experiment piece. 1 And displacement data M 1 ；
S3, constructing a thermal strength calculation model: importing the intercepted state value of the actual characteristic data obtained in the step S1 into finite element calculation software, constructing a thermal strength calculation model of the complex curved surface structure, and measuring strain data L of the complex curved surface structure under the thermal strength calculation model 2 And displacement data M 2 ；
S4, data comparison: the strain data L obtained in step S2 1 And the strain data L obtained in step S3 2 Comparing the displacement data M obtained in step S2 1 And step (d)Displacement data M obtained in S3 2 Comparing to obtain a relative error C 1 Relative error C 1 The calculation formula of (2) is as follows:
C 1 =（L 2 -L 1 ）/L 1 or C 1 =（M 2 -M 1 ）/M 1 ；
If two sets of relative errors C 1 If any one of the above is greater than 6%, the heat intensity calculation model in step S3 is modified, the calculation unit types in the heat intensity calculation model are adjusted, the unit meshes of the heat intensity calculation model are subdivided, the contact state between the components in the heat intensity calculation model is adjusted, the basic thermodynamic performance parameters of the material in the heat intensity calculation model are adjusted to obtain a modified heat intensity calculation model, and step S3 is repeated to obtain the strain data L under the modified heat intensity calculation model 2 ʹ and displacement data M 2 ʹ, completing a correction cycle;
then the strain data L 2 ʹ and strain data L 1 Comparing the displacement data M 2 ʹ and displacement data M 1 Comparing to obtain a relative error C 1 ʹ relative error C 1 ʹ is calculated as:
C 1 ʹ=（L 2 ʹ-L 1 ）/L 1 or C 1 ʹ=（M 2 ʹ-M 1 ）/M 1 ；
If two sets of relative errors C 1 If any one of the two groups is more than 6%, the correction cycle is carried out again until the two groups of relative errors C 1 n ʹ are all less than 6%, wherein n is C 1 n ʹ, ʹ, i.e., the number of cycles;
s5, secondary hot strength experiment: in a thermal intensity laboratory, the actual characteristic data obtained in the step S1 are applied to a complex curved surface structure of the aerospace plane in a thermal radiation mode, high-temperature strain sensors and displacement sensors are distributed on the complex curved surface structure, the distribution number of the high-temperature strain sensors is 33, 11 high-temperature regions are distributed, the rest high-temperature strain sensors are uniformly distributed in non-extreme high-temperature regions of the complex curved surface structure, and the displacement sensors are distributedThe number of the test pieces is 4, wherein one test piece is respectively arranged at an extremely high temperature position, a large temperature gradient value position, a position 75cm away from a constraint point of an experimental piece with a complex curved surface structure and a position 1m away from the constraint point of the experimental piece with the complex curved surface structure, and strain data L of the complex curved surface structure under a thermal strength secondary experiment is measured 3 And displacement data M 3 ；
S6, secondary construction of a thermal strength calculation model: importing the actual characteristic data selected in the step S1 into the thermal intensity calculation model corrected in the step S4, and measuring strain data L of the complex curved surface structure under the corrected thermal intensity calculation model 4 And displacement data M 4 ；
S7, secondary data comparison: the strain data L obtained in step S5 3 And the strain data L obtained in step S6 4 Comparing the displacement data M obtained in step S5 3 And the displacement data M obtained in step S6 4 Comparing to obtain a relative error C 2 Relative error C 2 The calculation formula of (2) is as follows:
C 2 =（L 4 -L 3 ）/L 3 or C 2 =（M 4 -M 3 ）/M 3 ；
If two sets of relative errors C 2 If any one of the two is greater than 12%, secondarily modifying the heat intensity calculation model in the step S6, adjusting the calculation unit type in the heat intensity calculation model, subdividing the unit mesh of the heat intensity calculation model, adjusting the contact state between the components in the heat intensity calculation model, adjusting the basic thermodynamic performance parameters of the material in the heat intensity calculation model to obtain a secondarily modified heat intensity calculation model, and repeating the step S6 to obtain strain data L under the secondarily modified heat intensity calculation model 4 ʹ and displacement data M 4 ʹ, completing a secondary correction cycle;
then the strain data L 4 ʹ and strain data L 3 Comparing the displacement data M 4 ʹ and displacement data M 3 Comparing to obtain a relative error C 2 ʹ relative error C 2 ʹ is calculated as:
C 2 ʹ=（L 4 ʹ-L 3 ）/L 3 or C 2 ʹ=（M 4 ʹ-M 3 ）/M 3 ；
