CN111291451A - Method for enhancing aeroelastic stability of cylindrical shell structure for spacecraft - Google Patents
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Abstract
A method for enhancing the aeroelasticity stability of a cylindrical shell structure for an aerospace craft belongs to the technical field of structure dynamics. The invention solves the problem that the existing research has limited effect on enhancing the aeroelasticity stability of the cylindrical shell structure for the spacecraft. According to the method, the basic size and the material properties of the cylindrical shell structure are designed according to actual needs, and then the variable-thickness axial functional gradient model and the variable-elasticity-modulus axial functional gradient model of the cylindrical shell structure are designed, so that the thickness and the elasticity modulus of the cylindrical shell structure along the axial direction are changed. The invention can be used for enhancing the aeroelastic stability of the cylindrical shell structure for the spacecraft.
Description
Technical Field
The invention belongs to the technical field of structural dynamics, and particularly relates to a method for enhancing the aeroelasticity stability of a cylindrical shell structure for an aerospace craft.
Background
The structural flutter of the cylindrical shell structure for the spacecraft is a self-excited vibration phenomenon generated by the spacecraft in high-speed airflow, and the self-excited vibration phenomenon is more obvious on supersonic speed aircrafts and hypersonic speed aircrafts. When the flutter phenomenon occurs, the cylindrical shell structure generates nonlinear large-deflection vibration, so that the operation safety of the aircraft is influenced. Although the existing research has achieved certain achievement in the aspect of enhancing the aeroelastic stability of the cylindrical shell structure for the spacecraft, the enhancement effect on the aeroelastic stability of the cylindrical shell structure for the spacecraft is still limited.
Disclosure of Invention
The invention aims to solve the problem that the existing research on the strengthening effect of the aeroelasticity stability of the cylindrical shell structure for the spacecraft is limited, and provides a method for strengthening the aeroelasticity stability of the cylindrical shell structure for the spacecraft.
The technical scheme adopted by the invention for solving the technical problems is as follows: a method for enhancing the aeroelastic stability of a cylindrical shell structure for an aerospace craft specifically comprises the following steps:
designing the basic size and material properties of a cylindrical shell structure for an aerospace aircraft: the basic dimensions comprise the length L of the cylindrical shell structure, the radius R of the cylindrical shell structure and the thickness h of the cylindrical shell structure;
step two, designing a variable-thickness axial functional gradient model of the cylindrical shell structure: the thickness h of the cylindrical shell structure along the axial direction is changed;
step three, designing a variable elastic modulus axial functional gradient model of the cylindrical shell structure: the method is realized by changing the integral elastic modulus of the cylindrical shell structure along the axial direction;
and step four, designing the cylindrical shell structure according to the variable-thickness axial functional gradient model and the variable-elasticity-modulus axial functional gradient model so as to enhance the aeroelastic stability of the cylindrical shell structure for the aerospace craft.
The invention has the beneficial effects that: the invention provides a method for enhancing the aeroelastic stability of a cylindrical shell structure for an aerospace craft, the basic size and the material property of the cylindrical shell structure are designed according to actual needs, and then a variable-thickness axial functional gradient model and a variable-elasticity-modulus axial functional gradient model of the cylindrical shell structure are designed, so that the thickness and the elasticity modulus of the cylindrical shell structure along the axial direction are changed.
Drawings
FIG. 1 is a schematic view of a cylindrical shell structure and aerodynamic direction;
in the figure, x represents the axial direction of the cylindrical shell, z represents the thickness direction of the cylindrical shell, and α represents radian;
FIG. 2 is a schematic structural diagram of the model 1;
FIG. 3 is a schematic structural diagram of the model 2;
FIG. 4 is a schematic structural diagram of the mold 3;
FIG. 5 is a diagram illustrating the best effect of model 1 in an example;
FIG. 6 is a schematic diagram of the best effect of model 2 in the example;
fig. 7 is a schematic diagram of the best effect of the model 3 in the example.
