Table Of ContentIEEE T R A N S A C T I 0 N S O N
MICROWAVE THEORY
AND TECHNIQUES
A PUBLICATION OF THE IEEE MICROWAVE THEORY AND TECHNIQUES SOCIETY
JULY 1996 VOLUME 44 NUMBER 7B IETMAB (ISSN 0018-9480)
[email protected]
PART II OF TWO PARTS
PAPERS
MTT Special Issue Guest Editorial - M. Nisenoff ; W.J. Meyers 1193 - 1197
The high temperature superconductivity space experiment (HTSSE-II) design –
T.G. Kawecki ; G.A. Golba ; G.E. Price ; V.S. Rose ; W.J. Meyers 1198 - 1212
Design considerations of superconductive input multiplexers for satellite applications -
R.R. Mansour ; Shen Ye ; V. Dokas ; B. Jolley ; G. Thomson ; Wai-Cheung Tang ; C.M. Kudsia 1213 - 1228
High temperature superconducting space-qualified multiplexers and delay lines -
S.H. Talisa ; M.A. Janocko ; D.J. Meier ; J. Talvacchio ; C. Moskowitz ; D.C. Buck ; R.S. Nye ; S.J. Pieseski ; G.R. Wagner 1229 - 1239
Cryogenic microwave channelized receiver - C. Rauscher ; J.M. Pond ; G.B. Tait 1240 - 1247
Low loss multiplexers with planar dual mode HTS resonators - S.J. Fiedziuszko ; J.A. Curtis ; S.C. Holme ; R.S. Kwok 1248 - 1257
High temperature superconductive wideband compressive receivers -
W.G. Lyons ; D.R. Arsenault ; A.C. Anderson ; T.C.L.G. Sollner ; P.G. Murphy ; M.M. Seaver ; R.R. Boisvert ; R.L. Slattery ;
R.W. Ralston 1258 - 1278
Jet Propulsion Laboratory/NASA Lewis Research Center space qualified hybrid high temperature superconducting/semiconducting 7.4
GHz low-noise downconverter for NRL HTSSE-II program - H.H.S. Javadi ; J.G. Bowen ; D.L. Rascoe ; R.R. Romanofsky ; C.M.
Chorey ; K.B. Bhasin 1279 - 1288
Space-qualified superconductive digital instantaneous frequency-measurement subsystem
Guo-Chun Liang ; Chien-Fu Shih ; R.S. Withers ; B.F. Cole ; M.E. Johansson 1289 - 1299
A space-qualified experiment integrating HTS digital circuits and small cryocoolers
A. Silver ; G. Akerling ; R. Auten ; D. Durand ; J. Godden ; K.-F. Lan ; J. Murduck ; R. Orsini ; J. Raab ; S. Schwarzbek ; E. Tward ;
M. Wire 1300 - 1307
The NRL Josephson junction monitoring experiment on HTSEE-II - J.H. Claasen ; R.G. Skalitzky ; R.J. Soulen 1308 - 1312
Design of HTS, lumped-element, manifold-type microwave multiplexers - G.L. Matthaei ; S.M. Rohlfing ; R.J. Forse 1313 - 1321
On the power handling capability of high temperature superconductive filters –
R.R. Mansour ; B. Jolley ; Shen Ye ; F.S. Thomson ; V. Dokas 1322 - 1338
Miniature superconducting filters - M.J. Lancaster ; F. Huang ; A. Porch ; B. Avenhaus ; Jia-Sheng Hong ; D. Hung 1339 - 1346
High temperature superconducting resonators and switches: design, fabrication, and characterization -
M. Feng ; F. Gao ; Zhongmin Zhou ; J. Kruse ; M. Heins ; Jianshi Wang ; S. Remillard ; R. Lithgow ; M. Scharen ; A. Cardona ; R. Forse 1347 - 1355
Properties and applications of thick film high temperature superconductors -
T.W. Button ; P.A. Smith ; G. Dolman ; C. Meggs ; S.K. Remillard ; J.D. Hodge ; S.J. Penn ; N.M. Alford 1356 - 1360
Ferrite-superconductor devices for advanced microwave applications - G.F. Dionne ; D.E. Oates ; D.H. Temme ; J.A. Weiss 1361 - 1368
( Continued on back cover)
Properties and applications of HTS-shielded dielectric resonators: a state-of-the-art report
N. Klein ; A. Scholen ; N. Tellmann ; C. Zuccaro ; K.W. Urban 1369 - 1373
Adaptive high temperature superconducting filters for interference rejection –
K.F. Raihn ; N.O. Fenzi ; G.L. Hey-Shipton ; E.R. Saito ; V. Loung ; D.L. Aidnik 1374 - 1381
High Q-value resonators for the SHF-region based on TBCCO-films –
M. Manzel ; S. Huber ; H. Bruchlos ; S. Bornmann ; P. Gornert ; M. Klinger ; M. Stiller 1382 - 1384
Twenty-GHz broadband microstrip array with electromagnetically coupled high T/sub c/ superconducting feed network
J.S. Herd ; L.D. Poles ; J.P. Kenney ; J.S. Derov ; M.H. Champion ; J.H. Silva ; M. Davidovitz ; K.G. Herd ; W.J. Bocchi ;
S.D. Mittleman ; D.T. Hayes 1384 - 1389
High-spatial resolution resistivity mapping of large-area YBCO films by a near-field millimeter-wave microscope
M. Golosovsky ; A. Galkin ; D. Davidov 1390 - 1392
(end)
IEEE TRANSACTIONS ON MICROWAVE THEORY AND TIECHNIQUES, VOL. 44, NO. I, JULY 1996 1193
MTT Special Issue Guest Editorial
Martin Nisenoff, Member, IEEE, and William J. Meyers, Member, IEEE
1. INTRODUCTION yttrium-barium-copper-oxide (YBCO) at temperatures near
T 90 K, scientists and engineers at NRL became interested in
HIS SPECIAL Issue of the IEEE TRANSACTIONOSN
the prospects of employing high temperature superconduct-
MICROWAVTEH EORYA ND TECHNIQUEiSs focused On
ing electronic devices and subsystems in operational remote
the microwave and millimeter wave applications of high
sensing and communication systems. Such devices could be
temperature superconductivity (HTS) with an emphasis on the
operated using only liquid nitrogen, or, possibly, physically
Naval Research Laboratory’s program known as the high tem-
small, closed-cycle cryogenic refrigeration systems. These
perature superconductivity space experiment (HTSS E). High
coolers have orders of magnitude smaller weight, volume and
temperature superconductivity was discovered in 1986 and su-
electrical input power requirements than those for the better
perconducting materials with transition temperatures in excess
known “low temperature superconducting” materials which
of 77 K, the boiling point of liquid nitrogen at atmospheric
must be operated below 20 K.
