ANNUAL PROGRESS REPORT
FOREWORD
The year 1979 marks the completion of the third decade of operation by the Institute for Aerospace Studies. We are a1so entering the 80 l s af ter a
decade of considerab1e strain and change. It is therefore of interest to
ref1ect upon some of the changes th at háve characterized the past decade. The Institute performs an extensive program of aerospace motivated
research, supp1emented by work in various app1ied fie1ds that have originated direct1y from earl ier aerospace activities. Most of this research is performed through research projects as part of our graduate educationa1 function. In addition, the Institute carries the responsibi1ity in the Facu1ty of App1ied Science and Engineering for undergraduate instruction in aerospace subjects within the framework of the Division of Engineering Science. Whi1e the under-graduate enro1ment in the aerospace option of Engineering Science has remained stab1e during the last decade, the number of graduate students has experienced considerab1e change. We started the decade with 84 students, actua11y touched an enro1ment high of 90 students in 1971 and then experienced a re1ative1y rapid decrease to 55 students in 1974, which was in turn fo11owed by an increas-ing trend to the present number of 70 graduate students. The makeup of the present student body differs marked1y from that in 1969. At that time we had 38 M.A.Sc., 6 M.Eng. and 40 Ph.D. candidates, with the fo11owing distribution:
55% of the students in the Masterls program and 50% of the Ph.D. students came
from within Canada. At present our enro1ment comprises 45 M.A.Sc., 4 M.Eng. and 21 Ph.D. candidates and 63 out of the 70 students are permanent Canadian residents. Two observations jump to minde Our abi1ity to attract students from within Canada has in fact increased over that of 10 years ago and there is a significant dec1ine in the number of current Ph.D. candidates. This has had a serious impact on the way our research projects have had to be staffed and it is no surprise to see that this year our Research Associates and Research Staff numbered 15 as compared to 7, 10 years ago.
In 1979 we graduated 18 M.A.Sc. students and 6 Ph.Dls. Since the creation of the Institute in 1949, 126 Ph.Dls, 335 M.A.Sc. and 22 M.Eng. candidates have comp1eted their programs at UTIAS.
In conjunction with our educationa1 responsibi1ities a major objective of the Institutels research programme is to bui1d and maintain a unique capabi1ity, both in staff and research faci1ities to make significant contributions in our fie1ds of expertise. In particu1ar, our research is based to a significant extent on experimenta1 work in major insta11ations. The avai1abi1ity of these faci1ities and the time1y incorporation of new innovative research techniques have provided unique opportunities to undertake 1eading research on a significant sca1e. The dependence on such major insta11ations has a1so created unusua1 and cost1y prob1ems of up keep over and above the a1ready inadequate provisions for the renovation of our instrumentation in general. Fortunate1y, prospects for very significant improvements in the funding of university research have recent1y been announced in the 5 year "P1an for Action" by NSERC, and the concomitant NSERC budget increase for 1980-81 promises to reverse the steady deterioration of research grant support that we have experienced over most of the past decade. This 5-year plan contains an incisive and complete ana1ysis of the university
research support situation and presents carefu11y and persuasive1y argued sugges-tions for an appropriate programmatic response. The first step of its imp1emen-tation has now been incorporated in the 1980/81 budget and congratu1ations are due to NSERC for this impressive performance.
One of the premises for this newly increased support through NSERC is that university research is a necessary ingredient for a healthy total R & D effort in the country. The Institute has always operated explicitly and with determination at the interface between the University and the external
research community. This is clearly shown, for instance, by the fact that this year 57% of our external funding was in the form of research contracts. Also, 1 noted in last yearls report three instances of direct collaborative
research efforts with industry, based on Institute research and devoted to enhance R & D work in industry. I am pleased to note that this year Dr. N. Salansky, from the 3M Company, and working on new materials produced by implosions, has become an Adjunct Professor at the Institute and so has joined Dr. F. Cicci of de Havilland who has participated in our work on crashworthiness for the past few years.
The question of a desirable balance between the more fundamentally oriented research at the Institute supported by grants and those research activities that are funded by various agencies in the form of contracts has been a matter of continuing scrutiny over the years. The just quoted figure of 57% for contract research represents a noticeable increase in this ratio compared with the 45% that we experienced in 1975/76, for instance. It re-flects the persistent relative decline of the research effort based on grant support and has become a source of real concern.
We are hopeful that the recently announced increase in research funding by NSERC will offer new scope for strengthening the grant research at the Institute. Against this background we are intent on further improving our contact with the aeronautical and space industry so that we can select our own research interests with full appreciation of the current problems in industry. In this way we are confident that the anticipation of enhanced technological capability supported by strengthened university research will be realized.
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J. H. de Leeuw, Director.
TABLE OF CONTENTS Page Personnel 4 Major Installations 16 Institute Laboratories 25 Progress Reports 33 Aeroacoustics 33
Air Cushion Technology 36
Energy Technology 38
Flight and Ground Transportation 40
Gasdynamics, Shock-Wave Phenomena, Implosion Dynamics, New Materials, Thermonuclear Fusion, and Turbulent
Combustion 42
Industrial and Architectural Aerodynamics 44
Laser Excitation and Diagnostic Applications 46
Psychoacoustic Research 48
Sonic Boom and Thunder 49
Space Dynami cs and Control 51
Structural Mechanics and Materials Science 53
Subsonic Aerodynamics 56
Trace Gas Analysis 58
Upper Atrnospheri c and Fl i ght Research 61
UTIAS Publications
STAFF OF THE INSTITUTE FOR AEROSPACE STUDIES
PROFESSOR AND DIRECTOR OF THE INSTITUTE
J. H. de Leeuw, Dipl. Eng. (Delft), M.S. in A.E. (Georgia Tech.), Ph.D., F.R.S.C., F.C.A.S.I., F.A.P.S.
PROFESSOR AND ASSOCIATE DIRECTOR
J. B. French, M.Sc. (Birmingham), B.A.Sc., Ph.D., F.C.A.S.I., F.R.S.A.
ASSOCIATE PROFESSOR AND ASSOCIATE DIRECTOR
P. C. Stangeby, Dipl.-Sci., D.Phil. (Oxon), B.Sc., M.Sc.
PROFESSORS
B. Etkin, D.Eng. (Carleton), B.A.Sc., M.A.Sc., F.R.S.C., F.C.A.S.I., F.A.I.A.A. I. I. Glass, B.A.Sc., M.A.Sc., Ph.D., F.A.P.S., F.A.A.A.S., F.C.A.S.I.,
F.A.I.A.A., F.R.S.C.
P. C. Hughes, B.A.Sc., M.A.Sc., Ph.D., F.C.A.S.I. R. M. Measures, B.Sc., A.R.C.S., D.I.C., Ph.D. (Lond.)
H. S. Ribner, B.S. (Cal. Tech.), M.S., Ph.D. [Wash. (St. Louis)], F.R.S.C., F.C.A.S.I., F.A.I.A.A., F.A.P.S., F.A.S.A.
R. C. Tennyson, B.A.Sc., M.A.Sc., Ph.D., F.C.A.S.I. ASSOCIATE PROFESSORS
J. D. DeLaurier, B.S. (Illin.), M.S., Ph.D. (Stan.) G. W. Johnston, B.A.Sc., M.A.Sc., Ph.D., F.C.A.S.I. L. D. Reid, B.A.Sc., M.A.Sc., Ph.D.