Detailed Description
The first embodiment is as follows: as shown in fig. 1. The method for enhancing the aeroelastic stability of the cylindrical shell structure for the spacecraft in the embodiment specifically comprises the following steps:
designing the basic size and material properties of a cylindrical shell structure for an aerospace aircraft: the basic dimensions comprise the length L of the cylindrical shell structure, the radius R of the cylindrical shell structure and the thickness h of the cylindrical shell structure;
step two, designing a variable-thickness axial functional gradient model of the cylindrical shell structure: the thickness h of the cylindrical shell structure along the axial direction is changed;
step three, designing a variable elastic modulus axial functional gradient model of the cylindrical shell structure: the method is realized by changing the integral elastic modulus of the cylindrical shell structure along the axial direction;
and step four, designing the cylindrical shell structure according to the variable-thickness axial functional gradient model and the variable-elasticity-modulus axial functional gradient model so as to enhance the aeroelastic stability of the cylindrical shell structure for the aerospace craft.
In the embodiment, the basic size and the material properties of the cylindrical shell structure for the spacecraft are designed according to actual needs.
The second embodiment is as follows: the first difference between the present embodiment and the specific embodiment is: the variable thickness axial functional gradient model of the cylindrical shell structure is expressed in a functional form as follows:
wherein h (x) is the thickness change of the cylindrical shell structure along the axial direction x, and theta is an inclination angle.
As shown in fig. 2, the thickness of the cylindrical shell structure linearly changes along the axial direction, and the magnitude of the thickness change is determined by the inclination angle θ, which is a model 1 designed in the present embodiment. Starting from one axial end of the cylindrical shell structure, x varies from 0 to L to the other axial end of the cylindrical shell structure.
The third concrete implementation mode: the first difference between the present embodiment and the specific embodiment is: the variable thickness axial functional gradient model of the cylindrical shell structure is expressed in a functional form as follows:
as shown in FIG. 3, the cylindrical shell structure is divided into x ≦ 0 ≦ x in the axial direction x0、x0＜x＜L-x0And L-x0X is not less than X and not more than L, h (x) is the thickness change of the cylindrical shell structure along the axial direction x, theta is the inclination angle, x0Are segmentation points.
The model designed by the embodiment is marked as model 2, and x is more than or equal to 0 and less than or equal to x0And L-x0In the section of which x is less than or equal to L, the thickness of the cylindrical shell structure is linearly changed, and the thickness change is determined by the inclination angle theta. x is the number of0＜x＜L-x0The sections being of uniform thickness
The division point of the three segments is defined by x0It is determined that the parameters to be determined in the variable thickness axial functional gradient function model according to the present embodiment include the inclination angles θ and x0。
The fourth concrete implementation mode: the first difference between the present embodiment and the specific embodiment is: the variable thickness axial functional gradient model of the cylindrical shell structure is expressed in a functional form as follows:
as shown in FIG. 4, the cylindrical shell structure is divided into x ≦ 0 ≦ x in the axial direction x0And x0L two sections < x ≦ h (x) is the thickness change of the cylindrical shell structure along the axial direction x, theta is the inclination angle, x0Are segmentation points.
The model designed in the present embodiment is referred to as model 3, and the parameters to be determined in the variable thickness axial functional gradient function model of the present embodiment include inclination angles θ and x0。
The variable elastic modulus axial functional gradient model is characterized in that the overall elastic modulus of the cylindrical shell is changed along the axial direction, a second material with different elastic modulus is added on the basis of the original first design material, and the volume fractions of the two materials are changed along the axial direction according to a certain form.
The fifth concrete implementation mode: the first difference between the present embodiment and the specific embodiment is: the variable elastic modulus axial functional gradient model of the cylindrical shell structure is designed, and the variable elastic modulus axial functional gradient model is expressed in a functional form as follows:
V2(x)＝1-V1(x)
wherein, V1(x) Is a first material (step)A defined material property) of the volume fraction variation, V, in the axial direction x of the cylindrical shell structure2(x) Is the volume fraction change, p, of the second material along the axial direction x of the cylindrical shell structurexIs a constant.
The properties of the second material may be determined by specific simulation effects.
