Non-probability aerothermoelasticity reliability designing method for hypersonic control surface

Abstract

The invention discloses a non-probability aerothermoelasticity reliability designing method for a hypersonic control surface. The method is characterized in that uncertainties in aerothermoelasticity designing for the hypersonic control surface are considered, and a sample space for uncertain input parameters is established according to a vertex method; the effects of thermal stress generated by aerodynamic heating on inherent attributes of the control surface are considered, and a bidirectional fluid-structure coupling method is achieved to accurately simulate a dynamic response process of the control surface under the effects of gust loads; on such a basis, reliability indexes are introduced, and reliability analysis of a control surface structure is carried out according to upper and lower bounds of analysis results. Based on the steps, with the control surface structure weight as an optimization objective, and with reliabilities of the maximum displacement of the control surface, the maximum root restraint force and the maximum root restraint moment as restraint conditions, non-probability aeroelasticity reliability optimization designing for the hypersonic control surface can be achieved. The method provided by the invention has the advantages that high reliability of the hypersonic control surface structure is ensured while the structure mass is reduced, so that a new thought is provided for the aerothermoelasticity designing for the hypersonic control surface.

Description

technical field [0001] The invention relates to the field of hypersonic rudder surface structure optimization design method, in particular to a hypersonic rudder surface structure optimization design method combining high-fidelity two-way fluid-solid coupling analysis and non-probabilistic reliability analysis. Background technique [0002] As an elastic structure, the hypersonic rudder surface exhibits dynamic response characteristics under gust loads under the interaction of aerodynamic force, inertial force, and elastic force. cannot be ignored in elastic response analysis. The numerical solution algorithms for this aeroelastic dynamics problem can be divided into two types: one-way fluid-structure coupling method and two-way fluid-structure coupling method. One-way fluid-solid coupling analysis refers to solving the change of aerodynamic force during the whole analysis process first, and then loading the aerodynamic force on the structure to calculate the dynamic respon...

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Problems solved by technology

The advantages of these two reliability models have been reflected in engineering applications, but their defects are also ignored: both models need to obtain a large amount of experimental data through experiments to determine the probability distribution and membership function of the model; Both models require a large amount of calculation; for the probabilistic reliability model, it is very sensitive to parameters, and a small error in the selection of the distribution function may lead to large deviations in the reliability analysis; for the f

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