Reentry aerodynamic environment induced structure thermal response finite element solving optimization method
An optimization method and aerodynamic environment technology, applied in thermal and material science, thermal-mechanical coupling response solution of structural deformation, mechanics, can solve problems such as re-entry, crash and fall flight track
Active Publication Date: 2021-02-12
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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After the completion of the in-orbit mission of this type of large spacecraft, it will face the problems of reentry crash, safety assessment prediction, and determination of the flight path of the fall.
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[0064] In the thermoelastic dynamic equation, set in the space region In , without considering the influence of damping, the material thermoelastic dynamics equation can be expressed as:
[0065]
[0066] 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 Indicates the matrix transpose, ρ is the material density, τ is the 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 ).
[0067] 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:
[0068] 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...
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The invention discloses a reentry aerodynamic environment induced structure thermal response finite element solving optimization method. The method comprises the steps of conducting the discretizationon a control equation based on heat conduction and material thermoelastic dynamics coupling through a finite element method, and giving a corresponding algorithm process; wherein in an algorithm process, for a partial differential equation depending on time, a finite element method firstly discretizes a space region and obtains mesh generation of a solving region, then performs differential discretization on a time term, and performs iterative coupling relaxation calculation according to an iterative coupling relaxation calculation principle; gradually propelling to capture the vibration of the structural material in the space and the thermal response deformation nonlinear behavior caused by the deorbital reentry strong aerodynamic thermal environment of the large spacecraft at the expiration of the service period. The invention provides a thermal coupling response solving optimization method based on a finite element method, which is beneficial to analyzing and researching the thermal coupling response of a material structure under a strong aerodynamic / thermal environment, and is beneficial to carrying out structural performance prediction and simulation on aircrafts and spacecrafts.
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 the end of service life of large spacecraft operating in low-Earth orbit is over, de-orbit control is often adopted to make it leave the current orbit and fall naturally, which belongs to the state of uncontrolled flight. After the completion of the in-orbit mission of this type of large spacecraft, it will face the problems of re-entry 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 aerodynam...
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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