The model designed in this embodiment is referred to as model 4, and p in model 4xThe values of (1), (2) and (3) are obtained, and when the cylindrical shell is designed by using the embodiment, different p needs to be selected according to different basic parameters of the cylindrical shell actually requiredxThe value of (a) is subjected to simulation analysis, and finally p which enables the aeroelastic stability of the cylindrical shell structure to be the best is determinedxAnd (4) taking values.
The sixth specific implementation mode: the first difference between the present embodiment and the specific embodiment is: the variable elastic modulus axial functional gradient model of the cylindrical shell structure is designed, and the variable elastic modulus axial functional gradient model is expressed in a functional form as follows:
V2(x)＝1-V1(x)
dividing the cylindrical shell structure into x which is more than or equal to 0 and less than or equal to x along the axial direction x0And x0Two stages of < x > and < L, V1(x) Is the volume fraction change, V, of the first material along the axial direction x of the cylindrical shell structure2(x) Is the volume fraction change, p, of the second material along the axial direction x of the cylindrical shell structurexIs a constant.
The model designed in this embodiment is referred to as model 5, and p in model 5xThe values of (1), (2) and (3) are obtained, and when the cylindrical shell is designed by using the embodiment, different p needs to be selected according to different basic parameters of the cylindrical shell actually requiredxThe value of (a) is subjected to simulation analysis, and finally p which enables the aeroelastic stability of the cylindrical shell structure to be the best is determinedxAnd (4) taking values.
In practical application, any one of the models 1 to 5 may be selected to design the cylindrical shell structure, or any one of the models 1 to 3 may be selected to be used in combination with any one of the models 4 to 5, and the cylindrical shell structure may be designed by the combination of the models.
The seventh embodiment: the method for enhancing the aeroelastic stability of the cylindrical shell structure for the spacecraft in the embodiment specifically comprises the following steps:
step 1, designing the basic size and material properties of a cylindrical shell structure for an aerospace aircraft: the basic dimensions comprise the length L of the cylindrical shell structure, the radius R of the cylindrical shell structure and the thickness h of the cylindrical shell structure;
and 3, designing the cylindrical shell structure according to the variable-thickness axial functional gradient model so as to enhance the aeroelastic stability of the cylindrical shell structure for the space shuttle.
The specific implementation mode is eight: the seventh embodiment is different from the seventh embodiment in that: the variable-thickness axial functional gradient model of the cylindrical shell structure is a model 1, a model 2 or a model 3, wherein the model 1 is expressed in a functional form as follows:
wherein h (x) is the thickness change of the cylindrical shell structure along the axial direction x, and theta is an inclination angle;
the model 2 is expressed in functional form as:
dividing the cylindrical shell structure into x which is more than or equal to 0 and less than or equal to x along the axial direction x0、x0＜x＜L-x0And L-x0X is not less than X and not more than L, h (x) is the thickness change of the cylindrical shell structure along the axial direction x, theta is the inclination angle, x0Is a segmentation point;
the model 3 is expressed in functional form as:
dividing the cylindrical shell structure into x which is more than or equal to 0 and less than or equal to x along the axial direction x0And x0L two sections < x ≦ h (x) is the thickness change of the cylindrical shell structure along the axial direction x, theta is the inclination angle, x0Are segmentation points.
The specific implementation method nine: the method for enhancing the aeroelastic stability of the cylindrical shell structure for the spacecraft in the embodiment specifically comprises the following steps:
①, designing the basic size and material property of the cylindrical shell structure for the spacecraft, wherein the basic size comprises the length L of the cylindrical shell structure, the radius R of the cylindrical shell structure and the thickness h of the cylindrical shell structure;
②, designing a variable elastic modulus axial functional gradient model of the cylindrical shell structure, which is realized by changing the overall elastic modulus of the cylindrical shell structure along the axial direction;
and ③, designing the cylindrical shell structure according to the variable elastic modulus axial functional gradient model so as to enhance the aeroelastic stability of the cylindrical shell structure for the spacecraft.