P. A. Sullivan, B.E., M.E. (N.S.W.), D.I.C., Ph.D. (Lond.), F.C.A.S.I. ASSISTANT PROFESSORS
A. A. Haasz, B.A.Sc., M.A.Sc., Ph.D.
J. S. Hansen, B.A.Sc., M.A.Sc., Ph.D. (Waterloo) W. G. Richarz, B.A.Sc., M.A.Sc., Ph.D.
VISITING AND ADJUNCT PROFESSORS
F. Cicci, B.A.Sc., M.A.Sc., Ph.D., Ad,iunct Assistant Professor
A. A. Gruzdev, Cand. Phys. Math. (Moscow Aviation Inst.), Visiting Professor H. Honma, B.Eng., D.Eng. (Tokyo), Visiting Professor
N. Salansky, Ph.D. (Krasnoyarsk), D.Sc. (Novosibirsk), Adjunct Professor
K. Takayama, Dr.Eng. (Tohoku), Visiting Professor
SENIOR RESEARCH ASSOCIATE
rt M. Reid, B.Sc., Ph.D. (St. Andrewis), C.Chem., M.R.I.C.
RESEARCH ASSOCIATES
S. C. Garg, B.Tech. (Kanpur), M.A.Sc., Ph.D.
J. P. Sislian, M.Sc. (Yerevan), Cand. Phys. & Math. Sci. (Moscow), Ph.D. RESEARCH STAFF
O. H. Auciello, B.Sc., M.Sc., Ph.D. (Cuyo) S. Basu, B.Sc., Ph.D. (Lond.)
G. Ben-Dor, B.Sc., M.Sc. (Ben-Gurion), Ph.D. W. E. R. Davies, B.Sc. (Ottawa)
W. O. Graf, B.Sc., M.Sc. (Eng.) (Pretoria) P. V. Hartmann, B.Eng. (N.S.W.), r~.A.Sc.
M. J. Hinchey, Dipl.Eng. (Mer,lorial), B.A.Sc., M.A.Sc., Ph.D. J. E. D. Kennedy, B.Sc. n~aterloo), r~.sc. (U.W.O.), Ph.D. (York) G. E. r~abson, B.A.Sc., M.A.Sc.
H. A. r~ar, B.A.Sc., M.A.Sc., Ph.D.
C. C. Poon, B.E., B.Sc. (Tas. U.), M.S. (Syr. U.), Ph.D. (Cal.) S. Raimondo, B.A.Sc., M.A.Sc.
D. Sagie, B.Sc. (Technion)
D. Solomon, B.Sc. (Technion), M.Eng.
W. T. Shmayda, B.Sc. (Queenls), M.A.Sc., Ph.D. B. T. Uffen, B.A.Sc., M.A.Sc.
I. Youle, B.Sc. (Dal.), M.A.Sc.
SPECIAL LECTURERS
S. F. Archer, B.A.Sc., M.A.Sc.
B. Eggleston, Aero.Eng. (Bristol), M.Sc. (Cranfield) G. Georges, B.A.Sc.
A. M. Gray, B.Sc. (Aberystwyth) K. Griffin, B.A. (Bristol) G. B. Lang, B.Sc. (Adelaide) P. S. r~artin, P.Eng., F.R.Ae.S. G. Oates, B.Eng. (Manchester)' CONSULTANTS
w.
Czerwinski, Dipl.-Ing. (\~arsaw), F.C.A.S.I. A. K. Kudian, B.Sc., M.Sc., Ph.D.S. Reinis, H.O., Ph.D. (Charles) LIBRARIAN
Mrs. Asta Luik, B.A. (Estonia), B.L.S., M.L.S. (Toronto)
RESEARCH ASSISTANTS M. S. Abu Khalaf S. Ando A. B. Antoniazzi M. R. Arnfield K. L. Ashworth N. Ba 11 R. P. Baronet C. G. Barringer J. C. Bird D. S. Breitman \>J. L. Buchanan J. L. Campbe 11 P. G. Cardinal J. A. Catalano P. Chodas 1. Y.-P. Chung ft A. Daoud T. E. Darci e D. F. Davidson J. R. J. de Lafontaine E. Della Penna R. L. Deschambault 1-1. Drewell A. D. Dupuis [3. C. Eatock J. R. Evans J. D. Fairgrieve R. G. Fehr 1. G. Fejtek P. A. Gagnon A. Gak\vaya M. J. Giliberto T. A. Graham E. G. Hartwell L.-P. Hébert G. R. Heppler O. Holst-Jensen P. Hodes D. Hui K. Hui M. Jankovi e J. G. Kavanagh J. Kleiman V. Kotasek
ADMINISTRATIVE AND TECHNICAL STAFF S. Basdeo K. Bopp J. L. Bradbury H. Dillon D. Douglas R. Eisen M. Fitzgerald H. Kleinberg M. Kl ine J. Leffers J. H. McCormack 6 W. L. Kung V. H. S. Kwong B. A. Lay R. LeBl anc J. H. Lever B. J. Lewis A. Manz A. B. Markov W. D. Mori son D. A. McCoy W. D. MeKi nney I. R. MeLean N. J. MeNeill S. Y. Naeson A. P. Nanyaro D. J. Nob 1 e K. Ogimoto M. Oguztoreli J. G. Parravano J. Potj ewyd D. Roy T. Sa ito D. M. Sehenc k P. Sergejewieh G. B. Sinearsin B. A. ~J. Smith E. N. Solowka P. S. Speda 1 er 1. A. Stodda rd H. Teiehman C. Tessier W. G. Timbers A. H. von Flotow A. T. Vourl as N. N. Wahba G. Waters C. Walsh A. ~Jei ss G. E. Wharram P. L. Wizinowich G. S. West-Vukovich R. L. M. Wong S. S. K. Wong D. W. Zingg E. Mills E. Moffitt A. Morte A. Perrin L. Quintero W. Ryan G. Sachade H. Schumacher G. Singh J. Tonigold J. Unger
The Gordon N. Patterson Lecture is given annually in honour of the Founder of the Institute by a distinguished graduate of the Institute. This yearls Lecturer, Prof. John D. Lee, Director of the Aeronautical and Astronautical Research Laboratory of Ohio State University, received his Ph.D. from the Institute in 1952. Professor Lee spoke on "Some Effects of Technological Advances on Academic Research and Instruction".
In his lecture Professor Lee described how techniques in data acquisition, automation and computing methods have changed considerably in the past twenty-five years and how these changes have had astrong influence on the type and scope of research which can be undertaken at a university laboratory and also in the material and methods that can be utilized in the classroom. Professor Lee discussed several aspects of these matters from his personal teaching experience.
On the occasion of the Lecture, which was held on October 5, the G. N. Patterson Student Award for outstanding scholarship was presented to Dr. M. J. Hinchey. Dr. Hinchey received his doctorate this year under the supervision of Dr. P. A. Sullivan on the topic of "Heave Instabilities of Amphibious Air Cushion Suspension Systems".
Shown above from left to right: Drs. de Leeuw, Hinchey, Lee and Patterson.
