CN114528736B - Optimization design method for structural parameters of solid rocket engine nozzle - Google Patents

Optimization design method for structural parameters of solid rocket engine nozzle Download PDF

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CN114528736B
CN114528736B CN202210155714.4A CN202210155714A CN114528736B CN 114528736 B CN114528736 B CN 114528736B CN 202210155714 A CN202210155714 A CN 202210155714A CN 114528736 B CN114528736 B CN 114528736B
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CN114528736A (en
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郑昌军
余志强
许凯
张光喜
校金友
王帅
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Hefei University of Technology
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Abstract

The invention discloses an optimal design method for structural parameters of a solid rocket engine nozzle, which comprises the following steps: 1. constructing a material thermophysical parameter model of each component of the spray pipe by a three-stage Hermite interpolation method; 2. constructing a thermal boundary condition model of the inner wall of the spray pipe by a Lagrange interpolation method; 3. analyzing and considering the temperature distribution and the thermal stress failure stress of the spray pipe in the complex environment of interface debonding through a complete thermal coupling finite element method or a sequential thermal coupling finite element method; 4. and calculating the peak value of a thermal stress curve of the spray pipe in the working time under different axial lengths of the expansion section and different inclination angles of the contact surface of the expansion section and the throat lining to obtain the relation between the maximum value of the thermal stress of the spray pipe and the axial height of the expansion section and the inclination angle of the contact surface of the expansion section and the throat lining, and the relation is used for the structural optimization of the spray pipe of the solid rocket engine. The invention can effectively reduce the extreme value of the thermal stress of the spray pipe and optimize the parameter selection and design of the spray pipe structure.

Description

Optimization design method for structural parameters of solid rocket engine nozzle
Technical Field
The invention belongs to the technical field of solid rocket engines, and particularly relates to a thermal coupling analysis method and a structural optimization design method of a solid rocket engine nozzle structure.
Background
The solid rocket engine is a power device of space carrier rocket and strategic missile using solid propellant, it burns in the combustion chamber through solid propellant to produce high temperature gas, the gas expands rapidly when passing through the tail of the engine connecting jet pipe, and accelerates from sonic speed to supersonic speed, and after passing through the convergent section and throat liner, it is ejected to the surrounding environment through the divergent section to produce driving force, thus realizing the conversion from chemical energy to kinetic energy. In the working process of the engine, the spray pipe bears the fuel gas temperature of nearly 3400 ℃, the pressure is high, and the spray pipe is washed and corroded by chemical particles, so that the working environment is severe, the spray pipe is used as an important influence factor of the thrust-weight ratio of the solid rocket engine, and the design of the spray pipe assembly and the adopted materials and processing technology thereof directly influence the working performance of the solid rocket engine, so that the thermal coupling analysis of the spray pipe structure of the solid rocket engine is very important. The solid rocket engine jet pipe is subjected to structure optimization design, so that numerical reference can be provided for the design stage of the jet pipe, the design and experiment cost is reduced, the working performance of the engine is improved, and the safety and reliability of the jet pipe are improved.
At present, the structural failure behavior of a solid rocket engine nozzle in the working time is analyzed relatively by a finite element method, but the following problems exist in the related technology:
1. for the uncertain problem of the thermal physical properties of the composite material under the high-temperature condition, an effective method is lacked for determining the characteristic of the performance of the spray pipe material along with the temperature change;
2. the problem treatment of each interface of the spray pipe is simplified, the spray pipe is considered to be always in a firm bonding state, but under the conditions of certain high temperature and shearing force, the adhesive layer slides between layers and is not in strong transfer, and if the problems of interface debonding and adhesive layer softening failure are not considered, a large calculation error is caused;
3. the contact state of the spray pipe before and after interface debonding in the working time cannot be considered, so that the calculated position of the thermal stress extreme value has deviation, and the thermal stress extreme value has error;
4. the existing correlation analysis adopts a sequential coupling analysis method to calculate the thermal stress problem of the spray pipe, a complete coupling analysis method and the sequential coupling analysis method are not compared, and when the mutual influence of temperature gradient and stress is not considered, calculation errors can be caused by adopting the sequential coupling method;
at present, the optimization design method of the spray pipe by combining the thermal failure stress extreme value is less, and no public report exists on how to effectively select and optimize the geometric parameters of the spray pipe and the like aiming at reducing the thermal stress extreme value of the spray pipe in the working time and improving the safety and reliability of the spray pipe.
Disclosure of Invention
In order to solve the problems, the invention makes up the defects of the prior art, and provides an optimal design method for structural parameters of a solid rocket engine nozzle, so that the selection and design of the structural geometric parameters of the nozzle can be optimized while the structural damage thermal stress is effectively reduced, and technical support is provided for the safety and reliability analysis and the structural design of the solid rocket engine nozzle.