pressure, were discovered in the spring of 1987. Just four
The very low attenuation, wide bandwidth, low noise and
years after this latter discovery, there was a Special Issue of
high speed associated with high frequency superconductivity
the TRANSACTIONONS MICROWAVTEH EORYA ND TECHNIQUES
are very attractive attributes for high performance communi-
(vol. 39, no. 9, September 1991) entitled “Microwave Applica-
cations and remote sensing systems. The engineers in the NRL
tions of Superconductivity.” In that issue, there were I7 papers
Naval Center for Space Technology (NCST) quickly realized
describing relatively simple HTS microwave devices, such as
that these properties of superconductivity were nearly ideal for
filters and resonators, antennas, HTS materials, and simulation
their system requirements. Additionally, the reduced cryogenic
and modeling of HTS microwave devices. This current Special
burden for their deployment in space might be acceptable
Issue, appearing five years later and just nine years after
considering the improved performance that could be realized
the discovery of materials with superconducting transition
from the use of this “ultimate” electronic technology. In
temperatures above 77 K, contains a total of 2’1 articles. There
December 1988, the HTSSE program was approved by the
are ten invited papers describing complex and sophisticated
Navy with funding from the Space Technology Program
HTS advanced microwave devices and subsystems which were
Office of the U.S. Navy Space and Naval Warfare Systems
designed and built to specifications, interfaced with cryogenic
Command (SPAWAR). From the very beginning this program
refrigerators and integrated into a satellite payload which will
was designed to be very focused, with dejinite goals and
be launched in 1997. The remaining 11 contributed articles
objectives, speciJic deliverables, and periodic space Jlights to
describe additional novel and sometimes very sophisticated
demonstrate the space-worthiness of this new technology. One
microwave applications of HTS technology which were de-
of the goals of this program was to accelerate the development
veloped in laboratories throughout the world. The level of
of HTS into a viable electronic technology and to focus this
complexity of these HTS components, sometimes integrated
technology toward potential space applications. The HTSSE
with semiconductor components, and the attempts to insert
program was definitely a development program to produce
HTS microwave technology into systems, both space-based as
devices and components, not a research program to search
well as terrestrial, is amazing considering that a little over ten
for new materials or to understand the basic phenomena
years ago speculating about high performance superconducting
responsible for superconductivity at these (relatively) elevated
microwave components operating at temperatures near that of
temperatures. A broad agency announcement (BAA) published
liquid nitrogen would have been considered suitable script
in January 1989, which was the first public announcement of
material for Star Trek.
this program, clearly stated these goals.
It is generally agreed on by members of the microwave
superconductivity community that the Naval Ftesearch Labora-
tory program known as the high temperature superconductivity 11. HTSSE-I PROGRAM
space experiment (HTSSE) was a major catalyst to1 the de-
The HTSSE program consisted of three phases. The first
velopment of this technology. Shortly after the published
phase, which became known as HTSSE-I, focused on simple
account of the discovery of superconductivity in the compound
HTS electronic devices. The second, HTSSE-11, addressed,
complex HTS devices and subsystems. HTSSE-I11 was to have
Manuscript received March 11, 1996. been a complete operational system with HTS components
M. Nisenoff is with the Naval Research Laboratory, Washington, DC USA. performing crucial functions so as to enhance the performance
W. J. Meyers is with Allied Signal Technical Services Corp., Columbia,
of the candidate systems. When the contracts were awarded
MD USA.