Dr. J. B. French obtained his B.A.Sc. in Chemical Engineering, University of Toronto, M.A.Sc. in Thermodynamics at Birmingham, England, and Ph.D. in Plas-madynamics at UTIAS, where he joined the staff in 1961. His general fields of interest include gas dynamic mole-cular beams, space simulation, trace gas analysis instrumentation development,
Professor J. H. de Leeuw obtained his
Engineering Diploma in Aeronautical Engineering at the Delft Technical University in Holland. He obtained his M.S. degree in Aeronautical Engineering at the Georgia Institute of Technology and his Ph.D. in Aerophysics at the Institute for Aerospace Studies of the University of Toronto. He joined the staff of UTIAS in 1958 and is now
Director of the Institute. His original interest in shock tubes and their use in MHD research shifted subsequently to largely experimental work in low density gas and plasma flows with a special em-phasis on the development of new measuring techniques. Adaptations of these labora-tory techniques led to the construction of special rocket instruments for the measure-ment of the properties of the upper
atmos-phere. More recently his interests have included flow problems associated with fusion technology. Professor de Leeuw is a member of the NRC Advisory Committee on Fusion Research, he is a Fellow of the Canadian Aeronautics and Space Institute and a Fellow of the American Physical Society.
and many applications of the latter in environmental, military, medical and other areas. His projects included ion source development with Prof. A. O. Nier of Minnesota for the highly successful Project Viking t1artian up per atmospheric mas s spectrometer. Hi s re search has 1 ed to major advances in atmospheric pressure chemical ionization mass spectroscopy. Patents which make APCI/MS practical as a research and analytic tool (held
jointly VJith fL M. Reid, J. A. Buckley)
have been developed in Canada into a commercial instrument. Recently, Dr. French has been appointed to hold a watching Brief for NRC on Satellite Solar Pov/er systems. He is a Fellow of the Canadian Aeronautics and Space Institute, a Fellow of the Royal Society of Arts, and a member of the AIAA and the AlP.
Dr. P. C. Stangeby obtained his Bach-elor and Master degrees in Mathematics and Physics at the University of Toronto, and his Doctorate in Engineering Science (Plasmas) at Oxford University, joining the Institute staff in 1972. His primary research interest is in fusion energy. Current emphasis is on plasma-surface interaction studies related to wall mate-rials development for fusion reactor con-ditions. Research on the Gas Target Neutron Generator concept is directed toward the development of an intense neutron souree for fusion materials studies. Other energy research interests include synthetic fuel production from oil sand, coal and biomass feed-stocks. Dr. Stangeby is a member of the AIAA, the Canadian Association of
Physicists and the (UK) Inst{tute of Physics.
Dr. B. Etkin obtained his B.A.Sc. degree in Engineering Physics at the University of Toronto and an M.A.Sc. in Aeronautical Engineering. He has been on the staff of the Engineering Faculty since 1942. He served as Chairman of the Division of Engineering Science from 1967-1972 and as Dean of the Faculty from 1973-1979. His research interests have included air-craft structures, wing theory, shock waves, stability and control of aircraft, satel-lites and re-entry vehicles and aerosonics. Hi s two books on 11 Dynami cs of Fl ight" have
been widely used in English, Russian and German editions. He has served for many years as a consultant to U.S. and Canadian industry and government and spent consider-able time in the aircraft industry during and af ter World War 11. His current research interests inçlude the effects of atmospheric turbulence on flight vehicles, lighter-than-air lighter-than-aircraft, applications of lighter-than-air curtains, and aerodynamic means of sorting fine par-tieles. He is a Fellow of the Royal Society of Canada, of the CASI, and of the AIAA. He received the McCurdy Award in 1969, an hon-orary D.Eng. from Carleton University in 1971, and the Mechanics and Control of Flight Award of the AIAA in 1975.
Professor P. C. Hughes obtained his Ph.D. from the University of Toronto
(1966) in Aerospace Engineering Science. Most of his research has been related to space vehicle dynamics and control, including significant contributions to the dynamical rnodel-ling of the Alouette/ISIS and Hermes satellites and of the NASA Space Shuttle manipulator arm. Current
interests include the application of modern control theory to this class of applications, and the dynamics and control of large space structures. Professor Hughes is a Fellow of the Canadian Aeronautics and Space Institute, and reviews regularly for the U.S. aerospace journals.
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Professor I. I. Glass obtained his Bachelor and Master degrees (Engineering Physics-Aeronautical Engineering) and Doctorate (Aerophysics) at the University of Toronto in 1950, when he joined UTIAS. His fields of study have centred on gas-dynamics and shock-wave phenomena. He is currently interested in the interaction of shock structure with laminar, shock-tube sidewall and flat-plate boundary-layer flows in ionizing argon; various types of nonsta-tionary oblique-shock-wave reflections; implosion dynamics with a view to fusion diagnostics and new materials; effects of sonic boom on structures and shock transi-tions in N-waves; turbulent combustion. Professor Glass is a Fellow of the Royal Society of Canada, the American Physical Society, the American Institute of Aero-nautics and AstroAero-nautics, the American Association for the Advancement of Science and the Canadian Aeronautics and Space
Dr. H. S. Ribner obtained his B.S. from Caltech and his M.S. and Ph.D. (1939) from Washington University (St. Louis), all in physics. Af ter a short period in gravity meter development, he spent eight years at the NACA (predecessor of NASA) Langley Laboratory and five years at the Lewis Laboratory, variously as aerodynamicist and section head (Stability Analysis
Section, Langley, Boundary Layer Sections, Lewis). He joined the Institute staff in 1955, was a Visiting Professor at Univer-sity of Southampton in 1960-61, and a Staff Scientist at NASA Langley in 1975-76. His research interests have covered, some-what chronologically, X-rays, cosmic rays, gravimetry, aerodynamics, aeroacoustics, sonic boom, and the acoustics of thunder. Professor Ribner is a Fellow of the Royal Society of Canada, the Canadian Aeronautics and Space Institute (CASI), AIAA and other American societies. He was the CASI Turn-bull Lecturer in 1968, Chairman of the ICAO Sonic Boom Panel in 1970-71, and received the AIAA Aeroacoustics Award in 1976.
Currently he divides his time between UTIAS and NASA Langley.
Professor R. M. Measures obtained his Bachelor and Doctorate degrees in Honours Physics at Imperial College of Science and Teehnology, London University, England. He has worked in the area of applied physies since he joined the staff of the Institute in 1964. His early work involved the mea-surement of atomie collision cross sections by laser interferometric studies of shock waves and the development of a new approach
at local plasma diagnostics using laser selective excitation spectroscopy. Dr. Measures spent a sabbatical year (1972-3) at the "Royal Institution of Great Britain" where he studied the possibility of develop-ing a laser based on Electrochemiluminescence. Over the past decade, he has maintained a substantial interest in laser environmental sensing, developing Canadals first laser fluorosensor and contributing a comprehen-sive chapter on the subject for a text on Laser Spectroscopy. His current interests inelude the development of a new kind of Laser Trace Element Mieroprobe and a study of laser created plasma ehannels that could be of importanee in particle beam fusion.
Dr. DeLaurier obtained his Bachelor
Prof. R. C. Tennyson obtained his B.A.Sc. at the University of Toronto and his graduate degrees (M.A.Sc., Ph.D.) at the Institute for Aerospace Studies. Af ter joining the Institute staff in 1965, he continued to work in the Structural Mechanics area with special interest in shell buckling problems. During these intervening years, his interests have expanded to include stress waves in solids, com-posite materials, biomechanics and space simulation studies. Dr. Tennyson is a member of the National Research Council of Canada Associate Committee on Aerospace Structures and Materials, the American Institute of Aeronautics and Astronautics and a Fellow of the Canadian Aeronautics and Space Institute.
degree fro~ the University of Illinois, a fter \vh i ch he worked as an aerodynar.t-icist at r·1cDonnell Aircraft. Subse-quently, he went to Stanford University where he received a Master and Ph.D. degree (1970). Af ter a year at the
von Karman Institute for Fluid Dynamics,
Dr. DeLaurier returned to industry, first, as a balloon analyst at Sheldahl Inc., and next, as a research engineer at Battelle Memorial Institute. Upon joining the staff at UTIAS in late 1974, Dr. DeLaurier has continued his work on Lighter-than-Air Technology, where he has developed programs for predicting the stability and control of modern airships, and their response to atmos-pheric turbulence. Other research interests include unsteadv subsonic aerodynamics and subsonic~ separated flows involving bound vortices. Dr. DeLaurier is a mer.tber of the Interna-tional Astronautical Federation's subcommittee of Lighter-than-Air Technology, and is a revielt/er for Applied Mechanics Reviews.