The invention adopts the following scheme for solving the technical problems:
the invention relates to an optimization design method of structural parameters of a solid rocket engine nozzle, which is composed of a throat liner, an outer shell, a heat insulation layer and an expansion section and is characterized in that: the structural parameters of the optimized design comprise: the contact inclination angle between the expansion section and the throat insert, the axial length of the expansion section and the radial thickness of the barb of the expansion section; the optimization design method comprises the following steps:
s1: establishing a material parameter interpolation model of the solid rocket engine nozzle according to a segmented three-time Hermite interpolation method shown as the formula (1), and obtaining a material parameter value sequence:
Figure BDA0003512450740000021
in the formula (1), m represents the type of material parameters, the values are 1,2,3 respectively, the values correspond to thermal conductivity, specific heat capacity and thermal expansion coefficient in sequence, n represents the total number of segments, T represents a temperature variable, and H m (T) represents a set of interpolation polynomials consisting of n polynomials, T i Represents the (i + 1) th temperature node,
Figure BDA0003512450740000022
an interpolation polynomial representing the parameter of the m-th material in the ith set of measurement temperature intervals and having:
Figure BDA0003512450740000023
in the formula (2), the reaction mixture is,
Figure BDA0003512450740000024
measuring temperature T for ith group i Lower mth material parameter value, < >>
Figure BDA0003512450740000025
For the value of the parameter of the mth material obtained by means of the finite difference method>
Figure BDA0003512450740000026
Derivative of, Δ T i Indicating the temperature difference between the i-th group of zones, i.e. Δ T i ＝T i -T i-1 ；
S2: obtaining parameter value sequences of gas temperature, convective heat transfer coefficient and pressure at different positions of the inner wall of the spray pipe along the axis direction through a Bartz convective heat transfer formula and a one-dimensional isentropic flow model, and establishing analytic fields of the gas temperature, the convective heat transfer coefficient and the pressure through a Lagrange interpolation method;
s3: initializing a contact dip angle theta of the expansion section and the throat insert as an initial dip angle theta 0 The axial length h of the expansion section is the initial axial lengthDegree h 0 (ii) a Wherein, theta 0 ∈[θ min ,θ max ]；θ min Is the minimum tilt angle; theta max Is the maximum inclination angle;
s4: establishing two-dimensional axisymmetric models of a throat insert, an outer shell, a heat insulation layer and an expansion section in a three-dimensional modeling software in a medium proportion according to the contact inclination angle theta and the axial length h, respectively introducing the two-dimensional axisymmetric models into part modules of ABAQUS software, and assembling through geometric constraint so as to obtain an initial nozzle finite element analysis model;
respectively constructing material attributes corresponding to the throat insert, the outer shell, the heat insulation layer and the expansion section according to the parameter value sequences of different types of material parameters in the step S1, and setting material attribute directions;
according to the analytical fields of the gas temperature, the convective heat transfer coefficient and the pressure intensity established in the step S2, mapping analytical fields of the gas temperature, the convective heat transfer coefficient and the pressure intensity are established through a coordinate mapping relation;
s5: complete thermal coupling finite element analysis is carried out on the spray pipe by ABAQUS software, and comprises the following steps: setting analysis types and analysis time in ABAQUS software, setting surface heat exchange conditions and contact types before and after interface debonding, setting load and geometric constraint, setting initial state of a spray pipe, setting grid types and grid sizes, and calculating to obtain a thermal stress-time history curve C11, thereby extracting the maximum value of thermal stress in the thermal stress curve C11;
s6: according to the initial axial length h 0 After the contact inclination angle theta between the expansion section (4) and the throat insert (1) is adjusted to be theta + delta theta in ABAQUS software, the step S4 is returned to and executed sequentially until the theta is up to the>θ max Until, where Δ θ represents an increment;
s7: let theta be theta 0 Then according to the initial axial length h 0 After the contact inclination angle theta between the expansion section and the throat insert is adjusted to be theta-delta theta in ABAQUS software, the step S4 is returned to be executed sequentially until the theta is up to the theta<θ min Until the end;
s8: drawing thermal stress-time history curves C22 corresponding to different contact inclination angles, and extracting the maximum value of thermal stress in each thermal stress curve C22 to obtain the expansionInitial axial length h of segment 0 The relation curve C33 between the contact inclination angle and the maximum value of the thermal stress and the relation curve C34 between the radial thicknesses of the barbs at the expansion section corresponding to the contact inclination angle are shown below;
s9: according to the maximum value of the thermal stress in the thermal stress curve C11, the relation curve C33 between the inclination angle of the contact surface and the maximum thermal stress and the relation curve C34 between the radial thicknesses of the barbs at the expansion section corresponding to the contact inclination angle, when the thicknesses of the barbs at the expansion section are in the range meeting the structural strength and the extreme value of the thermal stress is minimum, the optimal contact inclination angle theta of the engine spray pipe structure is determined end ；
S10: let the contact tilt angle theta be the initial tilt angle theta 0 After the axial length h of the expansion section is adjusted to h + delta h in the ABAQUS software, the step S4 is returned to be executed sequentially until h is more than h max So as to obtain thermal stress-time curves C44 corresponding to different axial lengths, and extracting the maximum value of the thermal stress in each thermal stress curve C44, and further obtaining the initial inclination angle theta between the expansion section and the throat insert 0 Below, the curve C55 of the relationship between the axial length and the maximum value of the thermal stress;
s11: according to the maximum value of the thermal stress in the thermal stress curve C11 and the relation curve C55 between the axial length of the expansion section and the maximum thermal stress, when the extreme value of the thermal stress is minimum, the optimal axial length h of the expansion section of the engine spray pipe structure is determined end 。
The method for optimally designing the structural parameters of the solid rocket engine nozzle is characterized in that the step S5 is replaced by the following steps:
sequential thermal coupling finite element analysis of the nozzle in ABAQUS software, comprising:
heat transfer analysis: setting analysis time, setting surface heat exchange conditions, setting contact types before and after interface debonding, setting geometric constraints, setting initial states, grid types and grid sizes, and calculating a temperature field of the spray pipe;
thermal stress analysis: setting analysis time, setting load, coupling temperature field, adjusting grid type, and calculating to obtain a thermal stress-time history curve C11, thereby extracting the maximum value of thermal stress in the thermal stress curve C11.
