Reduced-order model-based aerodynamic-heat-structure optimization method

A technology of reduced-order model and optimization method, applied in the aerospace field, can solve the problems of aero-thermal-structural coupling calculation efficiency and calculation accuracy contradiction, and achieve the effect of improving the optimization design efficiency, improving the comprehensive performance and shortening the design cycle.

Inactive Publication Date: 2018-03-06
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0004] In order to solve the problem of the contradiction between calculation efficiency and calculation accuracy in the prior art when considering the multidisciplinary optimization design of the aerodynamic-thermal-structural coupling problem of the hypersonic vehicle in the full trajectory

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  • Reduced-order model-based aerodynamic-heat-structure optimization method

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Embodiment 1

[0035] The aerodynamic-thermal-structural optimization design problem of a typical hypersonic lifting surface involves the three disciplines of fluid, heat conduction and structure. Through the optimization of the lifting surface skin and the thickness of the transverse and longitudinal bulkheads, under the condition of satisfying the minimum flutter velocity constraints, Reach the minimum mass of the lifting surface. The aerodynamic-thermal-structural optimization method based on the reduced-order model is used to optimize the design of typical lifting surfaces.

[0036] like figure 1 As shown, an aerodynamic-thermal-structural optimization method based on a reduced-order model disclosed in this embodiment, the specific implementation steps are as follows:

[0037] Step 1, in the typical lifting surface aerodynamic-thermal-structural optimization design, the thermal conduction of the lifting surface and the structural modal calculation considering the temperature load adopt ...

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Abstract

The invention discloses a reduced-order model-based aerodynamic-heat-structure optimization method and belongs to the field of aerospace. The method comprises the steps of building an aircraft analysis model; building an initial aerodynamic heat reduced-order model; verifying an overall average relative error of the built aerodynamic heat reduced-order model; building an aerodynamic heat reduced-order model meeting a design precision requirement; obtaining a change condition of a structural internal temperature field of an aircraft in a whole ballistic flight process; performing aeroelasticityanalysis considering temperature influence in a whole ballistic trajectory for the aircraft; and by taking aircraft aeroelasticity characteristics obtained by analysis as constraints, optimizing design variables in the aircraft by adopting an optimization algorithm with a global optimization capability, thereby improving comprehensive performance of the hypersonic aircraft. The aerodynamic-heat-structure multidisciplinary optimization design efficiency of the hypersonic aircraft can be improved; the design cost can be reduced; the engineering practicality of the multidisciplinary design optimization method in hypersonic aircraft design can be improved; and the method has the advantage of high universality.

Description

technical field [0001] The invention belongs to the field of aerospace, and relates to an aerodynamic-thermal-structure optimization method based on a reduced-order model. Background technique [0002] A hypersonic vehicle usually refers to an aircraft that can fly at a speed of not less than Mach 5, is powered by a ramjet engine, and can fly for a long distance in adjacent space. With the gradual improvement of human pursuit of speed and the promotion of demand in transportation, military and other fields, a large number of hypersonic vehicles continue to appear. Hypersonic aircraft represented by X-43 use a large number of new lightweight materials and thin-walled structure designs, and the aerodynamic layout is usually a slender waverider configuration to reduce the weight of the aircraft while increasing the internal volume of the aircraft and increasing the lift-to-drag ratio . These characteristics make the natural frequency of modern hypersonic vehicle structure low...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 刘莉岳振江康杰周思达陈树霖
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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