Dr. L. D. Reid earned his B.A.Sc., M.A.Sc. and Ph.D. degrees in Aerospace
Engineering at the University of
Toronto. He first joined the staff of the Institute as a Special Lecturer in 1965 and is presently an Associate Professor. His research interests lie in the general areas of aircraft sta-bility and control and piloted aircraft performance. At the present time Dr. Reid is investigating the response of aircraft to wind shear and low altitude turbulence during the landing approach. This work involves wind tunnel measure-ments, piloted flight simulators and computer simulations. Other current research interests include the on-line computer control of wind tunnel opera-tions, the development of Laser Doppler Anernometry and the study of the per-formance of automobile drivers. Dr. Reid is an Associate Fellow of the
Canadian Aeronautics and Space Institute and of the American Institute of Aero-nautics and AstroAero-nautics.
Professor G. W. Johnston received his Ph.D. from the University of Toronto, Institute of Aerophysics (1953). He spent 10 years with the de Havilland Aircraft Co. of Canada being responsible for a number of advanced STOL research and development proj ects. He joined the Research Laboratories of the United Tech-nologies Corp., East Hartford, Connecticut, in 1967 as Aerodynamic Consultant to their Fluid Dynamics Department. Activities here included the creation and development of a basic aeroacoustics research group and development of the anechoic wind tunnel facility. He joined the Institute staff in 1970 specializing in aeroacoustic research. Current research interests include the development and propagation of sound by aerodynamic bodies. Subjective "annoyance" research is also of continuing interest. Dr. Johnston is a Fellow of the Canadian Aeronautics and Space Institute.
Dr. A. A. Haasz obtained his 8.A.Sc. in Engineering Science and his M.A.Sc. anu Ph.D. uegrees in Aerospace Science and Engineering at the University of Toronto. His fields of study included electron iMpact excitation cross sec-tion measurements for atnospheric species, and thermospheric cOMposition/ temperature measurements with electron beam fluorescence probes. Af ter joining the Institute staff in 1972, his research interests expanded to include studies of Gas Target tJeutron Generators (related to fusion energy technology), industrial/ architectural aerodynamics (viz studies of air-curtain jets used for protection against precipitation and also for con-fineDent of environmentally hazaruous chemicals and particulates), and sub-jective Ilannoyancell studies of aircraft and traffic noise. Recent research efforts are directed towards naterials damage studies for fusion reactor applications. Dr. Haasz is a member of CAP, CASI, APS and AIAA; he is also a registered professional engineer.
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Dr. P. A. SulJivan obtalned his Bachelorls and Masterls degrees in Mechanical Engineering at the Univer-sity of Nel" South Wales, Austral ia, and then travelled to England to work for his Doctorate in Aeronautics at the Imperial College of Science and Technology, London. Af ter a post-doctoral year at Princeton University, he joined UTIAS in the fall of 1965, where he pursued his research interests in hypersonic aerodynamics and boundary layers. In response to declining in-terest in this area in Canada in the early 19701s, and to renewed Canadian
interest in air cushion vehicles, he developed a research program in the latter area. With the aid of generous funding from the National Research Council of Canada and the Transporta-tion Development Agency this program is now well established. Dr. Sullivan is an Associate Fellow of the Cdnadian Aeronautics and Space Institute, and of the American Institute for Aero-nautics and AstroAero-nautics. He is a licensed professional engineer and has active consultancies in air cushion technology.
Dr. W. G. Richarz obtained his B.A.Sc., M.A.Sc. and Ph.D. degrees in Aerospace Science and Engineering at the University of Toronto before joining the Institute
Staff in August, 1978. His fields of study
included combustión noise, performance of acoustic barriers, and jet noise. Current research centres on theoretical and experi-mental aeroacoustics with emphasis on jet noise diagnostics and reduction. Other areas of interest are turbulence, fluid flow measurements, such as laser Doppler velocimetry, and data analysis techniques.
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Dr. lIansen obtained his B.A.Sc., M.A.Sc. and Ph.D. degrees in the Division of Solid Mechanics of the Department of Civil Engineering at the University of Waterloo. He joined the Institute staff in 1975 af ter working
at the Technical University of Den~ark
and at University College, London, England as a NATO Postdoctorate Fellow. Dr. Hansen's current research emphasis is primarily in solid mechanics which includes programs in the theory of elastic stability, fracture mechanics, crashworthiness of aircraft structures, influence of the space environment on composite materials and the finite element methode
MAJOR INSTALLATIONS
AIR CUSHION VEHICLE TEST TRACK
This 45m diameter enclosed circular test track constitutes a unique facility for experimentation on air cushion vehicles under controlled conditions. The vehicle under test, up to 5m long and 1000 Kg in weight, is tethered to a central post.
Instrumentation data on vehicle motions are passed along the tether and through a
slip ring to an HP 2l00A computer. ~1oveable track panels permit studies of
vehi-cle stability for ramp traversal.
co
HYPERVELOCITY
SHOCK TUBE
This facility was designed for the investigation of dissociating and ionizing-gas flows encountered during hypervelocity flight. It consists of a 15-cm-diR combustion chamber (2H2 +
O2 + 7He), a recoil section, and a transition section (upper photo) to a 10 cm x 18 cm x 16 m channel, test section, recoil section and dump tank
(lower photo). The major measuring instrument is a Mach-Zehnder inter-ferometer with a 23-cm-dia field of view. A Q-switched giant-pulse ruby
(or neodymium) laser light souree with a Pockell cell and frequency doubler provide dual-wavelength inter-ferograms. From these it is possible to measure point-by-point electron number density and total density in the flow field. Pre-scribed stainless steel diaphragms are used up to com-bustion pressures of 400 atm. Cylin-drical deflagration is initiated by an impulsively-heated tungsten wire. Channel pressures ~o ~ 10-5 torr with a leak rate of 10- torr/min are possible. Shock f1ach numbers Ms ~ 25 in argon at Po ~ 0.3 torr can be produced with degrees of ionization x ~ 50~L Piezo-pressure gauges, thin-film heat gauges and other instrumenta-tion are also utilized.
\0
LOW DENSITY WIND TUNNEL
The Institute's Low Density Wind Tunnel, LDWT, was constructed for studies of rarefied gasdynamics and to simulate the near space environment. The LDWT consists of nine vacuum booster pumps capable of 18,000 1/5 pumping speed at 10-2 torr, backed by Roots Blowers and mecllanical pumps. Currently, the LDWT is finding
application outside the traditional aerospace field, in fusion energy studies on a gas target neutron generator concept. Such studies are only possible with large gas pumping facilities, such as the LDWT, which are generally unique to aerospace laboratories.
