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 This page intentionally left blank 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.