A Coupled Calculation Method for Thermo-Aeroelastic Properties of Hypersonic Vehicles

Abstract

The invention discloses a coupling computing method of dynamic elasticity characteristics of a high supersonic velocity flight vehicle. Starting from physical field characteristic times like aerodynamic force, aerodynamic heat, structural heat transfer and structural stress / deformation, on the premise of considering existing computing resources and not lowering coupling computing precision, the computing amount of a coupling analysis method is effectively reduced, and the coupling computing method can be applied to hot-gas dynamic elasticity analysis of an actual structure of the high supersonic velocity flight vehicle. By monitoring the change condition of the structural temperature field, dynamic adjustment of the coupling time step length can be achieved, and on the condition of effectively guaranteeing the coupling computing precision, the problem of improving the coupling computing efficiency by a large margin is solved. According to the coupling computing method of the dynamic elasticity characteristics of the high supersonic velocity flight vehicle, hot-gas dynamic elasticity characteristic analysis of whole-machine structure or parts of the high supersonic velocity flight vehicle can be effectively achieved; meanwhile, for flow-heat-solid coupling computing problems like the aerodynamic heat and heat transfer coupling problem and the structural heat safety evaluation problem which are also related to the flight vehicle, the coupling computing method also has the solving capability.

Description

technical field [0001] The invention relates to a coupling calculation method for thermoaeroelastic characteristics of a hypersonic aircraft. Background technique [0002] Affected by the mission requirements of high speed, high maneuverability and long endurance, the new generation of hypersonic vehicles mostly adopt the configuration of slender body, lifting body or waverider body. At the same time, it has greater structural flexibility due to mass limitations. Under the combined effects of long-term aerodynamic force and aerodynamic heat, the significant changes in structural stress, stiffness, and mode caused by temperature rise have a great impact on the aeroelastic characteristics of the aircraft. Aircraft thermal safety poses unprecedented challenges. For the prediction of thermoaeroelastic properties of real aircraft structures, there is no experimental research capability at home and abroad, and the research mainly relies on numerical analysis. And due to the com...

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Problems solved by technology

[0004] In order to overcome the above-mentioned shortcomings of the prior art, the present invention proposes a coupling calculation method for the thermoaeroelastic properties of a hypersonic vehicle. By reasonably adjusting the coupling time interval, the total calculation amount is greatly reduced, and the calculation time can be calculated in days , making the calculation of thermoaeroelastic problems practical

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