Publisher Item Identifier S OOIX-9480(96)047X3-7. in June 1989 for the HTSSE-I deliverables, each successful
0018--9480/96$05.00 0 1996 IEEE
I194 IEEE TRANSACTIOKS ON MICROWAVE THEORY AND TECHNIQUES, VOL 44, NO I, JULY 1996
provider agreed to supply to NRL five devices of nominally a cryogenic refrigerator and spacecraft ambient temperature
“identical” electrical performance, each in a package that measurement electronics and would be integrated onto a host
would be space qualified. Each provider had 12 months DOD satellite. The electronic measurement system was a fully
to complete their devices. Thus, only three years after the space-qualified scalar network analyzer. Once the satellite was
discovery of these materials, physically and electrically robust launched and on orbit, the devices would be cooled by the
HTS components-five each-had to be delivered for space cryogenic refrigerator to operating temperatures (77 K). Then,
qualification and integration onto a specially designed and built on command from the ground, a sequence of measurements
satellite payload. This was a significant challenge considering would be initiated to measure the microwave parameters of
the lack of maturity of this technology at that time. the HTS devices. The data collected would be downlinked to
To achieve the goals of HTSSE-I, the device providers had a ground station, where the data could be analyzed to detect
to accomplish the following very challenging tasks: changes, if any, due to the space environment. The planned
mission duration was about one year.
1) Stabilize a thin or thick film or bulk HTS materials
The HTSSE-I payload was completed in late 1992 and
fabrication technology so that they could produce at least
manifested on a U.S. Air Force satellite launch scheduled
five copies of the desired device;
for 1993. Unfortunately, the payload did not achieve orbit
2) design and fabricate the devices of interest;
and the HTSSE-I experiment was lost. Despite the unfor-
3) make careful electrical measurements at cryogenic tem-
tunate loss of on-orbit data from the HTSSE-I experiment,
perature (this was especially challenging for microwave
the program did conclusively demonstrate that viable and
devices where the network analyzer used to measure
robust HTS microwave devices could be fabricated, packaged,
these devices had to be properly calibrated for use at
and space qualified. The performance of the HTS devices
cryogenic temperatures);
demonstrated superior electrical performance compared to
4) mount the device in a box or structure with standard con-
competing technologies with the same weight and volume or
nectors and make mechanically strong contacts between
their performance was comparable to conventional technolo-
the standard connectors and the HTS device;
gies with at least an order of magnitude reduction in weight
5) subject the packaged device to the shock and vibration
and volume. The demonstration in 1992, just five years after
required for electronic components designed for satellite
its discovery, that high temperature superconductivity was a
use.
viable and robust technology which could be qualified for
These were very serious challenges. Not only was the technol- space deployment was a major milestone in the development
ogy relatively immature but most of the researchers interested of HTS electronics.
in superconductivity had never addressed the issues associated
with packaging electronic devices for space. Despite these
technological obstacles, more than 45 proposals were received 111. HTSSE-I1 PROGRAM
from industrial, government, and academic laboratories. Some
In the 1991-1992 timeframe while the HTSSE-I payload
were proposals in response to the BAA; others were offers
was under construction and test, a solicitation for proposals
of devices whose development was funded by other U.S.
was issued for HTSSE-I1 which focused on advanced HTS de-
or foreign agencies. After careful review, the HTSSE team
vices and subsystems. In HTSSE-I, any device that performed
selected 23 devices for inclusion in the program. Of these,
a useful spacecraft electronic function was accepted. In this
19 were thin film microwave devices (e.g., resonators, filters,
second phase, the prospective provider had to design and, then,
delay lines, couplers, and antennas) and two thick film or bulk fabricate to this design an HTS component which performed
devices (e.g., cavity resonators). The remaining two were an a significant function in a typical spacecraft payload. An
infrared bolometer array and high current capacity electrical example is a four-channel multiplexer with a specific center
leads. frequency for each channel, bandwidths, and band-edge roll-
During the one-year development period for the HTSSE-I off characteristics. Other proposed deliverables consisted of
devices, more than 20 research and development organizations HTS components integrated with semiconductor devices, the
had very concentrated efforts to perfect this technology. NRL latter operating either at the same temperature as the HTS
provided about one-person-year of financial support but, in components, or, possibly, operating at spacecraft ambient
most instances, the research organization invested many times temperature. Some of the proposed components were digital
that effort (either funded internally or by other sources) to circuits, which at that time had not yet been demonstrated.
develop these devices. Hence, during the 1990-1 991 time If successful, the very low power and high speed poten-
frame, microwave applications were the major thrust driving tial of these digital circuits could have a major impact on
the HTS device community, possibly rivaled only by the inter- future spacecraft systems. These proposals were clearly the
est in superconducting quantum interference device (SQUID) next major step in the development of HTS technology for
magnetometry. spacecraft deployment. In Spring 1992, a total of 13 deliv-
Of the 23 devices developed for HTSSE-I, 18 were delivered erables was selected from more than 30 proposals received
to NRL for electrical verification and space qualification. All of in response to the NRL solicitations. These development
these were microwave devices. While the devices were under programs were funded, either under direct NRL contracts,
test, the engineers in the NCST at NRL designed and fabricated by other government agencies, or by foreign governments.