The detailed implementation mode is ten: the present embodiment differs from the ninth embodiment in that: the variable elastic modulus axial functional gradient model of the cylindrical shell structure is a model 4 or a model 5, and the model 4 is expressed in a functional form as follows:
V2(x)＝1-V1(x)
wherein, V1(x) Is the volume fraction change, V, of the first material along the axial direction x of the cylindrical shell structure2(x) Is the volume fraction change, p, of the second material along the axial direction x of the cylindrical shell structurexIs a constant;
the model 5 is represented in functional form as:
V2(x)＝1-V1(x)
dividing the cylindrical shell structure into x which is more than or equal to 0 and less than or equal to x along the axial direction x0And x0Two stages of < x > and < L, V1(x) Is the volume fraction change, V, of the first material along the axial direction x of the cylindrical shell structure2(x) Is the volume fraction change, p, of the second material along the axial direction x of the cylindrical shell structurexIs a constant.
Examples
The process of the present invention is further described below with reference to specific examples:
firstly, designing the specific size of a cylindrical shell structure according to the specific use requirement of the cylindrical shell structure in the aerospace craft, and selecting materials, wherein the parameters of the cylindrical shell structure and the parameters of the materials are E1＝110Gpa,ρ1＝8900kg/m3L is 0.381m, R is 0.203m, h is 0.0001015m, poisson's ratio ν is 0.35, called uniform cylindrical shell.
And secondly, after the structural parameters and the material parameters of the cylindrical shell are determined, programming and simulating by using MATLAB simulation software under the action of determined aerodynamic force to obtain the flutter order and the flutter boundary of the uniform cylindrical shell.
And thirdly, on the basis of specific parameters of the uniform cylindrical shell structure, designing by respectively utilizing a variable-thickness axial functional gradient model and a variable-material axial functional gradient model, and improving the aeroelastic stability of the structure.
Fourthly, designing is performed by using the variable thickness axial functional gradient model, and the model 2 is taken as an example for explanation. When carrying out MATLAB software programming simulation, setting the thickness h as 0.0001m as a model 2 function with variable thickness, and continuously changing x in an MATLAB program0And theta, observing the flutter order and the change of the flutter boundary from the simulation result, and finding out x which enables the flutter boundary of the cylindrical shell structure to be maximum0And theta, determining a specific function model suitable for the cylindrical shell structure, and designing and processing the cylindrical shell according to the function model, so that the aeroelastic stability of the cylindrical shell can be improved. In the present example, the number of the first and second,performing programming simulation analysis by MATLAB software, when x0When L/4 and θ is 0.001 °, the chatter boundary is improved by 22% compared with that of a uniform cylindrical shell. The schematic structure is shown in fig. 6. Similarly, when designing a cylindrical shell using model 3, x is also changed continuously in the MATLAB program0And the value of theta, observing the change of the flutter boundary, and taking x as the value in the model 30When L/2 and theta are 0.002 degrees, the designed cylindrical shell flutter boundary is improved by 29 percent compared with a uniform cylindrical shell. The schematic structure is shown in fig. 7. When utilizing model 1 design cylinder shell, only need change inclination angle theta in the MATLAB procedure, through simulation analysis, when theta is 0.001 when being the terms in the model 1, the cylinder shell flutter border of design improves 19% than even thickness cylinder shell. The schematic structure is shown in fig. 5.
And fifthly, designing by using a variable elastic modulus axial functional gradient model, and taking the model 5 as an example for explanation. Modulus of elasticity E of Material 1 selected for use in a homogeneous cylindrical Shell1On the basis of 110Gpa, a second structural material, referred to as material 2, is added, the volume fractions of the two materials varying in the axial direction as a function of model 5. According to different actual models, programming simulation is carried out through MATLAB simulation software, the flutter boundary of the cylindrical shell structure is observed, and the most suitable x is determined0And pxThe value is obtained.