The step S5 includes:
s5.1a: establishing a transient temperature-displacement analysis module for the initial finite element analysis model of the spray pipe, and setting the analysis time as t 1 Setting the maximum temperature change quantity of each step as Temp _ Max;
s5.2a: establishing a Surface heat exchange type as Surface film condition, applying a convection heat exchange coefficient and a gas temperature to the nozzle finite element analysis model, and setting each interface of the nozzle finite element analysis model as a Tie binding type;
s5.3a: creating a load type as Pressure, applying Pressure to the finite element analysis model of the nozzle, and setting the environmental temperature as T in a Predefined Field defined-Field a Setting geometric constraint on the outer shell of the finite element model of the spray pipe;
s5.4a: the method comprises the following steps of (1) carrying out unit division on a spray pipe after the size of a surface grid is set, and setting the type of a divided unit as a temperature-displacement coupling unit CAX8RT;
s5.5a: 0-t of the position of the divided spray pipe before interface debonding 1 Transient complete thermodynamic coupling analysis of the time period is carried out, and a file F1 before debonding is obtained;
s5.6a: another identical initial finite element analysis model was created and the analysis time in S5.1a was adjusted to (t) 2 -t 1 ) Adjusting the interface type of the expansion section and the heat insulating layer in each interface of the spray pipe model of S5.2a to be a surface contact type, setting tangential and normal contact attributes, setting a Predefined Field in S5.3a to be an initial state type, selecting a file F1, executing the steps according to the process sequence of the steps S5.1a to 5.4a, and then performing interface debonding on the divided spray pipe at the position t 1 ～t 2 Transient complete thermodynamic coupling analysis of the time period to obtain the file F2 after debonding for querying 0-t 2 Thermal stress of the nozzle assembly over time.
The step S5 includes:
s5.1b: creating a heat transfer component for an initial nozzle finite element analysis modelAn analysis module for setting analysis time t 2 Setting the maximum temperature change quantity of each step as Temp _ Max;
s5.2b: creating a Surface heat exchange type Surface film condition, applying a convection heat exchange coefficient and a gas temperature to the finite element analysis model of the spray pipe, and setting each interface of the analysis model as a Tie binding type;
s5.3b: setting the ambient temperature to T in a Predefined Field Predefined-Field a Setting geometric constraint on an outer shell (2) of the finite element model of the spray pipe;
s5.4b: the unit division is carried out on the spray pipe after the size of the surface grid is set, and the divided unit type is set as a heat transfer unit DCAX8;
s5.5b: performing transient heat transfer analysis on the divided spray pipes to obtain a spray pipe temperature field file F3;
s5.6b: establishing another same initial analysis model and creating a statics analysis module, setting the analysis time as t 1 ；
S5.7b: establishing a load type as Pressure, applying Pressure to a finite element analysis model of the spray pipe, establishing an initial state type in a Predefined Field Predefined-Field, and selecting a file F3;
s5.8b: after the adjusting unit is an axisymmetric stress unit CAX8R, the position of the adjusting unit is 0-t before the interface debonding of the spray pipe 1 Performing transient sequence thermal coupling analysis on the time periods to obtain a file F4 before debonding;
s5.9b: the analysis time in S5.6b was adjusted to (t) 2 -t 1 ) Adding the interface type of the expansion section and the heat insulating layer in S5.7b as a surface contact type and setting tangential and normal contact properties, adding the initial state type in the Predefined Field Predefined Field of S5.7b and selecting the file F4, and then performing interface debonding on the nozzle at t 1 ～t 2 Transient sequence thermal coupling analysis of the time period spray pipe to obtain a de-glued file F5 for inquiring 0-t 2 Thermal stress of the nozzle assembly over time.