N
o
PLASMA TUNNEL
The Plasma Tunnel is a low density flow facility which can be operated in different pumping modes. It can be operated at background flow pressures up to about 10 Pascal (1 Pascal = 1.3 micron of Hg) at volume flow rates
of several 1000 liter/sec. Alternatively, it can provide working pressures near its blank-off pressure of about 5 x 10-3p at effective flow rates of 500 l/sec. Plasma flows can be produced by an RF arc source operating near
atmospheric pressure and te~peratures of 5000K or by an ion thruster providing high speed-ratio plasma flows for low mass flow applications. The test section, with a diameter of 2m and a volume of 15m3, is equipped ~ith a traversing mechanism, extensive pressure instrumentation, and an electron beam fluorescence probe. It 1S a
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SONIC BOOM SIMULATORS
Two major facilities exist at UTIAS for
investigat-ing the effects of sonic boom on humans, animals, and structures. The booth (upper left) driven by
12 loudspeakers, yields accurate vJaveform
sir.1ula-tion; it is most useful for psychoacoustic studies. The horn (right, top and bottom) is a 3m x 3m x 26m horizontal pyramid, driven by either a shock-tube
or special compressed-air valve; its very powerful
booms are useful for a variety of problems,
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SPACE SIMULATION AND MOLECULAR BEAMS FACILITY
The facilities consist of a high speed gasdynamic molecular beam system, with recently developed intense
mono-energetic atomic hydrogen and atomic oxygen sources for simulating upper planetary orbital flight, for basic studies of reactive gas-surface interactions, for development of spacecraft instrumentation or for simulation of atmospheric surface effects in orbit on advanced engineering materials, such as composites, etc. A 9 ft diameter ultra clean, ultra high vacuum thermal vacuum space simulation chamber is available, and molecular
beams of up to several centimeters in diameter can be introduced. Several smaller chambers are available for
specialized studies, and include a variety of mass spectrometer, vacuum, surface deposition and other instru-mentation. Recently the Space Simulator has been used for plasma-surface interaction studies of interest in fusion energy development.
General view of wind tunnel.
SUBSONIC
The subsonic wind tunnel was originally designed to perform aerodynamic tests on aircraft and aircraft components in a low turbulence test section. As our research emphasis shifted towards an interest in the influence of turbulence on aerodynamic performance a decision was made to recon-figure the test section into one more suited to such work. A recently completed program has converted the facility into a boundary layer wind tunnel capable of a wide range of turbulent flow simulations. The tunnel has a closed circuit and is powered by both a fan in the return duct and by a unique jet grid fed from an external blower. Control over the flow from this jet grid is used to tailor the velocity profile in the l.lm x 1.7m test section.
The wind tunnel laboratory instrumenta-tion includes 4 channels of OrSA hot wire anemometry, a TR-48 analog compu~er and a HP 2l00A digital computer. This equipment
is used to set up the flow conditions in the tunnel and to take measurements and analyze data. Sharing the computers is a general purpose manned simulation facility used for a variety of man/machine system eval uations.
WIND TUNNEL
General purpose manned simulation facility. Analog and digital computers.
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VACUUM SPHERE AND HOT FLOW TEST FACILITY
The vacuum sphere, of volume 1000 m3 , can be pumped down to less than 10-3 atm pressure, and used as a high mass-flow, blow-down test facility, e.g., as a hypersonic wind tunnel. The vacuum pumping plant, insert, can also operate in a compression mode and in conjunction with an electric gas heater can perform as a hot flow test facility with typical continuously-operating characteristics: 0.5 kg/s, 300°F, 1 atm overpressure.
INSTITUTE LABORATORIES
AEROACOUSTICS LABORATORY
Aeroacoustics is the study of sound associated with airflow; it is an intri-guing combination of aerodynamics and acoustics. UTIAS researches spread over a quarter century - both experimental anu theoretical - have included aeolian tones, the noise from boundary layers, jets, turbulence and combustion, as well as sonic booms and even thunder. The UTIAS Aeroacoustics Laboratory -aside from the Sonic Boom Simulators - centres around the two anechoic chambers
pictured above. Both accommodate a 3/4" air jet, and the right hand one may be traversed by a 3 foot open jet capable of speeds up to 225 ft/sec. In addition there is a duct flow facility (8" x 10" x 361
) with comparable flow speeds. For the measurement of auto- and correlations of random signals, cross-spectral densities, signal averaging, etc., there is an advanced DSP360 digital FFT processor. Further data processing is available from a dedicated HP 2100A computer with fast A/D and D/A capability. ~1easurement of jet flow is via hot wire anemometers and a Laser Doppler Velocimeter system. All this is supplemented by a variety of microphones, amplifiers, spectrum analyzers, recorders, oscilloscopes, calibrators, etc.
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IMPLOSION DYNAMICS LABORATORY
A 20-cm dia hemispherical implosion chamber is the major piece of equipment. The chamber is machined into a massive steel block, which is closed by a massive steel plate, both fastened by 32 x 3.8 cm dia bolts. Stoi-chiometric oxygen-hydrogen (up to 60 atm) is detonated at the cent re by a short (1 mil dia x 1 mm long)
exploding nickel wire. The detonation wave initiates a mehispherical shell of PETN at the periphery of the
chamber and a powerful implosion follows. As far as we know this is the only laboratory capable of producing stable, focussed, explosive-driven implosions in a safe, reusable facility. It has been used to drive
projec-tiles to hypervelocity, to generate planar shock waves in a 2.54 cm channel at 20,000 mis, and produce diamonds
from graphite. Other new materials could well be generated through solid-phase transitions. An image converter camera, a Hilger medium quartz spectroscope with an 8-photocell Strassheim attachment, piezo gauges, manganin gauges and pure iron "witness plates" are utilized for measuring temperatures and pressures as functions of radius and time.
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INSTITUTE COMPUTERS
The Institute has a computer terminal directly linked to the large IBM 3033 (MVS) digital computer on the main (St. George) campus. This is accomplished by a general purpose IBM 1130 digital
com-puter which also has a stand-alone capability and which may be used to drive a Calcomp plotter. Other more specialized analog and digital computers are used in specific research programs at the
Institute. Several other computers at the main (St. George) campus are also available to UTIAS researchers, in particular, an IBM 370-165-11, a powerful DECSYSTEM 1090, an IBM 3031, and, for graphics and communications research, a DEC Gï44 system and two Z-BO based microcomputers. A full-time computer coordinator is available to assist in resolving computational difficulties.
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LASER LABORATORY
The Institute's Laser Laboratory currently uses one nitrogen laser, two nitrogen laser pumped tunable dye lasers, one flashlamp pumped tunable dye laser and one Q-switched pulsed ruby laser. These lasers are used
in a variety of projects and form the backbone of two main facilities: the Laser Ablation and Selective Excitation Spectroscopy (LASES) facility and the Laser Interaction Based on Resonance Saturation (LIBORS)
facility. The LASES facility has recently been shown to be capable of undertaking several experiments
ranging from the measurement of atomic radiative lifetimes to the study of plasma conditions. This facility
has also served as the work horse of a new approach to trace element analysis. The LIBORS facility will be
used to study a new kind of laser ionization and heating technique based on resonance saturation of an atomic vapor. Of particular interest is the possibility of creating long plasma channels that could be used for
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PRECIPITATION WIND TUNNEL LABORATORY
The UTIAS precipitation wind tunnel has a working test section of about lm x lm cross sectional area and 5m length, and operates in the 0-3 mis speed range. The precipitation feature of the tunnel consists of a cylindrical hopper containing the simulation material, which is being traversed automatically at preselected speeds in the x-y directions in a horizontal plane above an opening in the tunnel roof. The precipitation is simulated by glass beads of approrriate sizes and densities to yield the desired terminal velocity ranges. The bead feed system is equipped with control features for varying the bead mass flow rate, which is essential in order to ensure that the particles introduced into the tunnel travel through the flow field without inter-acting with each other.