a satellite payload for these HTS devices which contained Again, as in the case of HTSSE-I, the funds provided by NRL
NISENOFF AND MEYERS: MTT SPECIAL ISSUE GUEST EDITORIAL 1195
under the HTSSE contracts were very heavily leveraged by on the program. Information is a vital ingredient to
internal R&D funds, or by funding from otheir U.S. or foreign any program. Each of the participants has different
government’s agencies. The HTSSE program continued in a experiences and expertise which should be made avail-
major leadership role in expediting the devellopment of HTS able to all the other participants. For example, in the
microwave technology. HTSSE-I program, we had three reviews, a kick-off
The first invited article in this Special Issue contains a list meeting, a mid-year and a final review, at which all
of the 13 HTS advanced devices and subsystems selected for 23 participating organizations presented their successes
development by the HTSSE-I1 program as well as a description as well as failures in a very open and “no-holds-barred”
of the common cryogenic cold bus where seven of ithe eight manner. Thus, each participant was able to learn from
HTSSE-I1 components selected to be flown are mounted. The their colleagues what worked and what did not work,
eighth device is a stand-alone subsystem where the HTS device and did not have to repeat failures.
is integrated with its own cryogenic refrigerator. After integra- 4) Minimize paperwork and formal reviews. It is the re-
tion with their refrigerators into thermally efficient cryogenic sponsibility of the program management to know the
packages, they were mounted onto the HTSSE-I1 satelllite deck goals and milestones, which projects are on schedule
along with several spacecraft ambient temperature electronic and which are falling behind, and which performers
packages (amplifiers, multiplexers, receivers, analog- to-digital are making progress and which are marginal. This can
converters, etc.). The entire HTSSE-11 payload was tested be done by frequent (but not too frequent) visits to
for electrical functionality and for space qualification. The the participating organizations for informal progress
HTSSE-I1 payload and its HTS components have ftinctioned reviews and, most importantly, for discussions with the
exceedingly well except for a few minor problems with workers in a casual environment, for example, over
two of the subsystems. The payload is to be shipped to coffee or a soft drink. Formal presentations consume
Rockwell International in Spring 1996 for integration onto the time and resources to prepare complex, multicolored
advanced research and global observation saiellite ( ARCOS) visual materials which can easily disguise or mask
for a scheduled launch in Spring 1997. deficiencies in the program. In an informal meeting in
the laboratory or over a cup of coffee, the true situation
and status usually will be evident. This is a much better
1V. LESSONSL EARNED
means for maintaining awareness of progress in any
As the payload for HTSSE 11 was going through space- program as well as establishing good rapport with the
craft acceptance testing prior to shipment to Rockwell, the participants.
NRL team who managed the two completed phases of the 5) lf the development program isf unded by the government,
HTSSE program, concluded that they had established a unique leveraging other government programs and industrial
paradigm for developing a new technology. They also have R&D programs is essential. In any new program, fund-
a set of “lessons learned” which might be helpful to other ing is always scarce; and if one can leverage other
organizations who are attempting to develop new technologies. government or industrial-supported R&D activities, a
Hopefully, these lessons, based on experiences with high much stronger program will develop. In the cases of
temperature superconductivity, are universal and will be useful HTSSE-I and 11, we estimate that the program was able
in developing other technologies. They are: to leverage, by a factor of two to three, its own funding
Provide a challenging time schedule with intermediate when the participants had other funding sources which
goals and objectives and, if appropriate, periodic de- could be applied to this program.
liverubles to verifjl the maturing of th<et echnology. By 6) Use an impartial laboratory, such as a government in-
structuring the HTSSE program in phases with each house laboratory, with the relevant expertise and expe-
phase having deliverables, an impartial evalua.tor could rience to coordinate the program and to verifjt perjfor-
observe significant advancements since the previous mance of the deliverables. It is extremely important to
goal. By requiring deliverables during the program, the have the program managed by a competent and impartial
community had to address issues such as packaging organization, who has no vested financial interest in the
and integration with conventional electronics ;and, thus, outcome of the program. For the HTSSE program, NRL
demonstrate that the technology is indeed robust and was a logical and qualified candidate for managing the
viable. program. NRL’s Naval Center for Space Technology has
Offer an attractive final goal. A final godl is very built more than 80 satellites in the previous 30 years
helpful to focus attention of the developmen1 team on and NRL has a large group specializing in radiation
the long-term activity. Although interrnediate goals and effects on structural and electronic materials in the space
milestones are important, it is extremely criticad to focus environment. Furthermore, NRL has a strong research
on the final goal. In the HTSSE program, the goal was team experienced in superconducting materials and elec-
a satellite launch. For a commercial activity, the final tronics. Thus, NRL could be and was an impartial judge
goal might be a final prototype or preproduction package to exercise the choice of devices and components and
ready for marketing. to evaluate the eventual results of the program without
Encourage free exchange of information among team fear of jeopardizing the long term interests and goals of
members and among the several contractors working the organizations.
1196 IEEE TRANSACTICI NS ON MICROWAVE THEORY AND TECHNIQUES, VOL. 44, NO. 7, JULY 1996
v.