Compared with the prior art, the invention has the beneficial effects that:
1. the numerical interpolation model is used for solving the value range of the thermophysical performance parameters of the composite material at high temperature, and the uncertainty of the material parameter values can be effectively avoided;
2. the method solves the problem of interface debonding caused by softening of an interface adhesive layer at high temperature by changing the contact state before and after interface debonding, avoids the problems of poor precision and the like caused by over simplification of the interface problem in the existing method, more accurately simulates the working state of the solid rocket engine spray pipe, has high applicability, and is suitable for thermal coupling analysis of solid rocket engine spray pipes with different shapes;
3. the method of the invention provides reliable basis for the structural design of the spray pipe by obtaining the change relation curve of the maximum thermal failure stress of the spray pipe of the solid rocket engine, the contact inclination angle and the axial length of the expansion section, and is beneficial to realizing the maximum reduction of the thermal failure of the spray pipe, thereby improving the safety and reliability of the spray pipe.
Drawings
FIG. 1 is a two-dimensional cross-sectional view of a finite element model of a solid rocket engine nozzle used in the present invention;
FIG. 2 is a flow chart of thermal coupling analysis of a nozzle structure of the solid rocket engine according to the present invention;
FIG. 3 is a curve of the relationship between the contact inclination angle of the expansion section and the throat insert and the maximum hoop stress of the nozzle pipe in the present invention;
FIG. 4 is a graph of the thickness of the barbs at the expansion section versus the contact dip angle in the present invention;
the reference numbers in the figures: 1: throat insert, 2: outer shell, 3: heat insulating layer, 4: and (4) an expansion section.
Detailed Description
Referring to fig. 1, in the embodiment, the solid rocket engine nozzle is composed of a throat insert 1, an outer shell 2, a heat insulating layer 3 and an expansion section 4; in the method for optimally designing the structural parameters of the solid rocket engine nozzle, the optimally designed structural parameters comprise: the contact inclination angle theta of the expansion section 4 and the throat insert 1, the axial length h of the expansion section 4 and the radial thickness d of the barb of the expansion section 4 are measured;
s1: establishing a material parameter interpolation model of the solid rocket engine nozzle according to a three-time Hermite interpolation method in a segmentation manner shown in the formula (1), and obtaining a material parameter value sequence:
Figure BDA0003512450740000061
in the formula (1), m represents the type of material parameters, the values are 1,2,3 respectively, the values correspond to thermal conductivity, specific heat capacity and thermal expansion coefficient in sequence, n represents the total number of segments, T represents a temperature variable, and H m (T) represents a set of interpolation polynomials consisting of n polynomials, T i Represents the (i + 1) th temperature node,
Figure BDA0003512450740000062
an interpolation polynomial representing the parameter of the m-th material for the ith set of measurement temperature intervals, having:
Figure BDA0003512450740000063
in the formula (2), the reaction mixture is,
Figure BDA0003512450740000064
measuring temperature T for ith group i A value for a parameter of m seed material->
Figure BDA0003512450740000065
For the value of the parameter of the mth material obtained by means of the finite difference method>
Figure BDA0003512450740000066
Derivative of, Δ T i Indicating the temperature difference, i.e. Δ T, between the i-th group of zones i ＝T i -T i-1 ；
S2: obtaining parameter value sequences of gas temperature, convective heat transfer coefficient and pressure at different positions of the inner wall of the spray pipe along the axis direction through a Bartz convective heat transfer formula and a one-dimensional isentropic flow model, and establishing analytic fields of the gas temperature, the convective heat transfer coefficient and the pressure through a Lagrange interpolation method;
s3: initialThe contact inclination angle theta of the chemical expansion section 4 and the throat insert 1 is the initial inclination angle theta 0 The axial length h of the expansion section 4 is the initial axial length h 0 (ii) a Wherein, theta 0 ∈[θ min ,θ max ]；θ min A given minimum tilt angle; theta.theta. max For a given maximum inclination;
s4: establishing two-dimensional axisymmetric models of the throat insert 1, the outer shell 2, the heat insulation layer 3 and the expansion section 4 in a three-dimensional modeling software in a moderate proportion according to the contact inclination angle theta and the axial length h, then respectively guiding the two-dimensional axisymmetric models into part modules of ABAQUS software in a sketch mode, and assembling the two-dimensional axisymmetric models in an assembly module by geometric constraint so as to obtain an initial spray pipe finite element analysis model as shown in figure 1;
in the property module property, respectively constructing material properties corresponding to the outer shell 2 of the throat insert 1, the heat insulation layer 3 and the expansion section 4 according to parameter value sequences of different types of material parameters in the step S1, and setting material property directions;