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- ' SHELL MECHANICS
SPACE SIMULATOR
AIRCRAFT CRASH FACILITY
STRUCTURES end MATERlALS
LABORATORY
The major facilities contained in this laboratory include a universal tension/compression testing machine (60,000 lbs
capacity), a thermal-vacuum space simulator, capable of 10-7
torr with in-situ loading, a 13 foot long high pressure gas gun
for impact studies, fatigue machines, a belt-wrapper apparatus and autoclave for manufacturing conposite structures and an
aircraft fuselage (~1/3 scale) drop test facility for investi-gating crash response.
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TRACE GAS ANALYSIS LABORATORY
The laboratory is centred around a highly flexible atmospheric pressure chemical ionization mass spectrometer system. This has different inlets to be able to accept different samples such as ambient air, gas chromatograph
effluents, volatized liquid samples, etc. It is currently capable of detecting many trace organic substances in air at parts per trillion concentrations instantaneously in real-time. Developmental research is steadily
improving its performance. The facilities also include a variety of developmental vacuum chamber quadrupole mass spectrometers, ion sources, an electron multiplier test facility, analogue and digital electronic equipment,
and a dynamic calibration facility capable of adding knovin trace amounts of organics to air, in the ppm to ppt
range. The laboratory is currently engaged in applications research in biomedical, military and environmental areas. A basic program to provide better understanding of the transmission of ions into, through and out of quadrupole mass filters has been initiated as a collaborative project with the Physics Division of NRC, aimed
AEROACOUSTICS
Principa1 Investigators: Ph.D. Students:
M.A.Sc. Students:
PROGRESS REPORTS
G. W. Johnston, H. S. Ribner, W. G. Richarz B. Eatock, D. Nob1e, K. Ogimoto, R. Wong
N. Ba 11, D. Breitman , E. De11 aPen na , D. Di gnam, I. McLean
THEORY OF CROSS-SPECTRAL DENSITIES OF JET NOISE (NSERC) The present
investi-gation comp1ements Ribner's theory of broadband corre1ations between two
microphones on the far field of a jet. The jet flow is modelled in much more detail and the ana1ysis is extended to the frequency domain. Theoretica1
predictions compare favourab1y with experimenta1 results of severa1 investi-gators. Two mechanisms appear to shape the patterns of the cross-spectra: namely the instantaneous directivity of the sourees and the non-compactness of the source region.
JET NOISE DIAGNOSTICS: SPURIOUS SOUND GENERATED BY HOT-WIRE TURBULENCE
INTERACTION (NSERC) Many attempts to measure source terms of jet noise by
means of jet flow-jet noise corre1ations have been on1y partia11y successfu1. The major difficulty is suspected to be spurious lIprobe noisell generated by
turbu1ence-sensor interaction. The effects of probe noise on measured cross-corre1ations and cross-spectra are predicted and are supported by experimenta1 evidence. Hot wires are found to generate spurious, but we11 correlated noise; this leads to significant errors in jet noise diagnostics of low speed flows. UNCORRELATED VS MODALLY CORRELATED SOURCES: INFERENCES FOR JET NOISE (NAS4
Langley and NSERC) A computer-aided investigation in the context of broadband
radiation was initiated during a stay at NASA Langley. The dependence of the radiation properties (two-point correlations) on the source correlation properties helps clarify the ro1e of 'large scale structures' in jet noise.
JET NOISE SUPPRESSION (NSERC) Further studies of shie1ding concepts for jet
noise have been carried out. The boundary for closest approach to a jet for negligib1e 'edge' interference noise has been established; it approximates a cone close to the 1% jet exit velocity contour. Flat shields with hyperbolic cutout at the cone limit were, according1y, found
fo
attenuate better than shields without the cutout. Other studies explored Strouhal sealing and the shielding of simulated point sources.TRANSMISSION/REFLECTION OF PLANE WAVES BY A CASCADE BLADE ROW (NSERC) A two dimensional (stationary) cascade rig has been fabricated simulating a high hub to tip ratio rotor, and used to make acoustic measurements of the reflected and transmitted acoustic intensities covering a range of plane wave incident angles and cascade flow conditions. Transmission loss coefficients have been computed and compared to availab1e long wavelength predictions. A technical note has been completed covering activity to date.
SOUND RADIATION FROM FINITE LENGTH CIRCULAR DUCTS (NSERC) The sound radiation from a finite length unflanged hard wall circular duct due to an arbitrarily 10cated internal acoustic planar source distribution has been completed. Diffraction of the sound at both duct terminations and the effects of a sub-sonic axial flow are included. A report has been prepared (UTIAS Report No. 231) and parts of this work have been submitted for publication (JASA).
AIRFOIL NOISE RADIATION DUE TO TURBULENCE (NSERC) A theoretical study of the noise radiated by a finite span wing moving in a compressible airstream, due to convecting in-flow turbulence has been completed and a report has been drafted covering results obtained.
ANECHOIC WIND TUNNEL DEVELOP~NTS (NSERC) Experimental studies have been
initiated to determine practical schemes for improving the background noise of open jet anechoic wind tunnels. This is presently dominated by the down-stream collector configuration and the impingement of the free jet.
DIFFRACTION OF A PLANE WAVE BY A HALF PLANE AT THE INTERFACE OF TWO DIFFERENT
VELOCITY FLOWS (NSERC) The diffraction problem due to a plane wave incident
on a half plane placed at the interface of two different flows has been studied and a complete far field solution obtained. Because of the presence of the two different flow regimes at the interface, partial reflection occurs which gives rise to a modification in the pressure field above the plate. An addi-tional diffracted wave is obtained that is not present in the uniform flow half plane problem. A technical note has been prepared outlining the solution obtained.
RECENT PUBLICATIONS
1. W. G. Richarz, "Direct Correlation of Noise and Flow of a Jet Using
Laser Doppler", UTIAS Report tlo. 230, June 1978.
2. H. G. Richarz, "Jet Noise Diagnostics: Spurious Sound Generated by
Hot-Wire Turbulence Interaction", submitted (March 1979) and accepted for publication in Jour. Acoustical Soc. Amer., presented at 4th Meeting of Acoustical Society of America, November 1978, Honolulu, Hawaii.
3. W. G. Richarz, "Theory of Cross-Spectral Densities of Jet Noise", presented at and to be published in Proceedings, Int. Symposium on the Mechanics of Sound Generation by Flow, Aug. 1979, Goettingen.
4. W. G. Richarz, "Direct Correlation of Noise and Flow of a Jet Using Laser Doppler", AIAA Paper 79-571; presented at 5th AIAA Aeroacoustics Conf., March 1979, Seattle.
5. H. S. Ribner, "Influences of Source Coherence from Correlations of Jet Noise", Proc. 9th Internat. Congress on Acoustics, Madrid, July 4-9, 1977, p. E33.
6. H. S. Ribner, "Two-Point Correlations of Jet Noise", J. Sound & Vibr.,
56(1), 1978, 1-19. (Condensation and slight revision of NASA TN 0-8330,
Dec. 1976.)