If two sets of relative errors C 2 ʹ is greater than 12%, the above two correction cycles are carried out until the two sets of relative errors C are reached 2 n ʹ are all less than 12%, and strain data L is obtained correspondingly 4 n ʹ and displacement data M 4 n ʹ, wherein n is the number ʹ, namely the cycle number;
s8, strain final value weighting calculation: the strain data L obtained in step S5 3 Given a weight A 1 The strain data L obtained in step S7 4 n ʹ to give weight A 2 ，A 1 A value of 50%, A 2 The value is 50%, the weighted average value of the two is the final strain value L in the corresponding temperature range, and L = L 3 ×A 1 +L 4 n ʹ×A 2 ；
S9, displacement final value weighting calculation: the displacement data M obtained in step S5 3 Given a weight B 1 The displacement data M obtained in step S7 4 n ʹ to give weight B 2 ，B 1 Value of 70%, B 2 The value is 30%, the weighted average value of the two is the final displacement value M in the corresponding temperature range, and M = M 3 ×B 1 +M 4 n ʹ×B 2 。
Example 2
A method for evaluating the large-gradient extremely-high-temperature thermal strength of a complex curved surface structure of an aerospace plane, as shown in figure 2, comprises the following steps:
s1, intercepting actual characteristic data: selecting large-gradient fast-time-varying extreme high-temperature environment actual characteristic data of a complex curved surface structure of the aerospace plane, wherein the complex curved surface structure is a nose cone of the aerospace plane, the selected actual characteristic data are a temperature gradient value, a temperature time-varying speed value and a temperature peak value, multiplying the selected actual characteristic data by 1/2 respectively to realize equal-proportion adjustment of the large-gradient fast-time-varying extreme high-temperature environment actual characteristic data in an original state, and the intercepted data are intercepted state values of the actual characteristic data;
s2, heat strength test: in a thermal intensity laboratory, applying the intercepted state value of the actual characteristic data obtained in the step S1 to a complex curved surface structure of the aerospace plane in a thermal radiation mode, arranging high-temperature strain sensors and displacement sensors on the complex curved surface structure, wherein the arrangement number of the high-temperature strain sensors is 30, 10 high-temperature areas are arranged, the rest high-temperature areas are uniformly distributed in non-extreme high-temperature areas of the complex curved surface structure, the arrangement number of the displacement sensors is 3, one high-temperature area, one large-temperature gradient value area and one test piece constraint point 75cm away from the complex curved surface structure are respectively arranged at the extreme high temperature, and strain data L of the complex curved surface structure under a thermal intensity experiment are measured 1 And displacement data M 1 ；
S3, constructing a heat intensity calculation model: importing the intercepted state value of the actual characteristic data obtained in the step S1 into finite element calculation software, constructing a thermal strength calculation model of the complex curved surface structure, and measuring strain data L of the complex curved surface structure under the thermal strength calculation model 2 And displacement data M 2 ；
S4, data comparison: the strain data L obtained in step S2 1 And the strain data L obtained in step S3 2 Comparing the displacement data M obtained in step S2 1 And the displacement data M obtained in step S3 2 Comparing to obtain a relative error C 1 Relative error C 1 The calculation formula of (2) is as follows:
C 1 =（L 2 -L 1 ）/L 1 or C 1 =（M 2 -M 1 ）/M 1 ；
If two sets of relative errors C 1 If any one of the above is greater than 6%, the heat intensity calculation model in step S3 is modified, the calculation unit types in the heat intensity calculation model are adjusted, the unit meshes of the heat intensity calculation model are subdivided, the contact state between the components in the heat intensity calculation model is adjusted, the basic thermodynamic performance parameters of the material in the heat intensity calculation model are adjusted to obtain a modified heat intensity calculation model, and step S3 is repeated to obtain the modified heat intensity calculation modelStrain data under type L 2 ʹ and displacement data M 2 ʹ, completing a correction cycle;
then the strain data L 2 ʹ and strain data L 1 Comparing the displacement data M 2 ʹ and displacement data M 1 Comparing to obtain a relative error C 1 ʹ relative error C 1 ʹ is calculated as:
C 1 ʹ=（L 2 ʹ-L 1 ）/L 1 or C 1 ʹ=（M 2 ʹ-M 1 ）/M 1 ；
If two sets of relative errors C 1 If any one of the two groups is more than 6%, the correction cycle is carried out again until the two groups of relative errors C 1 n ʹ are all less than 6%, wherein n is C 1 n ʹ, ʹ, i.e., the number of cycles;