according to the analytical fields of the gas temperature, the convective heat transfer coefficient and the pressure intensity established in the step S2, mapping analytical fields of the gas temperature, the convective heat transfer coefficient and the pressure intensity are established through a coordinate mapping relation;
s5: carrying out complete thermal power coupling finite element analysis on the spray pipe by using ABAQUS software, wherein the analysis comprises the following steps: setting an analysis type and analysis time in an ABAQUS software analysis module step, setting a surface heat exchange condition and a contact type before and after interface debonding in an Interaction module Interaction, setting a Load, a geometric constraint and an initial state of a spray pipe in a Load module Load, and calculating to obtain a thermal stress-time history curve C11 after setting a grid type and a grid size in a grid module mesh, thereby extracting a maximum value of the thermal stress in the thermal stress curve C11. The flow of the nozzle complete thermal coupling analysis is shown in figure 2;
in this embodiment, step S5 specifically includes:
s5.1a: establishing a Transient temperature-displacement analysis module Transient-Coupled temperature-displacement analysis in a step module of ABAQUS software for an initial nozzle finite element analysis model, and setting analysis time as t 1 Setting max.allowable t as maximum temperature change per stepThe expert change per increment is a given artificial Temp _ Max;
s5.2a: establishing a Surface heat exchange type of Surface filter condition in an Interaction module, applying a convection heat exchange coefficient and a gas temperature to a nozzle finite element analysis model, respectively corresponding the convection heat exchange coefficient and the gas temperature to Definition and Sink Definition in the Surface filter condition, and setting each interface of the analysis model as a Tie binding type in Constraint;
s5.3a: establishing a Load type as Pressure in a Load module, applying Pressure to a finite element analysis model of the nozzle, setting the Pressure as Distribution, and setting the environment Temperature as T in a Predefined Field Predefined-Field a Setting the geometric constraint of Symmetry/asymmetry/Encastre on the outer shell 2 of the finite element model of the jet pipe;
s5.4a: the method comprises the steps that unit division is carried out on a spray pipe after the size of a surface grid is set in a Mesh module, and the divided unit Type is set to be a temperature-Displacement coupling-Displacement second-order unit CAX8RT in an Element Type;
s5.5a: 0-t of the divided spray pipe before interface debonding in the Job module 1 Transient complete thermodynamic coupling analysis of the time period is carried out to obtain a file F1 before debonding;
s5.6a: another identical initial finite element analysis model was built in the part module of the ABAQUS software and the analysis time in S5.1a was adjusted to (t) 2 -t 1 ) Adjusting the interface type of the expansion section 4 and the heat insulating layer 3 in each interface of the nozzle model of the S5.2a to be a surface contact type, setting tangential and normal contact properties, setting a predefined field PredefinedField in the S5.3a to be an initial state type, selecting a file F1, executing the steps according to the process sequence from the step S5.1a to the step S5.4a, and then performing interface debonding on the divided nozzle at the position t 1 ～t 2 Transient complete thermodynamic coupling analysis of a time period to obtain a file F2 after debonding, and inquiring 0-t in visualization module visualization 2 Thermal stress of the nozzle assembly over time.
S6: according to the initial axial length h 0 In ABAQUS software part modelAfter the contact inclination angle theta between the expansion section 4 and the throat insert 1 is adjusted to be theta + delta theta in the block, the step S4 is returned to and executed sequentially until the theta is adjusted>θ max Thus, where Δ θ represents the magnitude of the increment;
s7: let theta be theta 0 Then, according to the initial axial length h 0 After the contact inclination angle theta between the expansion section 4 and the throat insert 1 is adjusted to be theta-delta theta in the ABAQUS software part module, the step S4 is returned to and executed sequentially until the theta is up to theta<θ min Until the end;
s8: according to the results of the steps S6 and S7, thermal stress-time history curves C22 corresponding to different contact inclination angles are drawn, and the maximum value of the thermal stress in each thermal stress curve C22 is extracted, thereby obtaining the initial axial length h of the expansion section 4 0 The relation curve C33 between the contact inclination angle and the maximum value of the thermal stress and the relation curve C34 between the radial thicknesses of the barbs at the expansion section corresponding to the contact inclination angle are shown below;
s9: according to a relation curve C33 between the maximum value of the thermal stress, the inclination angle of the contact surface and the maximum thermal stress in the thermal stress curve C11, as shown in FIG. 3, a relation curve C34 between radial thicknesses of the barbs at the expansion section corresponding to the contact inclination angle, as shown in FIG. 4, when the thicknesses of the barbs at the expansion section are in a range meeting the structural strength and the extreme value of the thermal stress is minimum, the optimal contact inclination angle theta of the engine nozzle structure is determined end ；