7. H. S. Ribner, "0n the Role of the Shear Term in Jet Noise", J. Sound
&
Vibr., 52(1), 1977, 121-132.8. H. S. Ribner, "Author's Reply" [to Letter to Editor by H. V. Fuchs, "Two Point Correlations of Jet Noise and Their Interpretation", 61(1), 153-156J,
J. Sound & Vibr., 61(1), 156-159 (1978).
-9. G. W. Johnston, "Diffraction of Arbitrary Oriented Directional Sources by Rigid Planar Screens", Jour. Acoust. Soc. of America, Vol. 64(2), Aug. 1978, 665-676.
10. G. W. Johnston, K. Ogimoto, "t~odal Radiation Impedances for Semi-Infinite
Unflanged Circular Ducts Including Flow Effects", submitted to Jour. of Acoustical Soc. Amer.
11. K. Ogimoto, "Soun d Radiation fr om a Finite Length Unflanged Circular Duct
with Uniform Axial Flow", UTIAS Report No. 231, 1979.
12. G. W. Johnston, A. A. Haasz, "Traffic Background Level and Signal Duration
Effects on Ai rcraft Noi se Judgment", Jour. Sound & Vibr., Vol. 63, 1979,
543-560.
13. D. B. Breitman, "Diffraction of a P1ane Wave by a Half P1ane P1aced at the Interface of Two Different Speed F1ows " , M.A.Sc. Thesis, Sept. 1979. 14. Johnston, G. W., "The Dynamics of the Curling Stone", submitted and
accepted for pub1ication by CASI Trans., August 1978.
15. N. G. Ball, "Transmission of P1ane Waves Through a B1ade Row", M.A.Sc.
Thesis, 1978.
C10seup vi ew of a 11 sugar SCOOp" barri er with burners insta 11 ed
at the trai1ing edge. The hot gas enhances the noise reduction by means of a refractive 1ayer. Typica1 PNdB reductions are of the order of 8 dB.
AIR CUSHION TECHNOLOGY Principal Investigators: Co-Investigators: Visiting Professor: Research Scientists: M.A.Sc. Students: Research Assistant: P. A. Sullivan, J. S. Hansen A. J. Cousin, P. C. Hughes A. A. Gruzdev P. V. Hartmann, M. J. Hinchey
A. Dupuis, T. Graham, D. Ribner G. Green
DEVELOPMENT OF THE UTIAS 43 f.1l!,""TRE DIAMETER AIR CUSHION VEHICLE TEST TRÁCK
(NSERC; TDC) A second generation digital data acquisition system (DDAS), which makes use of a dedicated microprocessor has been designed, assembled and is
currently being programmed. It features automatic gain control and zero setting
of the on-board signal conditioning amplifiers. It can also perform some elemen-tary data processing.
STATIC PITCH AND ROLL STIFFNESS CHARACTERISTICS OF A SEGMENTED SKIRT CUSHIOlJ
(TDC; NSERC) Th~ work on this cushinn started in 1978 and is now usefully divided into two parts, described by this and the next item respectively. A simple theory for static pitch and roll stiffness has been developed and compared with
experi-mental measun,ments obtai ned on the cushi on dynami cs facil ity. Results we re
obtained for two skirt materials, an isotropic polyethylene film and a urethane coated nylon fabric. Good agreement between the theory and experiment was
ob-tained for the second material, but the first showed very large hysteresis similar
to that observed on earl ier work on multicell cushions.8 This work emphasizes the
need to determine the extent to which this phenomenon is important at full scale. Observations of this system in motion have demonstrated that differences in skirt material properties can greatly affect the dynamics.
PITG7i-HEAVE DYlJAMICS OF A SEGMENTED SKIRT CUSHION (TDC; NSERC) The objective is
the determination of the relative inportance of several possible sources of
cushion damping. It is the first attempt to use the full Circular Track concept
involving instrumentation, the DDAS, and an optimal estimation procedure to extract estimates of the parameters describing cushion stiffness and damping. The first estimates of pitch stiffness obtained from dynamic motion excited by flight over the track ramp were very close to those measured directly in a static experiment.
DYNAMIC INSTABILITIES OF AIR CUSHIONS (NSERC; TDC) The success of the experiments
undertaken last year to verify the magnitude of theoretically predicted duct
effects has been an important key to the systematic exploration of the many aspects
of this subtle problem.7 It has also demonstrated the value of the UTIAS 12 metre
diameter Vacuum Sphere as an idealized air flow source. Projects under way include improvement in the methods of measurement of stability boundaries, measurement of limit cycle frequencies, and examination of the effect of fan dynamics, skirt geometry, viscoelastic skirt material properties and hovering over water on basic vehicle stability.
INVESTIGATIONS OF PRESSURIZED MEMBRANE STRUCTURES (NSERC; TDC) Thi s work i s a imed
at exploring methods for predicting the structural stability of flexible skirt
geometries under loading patterns characteristic of ACV's. Even though the skirt
can usually be treated as membranes, two features complicate the analysis. The
first is the phenomenon of wrinkling.6 When wrinkles appear, the overall structure
softens but does not necessarily fail. The second is that typical ACV skirt mate-rial may he highly anisotropic. Recently, a finite element programme for the
analysis of the buckling of pressurized cylinders developed at UTIAS by the Structures Group has been extended to include the effect of applied bending moments and using orthotropic materials. The key feature of the last step is that it allows examination of both the effect of the particular properties of skirt materials and the wrinkling of isotropie materials. Basically, the
wrinkled porti ons of an otherwise isotropie material behave as if the effective Young's modulus in the direction of the lesser principal stress is extremely small compared to that in the other principal stress direction.
A COMPLIANT SURFACE GAS BEARING CONCEPT FOR RAPID LOADING AND UNLOADING OF HIGHWAY T&UvSPORT TRAILERS (E. B. Eddy Forest products; DSS) Ouring the past
year it has been shown by the Developer that this concept has the potential for innovation in other aspects of the general problem of handling of goods trans-ported on pallets. For example, when perishable commodities are handled and stored in a warehouse, it is extremely important that this be done on a "first in - first out" basis, and the concept can greatly simplify the layout of such warehouses and effect other economies. Ouring the last year, a contract has
been secured from OSS/TOC to continue the investigation of the air bearing aspects of the concept.
UNSTEADY AIR FLOW FROM AIR CUSHIONS (NSERC) All of our work on the dynamics of
air cushions has to date assumed that the process of air escape from the cushion or between volumes within the cushion is quasisteady. Two cases where this is probably not an accurate assumption7 are: high frequency skirt flutter, and
when the mean value of a periodic volume flux is zero. Currently we are examing the limitation of this assumption by using analytical techniques to obtain solu-tions for truly unsteady flow for representative cases.
RECENT PUBLICATIONS
1. P. A. Sullivan, J. G. Parravano, "Analysis of a Loop Type Flex~ble Skirted Cushion", CASI Jour., 23, 6, 1977, 346-358.
2. P. A. Sullivan, M. J. Hinchey, R. G. Oelaney, "Statie Roll Stiffness Char-acteristics of Two Multicell Type Air Cushions", Jour. of Terramechanics, 15,1, 1978. 15-41.
3. M.'" J. Hinchey, P. A. Sull ivan, "Duet Effects on the Heave Stabil ity of Plenum Air Cushions", Jour. of Sound and Vibration, 60, 1, 1978, 87-99. 4. M. J. Hinchey, P. A. Sull ivan, "Duet Effects on the Oynamic Fan
Character-istics of Air Cushion Systems" (Technical Note), Jour. of Hydronautics,
Il,
1,1979, pp. 28-29.UTIAS, TDC CONTRACT REPORTS AND SYMPOSIA PROCEEDINGS
5. J. G. Parravano. P. A. Sullivan, "A Theoretical and Experimental Investiga-tion of a Hinged Lip Tracked Air Cushion Vehicle Suspension Report", TOC Report File 0-500-210-2. March 1977.