s5, secondary hot strength experiment: in a heat intensity laboratory, the actual characteristic data selected in the step S1 is applied to a complex curved surface structure of the aerospace plane in a heat radiation manner, if a temperature peak value in the actual characteristic data exceeds the maximum testable temperature of the strain sensor, the maximum testable temperature of the strain sensor is taken when the strain data is tested, the original temperature peak value is kept when the displacement data is tested, and meanwhile, the maximum testable temperature of the strain sensor is also taken when the strain data is tested in the step S6, and under the condition, the method further comprises a step S10;
high-temperature strain sensors and displacement sensors are arranged on a complex curved surface structure, the arrangement number of the high-temperature strain sensors is 33, 11 high-temperature regions are arranged, the rest high-temperature regions are uniformly distributed in the non-extreme high-temperature regions of the complex curved surface structure, the arrangement number of the displacement sensors is 4, one strain data L of the complex curved surface structure under the thermal strength secondary experiment is measured at each of an extreme high temperature position, a large temperature gradient value position, a position 75cm away from a complex curved surface structure experiment piece constraint point and a position 1m away from the complex curved surface structure experiment piece constraint point 3 And displacement data M 3 ；
S6, secondary construction of a thermal strength calculation model: will be in step S1The selected actual characteristic data is imported into the thermal intensity calculation model corrected in the step S4, and strain data L of the complex curved surface structure under the corrected thermal intensity calculation model is measured 4 And displacement data M 4 ；
S7, secondary data comparison: the strain data L obtained in step S5 3 And the strain data L obtained in step S6 4 Comparing the displacement data M obtained in step S5 3 And the displacement data M obtained in step S6 4 Comparing to obtain a relative error C 2 Relative error C 2 The calculation formula of (2) is as follows:
C 2 =（L 4 -L 3 ）/L 3 or C 2 =（M 4 -M 3 ）/M 3 ；
If two sets of relative errors C 2 If any one of the two is greater than 12%, secondarily modifying the heat intensity calculation model in the step S6, adjusting the calculation unit type in the heat intensity calculation model, subdividing the unit mesh of the heat intensity calculation model, adjusting the contact state between the components in the heat intensity calculation model, adjusting the basic thermodynamic performance parameters of the material in the heat intensity calculation model to obtain a secondarily modified heat intensity calculation model, and repeating the step S6 to obtain strain data L under the secondarily modified heat intensity calculation model 4 ʹ and displacement data M 4 ʹ, completing a secondary correction cycle;
then the strain data L 4 ʹ and strain data L 3 Comparing the displacement data M 4 ʹ and displacement data M 3 Comparing to obtain a relative error C 2 ʹ relative error C 2 ʹ is calculated as:
C 2 ʹ=（L 4 ʹ-L 3 ）/L 3 or C 2 ʹ=（M 4 ʹ-M 3 ）/M 3 ；
If two sets of relative errors C 2 ʹ is greater than 12%, the above two correction cycles are carried out until the two sets of relative errors C are reached 2 n ʹ are all less than 12%, and strain data L is obtained correspondingly 4 n ʹ sum positionMove data M 4 n ʹ, wherein n is the number ʹ, namely the cycle number;
s8, calculating the weighting of the final strain value: the strain data L obtained in step S5 3 Given a weight A 1 The strain data L obtained in step S7 4 n ʹ to give weight A 2 ，A 1 A value of 50%, A 2 The value is 50%, the weighted average value of the two is the final strain value L in the corresponding temperature range, and L = L 3 ×A 1 +L 4 n ʹ×A 2 ；
S9, displacement final value weighting calculation: the displacement data M obtained in step S5 3 Given a weight B 1 The displacement data M obtained in step S7 4 n ʹ to give weight B 2 ，B 1 Value of 70%, B 2 The value is 30%, the weighted average value of the two is the final displacement value M in the corresponding temperature range, and M = M 3 ×B 1 +M 4 n ʹ×B 2 ；
S10, calculating a theoretical final value: importing the actual characteristic data selected in the step S1 into the thermal intensity calculation model corrected in the step S7, and measuring theoretical final strain data L of the complex curved surface structure under the thermal intensity calculation model subjected to secondary correction 5 。
Example 3
This embodiment is substantially the same as embodiment 1, except that: the complex curved surface structures selected in the experiment are different.