S10: let the contact tilt angle theta be the initial tilt angle theta 0 After the axial length h of the expansion section 4 is adjusted to h + delta h in the part module in the ABAQUS software, the step S4 is returned to be executed in sequence until h is more than h max To a, wherein, h max Obtaining thermal stress-time curves C44 corresponding to different axial lengths for a given maximum axial length, extracting the maximum value of the thermal stress in each thermal stress curve C44, and further obtaining the initial inclination angle theta between the expansion section 4 and the throat insert 1 0 Below, the curve C55 of the relationship between the axial length and the maximum value of the thermal stress;
s11: according to the maximum value of the thermal stress in the thermal stress curve C11 and the relation curve C55 between the axial length of the expansion section and the maximum thermal stress, when the extreme value of the thermal stress is minimum, the optimal axial direction of the expansion section 4 of the engine spray pipe structure is determinedLength h end 。
In a specific implementation, the step S5 is replaced by the following steps:
in ABAQUS software, the spray pipe is subjected to sequential thermal coupling finite element analysis, so that the analysis result reliability is improved by comparing with complete thermal coupling finite element analysis, and the method comprises the following steps:
first, heat transfer analysis was performed: setting analysis time in an analysis module step, setting surface heat exchange conditions and contact types before and after interface debonding in an Interaction module Interaction, setting geometric constraint and an initial state in a Load module Load, and calculating and exporting a temperature field result of the spray pipe after setting a grid type and a grid size in a grid module mesh;
then, thermal stress analysis was performed: setting analysis time in an analysis module step, setting a Load and coupling temperature field in a Load module Load, and calculating to obtain a thermal stress-time history curve C11 after adjusting the grid type in a grid module mesh, thereby extracting the maximum value of the thermal stress in the thermal stress curve C11.
In a specific implementation, step S5 specifically includes:
s5.1b: creating a Heat transfer analysis module transfer-Heat transfer for the initial nozzle finite element analysis model in a step module of ABAQUS software, and setting the analysis time as the nozzle working time t 2 Setting the maximum temperature change per step, namely, max.allowable temperature change per increment, as the artificially given Temp _ Max;
s5.2b: establishing a Surface heat exchange type Surface filter condition in an Interaction module, applying a convection heat exchange coefficient and a gas temperature to a finite element analysis model of a spray pipe, respectively corresponding the convection heat exchange coefficient and the gas temperature to Definition and Sinkdefination in the Surface filter condition, and setting each interface of the analysis model as a Tie binding type in Constraint;
s5.3b: setting the ambient Temperature to T in the Predefined Field Predefined-Field a Setting the geometric constraint of Symmetry/asymmetry/Encastre on the outer shell 2 of the finite element model of the jet pipe;
s5.4b: the method comprises the following steps of (1) carrying out unit division on a spray pipe after the size of a surface grid is set in a Mesh module, and setting the divided unit Type to be a Heat Transfer second-order unit DCAX8 in an Element Type;
s5.5b: performing transient heat transfer analysis on the divided spray pipes in a Job module to obtain a spray pipe temperature field file F3;
s5.6b: establishing another same initial analysis model and creating a statics analysis module, setting the analysis time as t 1 ；
S5.7b: establishing a Load type as Pressure in a Load module, applying Pressure to a finite element analysis model of the spray pipe, setting the model as Distribution, establishing an initial state type in a Predefined Field Predefined-Field, and selecting a calculated spray pipe temperature Field file F3;
s5.8b: after the adjusting unit is an Axisymmetric Stress Axisymetric Stress second-order unit CAX8R, the position of the adjusting unit is 0-t before the interface debonding of the spray pipe in the Job module 1 Performing transient sequence thermal coupling analysis on the time periods to obtain a file F4 before debonding;
s5.9b: the analysis time in S5.6b was adjusted to (t) 2 -t 1 ) Adding in s5.7b the type of interface of the expansion section 4 with the heat insulation layer 3 of the surface Contact type and setting the Tangential tangental Behavior-Penalty at 0.25 and the Normal at normals, adding in the Predefined Field of s5.7b the type of initial state and selecting the file F4, then in the Job module, the t at which the interface debonding of the lance takes place is t 1 ～t 2 Performing transient sequence thermal coupling analysis on the time period spray pipe to obtain a document F5 after debonding, and inquiring 0-t in visualization module visualization 2 Thermal stress of the nozzle assembly over time.

