scholarly journals Conceptual Analysis of Electron Transpiration Cooling for the Leading Edges of Hypersonic Vehicles

2014 ◽  
Author(s):  
Hicham Alkandry ◽  
Kyle Hanquist ◽  
Iain D. Boyd
Keyword(s):  
Conceptual Analysis ◽  
Hypersonic Vehicles ◽  
Transpiration Cooling ◽  
Leading Edges

Plasma sheath models for electron transpiration cooling in hypersonic vehicles

2022 ◽  
Author(s):  
Rupali Sahu ◽  
Albina Tropina ◽  
Daniil Andrienko ◽  
Richard B. Miles
Keyword(s):  
Plasma Sheath ◽  
Hypersonic Vehicles ◽  
Transpiration Cooling

An Experimental Investigation on Transpiration Cooling for Supersonic Vehicle Nose Cone Using Porous Material

2014 ◽  
Vol 541-542 ◽  
pp. 690-694 ◽  
Author(s):  
Lian Jin Zhao ◽  
Jia Lin ◽  
Jian Hua Wang ◽  
Jin Long Peng ◽  
De Jun Qu ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Porous Material ◽  
Supersonic Jet ◽  
Leading Edge ◽  
Injection System ◽  
Aerodynamic Heating ◽  
Hypersonic Vehicles ◽  
Transpiration Cooling ◽  
Cone Model ◽  
Nose Cone

During hypersonic flight or cruise in the near space, the aerodynamic heating causes a very high temperature on the leading edge of hypersonic vehicles. Transpiration cooling has been recognized the most effective cooling technology. This paper presents an experimental investigation on transpiration cooling using liquid water as coolant for a nose cone model of hypersonic vehicles. The nose cone model consists of sintered porous material. The experiments were carried out in the Supersonic Jet Arc-heated Facility (SJAF) of China Academy of Aerospace Aerodynamics (CAAA) in Beijing. The cooling effect in the different regions of the model was analyzed, and the shock wave was exhibited. The pressure variations of the coolant injection system were continuously recorded. The aim of this work is to provide a relatively useful reference for the designers of coolant driving system in practical hypersonic vehicles.

An integrated algorithm for hypersonic fluid–thermal–structural analysis of aerodynamically heated cylindrical leading edge

2019 ◽  
Vol 233 (14) ◽  
pp. 5177-5191 ◽  
Author(s):  
Jiawei Li ◽  
Jiangfeng Wang
Keyword(s):  
Structural Analysis ◽  
Finite Volume Method ◽  
Finite Volume ◽  
Maximum Temperature ◽  
Aerodynamic Heating ◽  
Hypersonic Vehicles ◽  
Time Step ◽  
Heated Cylinder ◽  
Leading Edges ◽  
Volume Method

The accurate and efficient prediction of the fluid–thermal–structural performance of thermal protection systems on hypersonic vehicles to protect against severe aerodynamic heating is attracting increasing worldwide attention. In this paper, a new integrated fluid-structural-thermal investigation based on the finite volume method is proposed to study the thermal behavior of aerodynamically heated cylinder leading edges in hypersonic flows. A unified integral equation system is developed based on the governing equations for the physical processes of aerodynamic heating and structural heat transfer, which is resolved by using an up-wind finite volume method and a new two-thermal-resistance model in one integrated, vectorized computer program. To demonstrate its capability and reliability, applications for steady/unsteady fluid–thermal–structural analysis are demonstrated on aerodynamically heated cylinder leading edges at Ma 6.47. The results show that the steady maximum temperature of the cylinder can reach approximately 648 K at the stagnation point, and the unsteady results are in good agreement with the experimental data and related references. Compared with the partitioned approach, the integrated method shows better computational stability with relatively small sensitivity to mesh scale and time step, reducing the computation time for the same unsteady case by approximately 50%. The present study indicates that the integrated approach has potential for significant improvements and efficiency in predicting long-endurance fluid-structural-thermal problems of hypersonic vehicles.

A Heat Plate Leading Edge for Hypersonic Vehicles

2008 ◽  
Author(s):  
Scott D. Kasen ◽  
Doug T. Queheillalt ◽  
Craig A. Steeves ◽  
Anthony G. Evans ◽  
Haydn N. G. Wadley
Keyword(s):  
Heat Flux ◽  
Low Temperature ◽  
Heat Pipe ◽  
Thermal Management ◽  
Leading Edge ◽  
Maximum Temperature ◽  
Working Fluid ◽  
Hypersonic Vehicles ◽  
Vapor Flow ◽  
Leading Edges

The intense thermal flux at the leading edges of hypersonic vehicles (traveling at Mach 5 and greater) requires creative thermal management strategies to prevent damage to leading edge components. Carbon fiber composites and/or ablative coatings have been widely utilized to mitigate the effects of the impinging heat flux. This paper focuses on an alternative, metallic leading edge heat pipe concept which combines efficient structural load support and thermal management. The passive concept is based on high thermal conductance heat pipes which redistribute the high heat flux at the leading edge stagnation point through the evaporation, vapor flow, and condensation of a working fluid to a location far from the heat source. Structural efficiency is provided by a sandwich construction using an open-cell core that also allows for vapor flow. A low temperature proof-of-concept copper–water system has been investigated by experimentation. Measuring of the axial temperature profile indicates effective spreading of thermal energy, a lowering of the maximum temperature and reduced overall thermal gradient compared to a non-heat pipe leading edge. A simple transient analytical model based on lumped thermal capacitance theory is compared with the experimental results. The low-temperature prototype shows potential for higher temperature metallic leading edges that can withstand the hypersonic thermo-mechanical environment.

scholarly journals Detailed modeling of electron emission for transpiration cooling of hypersonic vehicles

2017 ◽  
Vol 121 (5) ◽  
pp. 053302 ◽  
Author(s):  
Kyle M. Hanquist ◽  
Kentaro Hara ◽  
Iain D. Boyd
Keyword(s):  
Electron Emission ◽  
Hypersonic Vehicles ◽  
Transpiration Cooling
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