In step S1, the complex curved surface structure is the warhead of the missile.
Example 4
This embodiment is substantially the same as embodiment 1, except that: in step S1, the large gradient of the original state changes rapidly and the scaling of the actual characteristic data of the extremely high temperature environment is different.
S1, intercepting actual characteristic data: selecting large-gradient fast-time-varying extreme high-temperature environment actual characteristic data of a complex curved surface structure of the aerospace plane, wherein the selected actual characteristic data are a temperature gradient value, a temperature-time-varying speed value and a temperature peak value, multiplying the selected actual characteristic data by 1/3 respectively to realize equal-proportion adjustment of the large-gradient fast-time-varying extreme high-temperature environment actual characteristic data in an original state, and the intercepted data are intercepted state values of the actual characteristic data.
Example 5
This embodiment is substantially the same as embodiment 1, except that: the number of high temperature strain sensors differs in steps S2 and S5.
S2, heat strength test: in a thermal intensity laboratory, applying the intercepted state value of the actual characteristic data obtained in the step S1 to a complex curved surface structure of the aerospace plane in a thermal radiation mode, arranging high-temperature strain sensors and displacement sensors on the complex curved surface structure, wherein the arrangement number of the high-temperature strain sensors is 28, 9 high-temperature areas are arranged, the rest high-temperature areas are uniformly distributed in non-extreme high-temperature areas of the complex curved surface structure, the arrangement number of the displacement sensors is 3, one high-temperature area, one large-temperature gradient value area and one complex curved surface structure experimental part constraint point 50cm away are respectively arranged at the extreme high temperature position, the large-temperature gradient value position and the complex curved surface structure experimental part constraint point, and measuring the strain data L of the complex curved surface structure under a thermal intensity experiment 1 And displacement data M 1 ；
S5, secondary hot strength experiment: in a heat intensity laboratory, the actual characteristic data selected in the step S1 is applied to the complex curved surface structure of the aerospace plane in a heat radiation mode, if the temperature peak value in the actual characteristic data exceeds the maximum testable temperature of the strain sensor, the maximum testable temperature of the strain sensor is selected, high-temperature strain sensors and displacement sensors are distributed on the complex curved surface structure, the distribution quantity of the high-temperature strain sensors is 30, wherein, 10 displacement sensors are distributed in the extreme high temperature area, the rest displacement sensors are uniformly distributed in the non-extreme high temperature area with the complex curved surface structure, the distribution number of the displacement sensors is 4, the strain data L of the complex curved surface structure under the heat intensity secondary experiment is measured by respectively arranging one strain data L at an extremely high temperature position, a large temperature gradient value position, a position 50cm away from a constraint point of the complex curved surface structure experimental piece and a position 80cm away from the constraint point of the complex curved surface structure experimental piece. 3 And displacement data M 3 。
Example 6
This embodiment is substantially the same as embodiment 1, except that: the number of high temperature strain sensors differs in steps S2 and S5.