Claims (4)

1. The solid rocket engine jet pipe structure parameter optimization design method is characterized in that: the structural parameters of the optimized design comprise: the contact inclination angle of the expansion section (4) and the throat insert (1), the axial length of the expansion section (4) and the radial thickness of the barb of the expansion section (4); the optimization design method comprises the following steps:
s1: establishing a material parameter interpolation model of the solid rocket engine nozzle according to a segmented three-time Hermite interpolation method shown as the formula (1), and obtaining a material parameter value sequence:
Figure QLYQS_1
in the formula (1), m represents the type of material parameters, the values are 1,2,3 respectively, the values correspond to thermal conductivity, specific heat capacity and thermal expansion coefficient in sequence, n represents the total number of segments, T represents a temperature variable, and H m (T) represents a set of interpolation polynomials consisting of n polynomials, T i Represents the (i + 1) th temperature node,
Figure QLYQS_2
an interpolation polynomial representing the parameter of the m-th material in the ith set of measurement temperature intervals and having:
Figure QLYQS_3
in the formula (2), the reaction mixture is,
Figure QLYQS_4
measuring the temperature T for the ith group i Lower mth material parameter value, < >>
Figure QLYQS_5
For the value of the parameter of the mth material obtained by means of the finite difference method>
Figure QLYQS_6
Derivative of, Δ T i Indicating the temperature difference between the i-th group of zones, i.e. Δ T i ＝T i -T i-1 ；
S2: obtaining parameter value sequences of gas temperature, convective heat transfer coefficient and pressure at different positions of the inner wall of the spray pipe along the axis direction through a Bartz convective heat transfer formula and a one-dimensional isentropic flow model, and establishing analytic fields of the gas temperature, the convective heat transfer coefficient and the pressure through a Lagrange interpolation method;
s3: initializing a contact dip angle theta of the expansion section (4) and the throat insert (1) to be an initial dip angle theta 0 The axial length h of the expansion section (4) is the initial axial length h 0 (ii) a Wherein, theta 0 ∈[θ min ,θ max ]；θ min Is the minimum tilt angle; theta max Is the maximum inclination angle;
s4: establishing two-dimensional axisymmetric models of the throat insert (1), the outer shell (2), the heat insulating layer (3) and the expansion section (4) in a three-dimensional modeling software in a medium proportion according to the contact inclination angle theta and the axial length h, respectively introducing the two-dimensional axisymmetric models into part modules of ABAQUS software, and assembling the two-dimensional axisymmetric models through geometric constraint to obtain an initial nozzle finite element analysis model;
respectively constructing material properties corresponding to the throat insert (1), the outer shell (2), the heat insulation layer (3) and the expansion section (4) according to the parameter value sequences of different types of material parameters in the step S1, and setting material property directions;
according to the analytical fields of the gas temperature, the convective heat transfer coefficient and the pressure intensity established in the step S2, mapping analytical fields of the gas temperature, the convective heat transfer coefficient and the pressure intensity are established through a coordinate mapping relation;
s5: carrying out complete thermal power coupling finite element analysis on the spray pipe by using ABAQUS software, wherein the analysis comprises the following steps: setting analysis types and analysis time in ABAQUS software, setting surface heat exchange conditions and contact types before and after interface debonding, setting load and geometric constraint, setting initial state of a spray pipe, setting grid types and grid sizes, and calculating to obtain a thermal stress-time history curve C11, thereby extracting the maximum value of thermal stress in the thermal stress curve C11;
s6: according to the initial axial length h 0 After the contact inclination angle theta between the expansion section (4) and the throat insert (1) is adjusted to be theta + delta theta in ABAQUS software, the step S4 is returned to and executed sequentially until the theta is up to the>θ max Until, where Δ θ represents an increment;
s7: let theta be theta 0 Then, according to the initial axial length h 0 After adjusting the contact dip angle theta of the expansion section (4) and the throat insert (1) to be theta-delta theta in ABAQUS software, returningStep S4 is executed sequentially until theta<θ min Until the end;
s8: drawing thermal stress-time history curves C22 corresponding to different contact inclination angles, and extracting the maximum value of the thermal stress in each thermal stress curve C22 so as to obtain the initial axial length h of the expansion section (4) 0 Next, a relation curve C33 between the contact inclination angle and the maximum value of the thermal stress and a relation curve C34 between the radial thicknesses of the barbs at the expansion section corresponding to the contact inclination angle are shown;
s9: according to the maximum value of the thermal stress in the thermal stress curve C11, the relation curve C33 between the inclination angle of the contact surface and the maximum thermal stress and the relation curve C34 between the radial thicknesses of the barbs at the expansion section corresponding to the contact inclination angle, when the thicknesses of the barbs at the expansion section are in the range meeting the structural strength and the extreme value of the thermal stress is minimum, the optimal contact inclination angle theta of the engine spray pipe structure is determined end ；
S10: let the contact tilt angle theta be the initial tilt angle theta 0 After the axial length h of the expansion section (4) is adjusted to h + delta h in the ABAQUS software, the step S4 is returned to and executed in sequence until h is more than h max So as to obtain thermal stress-time curves C44 corresponding to different axial lengths, extract the maximum value of the thermal stress in each thermal stress curve C44, and further obtain the initial inclination angle theta between the expansion section (4) and the throat insert (1) 0 Below, the curve C55 of the relationship between the axial length and the maximum value of the thermal stress;
s11: according to the maximum value of the thermal stress in the thermal stress curve C11 and the relation curve C55 between the axial length of the expansion section and the maximum thermal stress, when the extreme value of the thermal stress is minimum, the optimal axial length h of the expansion section (4) of the engine spray pipe structure is determined end 。
2. The method for optimally designing structural parameters of a solid rocket engine nozzle according to claim 1, wherein the step of S5 is replaced by the steps of:
sequential thermal coupling finite element analysis was performed on the nozzle in ABAQUS software, including:
heat transfer analysis: setting analysis time, setting surface heat exchange conditions, setting contact types before and after interface debonding, setting geometric constraints, setting initial states, grid types and grid sizes, and calculating a temperature field of the spray pipe;
and (3) thermal stress analysis: setting analysis time, setting load, coupling temperature field, adjusting grid type, and calculating to obtain a thermal stress-time history curve C11, thereby extracting the maximum value of thermal stress in the thermal stress curve C11.
