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Finite element solution optimization method for structural thermal response induced by re-entry aerodynamic environment

An optimization method and aerodynamic environment technology, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as reentry crashes and falling flight tracks

Active Publication Date: 2022-04-12
中国空气动力研究与发展中心超高速空气动力研究所 +2
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Problems solved by technology

After the in-orbit mission of this type of large spacecraft is completed, it will face the problems of reentry crash, safety assessment prediction, and determination of the flight path of the fall.

Method used

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  • Finite element solution optimization method for structural thermal response induced by re-entry aerodynamic environment
  • Finite element solution optimization method for structural thermal response induced by re-entry aerodynamic environment
  • Finite element solution optimization method for structural thermal response induced by re-entry aerodynamic environment

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Embodiment

[0068] In the thermoelastic dynamic equation, set in the space region In , without considering the influence of damping, the material thermoelastic dynamic equation can be expressed as:

[0069]

[0070] Among them, u=[u 1 u 2 u 3 ] T Indicates the displacement vector, f=[f 1 f 2 f 3 ] T is the body force vector, superscript T means matrix transpose, ρ is material density, τ is material damping coefficient, C ijkl is the fourth-order elastic tensor of the material, for homogeneous and isotropic materials, C ijkl Expressed as: C ijkl =λδ ij δ kl +G(δ ik δ jl +δ il δ jk ).

[0071] Among them, δ ij is the Kronecker symbol, λ and G are the material Lamé constants, expressed by the material Young's modulus E and Poisson's ratio ν as:

[0072] Use θ=T-T 0 Indicates the temperature increment, T is the absolute temperature value, T 0 is the temperature value in the undeformed state. beta ij is the thermal elastic modulus, which can be expressed as: β ...

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Abstract

The invention discloses a finite element solution optimization method for structural thermal response caused by re-entry aerodynamic environment, which includes: discretizing the coupled control equation based on heat conduction and material thermoelastic dynamics through the finite element method and providing a corresponding algorithm flow; wherein, In the algorithm process, for time-dependent partial differential equations, the finite element method discretizes the spatial region first, and obtains the grid division of the solution region, and then differentially discretizes the time item. According to the iterative coupling relaxation calculation principle, step by step Advance to capture the vibration of structural materials in space and the nonlinear behavior of thermal response deformation of large spacecraft after de-orbiting and re-entry into a strong aerodynamic thermal environment. The present invention provides an optimization method based on the finite element method for solving thermal-mechanical coupling response, which is beneficial for analyzing and researching the thermal-mechanical coupling response of material structures under strong aerodynamic / thermal environments, and is conducive to carrying out the performance prediction of aircraft and spacecraft structures with simulation.

Description

technical field [0001] The invention belongs to the technical field of aircraft aerodynamics, and mainly relates to problems of mechanics, heat and material science, in particular to a method based on finite element method to solve the thermomechanical coupling response of the structural deformation caused by the aerodynamic thermal environment of the expired spacecraft after de-orbiting and re-entry Optimization. Background technique [0002] When the service period or end of life of large spacecraft operating in low-Earth orbit is over, de-orbit control is often used to make it leave the current orbit and fall naturally, which is an uncontrolled flight state. After the in-orbit mission of this type of large spacecraft is completed, it will face the problems of reentry crash, safety assessment prediction, and determination of the flight path of the fall. When this type of spacecraft re-enters the atmosphere, it encounters a strong aerodynamic / thermal environment, which mak...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F30/28G06F30/15G06F113/08G06F119/08G06F119/14
CPCG06F30/23G06F30/28G06F30/15G06F2113/08G06F2119/08G06F2119/14Y02T90/00
Inventor 李志辉马强李绪国石卫波柳治辉梁杰
Owner 中国空气动力研究与发展中心超高速空气动力研究所
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