Design technique evaluates optimum weight of space radiator consisting of finned, right circular cylinder

Burian, R. J.

Harris, D. W.

Ketchman, J. J.

English

Design procedure for weight optimization of straight finned radiators used to reject waste heat from power generators in spac

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A design procedure for the weight optimization of straight finned radiators

December 1966
	 Brief 66-10618 
NASA TECH BRIEF 
NASA Tech Briefs are issued to summarize specific innovations derived from the U.S. space program, 
to encourage their commercial application. Copies are available to the public at 15 cents each 
from the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151. 
A Design Procedure for the Weight Optimization of Straight Finned Radiators 
The design of space power systems is directed 
toward developing a minimum weight device for the 
required power output. For systems developing large 
quantities of electrical power, in the several 100-watt 
and kilowatt range, the radiators usually take the 
form of large panels containing a network of pas-
sages through which the power converter coolant 
flows. In the case of smaller systems, the radiator 
usually takes the form of straight fins extending 
radially from a central body which contains the 
power conversion device. The waste heat is trans-
mitted to the finned radiator from the conversion 
device by conduction. 
Several analyses of the latter type of radiator have 
appeared in the literature. These analyses, however, 
do not lend themselves to rapid design of finned 
radiators. A NASA Technical Note, "A Design Pro-
cedure for the Weight Optimization of Straight Finned 
Radiators", by D. W. Harris, R. J. Burian, and J. J. 
Ketchman, TN D-3489, August 1966, presents a 
technique based on these analyses whereby a weight 
optimized space radiator consisting of a finned, right 
circular cylinder can be readily evaluated. 
From data presented in the literature, the Techni-
cal Note derives 3 design equations which relate 12 
geometric, thermal, environmental, and material para-
meters of an idealized fin system with no base cylinder
interaction. A fourth equation is derived to take into 
account the base cylinder interaction and to reduce 
the idealized design to the realistic case. Three families 
of curves and auxiliary tables assist in the rapid re-
duction of the idealized design equations. 
Notes: 
1. The Technical Note is available from the Clear-
inghouse for Federal Scientific and Technical 
Information, Springfield, Virginia 22151—price 
$2.00 
2. Inquiries concerning this innovation may be di-
rected to: 
Technology Utilization Officer 
Goddard Space Flight Center 
Greenbelt, Maryland 20771 
Reference: B66-10618 
Patent status: 
No patent action is contemplated by NASA. 
Source: D. W. Harris 
of Goddard Space Flight Center 
and R. J. Burian and J. J. Ketchman 
of Batelle Memorial Institute 
under contract to 
Goddard Space Flight Center 
(GSFC-547) 
Category 05 
This document was prepared under the sponsorship of the National	 Government assumes any liability resulting from the use of the 
Aeronautics and Space Administration. Neither the United States 	 information contained in this document, or warrants that such use 
Government nor any person acting on behalf of the United States 	 will be free from privately owned rights.
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A design procedure for the weight optimization of straight finned radiators

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