Author:
Publisher: DIANE Publishing
ISBN: 1428995420
Category :
Languages : en
Pages : 26
Book Description
Design considerations for lightweight space radiators based on fabrication and test experience with a carboncarbon composite prototype heat pipe
Author:
Publisher: DIANE Publishing
ISBN: 1428995420
Category :
Languages : en
Pages : 26
Book Description
Publisher: DIANE Publishing
ISBN: 1428995420
Category :
Languages : en
Pages : 26
Book Description
Design Considerations for Lightweight Space Radiators Based on Fabrication and Test Experience with a Carbon-carbon Composite Prototype Heat Pipe
Author:
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 26
Book Description
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 26
Book Description
Design Considerations for Lightweight Space Radiators Based on Fabrication and Test Experience with a Carbon-Carbon Composite Prototype Heat Pipe. Rev
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781724093011
Category : Science
Languages : en
Pages : 28
Book Description
This report discusses the design implications for spacecraft radiators made possible by the successful fabrication and proof-of-concept testing of a graphite-fiber-carbon-matrix composite (i.e., carbon-carbon (C-C)) heat pipe. The prototype heat pipe, or space radiator element, consists of a C-C composite shell with integrally woven fins. It has a thin-walled furnace-brazed metallic (Nb-1%Zr) liner with end caps for containment of the potassium working fluid. A short extension of this liner, at increased wall thickness beyond the C-C shell, forms the heat pipe evaporator section which is in thermal contact with the radiator fluid that needs to be cooled. From geometric and thermal transport properties of the C-C composite heat pipe tested, a specific radiator mass of 1.45 kg/sq m can be derived. This is less than one-fourth the specific mass of present day satellite radiators. The report also discusses the advantage of segmented space radiator designs utilizing heat pipe elements, or segments, in their survivability to micrometeoroid damage. This survivability is further raised by the use of condenser sections with attached fins, which also improve the radiation heat transfer rate. Since the problem of heat radiation from a fin does not lend itself to a closed analytical solution, a derivation of the governing differential equation and boundary conditions is given in appendix A, along with solutions for rectangular and parabolic fin profile geometries obtained by use of a finite difference computer code written by the author. Juhasz, Albert J. Glenn Research Center NASA/TP-1998-207427/REV1, E-11139-2/REV1, NAS 1.60:207427/REV1
Publisher: Independently Published
ISBN: 9781724093011
Category : Science
Languages : en
Pages : 28
Book Description
This report discusses the design implications for spacecraft radiators made possible by the successful fabrication and proof-of-concept testing of a graphite-fiber-carbon-matrix composite (i.e., carbon-carbon (C-C)) heat pipe. The prototype heat pipe, or space radiator element, consists of a C-C composite shell with integrally woven fins. It has a thin-walled furnace-brazed metallic (Nb-1%Zr) liner with end caps for containment of the potassium working fluid. A short extension of this liner, at increased wall thickness beyond the C-C shell, forms the heat pipe evaporator section which is in thermal contact with the radiator fluid that needs to be cooled. From geometric and thermal transport properties of the C-C composite heat pipe tested, a specific radiator mass of 1.45 kg/sq m can be derived. This is less than one-fourth the specific mass of present day satellite radiators. The report also discusses the advantage of segmented space radiator designs utilizing heat pipe elements, or segments, in their survivability to micrometeoroid damage. This survivability is further raised by the use of condenser sections with attached fins, which also improve the radiation heat transfer rate. Since the problem of heat radiation from a fin does not lend itself to a closed analytical solution, a derivation of the governing differential equation and boundary conditions is given in appendix A, along with solutions for rectangular and parabolic fin profile geometries obtained by use of a finite difference computer code written by the author. Juhasz, Albert J. Glenn Research Center NASA/TP-1998-207427/REV1, E-11139-2/REV1, NAS 1.60:207427/REV1
Design Considerations for Lightweight Space Radiators Based on Fabrication and Test Experience with a Carbon-Carbon Composite Prototype Heat Pipe
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722150440
Category :
Languages : en
Pages : 24
Book Description