In this example, the modulus of elasticity of the material 1 is E1110Gpa, modulus of elasticity E of material 22Changing x in MATLAB program by MATLAB programming simulation analysis at intervals of 90GPa-130GPa and every 5GPa values0And pxTo obtain different x0And pxThe influence of the change of the elastic modulus of the material 2 under the value on the flutter boundary of the cylindrical shell structure. In this example model, when pxThe axial functional gradient function model when the value is 1 has the best effect on improving the aeroelastic stability of the structure. When the modulus of elasticity of material 2 is smaller than that of material 1, different x in the function model0And pxThe value of (A) has a large influence on the flutter boundary of the cylindrical shell, and x is taken out from the model0＝L/4、pxWhen 2, even if the added material 2 lowers the overall elastic modulus of the cylindrical shell structure, the material is bondedThe aeroelastic stability of the structure is still greatly improved. In this example model, the modulus of elasticity E of the material 2 is2At 90GPa, the flutter boundary of the structure is improved by 54% compared with a uniform cylindrical shell. When the modulus of elasticity E2 of material 2 was 130GPa, the flutter boundary of the structure increased by 159%.
From the results of the embodiment, the cylindrical shell structure designed by the five-axial functional gradient function model is obviously improved in flutter boundary compared with the conventional uniform cylindrical shell structure.
The above-described calculation examples of the present invention are merely to explain the calculation model and the calculation flow of the present invention in detail, and are not intended to limit the embodiments of the present invention. It will be apparent to those skilled in the art that other variations and modifications of the present invention can be made based on the above description, and it is not intended to be exhaustive or to limit the invention to the precise form disclosed, and all such modifications and variations are possible and contemplated as falling within the scope of the invention.
Claims (10)
1. A method for enhancing the aeroelastic stability of a cylindrical shell structure for an aerospace craft is characterized by comprising the following steps:
designing the basic size and material properties of a cylindrical shell structure for an aerospace aircraft: the basic dimensions comprise the length L of the cylindrical shell structure, the radius R of the cylindrical shell structure and the thickness h of the cylindrical shell structure;
step two, designing a variable-thickness axial functional gradient model of the cylindrical shell structure: the thickness h of the cylindrical shell structure along the axial direction is changed;
step three, designing a variable elastic modulus axial functional gradient model of the cylindrical shell structure: the method is realized by changing the integral elastic modulus of the cylindrical shell structure along the axial direction;
and step four, designing the cylindrical shell structure according to the variable-thickness axial functional gradient model and the variable-elasticity-modulus axial functional gradient model so as to enhance the aeroelastic stability of the cylindrical shell structure for the aerospace craft.
2. The method of claim 1, wherein the designing of the cylindrical shell structure comprises designing a variable thickness axial functional gradient model of the cylindrical shell structure, wherein the variable thickness axial functional gradient model is expressed as a function of:
wherein h (x) is the thickness change of the cylindrical shell structure along the axial direction x, and theta is an inclination angle.
3. The method of claim 1, wherein the designing of the cylindrical shell structure comprises designing a variable thickness axial functional gradient model of the cylindrical shell structure, wherein the variable thickness axial functional gradient model is expressed as a function of:
dividing the cylindrical shell structure into x which is more than or equal to 0 and less than or equal to x along the axial direction x0、x0＜x＜L-x0And L-x0X is not less than X and not more than L, h (x) is the thickness change of the cylindrical shell structure along the axial direction x, theta is the inclination angle, x0Are segmentation points.
4. The method of claim 1, wherein the designing of the cylindrical shell structure comprises designing a variable thickness axial functional gradient model of the cylindrical shell structure, wherein the variable thickness axial functional gradient model is expressed as a function of:
dividing the cylindrical shell structure into x which is more than or equal to 0 and less than or equal to x along the axial direction x0And x0L two sections < x ≦ h (x) is the thickness of the cylindrical shell structure along the axial direction xChange, theta is the angle of inclination, x0Are segmentation points.
5. The method for enhancing aeroelastic stability of a cylindrical shell structure for an aerospace craft according to claim 1, wherein the variable elastic modulus axial functional gradient model of the cylindrical shell structure is designed, and the variable elastic modulus axial functional gradient model is expressed in a functional form as:
V2(x)＝1-V1(x)
wherein, V1(x) Is the volume fraction change, V, of the first material along the axial direction x of the cylindrical shell structure2(x) Is the volume fraction change, p, of the second material along the axial direction x of the cylindrical shell structurexIs a constant.
