Spacecraft radiative transfer and temperature control : technical papers from the AIAA 19th aerospace sciences meeting, January 1981 [St. Louis, Mo.], and the AIAA 16th thermophysics conference, June 1981 [Palo Alto, Calif.]

552 Pages·1982·20.13 MB·English

by  Horton

SPACECRAFT RADIATIVE TRANSFER
AND TEMPERATURE CONTROL
Edited by
T. E. Horton
Department of Mechanical Engineering
The University of Mississippi, University, Mississippi
Volume 83
PROGRESS IN
ASTRONAUTICS AND AERONAUTICS
Martin Summerfield, Series Editor-in-Chief
Princeton Combustion Research Laboratories, Inc.
Princeton, New Jersey
Technical papers from the AIAA 19th Aerospace Sciences Meeting, January 1981,
and the AIAA 16th Thermophysics Conference, June 1981, and subsequently
revised for this volume.
Published by the American institute of Aeronautics and Astronautics, Inc.
1290 Avenue of the Americas, New York, N.Y 10104.
American Institute of Aeronautics and Astronautics, Inc.
New York, New York
Library of Congress Cataloging in Publication Data
Main entry under title:
Spacecraft radiative transfer and temperature control.
(Progress in astronautics and aeronautics; v. 83)
Technical papers from the AIAA 19th Aerospace Sciences Meeting,
January 1981, and the AIAA 16th Thermophysics Conference, June
1981.
Includes index.
1. Space vehicles—Thermodynamics—Congresses. 2. Temperature
control—Congresses. I. Horton, T.E. (Thomas E.) II. American In-
stitute of Aeronautics and Astronautics. III. AIAA Aerospace Sciences
Meeting (19th: 1981: St. Louis, Mo.) IV. AIAA Thermophysics
Conference (16th: 1981: Palo Alto, Calif.) V. Series.
TL507.P75 vol. 83 [TL900] 629.1s 82-6687
ISBN 0-915928-67-1 [629.47'044] AACR2
Copyright ©1982 by
American Institute of Aeronautics and Astronautics, Inc.
All rights reserved. No part of this book may be reproduced in any form or
by any means, electronic or mechanical, including photocopying,
recording, or by any information storage and retrieval system, without
permission in writing from the publisher.
Table of Contents
Preface............................................. vii
Editorial Committee .................................. xii
List of Series Volumes 1-83 ............................ xiii
Chapter I. Heat Transfer and Properties .................. 1
Effects of Polarization on Bidirectional Reflectance
of a One-Dimensional Randomly Rough Surface ............... 3
T.F. Smith and K.E. Nichols, The University of Iowa, Iowa City, Iowa
Determination of Radiative Properties from Transport Theory
and Experimental Data .................................. 22
J.A. Roux and A.M. Smith, The University of Mississippi, University,
Miss.
Melting of a Slab of Semitransparent Material by Irradiation
from an External Radiation Source......................... 38
L.A. Diaz and R. Viskanta, Purdue University, West Lafayette, Ind.
Transient Thermal Contact of Two Semi-infinite Bodies
over a Circular Area .................................... 61
J.V. Beck, Michigan State University, East Lansing, Mich., and
N.R. Keltner, Sandia National Laboratories, Albuquerque, N. Mex.
Thermal Contact Correlations............................... 83
M.M. Yovanovich, University of Waterloo, Waterloo, Ontario, Canada
Thermophysical Properties of Fine-Weave
Carbon-Carbon Composites .............................. 96
R.E. Taylor, H. Groot, and R.L. Shoemaker, Purdue University, West
Lafayette, Ind.
Chapter II. Plume Radiance .......................... 109
A Theoretical Model for Absorbing, Emitting,
and Scattering Plume Radiation .......................... Ill
C.B. Ludwig, W. Malkmus, and G.N. Freeman, Photon Research
Associates, Inc., La Jolla, Calif., and M. Slack and R. Reed, Grumman
Aerospace Corporation, Bethpage, N. Y.
iv
Calculation of Visible Radiation from Missile Plumes ........... 128
R.B. Lyons, J. Wormhoudt, and C.E. Kolb, Aerodyne Research, Inc.,
Bedford, Mass.
A Numerical Method for High-Altitude
Missile Exhaust Plume Flowfields ......................... 149
K.H. Wilson and P.O. Thomas, Lockheed Palo Alto Research
Laboratory, Palo Alto, Calif.
Effect of Particle Size Distribution on the Radiosity
of Solid-Propellant Rocket Motor Plumes .................. 169
D.K. Edwards, University of California, Irvine, Calif., and R.P. Bobco,
Hughes Aircraft Company, El Segundo, Calif.