CONCLUSION AND FUTURE result from the insertion of this technology into various
DIRECTIONSFO R THE TECHNOLOGY candidate operational systems. These studies were on-going at
the time this guest editorial was written. Based on these and
The unique properties of the superconducting state can
similar assessments, decisions about inserting high temperature
provide both military and civilian communities with the “ul-
superconductivity electronic components and subsystems into
timate” electronic technology possessing low insertion loss,
space systems, and, in addition, into terrestrial systems, will
wide bandwidth, low noise and high speed. The engineers and
be made.
scientists at the Naval Research Laboratory realized shortly
after the discovery of high temperature superconductivity that HTS technology will only be introduced into military
this newly discovered phenomenon could significantly impact or commercial systems when the end user can be over-
future generations of space-based communications and remote whelmingly convinced that this is the only technology
sensing systems. A program (HTSSE) was initiated to focus that can provide a signijicant and desired advantage at
a system level over what can be obtained using more
the attention of the superconductivity community on space
conventional technologies.
applications of this technology and to demonstrate that this
was a viable and robust technology that would survive space
deployment. During the initial phase of the HTSSE program,
a unique government, industry and academic partnership was MARTINN ISENOFF,G uest Editor
organized to provide HTS microwave devices which were Naval Research Laboratory
space qualified. Even at that very early stage of development, Washington, DC USA
this technology was viable and robust and could be configured
into practical electronic components. WILLIAMJ . MEYERS,G uest Editor
Starting in 1992, the second phase of the HTSSE program Allied Signal Technical Services Corporation
focused on the demonstration of advanced microwave devices Columbia, MD USA
and subsystems. These were either complex HTS components,
such as multiplexers, or subsystems with HTS devices inte-
grated with semiconductor devices operating either at the same
cryogenic temperature as the HTS components, or, possibly,
at spacecraft ambient temperatures. HTSSE demonstrated that
Alphabetical listing of referees used for IEEE
a low-cost, reliable cryogenic space test bed for state-of-the-
TRANSACTIONOSN MICROWAVTEH EORYA ND TECHNIQUES
art HTS components and subsystems can be built and space
Special Issue on HTSSE, vol. 44, no. 7, July 1996.
qualified and integrated onto a satellite. HTSSE also showed
that state-of-the art cryogenic refrigeration systems can be
integrated into space systems either to cool a major portion of Alfred0 Anderson Raafat R. Mansour
the spacecraft or for localized cooling of an individual device Steven Anlag George Matthaei
or subsystem. Stuart Berkowitz Steven Mettleman
During the evolution of the HTSSE-I1 phase, the HTS com- Kul Bhasin Dave Miller
munity remained focused on microwave applications. Concur- R. R. Bonetti Felix A. Miranda
rently, commercial activity started which is attempting to insert John H. Claassen Carl Mueller
HTS microwave technology into wireless communications Linda D’Evelyn Harvey Newman
base stations. This activity was started after the viability and Dale J. Durand Daniel E. Oates
robustness of HTS microwave devices had been demonstrated M. Feng Terry P. Orlando
in the HTSSE-I phase. This commercial interest is a spin off Neal Fenzi Paul A. Polakos
as much of the technology developed for the HTSSE program S. Jerry Fiedziuszko Jeffrey M. Pond
can be transitioned. As both applications of HTS microwave Michael Fitelson Kurt Raihn
technology mature, one will benefit from the successes of the Frank Gao Richard Ralston
other. Greg Hay-Shipton Stephen Remillard
In the original formulation of the HTSSE program, there Dallas T. Hayes Robert Romanofsky
was a third phase, usually designated HTSSE-111, which was Jeffrey S. Herd Paul Ryan
to have been the development and space qualification of a J. D. Hodge R. P. Salazar
complete space communications or remote sensing system Charles Jackson Zhi-Yuan Shen
whose performance would have been significantly enhanced H. H. S. Javadi T. C. L. Gerhard Sollner
by the use of HTS technology. Although HTSSE-I and I1 were A. M. Kadin S. H. Talisa
successful in demonstrating the enhanced performance and Gerhard Koepf Ted VanDuzer
robustness of HTS microwave components and subsystems, Clifford M. Krowne Denis C. Webb
before starting a program to develop an entire spacecraft Cheung-Wei Lam R. W. Weinert
system based on superconductivity, NRL and several other Guo-Chun Liang Charles Wilker
government laboratories have undertaken detailed trade-off R. Lithgow Richard Withers
studies to quantify and document the advantages that would W. Gregory Lyons Robert M. Yandrofski
NISENOFF AND MEYERS: MTT SPECIAL ISSUE GUEST EDITORIAL 1197
Martin Nisenoff (M’88) received the B.S. degree in physics from the Worcester Polytechnic
Institute, Worcester, MA, and the M.S. and Ph.D. degrees in physics from Purdue University,
Lafayette, IN.
From 1962 to 1970 he was a Research Physicist at the Ford Scientific Laboratory, Ford
Motor Co., IDearborn, MI, where he carried out research on spin wave resonance in thin
ferromagnetic: films and in the preparation of superconducting thin film Josephson devices,
primarily as low-frequency SQUID magnetometers. From 1970 to 1972, he was a Research
Scientist at the Stanford Research Institute (now SRI International, Menlo Park, CA) where
he studied rt:fractory metal low temperature superconducting device fabrication and device
physics. In 1‘972, he moved to the Naval Research Laboratory (NRL), Washington, DC, where,
as the Head of the Applied Superconducting Section, he directed research activities in refractory
low temperature superconducting thin films and refractory thin film devices, and was involved
in a number of programs to assess the impact of superconducting devices on operational
communication and remote sensing systems. After the discovery of high temperature superconductivity in 1987, he became a
Consultant, Microwave Technology Branch of the Electronics Science and Technology Division at NRL,. In this capacity, he had
reviewed, monitored, or was Scientific Officer on a number of research and development programs in HTS electronic device
technology funded by the Navy, Air Force, Advanced Research Projects Agency (ARPA) and the Ballistic Missile Defense
Organization. His interests have been on the high frequency properties of high temperature superconducting films and thin film,
high frequency devices, the insertion of high temperature devices into military remote sensing and communications systems,
and in the development of low-cost, high reliability cryogenic refrigeration systems. He was also responsible for the acquisition
of a wide variety of high temperature superconducting microwave devices for the NRL high temperature superconductivity
space experiment (HTSSE) which demonstrated the viability and robustness of HTS devices in a space environment.