6. The method for enhancing aeroelastic stability of a cylindrical shell structure for an aerospace craft according to claim 1, wherein the variable elastic modulus axial functional gradient model of the cylindrical shell structure is designed, and the variable elastic modulus axial functional gradient model is expressed in a functional form as:
V2(x)＝1-V1(x)
dividing the cylindrical shell structure into x which is more than or equal to 0 and less than or equal to x along the axial direction x0And x0Two stages of < x > and < L, V1(x) Is the volume fraction change, V, of the first material along the axial direction x of the cylindrical shell structure2(x) Is the volume fraction change, p, of the second material along the axial direction x of the cylindrical shell structurexIs a constant.
7. A method for enhancing the aeroelastic stability of a cylindrical shell structure for an aerospace craft is characterized by comprising the following steps:
step 1, designing the basic size and material properties of a cylindrical shell structure for an aerospace aircraft: the basic dimensions comprise the length L of the cylindrical shell structure, the radius R of the cylindrical shell structure and the thickness h of the cylindrical shell structure;
step 2, designing a variable-thickness axial functional gradient model of the cylindrical shell structure: the thickness h of the cylindrical shell structure along the axial direction is changed;
and 3, designing the cylindrical shell structure according to the variable-thickness axial functional gradient model so as to enhance the aeroelastic stability of the cylindrical shell structure for the space shuttle.
8. The method for enhancing aeroelastic stability of a cylindrical shell structure for an aerospace vehicle of claim 7, wherein the variable thickness axial functional gradient model of the cylindrical shell structure is model 1, model 2 or model 3, and the model 1 is expressed in a functional form as:
wherein h (x) is the thickness change of the cylindrical shell structure along the axial direction x, and theta is an inclination angle;
the model 2 is expressed in functional form as:
dividing the cylindrical shell structure into x which is more than or equal to 0 and less than or equal to x along the axial direction x0、x0＜x＜L-x0And L-x0X is not less than X and not more than L, h (x) is the thickness change of the cylindrical shell structure along the axial direction x, theta is the inclination angle, x0Is a segmentation point;
the model 3 is expressed in functional form as:
bonding the cylindrical shellThe structure is divided into x which is more than or equal to 0 and less than or equal to x along the axial direction x0And x0L two sections < x ≦ h (x) is the thickness change of the cylindrical shell structure along the axial direction x, theta is the inclination angle, x0Are segmentation points.
9. A method for enhancing the aeroelastic stability of a cylindrical shell structure for an aerospace craft is characterized by comprising the following steps:
①, designing the basic size and material property of the cylindrical shell structure for the spacecraft, wherein the basic size comprises the length L of the cylindrical shell structure, the radius R of the cylindrical shell structure and the thickness h of the cylindrical shell structure;
②, designing a variable elastic modulus axial functional gradient model of the cylindrical shell structure, which is realized by changing the overall elastic modulus of the cylindrical shell structure along the axial direction;
and ③, designing the cylindrical shell structure according to the variable elastic modulus axial functional gradient model so as to enhance the aeroelastic stability of the cylindrical shell structure for the spacecraft.
10. The method for enhancing aeroelastic stability of a cylindrical shell structure for an aerospace vehicle according to claim 9, wherein the variable elastic modulus axial functional gradient model of the cylindrical shell structure is model 4 or model 5, and the model 4 is expressed in a functional form as:
V2(x)＝1-V1(x)
wherein, V1(x) Is the volume fraction change, V, of the first material along the axial direction x of the cylindrical shell structure2(x) Is the volume fraction change, p, of the second material along the axial direction x of the cylindrical shell structurexIs a constant;
the model 5 is represented in functional form as:
V2(x)＝1-V1(x)
dividing the cylindrical shell structure into x which is more than or equal to 0 and less than or equal to x along the axial direction x0And x0Two stages of < x > and < L, V1(x) Is the volume fraction change, V, of the first material along the axial direction x of the cylindrical shell structure2(x) Is the volume fraction change, p, of the second material along the axial direction x of the cylindrical shell structurexIs a constant.
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