Chapter III. Contamination and Degradation............. 189
Development of Low-Outgassing Resins and Electrical Conductive
Paints for Thermal Control and Space Applications........... 191
J.C. Guillaumon and J. Guillin, Centre National d'Etudes Spatiales,
Toulouse, France
In-Flight Contamination and Changes of Thermo-optical Properties
Measurements ........................................ 201
A. Rolfo, Centre National d'Etudes Spatiales, Toulouse, France
Solar Absorptance Degradation of OSR Radiators
on the COMSTAR Satellites ............................. 212
N.L. Hyman, COMSATLaboratories, Clarksburg, Md.
a Measurements of Thermal Control Coatings on Navstar Global
s
Positioning System Spacecraft............................ 234
W.R. Pence and T.J. Grant, Rockwell International Corporation, Seal
Beach, Calif.
Chapter IV. Temperature Control Components ........... 247
Advanced Radiative Cooler with Angled Shields ............... 249
S. Bard, J. Stein, and S.W. Petrick, Jet Propulsion Laboratory,
California Institute of Technology, Pasadena, Calif.
Radiative Cryogenic Cooler for the Near-Infrared Mapping
Spectrometer for the Galileo Jupiter Orbiter................. 259
T.T. Cafferty, Santa Barbara Research Center, Goleta, Calif.
Thermionic Energy Conversion and Metallic-Fluid
Heat Pipes: High Power Densities from High-Temperature
Material Interactions ................................... 271
J.F. Morris, NASA Lewis Research Center, Cleveland, Ohio
The Monogroove High-Performance Heat Pipe ................ 305
J. Alario, R. Haslett, and R. Kosson, Grumman Aerospace Corporation,
Bethpage, N. Y.
Lightweight Moving Radiators for Heat Rejection in Space. ...... 325
K. Knapp, Astro Research Corporation, Carpinteria, Calif.
Chapter V. Complex Systems . . . . . . . . . . . . . . . . . . . . . . . .. 343
Interactive Design and Analysis
of Future Large Spacecraft Concepts ...................... 345
L. Bernard Garrett, NASA Langley Research Center, Hampton, Va.
Space Structure Heating: A Numerical Procedure for Analysis of
Shadowed Space Heating of Sparse Structures ............... 377
R.F. O'Neill and J.L. Zich, General Dynamics Convair Division,
San Diego, Calif.
The Application of Interactive Graphics
to Thermal Modeling................................... 396
M.J. Kutkus and R.L. Negvesky, Hughes Aircraft Company,
Los Angeles, Calif.
The Effect of Reticulate Shading upon Radiation Heat Transfer
by Means of Emissivity Reduction ........................ 421
R. Best and F. Zilly, Dornier System GmbH, Friedrichshafen,
Federal Republic of Germany
Chapter VI. Future Concepts . . . . . . . . . . . . . . . . . . . . . . . .. 437
Preliminary Design Study of Solar Probe Heat Shields .......... 439
C. Park, NASA Ames Research Center, Moffett Field, Calif.
Graphitic Heat Shields for Solar Probe Missions ............... 472
J.H. Lundell, NASA Ames Research Center, Moffett Field, Calif.
Radiatively Coupled Thermionic and Thermoelectric
Power System Concept ................................. 501
K. Shimada and R. Ewell, Jet Propulsion Laboratory, California
Institute of Technology, Pasadena, Calif.
The Use of a Thermal Utility with Space-Platform-Mounted
Instruments .......................................... 517
D.W. Almgren, A.A. Fowle, and J.T. Bartoszek, Arthur D. Little,
Inc., Cambridge, Mass., and S. Ollendorf and R. Mclntosh Jr.,
NASA Goddard Space Flight Center, Greenbelt, Md.
Author Index for Volume 83 ........................... 529
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Preface
Thermophysics represents a harmonious blend of the classical
engineering sciences of materials, thermofluids, heat transfer, and
electromagnetic theory with the microsciences of solid state,
physical optics, and atomic and molecular dynamics. The impetus
for the formation of a thermophysics community during the
predawn of the " space age" was the need for a science/technology
base which could cope with the thermal management problems
encountered in the early satellites and in ballistic re-entry. During
the past two decades the thermophysics community has met ever-
increasing mission requirements for more effective space systems, as
well as the demands of transfer of these technologies to terrestrial
energy problems. Today and in the near future we see a continuation
of the challenges in the thermophysics field presented by entry
systems, spacecraft thermal control, and laser technology.
This volume is devoted to the science and technology associated
with spacecraft thermal control and as such it is dominated by the
topic of radiative transfer. The thermal performance of a system in
space depends upon the radiative interaction between external
surfaces and the external environment (space, exhaust plumes, the
sun) and upon the management of energy exchange between com-
ponents within the spacecraft environment. For more efficient
designs of today's spacecraft, the questions of thermophysical
properties of materials, contact conductance between components,
radiative shielding and cooling, and many others, continue to be of
interest. However, contamination-caused degradation of thermal
control surfaces frequently determines the useful life of today's
spacecraft. For future systems, the old problems will be confronted
again but will be compounded by the increased complexity of the
system. Thus, there is a need for computer-aided design or
automated design.