Dr. Nisenoff is a member of the American Physical Society. He is a member of the Board of Directors of the Applied
Superconductivity Conference, a member of the Organizing Committee of the International Cryocooler Conference, and a
member of the Advisory Board of the journal Cryogenics. In MTT, he is Chairman of Technical Committee 18-Superconducting
Technology, and a member of the Technical Program Committee of the M’IT-S Symposium.
William J. Meyers (M’95) received the B.S. degree in physics from the University of Notre
Dame, Notre Dame, IN, in 1967 and the M.S. degree in experimental nuclear physics from
Florida State University, Tallahassee, FL, in 1968.
From 1969 until 11990 he was on active duty with the U.S. Navy as a Cryptologic Officer.
After completing Officer Candidate School, he was initially assigned as a Research Physicist to
the Materials, Research Branch, National Security Agency, and conducted R&D in high density,
electron beam addressable, memory storage devices using vanadium oxide thin films and
scanning electron microscope. Subsequent assignments over the next 12 years involved shore-
based operational field sites and at-sea duties involving radio wave propagation studies, signal
processing, ,geolocaf.ion, specific emitter identification techniques, and cryptologic support
operations at tactical, theater, and national command levels. In 1984, he was assigned as
Officer-in-Charge of the Navy’s Sugar Grove, WV facility which supported R&D in various
__
space programs, cryptologic exploitation techniques, and geolocation algorithm development.
From 1987 to 1990 he was assigned to Space and Naval Warfare Systems Command Space Technology Office, located at the
Naval Research Laboratory (NRL) in Washington, IDC, and served as Technical Division Director, responsible for all R&D
initiated by that office. Areas of R&D included: MICMMIC devices, vacuum microelectronics, signal analysis and processing
techniques, advanced power systems, high efficiency solar cells, high temperature superconductivity, and space cryogenic
systems. He was the Sponsor’s Program Manager for the high temperature superconductivity space experiment (HTSSE). In
1990, after retirement from active duty at the rank of Commander, he joined AlliedSignal Technical Services Corp. (ATSC)
as a Senior Scientist. His current activities ilnvolve supporting NRL’s Advanced Systems Technology Branch, Naval Center
for Space Technology, concerning evaluation and use of advanced technologies and their applicability to space systems. In
addition to serving as ATSC’s Project Manager for HTSSE, he is involved in other technology developments including: maritime
remote sensing, MMIC subsystems for modular payloads, focal plane array electronics, positioning and tracking via GPS, single
emitter identification, signal analysis, and e.rploitation techniques.
Mr. Meyers is a member of the American Physical Society (AF’S), American Institute of Aeronautics and Astronautics
(AIAA), Armed Forces Communications anid Electronics Association (AFCEA), and Institute of Electrical and Electronics
Engineers (IEEE). He has been Guest Lecturer at Florida State University, Michigan Technological University, Air Force
Institute of Technology, and the U.S. Naval Academy on the topics of HTSSE and development of advanced technologies
for space systems.
1198 IEEE TRANSACTIONS ON MICROWAVE THEORY AND TECHNIQUES, VOL. 44, NO. I,J ULY 1996
The High Temperature Superconductivity
Space Experiment (HTSSE-11) Design
Thomas G. Kawecki, Gerald A. Golba, George E. Price, Vincent S. Rose, and William J. Meyers, Member, ZEEE
(Invited Paper)
Abstruct- The high temperature superconductivity space ex- of the host spacecraft. Details concerning specific devices are
periment (HTSSE) program, initiated by the Naval Research in other articles in this special issue.
Laboratory (NRL) in 1988, is described. The HTSSE program
Selection of each device for development was based pri-
focuses high temperature superconductor (HTS) technology ap-
marily on DOD system requirements and the potential for
plications on space systems. The program phases, goals, and
objectives are discussed. The devices developed for the HTSSE- the device to provide improved performance or power or
I1 phase of the program and their suppliers are enumerated. weight savings. The channelizers, multiplexers, filters, re-
Eight space-qualified components were integrated as a cryogenic ceivers, downconverter, and antenna array all relate to com-
experimental payload on DOD’s ARGOS spacecraft. The payload
munications functions. The cueing receiver, analog-to-digital
was designed and built using a unique NRLIindustry partnership
(AD)co nverter, digital instantaneous frequency measurement
and was integrated and space-qualified at NRL.
system (DIFM), digital multiplexer, and delay lines have
signal processing applications. Whether or not a specific
device became part of the HTSSE-I1 payload involved several
I. INTRODUCTION additional factors. The size, geometry, and cooling capacity
T
HE high temperature superconductivity space experiment of the cryogenic bus for the devices dictated that only seven
(HTSSE) program, initiated by the Naval Research Labo- could be accommodated. The Loral multiplexer and NASA
ratory (NRL) in 1988, focused applications for HTS materials Lewis/JPL downconverter, although both were fully functional
on satellite electronic components. The program was con- and space qualified, were not manifested due to these con-
ducted in successive phases. Descriptions of the initial phase straints. The location of the HTSSE-I1 payload on the host
(HTSSE-I) are contained in [1]-[l l]. This article describes in spacecraft precluded the Wuppertal HTS antenna from having
detail the second phase (HTSSE-11). a usable field of view, thus eliminating it from consideration.