This report discusses the design implications for spacecraft radiators made possible by the successful fabrication and Proof-of-concept testing of a graphite-fiber-carbon-matrix composite (i.e., carbon-carbon (C-C)) heat pipe. The proto-type heat pipe, or space radiator element, consists of a C-C composite shell with integrally woven fins. It has a thin-walled furnace-brazed metallic (Nb-1%Zr) liner with end caps for containment of the potassium working fluid. A short extension of this liner, at increased wall thickness beyond the C-C shell, forms the heat pipe evaporator section which is in thermal contact with the radiator fluid that needs to be cooled. From geometric and thermal transport properties of the C-C composite heat pipe tested, a specific radiator mass of 1.45 kg/m2 can be derived. This is less than one-fourth the specific mass of present day satellite radiators. The report also discusses the advantage of segmented space radiator designs utilizing heat pipe elements, or segments, in their survivability to micro-meteoroid damage. This survivability is further raised by the use of condenser sections with attached fins, which also improve the radiation heat transfer rate. Since the problem of heat radiation from a fin does not lend itself to a closed analytical solution, a derivation of the governing differential equation and boundary conditions is given in appendix A, along with solutions for rectangular and parabolic fin profile geometries obtained by use of a finite difference computer code written by the author. Juhasz, Albert J. Glenn Research Center RTOP 632-1A-1X...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722150440
Category :
Languages : en
Pages : 24
Book Description
This report discusses the design implications for spacecraft radiators made possible by the successful fabrication and Proof-of-concept testing of a graphite-fiber-carbon-matrix composite (i.e., carbon-carbon (C-C)) heat pipe. The proto-type heat pipe, or space radiator element, consists of a C-C composite shell with integrally woven fins. It has a thin-walled furnace-brazed metallic (Nb-1%Zr) liner with end caps for containment of the potassium working fluid. A short extension of this liner, at increased wall thickness beyond the C-C shell, forms the heat pipe evaporator section which is in thermal contact with the radiator fluid that needs to be cooled. From geometric and thermal transport properties of the C-C composite heat pipe tested, a specific radiator mass of 1.45 kg/m2 can be derived. This is less than one-fourth the specific mass of present day satellite radiators. The report also discusses the advantage of segmented space radiator designs utilizing heat pipe elements, or segments, in their survivability to micro-meteoroid damage. This survivability is further raised by the use of condenser sections with attached fins, which also improve the radiation heat transfer rate. Since the problem of heat radiation from a fin does not lend itself to a closed analytical solution, a derivation of the governing differential equation and boundary conditions is given in appendix A, along with solutions for rectangular and parabolic fin profile geometries obtained by use of a finite difference computer code written by the author. Juhasz, Albert J. Glenn Research Center RTOP 632-1A-1X...
Mathematical Analysis of Space Radiator Segmenting for Increased Reliability and Reduced Mass
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
Book Description
Parametric Study of Radiator Concepts for a Stirling Radioisotope Power System Applicable to Deep Space Mission
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
Book Description
Space Technology and Applications International Forum 2007
Author: Mohamed S. El-Genk
Publisher: AIP Conference Proceedings (Nu
ISBN:
Category : Science
Languages : en
Pages : 1262
Book Description
The proceedings of STAIF-2007 feature a broad spectrum of topics on. These topics span the range from basic research to the most recent technology advances and hardware development and testing. The proceedings will be of particular interest to program managers, practicing engineers, academicians, graduate students, system designers, and researchers interested in the fields of space technology and space science.
Publisher: AIP Conference Proceedings (Nu
ISBN:
Category : Science
Languages : en
Pages : 1262
Book Description
The proceedings of STAIF-2007 feature a broad spectrum of topics on. These topics span the range from basic research to the most recent technology advances and hardware development and testing. The proceedings will be of particular interest to program managers, practicing engineers, academicians, graduate students, system designers, and researchers interested in the fields of space technology and space science.
A Collection of Technical Papers
Author: Conference
Publisher:
ISBN: 9780780357075
Category : Direct energy conversion
Languages : en
Pages : 752
Book Description
Publisher:
ISBN: 9780780357075
Category : Direct energy conversion
Languages : en
Pages : 752
Book Description
Space Technology and Applications International Forum - STAIF 2004
Author: American Institute of Physics
Publisher: American Institute of Physics
ISBN:
Category : Science
Languages : en
Pages : 1292
Book Description
Albuquerque, New Mexico, 8-11 February 2004
Publisher: American Institute of Physics
ISBN:
Category : Science
Languages : en
Pages : 1292
Book Description
Albuquerque, New Mexico, 8-11 February 2004
A Power Conversion Concept for the Jupiter Icy Moons Orbiter
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description