S2, heat strength test: in a thermal intensity laboratory, applying the intercepted state value of the actual characteristic data obtained in the step S1 to a complex curved surface structure of the aerospace plane in a thermal radiation mode, arranging high-temperature strain sensors and displacement sensors on the complex curved surface structure, wherein the arrangement number of the high-temperature strain sensors is 33, 11 high-temperature areas are arranged, the rest high-temperature areas are uniformly distributed in non-extreme high-temperature areas of the complex curved surface structure, the arrangement number of the displacement sensors is 3, one high-temperature area, a large-temperature gradient value area and a position 1m away from a constraint point of an experimental part of the complex curved surface structure are respectively arranged at the extreme high temperature position, the large-temperature gradient value and the position 1m away from the constraint point of the experimental part of the complex curved surface structure, and measuring strain data L of the complex curved surface structure under a thermal intensity experiment 1 And displacement data M 1 ；
S5, secondary hot strength experiment: in a heat intensity laboratory, the actual characteristic data selected in the step S1 is applied to the complex curved surface structure of the aerospace plane in a heat radiation mode, if the temperature peak value in the actual characteristic data exceeds the maximum testable temperature of the strain sensor, the maximum testable temperature of the strain sensor is selected, high-temperature strain sensors and displacement sensors are distributed on the complex curved surface structure, the distribution quantity of the high-temperature strain sensors is 35, wherein 12 displacement sensors are distributed in the extreme high temperature area, the rest displacement sensors are uniformly distributed in the non-extreme high temperature area with the complex curved surface structure, the distribution number of the displacement sensors is 4, the strain data L of the complex curved surface structure under the heat intensity secondary experiment is measured by respectively arranging one strain data L at an extremely high temperature position, a large temperature gradient value position, a position 1m away from the constraint point of the complex curved surface structure experimental piece and a position 1.2m away from the constraint point of the complex curved surface structure experimental piece. 3 And displacement data M 3 。
Example 7
This embodiment is substantially the same as embodiment 1, except that: the relative error threshold values in steps S4 and S7 are different.
S4, data comparison: c 1 The critical value is 5%; s7, data secondaryAnd (3) comparison: c 2 The critical value is 10%.
Example 8
This embodiment is substantially the same as embodiment 1, except that: the relative error threshold values in steps S4 and S7 are different.
S4, data comparison: c 1 The critical value is 8%; s7, secondary data comparison: c 2 The critical value is 15%.
Examples of the experiments
The method for evaluating the large-gradient ultrahigh-temperature thermal strength of the complex curved surface structure of the aerospace plane is subjected to simulation experiments by combining the method parameters in the embodiment 2 of the invention, and the test results are as follows:
s1, intercepting actual characteristic data: selecting large-gradient fast-time-change extreme high-temperature environment actual characteristic data of a complex curved surface structure of the aerospace plane, wherein the selected actual characteristic data are a temperature gradient value, a temperature-time-change speed value and a temperature peak value, and the maximum value of the temperature gradient value is as follows: 120 ℃/cm, maximum value of rate of change value at temperature: 200 ℃/s, temperature peak: the selected actual characteristic data are respectively multiplied by 1/2 at 1800 ℃ to realize equal proportion adjustment of the actual characteristic data of the large-gradient fast-time-varying extremely high-temperature environment in the original state, the intercepted data are intercepted state values of the actual characteristic data, the intercepted state value of the maximum value of the temperature gradient value is 60 ℃/cm, the intercepted state value of the maximum value of the temperature-time-varying speed value is 100 ℃/s, and the intercepted state value of the temperature peak value is 900 ℃;
s2, heat strength test: in the heat intensity laboratory, the intercepted state value of the actual characteristic data obtained in the step S1 is applied to the complex curved surface structure of the aerospace plane by means of heat radiation, and the obtained strain test data L 1 Is 2000 microstrain (maximum value), displacement test data M 1 1cm (max);