Development of the TRW 60 GHz communications receiver
was terminated because millimeter wave HTS phased array
11. HTSSE-11 PHASE AND DEVICESD EVELOPED components, especially the phase shifter, proved to be beyond
The HTSSE-I1 mission objective is to demonstrate the the state-of-the-art at that time. Furthermore, HTS digital
functionality of advanced HTS devices and subsystems as technology, on which the Conductus A/D and the TRW digital
well as advanced cryocoolers in space. In early 1991, NRL MUX were based, had not matured sufficiently to build the
solicited proposals via public announcements and a broad circuits originally proposed. The Conductus A/D program was
agency announcement (BAA). Thirteen HTS device proposals redirected to terrestrial applications while the TRW digital
were selected and resulted in the eventual delivery of ten MUX was drastically simplified, consistent with the maturity
space qualified experiments, eight of which are on HTSSE- of HTS digital technology at the time of the delivery to NRL
I1 (see Table I). These experimental devices had to pass space for HTSSE-I1 integration.
qualification tests. Determination of long term effects on these Each of the devices to be flown on HTSSE-11 had to undergo
devices and the cryogenic subsystem that supports them is a very stringent space qualification testing (see [ 121). Several
specific objective for HTSSE-11. Their performance will be issues had to be addressed concerning the packaging of each
measured in detail during the one- to three-year mission life device. Techniques for bonding lead wires to HTS thin films,
precisely mounting patterned HTS thin films inside machined
cavities, and integrating conventional electronics with HTS on
Manuscript received February 15, 1996; revised March 11, 1996. This work
the same substrate were developed. These techniques had to
was supported in part by the Advanced Development Office, Space Tech-
nology Program, Space and Naval Warfare Systems Command (SPAWAR), survive the rigors of space qualification testing which include
NASA, ARPA, BMDO, the Canadian and German governments, and the Air three axis vibration, acoustic vibration, and thermal cycling.
Force Space Technology Program Office.
When something failed during testing, the device would be
T. G. Kawecki, G. A. Golba, and G. E. Price are with the Naval Research
Laboratory, Washington, DC 20375-5320 USA. returned to the vendor for redesign or rework. This was
V. S. Rose is with V. S. Rose Consultants, Bowie, MD 20720 USA. initially done using what is called the “qualification” unit
W. J. Meyers is with Allied Signal Technical Services Carp., Columbia.
to validate the design. Once this unit had passed all space
MD 21045 USA.
Publisher Item Identifier S 00 18-9480(96)048 10-7. qualification testing, the “flight” unit was built using the same
0018-9480/96S05.00 0 I996 IEEE
KAWECKI et al.: THE HIGH TEMPERATURE SUPERCONDUCTIVITY SPACE EXPERIMENT (HTSSE-11) DESIGN I199
TABLE I
HTSSE-I1 DFVICESS ELECTEFDO R DEVELOPMENT
2 hannelizers/Filters
mental Effects Monitor on TC,J c, Rs and h,
design as the qualification unit. The flight unit was !subjected and becomes an integral structural component of the host.
to “acceptance” level testing, a lower level than qualification There are standard power, command, and control and data bus
tests, (for example, the “acceptance” level for vibration was 3 interfaces with ARGOS. Electronic boxes are mounted on both
dB lower than for “qualification”) which verified workmanship sides of this deck. HTS experiments and supporting cryogenic
of the device before the device was installed on the flight subsystems are located on the exterior side to take advantage
cryogenic cold bus. of passive cooling available in a sun synchronous orbit. The
only component not mechanically mounted on this deck is the
antenna which is mounted on the nadir side of ARGOS in
111. HTSSE-11 PAYLOAD AND HOST SPACECRAFT order to receive ground transmitted signals used to test the
The HTSSE-I1 payload was manifested on the Air Force HTS devices. Fig. 1 is a drawing of the ARGOS spacecraft
Space Test Program Advanced Research and Global Ob- with HTSSE-I1 installed. The larger exploded view shows
servation Satellite (ARGOS) in March 1993. ARGOS is a the exterior HTSSE-11 deck with thermal blankets and some
three-axis stabilized, nadir-pointing satellite weighing 2500 kg structure removed for clarity. As with all space applications,
with total power of 1 K. It is the host to eight experiments strict limits were placed by the host ARGOS spacecraft on
with launch scheduled on a Delta 2 rocket in Spring 1997. mass, volume and power allocations. The HTSSE-I1 payload
ARGOS will operate in a 450-nautical-mile circular orbit at a design stayed well within these allocations with the power
sun synchronous inclination. ARGOS will remain in orbit for constraint being the most demanding.
a long time; however, data on HTSSE-I1 may only be taken
for one to three years.
