Size and temperature approximation analysis of cylindrical radiator with internal heat rejection use for SNAP-

Perez, E. F.

English

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APPROVED:
DEPARTMENT HEAD
P. I. Wood . C. Ross
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•	 SNAP-8
DIYI.S^N
TECNNIM MEMORANDUM
TM -. 345: 63-1-105
DATE 122 April 1963.
w.o. 0743-05-2000
4
PREPARED BY: E'• F. Perez
ABSTRACT
CYLINDRICAL RADIATOR WITH INTERNAL HEAT REJECTION .
An analysis of a cylindrical radiator with heat rejection out of the ends
is presented along with the resultant axial temperature profile and radiator
weight. The analysis is an approximation, based on several assumptions, which
permits a rapid evaluation by an iterative process. The results are based on
a design point consistent with SNAP-8 prime radiator requirements during opera-
tion with maximum heat load from solar and planetary sources. Results were
also obtained for operating temperature levels with no external heat load. A
size and weight comparison is made with a cylindrical radiator having the
interior surface completely insulated.
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CLEVELANID.
NOTE: This document is considered preliminary and is subject to revision as
analysis progresses and additional data arc acquired. The general reader may
encounter internal reference not available to him.
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DOPY MO
PAGE$:
64
TM 345:63-1-105
CYLINDRICAL RADIATOR WITH INTERNAL HEAT REJECTION
I. INTRODUCTION
An analysis was made to evaluate a cylindrical radiator with heat rejection
out of the ends. This analysis was made to permit a comparison to a cylindrical
radiator in which the inside of the cylinder is insulated and with no heat
rejection out of the ends.
This was a simplified analysis to obtain an approximate evaluation of the
radiator performance, prior to the date when more accurate information can be
supplied by NASA.
II. DISCUSSION
A. RADIATOR DESIGN CRITERIA
The radiator was designed to provide the required heat re2-ction,
337 kw thermal, at temperature levels corresponding to the system design point,
and with the maximum external heat load from solar and planetary sources. This
corresponds to a high-noon position in an earth orbit with the longitudinal axis
of the cylinder normal to the solar flux. After sizing the radiator for maximum
external heat load, an analysis was made to determine the radiator operating
temperature levels if no external heat load were considered, i.e., operating in
interplanetary space with the longitudinal axis parallel to the solar glut. or
in the shade.
B. APPROXIMATIONS AND ASSUMPTIONS
The analysis was performed by making certain simplifying assumptions
and approximations to permit a hand evaluation of the problem. The basic
assumptions are noted in the following:
1. The main radiator and the lube and coolant radiator were assumed
to be in a cylindrical configuration with a 20 foot diameter. Only the main
radiator was considered to have radiation to the inside of the cylinder. The
ins0 de of the L/C radiator was assumed to be insulated and the inside surface
was assumed to have an emissivity and reflectivity of 0.5.
2. The main radiator surface emissivity was assumed to be 0.85.
The surface absorptiv=ty was assumed to be .60 due to solar radiation and .85
due to diffused radiation from within the cylinder and to planetary radiation.
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SRI ^45.6^^1-105
3. The external heat sources, solar and planetary, were evaluated
on the basis of a 500 mile circular earth orbit. The average absorbed flux was
assumed to be uniform around the periphery of the cylinder.
4. Temperature of space was assumed to be zero.
5. The heat rejection from the fins was evaluated using the data
of Mackay and Bacha . The effects of irradiation between tubes and fins were
not considered.
6. The mutual irradiation between different sections within the
cylinder was assumed to be all diffused radiation. The effects of multiple
reflections within the cylinder were neglected because of the low reflectivity
of the L-- °ace material.
7. Longitudinal heat conduction along the tubes and fins was not
considered.
8. Fin dimensions were assumed to be: Sh = .080 in.,
Sc = .020 in. and i'h = 3.5 in.
9. The length of the L/C radiator section was assumed to be 6
feet long.
10. The obstruction of the view of space due to the NS, PCS and
payload was not considered. A preliminary calculation indicated that this was
a reasonable approximation.
III. METHOD OF ANALYSIS
The method of analysis is described in the appendix. The procedure was as
follows:
A. The temperature distribution and radiator size were evaluated by an
iterative process for the maximum external flux condition.
B. Using the size determined from the maximum external heat flux case,
the temperature distribution was evaluated for the case where there
is no external heat flux.
* D. B. Mackay, C. P. Bacha, Space Radiator Design and Analysis Part I ASD
Technical report 61-30 October 1961.
2
TM 345:63-1-105
IV. RESULTS
The results of the analysis are shown in the Figure 1 which shows the fluid
temperature distribution in the main radiator as well as the surface temperature
on the thermal radiation shield for the L/C radiator.
The size required for the main radiator was found to be considerably smaller,
9.5 feet long by 20 feet diameter compared to the cylindrical radiator in which
all of the interior surface is insulated, and has dimensions of 18 feet long by
20 feet in diameter. The weight of tube, armor and fins for the two radiators
compare as follows: 1040 lb for the radiator with internal heat rejection and
1150 lb for the radiator with all the interior insulated.
The average temperature variation due to the variation in external heat
load, assuming that the fluid heat rejection is the same for both cases is
approximately 20°F.
The surface temperature of the thermal radiation shield on the L/C radiator
is approximately 265°F. This means that the insulation requirements are minimal
since the temperature levels in the L/C radiator are 210°F to 250°F.
V. CONCLUSIONS
The conclusions which can be drawn from this preliminary analysis are:
A,	 The size and weight of the main radiator can be reduced by considering
heat rejection from the interior of the cylinder. Although additional
analysis must be made to evaluate the weight requirements for thermal
radiation shielding on the PCS and the payload to fully assess the
overall system weights using either radiator concept.
B. The temperature variation from tube-to-tube, due to the varying
external heat flux, should be minimized by having mutual irradiation
on the inside of th3 cylinder. This will minimize the problems of
flow distribution in the radiator tubes.
C. The structural weight should be reduced by virtue of the reduced
radiator size,
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Cylindrical radiator with internal heat rejection

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