Quick analysis and design method for heat protection system of aerospace flying vehicle

An aerospace vehicle, rapid analysis technology, applied in computer-aided design, design optimization/simulation, instruments, etc., can solve the problem of inability to realize automatic thermal protection system scheme selection, and there is no mature tool software and method for the thermal protection system of the entire aircraft. And other issues

Inactive Publication Date: 2017-07-21
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, the above method has the disadvantages that it cannot realize the automatic selection of thermal protection system solutions, and needs to use other software for analysis.
At present in China, the analysis and design of specific TPS are mainly carried out through numerical methods, and there are no mature tools and methods for the design of aircraft thermal protection systems.

Method used

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  • Quick analysis and design method for heat protection system of aerospace flying vehicle
  • Quick analysis and design method for heat protection system of aerospace flying vehicle
  • Quick analysis and design method for heat protection system of aerospace flying vehicle

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Embodiment Construction

[0072] The present invention will be further described below in conjunction with accompanying drawings and examples. The one-dimensional unsteady heat transfer process of a typical 15° semi-cone obtuse pyramid structure is taken as an example. The structure is selected from the NASA report "Effects of Angle of Attack and Bluntness on Laminar HeatingRate Distributions of a 15°Cone at a MachNumber of 10.6", the structure size is as follows image 3 As shown, the tip of the structure is a ball cap with a radius of 0.0095m, and the rear part is a cone with a half-cone angle of 15° as a whole.

[0073] (1) Calculation of thickness at nodes

[0074] Select reinforced carbon-carbon composite (RCC) (material density 1580kg / m 3 , specific heat 0.77kJ / kg-K, thermal conductivity k, 4.3W / m-K, radiation coefficient, 0.79), the default wall temperature is 300K, and the allowable temperature of the material is 1900K (for the convenience of case application, the allowable temperature of the...

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Abstract

The invention discloses a quick analysis and design method for a heat protection system of an aerospace flying vehicle. The method comprises three main modules, namely, a one-dimensional unsteady heat conduction calculation module, a heat protection system thickness optimization module, a heat protection system structure inner wall node coordinate determination and structure total weight calculation module, and a heat protection system analysis and design program structure description module. According to the method, the characteristic of quickness of heat protection system design is highlighted in a one-dimensional unsteady heat conduction calculation process; and the efficient and accurate thickness optimization process and the detailed heat protection system structure inner wall node coordinate determination and structure total weight calculation process provide a convenient tool for non-professional personnel to perform analysis and design of the heat protection system of the flying vehicle.

Description

Technical field: [0001] The invention relates to the field of analysis and design of thermal protection systems of aerospace vehicles, in particular to an unsteady-state heat conduction analysis and thermal protection system size optimization design method based on the finite difference method. Background technique: [0002] Aerospace vehicles are subjected to serious aerodynamic heating in the service environment. The high temperature generated by aerodynamic heating on the surface and the thermal stress caused inside the structure seriously threaten the safety of the structure. In order to cope with the high temperature and thermal stress of the structure, it is necessary to use a large number of high temperature resistant thermal structures and thermal protection systems (Thermal Protection System, TPS) in the structural design of aerospace vehicles. TPS consists of three parts: heat insulation layer, heat protection layer and load-bearing structure. These structures are...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23G06F2119/08Y02T90/00
Inventor 李洪双马远卓许青
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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