s3, constructing a heat intensity calculation model: importing the intercepted state value of the actual characteristic data obtained in the step S1 into finite element calculation software to obtain strain data L 2 2400 microstrain (maximum), displacement data M 2 1.3cm (max);
s4, dataAnd (3) comparison: relative error C 1 =（L 2 -L 1 ）/L 1 Or (M) 2 -M 1 ）/M 1 (ii) a All exceed 10%, and therefore the heat intensity calculation model in S3 is corrected, and the corrected strain data L 2 ʹ is 2080 microstrain (maximum value), displacement data M 2 ʹ is 1.05cm (maximum), and the relative error C of strain data and displacement data 1 Are all less than 6 percent;
s5, secondary hot strength experiment: in a thermal intensity laboratory, the actual characteristic data selected in the step S1 is applied to a complex curved surface structure of the aerospace plane in a thermal radiation mode, the actual extreme high temperature reaches 1800 ℃, the used strain sensor can only allow the test of the strain data below 900 ℃, only the strain data below 900 ℃ are obtained, and the strain test data L of 900 ℃ (maximum value of temperature gradient value: 120 ℃/cm, maximum value of temperature time variable rate value: 200 ℃/S, temperature peak value: 900 ℃) are obtained 3 2800 microstrain (max);
the displacement test data is not limited by the temperature of the strain sensor (maximum value of temperature gradient value: 120 ℃/cm, maximum value of rate-change value at temperature: 200 ℃/s, temperature peak value: 1800 ℃), and the displacement test data M at 1800 ℃ can still be measured 3 1.5cm (max);
s6, secondary construction of a thermal strength calculation model: introducing the actual characteristic data (maximum value of temperature gradient value: 120 ℃/cm, maximum value of rate of change value at temperature: 200 ℃/S, peak value of temperature: 900 ℃) selected in the step S1 into the heat intensity calculation model corrected in the step S4, and measuring strain data L of the complex curved surface structure under the corrected heat intensity calculation model 4 3000 microstrain (max);
introducing the actual characteristic data (maximum value of temperature gradient value: 120 ℃/cm, maximum value of rate of change value at temperature time: 200 ℃/S, temperature peak value: 1800 ℃) selected in the step S1 into the heat intensity calculation model corrected in the step S4, and measuring displacement data M of the complex curved surface structure under the corrected heat intensity calculation model 4 1.8cm (max);
and S7 data secondary comparison: subjecting the complex curved surface structure obtained in the step S5 to strain data L under the secondary experiment of thermal strength 3 And displacement data M 3 And the strain data L of the complex curved surface structure obtained in the step S6 under the corrected heat intensity calculation model 4 And displacement data M 4 Comparing to obtain a relative error C 2 =（L 4 -L 3 ）/L 3 Or C 2 =（M 4 -M 3 ）/M 3 Since the relative error of the displacement data exceeds 12%, which are 7.14% and 20%, respectively, the heat intensity calculation model in step S5 is secondarily corrected, and the secondarily corrected strain data L are 4 ʹ is 2900 microstrain (maximum), displacement data M 4 ʹ is 1.6cm (maximum value), and the relative error C of the strain data and displacement data after secondary correction 2 Are all less than 12 percent;
s8, strain final value weighting calculation: the strain data L obtained in step S5 3 Given a weight A 1 The strain data L obtained in step S7 4 ʹ to give weight A 2 ，A 1 A value of 50%, A 2 The value is 50%, the weighted average value of the two is the final strain value L within the temperature range of 900 ℃, and L = L 3 ×A 1 +L 4 ʹ×A 2 =2800 × 50% +2900 × 50% =2850 microstrain;
s9, displacement final value weighting calculation: the displacement data M obtained in step S5 3 Given a weight B 1 The displacement data M obtained in step S7 4 ʹ to give weight B 2 ，B 1 Value of 70%, B 2 The value is 30%, the weighted average value of the two is the final displacement value M within the temperature range of 1800 ℃, and M = M 3 ×B 1 +M 4 ʹ×B 2 =1.5×70%+1.6×30%=1.53cm；
S10, calculating a theoretical final value: introducing the actual characteristic data (maximum value of temperature gradient value: 120 ℃/cm, maximum value of rate of change value at temperature time: 200 ℃/S, temperature peak value: 1800 ℃) selected in the step S1 into the heat intensity calculation model corrected in the step S7, and measuring the complex curved surface structure after secondary correctionThe theoretical final strain data L in the temperature range of 1800 ℃ under the heat intensity calculation model 5 =3400 microstrain.