IV. HTSSE-I1 PAYLOADS YSTEMSD ESIGN
HTSSE-I1 is located on the zenith deck of ARGOS with
volume available on both the interior and exterior sides. The HTSSE-I1 has three principal goals which drove the systems
principal structural component of HTSSE-I1 is a 1.02 m by design: 1) fly the maximum number of HTS experiments; 2)
1.27 m honeycomb deck which bolts onto the ARGOS frame develop and demonstrate a cryogenic subsystem which would
1200 IEEE TRANSACTIONS ON MICROWAVE THEORY AND TECHNIQUES, VOL. 44, NO. 7, JULY 1996
radiation, and internal electrical (ohmic) losses. There is no
Cold Bus Structure +Z Radiator
convection in the vacuum of space. Conduction loss comes
from heat flow along the physical structure which supports
_-,Ca_vity &/ +Y Radiators the cryogenic cold bus and from input-output (I/O) cables that
connect the electronics and instrumentation on the cold bus to
ITRW Experiment
warm ambient temperature electronics. Conduction loss is pro-
portional to the temperature difference between the cryogenic
bus and the warm environment and a thermal conductance
which is material and form factor dependent. Radiation loss
comes from thermal radiation absorbed by the cryogenic cold
bus from the structure which surrounds it. Radiative heat
transfer is proportional to the difference between the fourth
powers of the temperatures of the radiator and absorber,
and the area and optical properties of the surfaces involved.
Because of the strong temperature dependence of radiative heat
loads, a small decrease in the warmer environment surrounding
the cryogenic payload leads to a large decrease in thermal
load. The large number of VO cables going into the cold bus
was another major design consideration. Internal ohmic heat
generation was not a large thermal load for HTSSE-11. The
superconducting components on the cold bus dissipated no
heat. Any heat load due to conventional electronic devices in
the cold package was small due to low duty cycle during the
experiment.
Fig. 1. Drawing of ARGOS host spacecraft with detail of HTSSE-I1 payload
The thermal design of most spacecraft maintains 040°C
* internal temperatures to ensure the proper operation of the
provide a continuous 77°K 1" Kelvin (K) environment electronics and propulsion components. External spacecraft
to support a long life space application; and 3) demonstrate components such as solar arrays and radiators can vary from
one year operation on orbit (three years desired). To achieve -100 to +lOO"C depending on the optical coating, view to
these goals required extensive and complex systems design space, and external environmental heat fluxes (sun and earth).
trade-offs in numerous areas. Lessons learned in building the Large ambient to cryogenic temperature differences of 100 to
cryogenic cold bus for HTSSE-I contributed significantly to 200°C inherent with cryogenic space applications can result in
this decision process (see [4] and [6])T. o help understand these high heat fluxes. Thus low radiative and conductive losses are
issues, a brief discussion concerning the design of cryogenic required to provide efficient thermal designs. The HTSSE-I1
subsystems for spacecraft follows. design strategy used two approaches to minimize the cryogenic
Cryogenic temperatures are difficult to achieve and maintain cooling load on the cold bus. First, the ambient temperature
over a long time on a spacecraft. Spacecraft electronics and of the spacecraft area surrounding the cryogenic payload was
propellants need to be kept warm which typically requires a reduced as much as possible; second, materials were used
040°C spacecraft bus temperature. Controlling temperatures which limited conductive and radiative thermal parasitics into
to this range is handled very adequately in conventional the cryogenic bus. The heat load on the HTSSE-I1 cryogenic
satellite designs, but creates a stressing environment for cryo- component had to be at the absolute minimum because of the
genic subsystems. There are many approaches to achieve limitations on the cooling method selected.
cryogenic temperatures, e&, stored cryogen, passive radiative If HTSSE-I1 is indicative of future HTS device payloads,
cooling, and mechanical cryocooler. One must also consider future cryogenic HTS commercial payloads are likely to
how to connect the components to be cooled to the cooling have significant volumes and numerous input/output (I/O)
source. One approach is to colocate all components on a thermal parasitics. Additionally, commercial space payloads
single cooler (cold bus cooling). A second approach has each typically require lifetimes of at least five years, preferably
component with its own individual cooler (local cooling). Yet ten years. Based on HTSSE-I and HTSSE-I1 experience,
another approach is to have a common cooler and distribute a cryogenic cooling capacities on the order of 300-1000 mW
cryogenic fluid to each component requiring cooling. Each has (or greater) in the 60-80 K temperature range are likely to
its pros and cons which impact on system design and mission be the norm for electronic payloads. Cryogenic thermal loads
life. There are other limitations placed on any cryogenic of this magnitude over long time periods preclude the use
subsystem design because of the inherently limited power, of solid cryogens for primary cooling due to the high mass
weight, and volume available on a spacecraft as well as cost and volume that would be required. Cryogenic radiators are
factors. Reference [I31 addresses several of these issues. undesirable for large thermal load payloads in this temperature
The cryogenic subsystem was the principal driver for the range because they greatly constrain orbit options and have a
design of the HTSSE-I1 payload. There are three sources of large impact on the overall spacecraft design. Long life, high
heat affecting any space-based cryogenic package: conduction, reliability mechanical refrigerators ("cryocoolers") appear to
