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Hypersonic flight vehicle thermal protection structure optimization method and system

A thermal protection structure and hypersonic technology, applied in multi-objective optimization, design optimization/simulation, instrumentation, etc., can solve the problems of limited analysis and research of hypersonic panel flutter

Pending Publication Date: 2021-02-05
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Culler simplified the TPS prototype for the NASAX-43 aircraft into a panel structure in order to reduce the modeling complexity and computational cost due to a comprehensive aeroelastic analysis of fluid-thermal-structure coupling, however, this is for high Integral study of panel flutter in supersonic flow, not TPS design
Research on hypersonic panel flutter analysis considering fluid-thermal-structural coupling is still limited

Method used

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  • Hypersonic flight vehicle thermal protection structure optimization method and system
  • Hypersonic flight vehicle thermal protection structure optimization method and system
  • Hypersonic flight vehicle thermal protection structure optimization method and system

Examples

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Effect test

example 1

[0195] Example 1: Thermo-aeroelastic coupling analysis under typical design trajectory of X-34A

[0196] Typical calculated ballistics of the X-34A aircraft ( Figure 13 ), including a post-boost acceleration phase and a long hypersonic cruise flight phase, as well as a speed and altitude descent phase. Calculation and analysis of the long-term aerodynamic heating state and thermoaeroelasticity of the wall plate in the ballistic state, Figure 14 The calculation results of this example are given, including the variation curves of the temperature at 1 / 4, 1 / 2, and 3 / 4 of the surface of the TPS metal plate with the trajectory, and the temperature, thermal stress, and Variation curve of thermal bending moment with ballistic trajectory.

[0197] like Figure 15 As shown, the present invention also provides a hypersonic vehicle thermal protection structure optimization system, including:

[0198] The aeroelastic model solving module 201 is used to solve the aeroelastic model by ...

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Abstract

The invention discloses a hypersonic flight vehicle thermal protection structure optimization method and system. According to the method, the thermo-pneumatic elastic analysis is carried out on the universal reusable launcher TPS metal wall plate in the hypersonic flow, a two-way coupling scheme considering the influence of elastic deformation on pneumatic heating is applied, and a thermo-pneumatic elastic coupling analysis technology is formed by establishing a model of pneumatic elasticity, pneumatic heat, heat conduction and multi-physical-field coupling; and the temperature of the bottom-layer wall plate is lower, the stress is smaller, and the stable boundary is widened, so that beneficial guidance is provided for the optimal design of the TPS structure.

Description

technical field [0001] The invention relates to the field of thermal protection structures for hypersonic aircraft, in particular to a method and system for optimizing the thermal protection structure of hypersonic aircraft. Background technique [0002] Due to the high Mach number of hypersonic vehicles and the prerequisites for flying in the atmosphere, severe aerodynamic heating will lead to material degradation, thermal stress and thermal bending moment under temperature changes, and finally bring about the thermo-aerodynamic-elasticity of the aircraft's thin-walled structure Multiphysics coupling problems. Taking a typical hypersonic vehicle as an example, its lower surface is also a part of the scramjet engine ( figure 1 ), in order to make the fuselage work in a safe temperature range and protect the fuselage from aerodynamic heating, a thermal protection system (TPS) is designed on the lower surface of the hypersonic vehicle. [0003] Existing TPS conceptual optimi...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/17G06F30/23G06F30/28G16C10/00G16C60/00G06F111/06G06F111/10G06F113/08G06F119/08G06F119/14
CPCG06F30/15G06F30/17G06F30/23G06F30/28G16C10/00G16C60/00G06F2111/06G06F2111/10G06F2113/08G06F2119/08G06F2119/14Y02T90/00
Inventor 谢丹张世豪冀春秀车驰
Owner NORTHWESTERN POLYTECHNICAL UNIV
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