Claims (9)
1. A method for evaluating the large-gradient extremely-high-temperature thermal strength of a complex curved surface structure of an aerospace plane is characterized by comprising the following steps of:
s1, actual feature data interception: selecting large-gradient fast-time-varying extreme high-temperature environment actual characteristic data of a complex curved surface structure of the aerospace plane, wherein the selected actual characteristic data are a temperature gradient value, a temperature-time-varying speed value and a temperature peak value, multiplying the selected actual characteristic data by 1/2 respectively to realize equal-proportion adjustment of the large-gradient fast-time-varying extreme high-temperature environment actual characteristic data in an original state, and the intercepted data are intercepted state values of the actual characteristic data;
s2, heat strength test: in a thermal strength laboratory, applying the intercepted state value of the actual characteristic data obtained in the step S1 to a complex curved surface structure of the aerospace plane, arranging a high-temperature strain sensor and a displacement sensor on the complex curved surface structure, and measuring strain data L of the complex curved surface structure under the thermal strength experiment 1 And displacement data M 1 ；
S3, constructing a heat intensity calculation model: importing the intercepted state value of the actual characteristic data obtained in the step S1 into finite element calculation software, constructing a thermal strength calculation model of the complex curved surface structure, and measuring strain data L of the complex curved surface structure under the thermal strength calculation model 2 And displacement data M 2 ；
S4, data comparison: the strain data L obtained in step S2 1 And the strain data L obtained in step S3 2 Comparing the displacement data M obtained in step S2 1 And the displacement data M obtained in step S3 2 Comparing to obtain a relative error C 1 The relative error C 1 The calculation formula of (2) is as follows:
C 1 =（L 2 -L 1 ）/L 1 or C 1 =（M 2 -M 1 ）/M 1 ；
If two sets of relative errorsC 1 If any one of the above is more than 6%, the heat intensity calculation model in step S3 is corrected to obtain a corrected heat intensity calculation model, and step S3 is repeated to obtain strain data L under the corrected heat intensity calculation model 2 ʹ and displacement data M 2 ʹ, completing a correction cycle;
then the strain data L 2 ʹ and the strain data L 1 Comparing the displacement data M 2 ʹ and the displacement data M 1 Comparing to obtain a relative error C 1 ʹ, the relative error C 1 ʹ is calculated as:
C 1 ʹ=（L 2 ʹ-L 1 ）/L 1 or C 1 ʹ=（M 2 ʹ-M 1 ）/M 1 ；
If two sets of relative errors C 1 ʹ is greater than 6%, the correction cycle is repeated until the two sets of relative errors C are equal 1 n ʹ are all less than 6%, wherein n is C 1 n ʹ, ʹ, i.e., the number of cycles;
s5, secondary hot strength experiment: in a heat intensity laboratory, the actual characteristic data selected in the step S1 is applied to a complex curved surface structure of the aerospace plane, a high-temperature strain sensor and a displacement sensor are arranged on the complex curved surface structure, and strain data L of the complex curved surface structure under a heat intensity secondary experiment is measured 3 And displacement data M 3 ；
S6, secondary construction of a thermal strength calculation model: importing the actual characteristic data selected in the step S1 into the thermal intensity calculation model corrected in the step S4, and measuring strain data L of the complex curved surface structure under the corrected thermal intensity calculation model 4 And displacement data M 4 ；
S7, secondary data comparison: the strain data L obtained in step S5 3 And the strain data L obtained in step S6 4 Comparing the displacement data M obtained in step S5 3 And the displacement data M obtained in step S6 4 Comparing to obtain a relative error C 2 The relative error C 2 Is calculated byComprises the following steps:
C 2 =（L 4 -L 3 ）/L 3 or C 2 =（M 4 -M 3 ）/M 3 ；
If two sets of relative errors C 2 If any one of the two is greater than 12%, performing secondary correction on the heat intensity calculation model in the step S6 to obtain a secondarily corrected heat intensity calculation model, and repeating the step S6 to obtain strain data L under the secondarily corrected heat intensity calculation model 4 ʹ and displacement data M 4 ʹ, completing a secondary correction cycle;
then the strain data L 4 ʹ and the strain data L 3 Comparing the displacement data M 4 ʹ and the displacement data M 3 Comparing to obtain a relative error C 2 ʹ, the relative error C 2 ʹ is calculated as:
C 2 ʹ=（L 4 ʹ-L 3 ）/L 3 or C 2 ʹ=（M 4 ʹ-M 3 ）/M 3 ；
If two sets of relative errors C 2 ʹ is greater than 12%, the above two correction cycles are carried out until the two sets of relative errors C are reached 2 n ʹ are all less than 12%, and strain data L is obtained correspondingly 4 n ʹ and displacement data M 4 n ʹ, wherein n is the number ʹ, namely the cycle number;
s8, strain final value weighting calculation: the strain data L obtained in step S5 3 Given a weight A 1 The strain data L obtained in step S7 4 n ʹ to give weight A 2 The weighted average value of the two is the final strain value L in the corresponding temperature range, and L = L 3 ×A 1 +L 4 n ʹ×A 2 ；
S9, displacement final value weighting calculation: the displacement data M obtained in step S5 3 Given a weight B 1 The displacement data M obtained in step S7 4 n ʹ to give weight B 2 The weighted average value of the two is the displacement final value M in the corresponding temperature range, M = M 3 ×B 1 +M 4 n ʹ×B 2 。
2. The method for evaluating the large-gradient ultrahigh-temperature thermal strength of the complex curved surface structure of the aerospace plane as claimed in claim 1, wherein the complex curved surface structure in the step S1 is a nose cone of the aerospace plane.