The volume presents a view of timely advances in spacecraft
radiative transfer and temperature control, which was drawn from
over 160 papers which were contributed to thermophysics sessions at
the AIAA 19th Aerospace Sciences Meeting in St. Louis, Missouri in
January 1981, and the AIAA 16th Thermophysics Conference in
Palo Alto, California in June 1981. These papers have been revised,
vli
VIM
updated, and organized into six coherent chapters which discuss heat
transfer and properties, plume radiance, contamination and degra-
dation, temperature control components, complex systems, and
future concepts.
Chapter I treats a diversity of problems pertinent to the
assessment of heat transfer in spacecraft, which are also of concern
in other areas of application. The first three papers deal with the
problems associated with radiation interaction with surfaces. Smith
and Nichols develop a bidirectional reflectance model to examine
polarization effects on preferentially roughened surfaces. Such a
model should aid in the correlation of experimental data on the
reflection of incidental energy from rough surfaces. In the second
paper, Roux and Smith present a method for extracting spectral
scattering and absorption coefficients from experimental data
employing the Chandrasekhar solution to the radiative transport
equation. Illustrations for cryodeposits and for home insulation are
presented. Diaz and Viskanta report on an investigation of solid-
liquid interface motion in a horizontal slab of a semitransparent
material, which is heated on its upper surface by an external
radiation source. The next two papers are studies of contact con-
ductance. Beck and Keltner present analytical solutions for the tran-
sient heat conduction problem arising when a sudden imperfect
contact occurs between two semi-infinite bodies. A new ap-
proach—the unsteady surface element method—was employed. The
paper by Yovanovich provides correlations for contact, gap, and
joint conductances for conforming rough surfaces when interstitial
fluids such as greases and gases are present in the gap. A com-
prehensive set of high-temperature thermophysical properties of
fine-weave carbon/carbon composites are provided by Taylor,
Groot, and Shoemaker in the last paper of this chapter.
Chapter II treats the problem of predicting the radiative transfer
from rocket exhaust plumes and presents a balanced view of the
mutual importance of both flowfield and radiative transport
predictions. The JANNAF Exhaust Plume Technology Sub-
committee has undertaken the development of a Standard Plume
Model which consists of a Standard Plume Flowfield (SPF) and a
Standard Infrared Radiation Model (SIRRM). In the first paper,
Ludwig, Malkmus, Freeman, Slack, and Reed describe the
theoretical basis for a radiation model for emitting/absorbing and
scattering plumes, which is used in the SIRRM code. In the second
paper, Lyons, Wormhoudt, and Kolb summarize the current status
IX
of predicting emission properties of low-altitude exhaust plumes in
the visible and near-ultraviolet spectral region. This region is a
particularly difficult one because of the scarcity of data on many of
the kinetic processes and the sensitivity to flowfield prediction
errors. Wilson and Thomas present an approach to exhaust plume
flowfield prediction, which is appropriate at high altitudes. The
paper concentrates upon the gasdynamics of the plume, because an
accurate prediction of the radiant emission is strongly dependent
upon an accurate prediction of the thermodynamic properties of the
flow. The analysis rests upon the continuum description of the flow,
so the authors have presented a quantitative criterion for the range
of applicability. Past predictions in this altitude/velocity range,
which is near transition, have been the subject of large uncertainties.
In the final paper, Edwards and Bobco present an engineering plume
model for predicting radiation from solid-propellant exhausts. The
model which should be useful in design and base heating estimates,
involves a closed-form solution for particle plume radiation in terms
of a particle distribution function parameter.
The properties of spacecraft control surfaces and their con-
figuration are the key factors in the passive temperature control of
spacecraft. Thus, the change of these surface properties with time
may be a decisive factor in defining the useful life of a spacecraft.
The contamination and degradation of the thermo-optic properties
is the topic of Chapter III. The degradation can result from the
vacuum outgassing, but usually it results from the uv irradiation or
charged particle interaction. Contamination can occur in the post
launch environment, during launch from engine exhaust, or in space
from several sources. Guillaumon and Guillin present data on
several, carefully tested, low-outgassing coatings which they have
developed. Other low-outgassing products and the binders for the
coatings were achieved through the purification of commercial
resins. In the second paper, Rolfo presents a careful survey of the
considerations for a French study program on contamination in-
volving in-flight measurements. The third paper by Hyman reports
on the changes in solar absorptance derived from temperature
telemetry data from four COMSTAR satellites, which implicate
deposits during storage. For a very severe space environment
combining both uv and charged particles, Pence and Grant present
solar absorptance data on four materials from NAVSTAR
spacecraft in-flight experiments.