6. P. A. Sullivan, M. J. Hinchey, 1. Murra, "Research on the Stability of Air Cushion Systems", TOC Contract Report TP 1469, October 1977; also issued as UTIAS Report 238, November 1979.
7. M. J. Hinchey, "Heave Instabilities of Amphibious Air Cushion Suspension Systems", Ph.D. Thesis, July 1979 (to be issued as UTIAS Report).
8. P. A. Sullivan, G. M. Green, P. V. Hartmann, "Statie Roll and Pitch Stiff-ness Measurements on Two Models of a Segmented Skirt Cushion", presented at l3th Canadian Symposium on Air Cushion Technology (CASI), Montreal, September 1979.
ENERGY TECHNOLOGY
Principal Investigators: Research Scientists: Students:
J. H. de Leeuw, A. A. Haasz, P. C. Stangeby O. Auciello, S. Basu, W. T. Shmayda, I. S. Youle A. Antoniazzi, O. Oavidson, R. Fehr, L. Hebert, J. H. Lever, B. J. Lewis, A. Manz, P. Sergejewich FUSION ENERGY: PLASMA SURFACE INTERACTIONS3 PSI (NSERC; Ontana Ministry af
Energy; Dilwarth3 Secard3 Meagher & Assaciates Ltd.) Fusion reactor plasmas
at 100,000,000 K will interface with reactor walls at < 1000 K. While plasma
surface interactions are minimized by the insulating magnetic field, serious erosion nevertheless occurs. A variety of plasma particles bombard the walls causing both loss of wall integrity as well as plasma contamination. This phenomenon is one of the most serious impediments to the development of practical fusion energy and has therefore become the object of widespread study.
Research at UTIAS centres on the study of one aspect of PSI, namely chemical erosion due to hot atomie hydrogen, HO. One of the primary species in a fusion plasma is HO which is highly corrosive especially toward some of the intended first wall materials for reactors, such as carbon. As it turns out, HO is the dominant ionospheric component at certain altitudes in near space, and the study of HO-surface interactions has been the object of research at UTIAS for some time. Extensive research facilities hav~ been assembled for this work including the ultra high vacuum Space Simulator, page 22, HO beams and related uhv hardware. These facilities have now been committed to fusion PSI studies and provide research opportunities which are unique in the field. The HO-beam directed onto substrates such as graphite causes erosion by producing gases, e.g. methane, which are monitored by a sensitive quadrupole mass spectrometer. Part of the group effort is directed toward the development of HO and H+ sources which extend beam energy from the present level of s 0.5 eV up toward the existing lower limit of conventional ion beams - 200 eV. This intermediate energy range, 1-200 eV, is the most critical for fusion reactor operation but is presently inaccessible for simulation studies due to the lack of appropriate Hsources.
FUSI ON ENERGY: GAS TARGET NEUTRON GENERATOR3 GTNG3 STUDIES (NSERC) The GTNG
will incorporate a high energy tritium ion beam"impingent on a high speed deuterium gas flow to produce an intense source of 14 MeV neutrons via the O-T fusion reaction. Such intense sources are required for fusion materials develop-ment and for cancer therapy. Studies at UTIAS continue to exploit the Low
Oensity Wind Tunnel, page 19, to produce high speed gas flows, i.e. gas targets, and an intense electron beam to simulate ion beam interaction with a gas flow. Experiments are proceeding on subsonic and supersonic gas targets. Gas flow patterns are monitored in supersonic targets by the schlieren technique and by measuring plasma behaviour in the target via analysis of light emission.
PLASMW CURRENT MULTIPLIER STUDIES (NSERC) The Plasma Current Multiplier, PCM,
is a simple electrical gas discharge device which has the ability to amplify electrical current to very high values. An extensive study of the operating properties of the PCM has been completed and the gain dependence on absolute current level and gas pressure has been elucidated for the first time. Appli-cations as a power cathode or as a current control device are under examination.
HYDROCARBON FUEL STUDIES (Environment Canada; AZberta Oil Sands TechnoZogy and
Research AuthorityJ Hydrocarbon fue1s, when subjected to rapid devo1atization
and hydrogenation, are known to show different yie1ds of gas and 1iquid products than if these fue1s are processed by traditional (slow) techniques. Oi1 sand, coa1, and biomass feedstocks have been tested in a rapid heating faci1ity at UTIAS, capab1e of heating rates up to 10,000 KIS and the products ana1ysed by gas chromatography. This work is aimed at the extraction of usefu1 oi1 and gas products from oi1 sand, coa1, wood and other feedstocks. The principa1 finding of the research to date is that tota1 product yie1d is not a function of heat-up ra te but is re1ated primari1y to the maximum temperature attained. The distribution of hydrocarbon products yie1ded, on the other hand, is very dramatica11y inf1uenced by heating rate, with faster heating rates producing 1ighter hydrocarbon products.
RECENT PUBLICATIONS
1. J. H. de Leeuw, A. A. Haasz, P. C. Stangeby, "Canadian Gas Target Neutron Generator Research", Nuc1. Instrum. & Meth., 145,1977,119. 2. J. H. de Leeuw, A. A. Haasz, P. C. Stangeby, 1. S. You1e, "Experimenta1
Simu1ation of a Hypersonic Gas Target Neutron Generator for Fusion Materials Studies", AlAA J. of Energy, 2, 1978, 238.
3. S. C. Johnston, A. A. Haasz, P. C. Stangeby, "Comparison of Experimenta1 Resu1ts of Gas Target Neutron Generator Simu1ation Studies", AIAA J. of Energy, 2, 1978, 253.
4. A. A. Haasz, P. C. Stangeby, 1. S. You1e, "Experimental Tests of Subsonic Gas Target", Nuc1. Instrum. & Meth., in press.
5. P. C. Stangeby, V. Chatoorgoon, "Subsonic Gas Target", AII\A J. of Energy 1, 1977, 387.
6. V. Chatoorgoon, P. C. Stangeby, "Subsonic Gas Target 14 MeV Neutron Generator" , AIAA J. of Energy 2, 1978, 129.
7. V. Chatoorgoon, P. C. Stangeby"-; "Start-Up and Stability of Subsonic Gas Targets", AIAA J. of Energy, 2, 1978, 254.
8. J. H. Lever, "S ch1ieren Diagnostics of a Hypersonic Gas Target Neutron Generator", M.A.Sc. Thesis, UTIAS, May 1979.
9. B. J. Lewis, "Design of a Bulk Titanium Sublimator System", M.Eng. Thesis, UTIAS, Sept. 1979.
10. P. C. Stangeby, P. L. Sears, "Total Yields of Heated Oi1 Sand", in Oil Sand and Oi1 Sha1e Chemistry, Ed. O. P. Strausz and E. t~i1own, Verlag C h em i e Int., 1 978, 1 Ol - 118.
11. W. T. Shmayda, P. C. Stangeby, "Pl asma Current Multip1 i er at Hi gh Current Leve1s", Can. J. Phys., in press.
12. P. C. Stangeby, W. T. Shmayda, "DC Plasma Production Without Electron Emission", Rev. Sci. Instrum., 47, 1976, 935-937.