3. The method for evaluating the large-gradient ultra-high-temperature thermal strength of the complex curved surface structure of the aerospace plane as claimed in claim 1, wherein the truncated state values of the actual characteristic data obtained in the step S1 are applied to the complex curved surface structure of the aerospace plane by means of thermal radiation in the step S2.
4. The method for evaluating the large-gradient ultrahigh-temperature thermal strength of the aerospace plane complex curved surface structure according to claim 1, wherein the actual characteristic data obtained in the step S1 is applied to the aerospace plane complex curved surface structure in a thermal radiation manner in the step S5, if the temperature peak value in the actual characteristic data exceeds the maximum temperature of the strain sensor in the step S5, the maximum temperature of the strain sensor is taken during the strain data test, the original temperature peak value is kept during the displacement data test, and the maximum temperature of the strain sensor is also taken during the strain data test in the step S6, and under the condition, the method further comprises the step S10:
s10, calculating a theoretical final value: importing the actual characteristic data selected in the step S1 into the thermal intensity calculation model corrected in the step S7, and measuring theoretical final strain data L of the complex curved surface structure under the thermal intensity calculation model subjected to secondary correction 5 。
5. The method for evaluating the large-gradient ultrahigh-temperature thermal strength of the aerospace plane complex curved surface structure according to claim 1, wherein the number of the high-temperature strain sensors arranged in step S2 is 28-33, 9-11 are arranged in the extreme high-temperature region, the rest are uniformly distributed in the non-extreme high-temperature region of the complex curved surface structure, the number of the displacement sensors arranged is 3, and one is arranged at each of the extreme high temperature, the large-temperature gradient value and the position 50 cm-1 m away from the complex curved surface structure experiment piece constraint point.
6. The aerospace plane complex curved surface structure large-gradient extremely high temperature thermal strength evaluation method according to claim 1, wherein the number of the high temperature strain sensors arranged in step S5 is 30-35, wherein 10-12 are arranged in the extreme high temperature region, the rest are uniformly distributed in the non-extreme high temperature region of the complex curved surface structure, the number of the displacement sensors arranged is 4, and one displacement sensor is arranged at each of the extreme high temperature position, the large temperature gradient value position, the position 50 cm-1 m away from the complex curved surface structure experimental part constraint point and the position 80 cm-1.2 m away from the complex curved surface structure experimental part constraint point.
7. The method for evaluating the large-gradient ultra-high-temperature thermal strength of the complex curved surface structure of the aerospace plane as claimed in claim 1, wherein the step of modifying the heat strength calculation model in the step S4 and the step of secondarily modifying the heat strength calculation model in the step S7 each comprise: adjusting the type of a computing unit in the heat intensity computing model, subdividing a unit grid of the heat intensity computing model, adjusting the contact state among components in the heat intensity computing model, and adjusting the basic thermodynamic performance parameters of materials in the heat intensity computing model.
8. The method for evaluating the large-gradient ultrahigh-temperature thermal strength of the complex curved surface structure of the aerospace plane according to claim 1, wherein in the step S8, A is 1 A value of 50%, A 2 The value is 50%.
9. The method for evaluating the large-gradient ultrahigh-temperature heat intensity of the complex curved surface structure of the aerospace plane according to claim 1, wherein in the step S9B 1 Value of 70%, B 2 The value is 30%.
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