Active cooling of aerospace plane using H2, CH4, and Xe

Ahmed Z. Al-Garni; Ahmet Z. Sahin; Bekir S. Yilbas; Saad A. Ahmed

Active cooling of aerospace plane using H₂, CH₄, and X_e

Ahmed Z. Al-Garni, Ahmet Z. Sahin, Bekir S. Yilbas, Saad A. Ahmed

King Fahd University of Petroleum and Minerals

Research output: Contribution to conference › Paper › peer-review

1 Citation (Scopus)

Abstract

The work presents a comparative study for cooling aerospace plane, using liquid H₂, CH₄, and X_e. The ascending optimized trajectory to minimize the heat load in the hypersonic part is used to perform the study. The amount of heat rate and the mass of liquid coolant needed for cooling are calculated. A design of minimum inlet-outlet areas for the amount of liquid needed for cooling, is made with the consideration of the coolant's physical constraints in liquids and gaseous states. The comparison shows that the hydrogen is a clear winner as a candidate for coolant and it saves mass as compared to the other two coolants. The study shows that there are no fundamental barriers for the cooling system of the vehicle in terms of its coolant mass and area size for coolant passage, especially, if H₁ is used.

Original language	English
Pages	435-442
Number of pages	8
Publication status	Published - 1995
Externally published	Yes
Event	20th Atmospheric Flight Mechanics Conference, 1995 - Baltimore, United States Duration: 7 Aug 1995 → 10 Aug 1995

Conference

Conference	20th Atmospheric Flight Mechanics Conference, 1995
Country/Territory	United States
City	Baltimore
Period	7/08/95 → 10/08/95

Bibliographical note

Publisher Copyright:
© 1995 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

UN SDGs

This output contributes to the following UN Sustainable Development Goals (SDGs)

Cite this

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title = "Active cooling of aerospace plane using H2, CH4, and Xe",

abstract = "The work presents a comparative study for cooling aerospace plane, using liquid H2, CH4, and Xe. The ascending optimized trajectory to minimize the heat load in the hypersonic part is used to perform the study. The amount of heat rate and the mass of liquid coolant needed for cooling are calculated. A design of minimum inlet-outlet areas for the amount of liquid needed for cooling, is made with the consideration of the coolant's physical constraints in liquids and gaseous states. The comparison shows that the hydrogen is a clear winner as a candidate for coolant and it saves mass as compared to the other two coolants. The study shows that there are no fundamental barriers for the cooling system of the vehicle in terms of its coolant mass and area size for coolant passage, especially, if H1 is used.",

author = "Al-Garni, \{Ahmed Z.\} and Sahin, \{Ahmet Z.\} and Yilbas, \{Bekir S.\} and Ahmed, \{Saad A.\}",

note = "Publisher Copyright: {\textcopyright} 1995 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.; 20th Atmospheric Flight Mechanics Conference, 1995 ; Conference date: 07-08-1995 Through 10-08-1995",

year = "1995",

language = "English",

pages = "435--442",

}

TY - CONF

T1 - Active cooling of aerospace plane using H2, CH4, and Xe

AU - Al-Garni, Ahmed Z.

AU - Sahin, Ahmet Z.

AU - Yilbas, Bekir S.

AU - Ahmed, Saad A.

PY - 1995

Y1 - 1995

N2 - The work presents a comparative study for cooling aerospace plane, using liquid H2, CH4, and Xe. The ascending optimized trajectory to minimize the heat load in the hypersonic part is used to perform the study. The amount of heat rate and the mass of liquid coolant needed for cooling are calculated. A design of minimum inlet-outlet areas for the amount of liquid needed for cooling, is made with the consideration of the coolant's physical constraints in liquids and gaseous states. The comparison shows that the hydrogen is a clear winner as a candidate for coolant and it saves mass as compared to the other two coolants. The study shows that there are no fundamental barriers for the cooling system of the vehicle in terms of its coolant mass and area size for coolant passage, especially, if H1 is used.

AB - The work presents a comparative study for cooling aerospace plane, using liquid H2, CH4, and Xe. The ascending optimized trajectory to minimize the heat load in the hypersonic part is used to perform the study. The amount of heat rate and the mass of liquid coolant needed for cooling are calculated. A design of minimum inlet-outlet areas for the amount of liquid needed for cooling, is made with the consideration of the coolant's physical constraints in liquids and gaseous states. The comparison shows that the hydrogen is a clear winner as a candidate for coolant and it saves mass as compared to the other two coolants. The study shows that there are no fundamental barriers for the cooling system of the vehicle in terms of its coolant mass and area size for coolant passage, especially, if H1 is used.

UR - https://www.scopus.com/pages/publications/84983208756

M3 - Paper

AN - SCOPUS:84983208756

SP - 435

EP - 442

T2 - 20th Atmospheric Flight Mechanics Conference, 1995

Y2 - 7 August 1995 through 10 August 1995

ER -