scholarly journals Thermo-Structural Behaviour Prediction of the Nose Cap of a Hypersonic Vehicle Based on Multifield Coupling

2020 ◽  
Vol 2020 ◽  
pp. 1-12
Author(s):  
Xuewen Sun ◽  
Haibo Yang ◽  
Tao Mi
Keyword(s):  
Heat Transfer ◽  
Flow Field ◽  
Principal Stress ◽  
Structural Model ◽  
Coupling Model ◽  
Maximum Principal Stress ◽  
Hypersonic Vehicle ◽  
Structural Behaviour ◽  
Structural Coupling ◽  
Initial Stage

The analysis of thermo-structural behaviour is crucial to the nose cap of a hypersonic vehicle under aerothermodynamic loads. Considering chemical nonequilibrium of the flow field, heat transfer, and deformation of the structure, a fluid-thermal-structural coupling model of the typical nose cap was established. The coupling relation between the flow field and nose cap was analyzed. The results show that the fluid-thermal-structural model can effectively predict the response of the nose cap under a hypersonic environment. The highest temperature and the peak of maximum principal stress appear at the front of the nose cap at an initial stage. As time goes on, the highest temperature increases gradually and the peak of maximum principal stress decreases after reaching a certain value. The position of the peak of maximum principal stress gradually moves to the inside of the nose cap and eventually stabilizes. With the increase in the Mach number, the highest temperature and the peak of maximum principal stress of the nose cap increase. The fluid-thermal-structural coupling model can provide guidance for the optimal design of the nose cap of a hypersonic vehicle.

scholarly journals Heat Transfer and Ablation Prediction of Carbon/Carbon Composites in a Hypersonic Environment Using Fluid-Thermal-Ablation Multiphysical Coupling

2020 ◽  
Vol 2020 ◽  
pp. 1-13
Author(s):  
Xuewen Sun ◽  
Haibo Yang ◽  
Tao Mi
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Flow Field ◽  
Thermal Ablation ◽  
Thermal Protection ◽  
Leading Edge ◽  
Coupling Model ◽  
Carbon Composites ◽  
Hypersonic Vehicles ◽  
Lateral Area

Carbon/carbon composites are usually used as a thermal protection material in the nose cap and leading edge of hypersonic vehicles. In order to predict the thermal and ablation response of a carbon/carbon model in a hypersonic aerothermal environment, a multiphysical coupling model is established taking into account thermochemical nonequilibrium of a flow field, heat transfer, and ablation of a material. A mesh movement algorithm is implemented to track the ablation recession. The flow field distribution and ablation recession are studied. The results show that the fluid-thermal-ablation coupling model can effectively predict the thermal and ablation response of the material. The temperature and heat flux in the stationary region of the carbon/carbon model change significantly with time. As time goes on, the wall temperature increases and the heat flux decreases. The ablation in the stagnation area is more serious than in the lateral area. The shape of the material changes, and the radius of the leading edge increases after ablation. The fluid-thermal-ablation coupling model can be used to provide reference for the design of a thermal protection system.

scholarly journals Microscale flow and heat transfer between the rotor and the flank for rotary engine

2019 ◽  
pp. 330-330
Author(s):  
Zhaoju Qin
Keyword(s):  
Heat Transfer ◽  
Temperature Field ◽  
Flow Field ◽  
Velocity Slip ◽  
Coupling Model ◽  
Rotary Engine ◽  
Flow And Heat Transfer ◽  
Microscale Flow ◽  
Commercial Code ◽  
Steady Laminar

This paper is to investigate microscale flow and transfer between the rotor and the flank for rotary engine. The rotor and flank is simplified to two disks in order to study flow field and temperature field conveniently. The paper takes analysis of steady laminar flow and heat transfer between two disks separated by a gas-filled gap due to machining tolerance. A 3-D multi-physical coupling model is used, involving velocity slip, temperature jump, rarefaction and dissipation. A solution based on commercial code COMSOL is derived and the results are used to illustrate the effects to velocity field, temperature distribution, disks' torque and Nusselt number based on the governing parameters. The paper also investigates the effects of different modified Knudsen number on flow field and temperature field.

FLOW FIELD AND HEAT TRANSFER ANALYSIS IN AMON/MMH BIPROPELLANT ROCKET ENGINE

2017 ◽  
Vol 16 (3) ◽  
pp. 263-280 ◽  
Author(s):  
Yu Daimon ◽  
Hideyo Negishi ◽  
Hiroumi Tani ◽  
Yoshiki Matsuura ◽  
Shigeyasu Iihara ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Flow Field ◽  
Rocket Engine ◽  
Heat Transfer Analysis

Fundamental Issues and Recent Advancements in Analysis of Aircraft Brake Natural Convective Cooling

1998 ◽  
Vol 120 (4) ◽  
pp. 840-857 ◽  
Author(s):  
M. P. Dyko ◽  
K. Vafai
Keyword(s):  
Heat Transfer ◽  
Natural Convection ◽  
Flow Field ◽  
Three Dimensional ◽  
Convective Cooling ◽  
Cooling Flow ◽  
Physical Mechanisms ◽  
Braking System ◽  
Flow And Heat Transfer ◽  
Convection Cooling

A heightened awareness of the importance of natural convective cooling as a driving factor in design and thermal management of aircraft braking systems has emerged in recent years. As a result, increased attention is being devoted to understanding the buoyancy-driven flow and heat transfer occurring within the complex air passageways formed by the wheel and brake components, including the interaction of the internal and external flow fields. Through application of contemporary computational methods in conjunction with thorough experimentation, robust numerical simulations of these three-dimensional processes have been developed and validated. This has provided insight into the fundamental physical mechanisms underlying the flow and yielded the tools necessary for efficient optimization of the cooling process to improve overall thermal performance. In the present work, a brief overview of aircraft brake thermal considerations and formulation of the convection cooling problem are provided. This is followed by a review of studies of natural convection within closed and open-ended annuli and the closely related investigation of inboard and outboard subdomains of the braking system. Relevant studies of natural convection in open rectangular cavities are also discussed. Both experimental and numerical results obtained to date are addressed, with emphasis given to the characteristics of the flow field and the effects of changes in geometric parameters on flow and heat transfer. Findings of a concurrent numerical and experimental investigation of natural convection within the wheel and brake assembly are presented. These results provide, for the first time, a description of the three-dimensional aircraft braking system cooling flow field.

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