3. The method for optimally designing structural parameters of a solid rocket engine nozzle according to claim 1, wherein said step S5 comprises:
s5.1a: establishing a transient temperature-displacement analysis module for the initial finite element analysis model of the spray pipe, and setting the analysis time as t 1 Setting the maximum temperature change quantity of each step as Temp _ Max;
s5.2a: establishing a Surface heat exchange type as Surface film condition, applying a convection heat exchange coefficient and a gas temperature to the nozzle finite element analysis model, and setting each interface of the nozzle finite element analysis model as a Tie binding type;
s5.3a: creating a load type as Pressure, applying Pressure to the finite element analysis model of the nozzle, and setting the environmental temperature as T in a Predefined Field defined-Field a Setting geometric constraint on an outer shell (2) of the finite element model of the spray pipe;
s5.4a: the method comprises the following steps of (1) carrying out unit division on a spray pipe after the size of a surface grid is set, and setting the type of a divided unit as a temperature-displacement coupling unit CAX8RT;
s5.5a: 0-t of the position of the divided spray pipe before interface debonding 1 Transient complete thermodynamic coupling analysis of the time period is carried out to obtain a file F1 before debonding;
s5.6a: another identical initial finite element analysis model was created and the analysis time in S5.1a was adjusted to (t) 2 -t 1 ) Adjusting the interface type of the expansion section (4) and the heat insulating layer (3) in each interface of the nozzle model of S5.2a to be a surface contact type, setting the contact properties in the tangential direction and the normal direction, and setting the Predefined Field in S5.3a to be S5.3aAfter the initial state type is selected and the file F1 is selected, the process sequence from the step S5.1a to the step S5.4a is carried out, and then the t where the interface is debonded is carried out on the divided spray pipes 1 ～t 2 Transient complete thermodynamic coupling analysis of the time period to obtain the file F2 after debonding for querying 0-t 2 Thermal stress of the nozzle assembly over time.
4. The method for optimally designing structural parameters of a solid rocket engine nozzle according to claim 2, wherein said step S5 comprises:
s5.1b: establishing a heat transfer analysis module for the initial finite element analysis model of the nozzle, and setting the analysis time to be t 2 Setting the maximum temperature change quantity of each step as Temp _ Max;
s5.2b: creating a Surface heat exchange type Surface film condition, applying a convection heat exchange coefficient and a gas temperature to the finite element analysis model of the spray pipe, and setting each interface of the analysis model as a Tie binding type;
s5.3b: setting the ambient temperature to T in a Predefined Field Predefined-Field a Setting geometric constraint on an outer shell (2) of the finite element model of the spray pipe;
s5.4b: the unit division is carried out on the spray pipe after the size of the surface grid is set, and the divided unit type is set as a heat transfer unit DCAX8;
s5.5b: performing transient heat transfer analysis on the divided spray pipe to obtain a spray pipe temperature field file F3;
s5.6b: establishing another same initial analysis model and creating a statics analysis module, setting the analysis time as t 1 ；
S5.7b: establishing a load type as Pressure, applying Pressure to a finite element analysis model of the spray pipe, establishing an initial state type in a Predefined Field Predefined-Field, and selecting a file F3;
s5.8b: the type of the adjusting unit is 0-t of the position of the spraying pipe before interface debonding after the axial symmetry stress unit CAX8R is adopted 1 Performing transient sequence thermal coupling analysis on the time periods to obtain a file F4 before debonding;
s5.9b: when the analysis in S5.6b is performedIs adjusted to (t) 2 -t 1 ) Adding the interface type of the expansion section (4) and the heat insulating layer (3) into the S5.7b to be a surface contact type and setting the contact properties of the tangential direction and the normal direction, adding the initial state type into the Predefined Field of the S5.7b and selecting a file F4, and then performing interface debonding on the spray pipe at t 1 ～t 2 Transient sequence thermal coupling analysis of the time period spray pipe to obtain a de-bonded file F5 for querying 0-t 2 Thermal stress of the nozzle assembly over time.
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