CEC Abstracts in PDF format (as of 7/3/07) - CEC-ICMC 2013

CEC 2007 - Abstracts
C1-N-09 Understanding dynamic behavior of a large scale
cryogenic plant
R. Maekawa, K. Ooba, T. Mito, National Institute for
Fusion Science; M. Nobutoki, Taiyo Nippon Sanso Co.
Development of Cryogenic Process REal-time SimulaTor (C-PREST)
has been finalized to provide a platform to study refrigeration process
simulation for the entire cryogenic system for the Large Helical
Device (LHD). To understand dynamic behavior of the LHD
cryogenic plant, the simulations have been carried out during the
cooldown operation. Although LHD has three different cooling
schemes, a pool boiling, a forced-flow supercritical helium cooling
and a two-phase flow cooling, C-PREST simulates comparable results
of LHD cooldown process. To validate the versatility of C-PREST,
the heat pulse(s) were applied to the 20000 liters liquid helium
reservoir of a helium refrigerator/liquefier. This paper describes
operations of large cryogenic plant and discusses dynamic behavior of
helium refrigerator/liquefier under various heat pulse inputs.
Tuesday, 07/17/07 Oral
3:00pm - 5:00pm
C1-O Stirling and Pulse Tube Capabilities
Overview (Aerospace)
C1-O-01 Heritage Overview: 20 Years of Commercial
Cryocooler Production for Space
A.S. Gibson, J.S. Reed, EADS Astrium Limited.
Space cryocooler production (formerly BAe and MMS) has spanned
more than 2 decades. Industrialisation has taken the cryocooler from
the laboratory to a proven space product. Over this period, Astrium
have manufactured more than 50 Stirling coolers, 15 of which have
flown. An historical review with lessons learned is presented.
Following transfer of the heritage design via Rutherford Appleton
Laboratory (RAL), manufacturing began at Astrium on the first 80K
Stirling coolers in 1986, with production of 2 development models (1
for ESA) and an EM unit. Following successes of Oxford/RAL
coolers on ISAMS, ATSR-1 and ATSR-2, Astrium built standard 80K
units for IMG-ADEOS(1996) and HTSSE-II(1997). 23 coolers of this
type were built in 4 batches. A higher heat lift version (1991) led to
the standard 50-80K product. These continue to fly in pairs on
MOPITT(1999), MIPAS(2002), AATSR(2002), INTEGRAL(2002)
and a military satellite (2004), with a single unit on ODIN(2001).
Another pair is to be launched in 2007.
Industrialisation of a 2-stage RAL Stirling cooler design began in
1990 (ESA funded), to provide cooling from 20-50K. An EM was
produced, followed by 3 QM units. In 2000, an improved 10K design
(collaboration with RAL) was built for the US-Air Force Research
Laboratory yielded a record temperature of 9.4K. Notably,
development of this design has recently been re-initiated (ESA
funding).
Astrium would like to acknowledge funding from ESA for
industrialisation of cryocoolers.
C1-O-02 An Overview of the Performance and Maturity
of Long Life Cryocoolers for Space Applications
D.G. Curran, S.W. Yuan, The Aerospace Corporation.
A 2007 survey is made of long life cryocoolers involving Stirling,
Pulse Tube, reverse Brayton, and Hybrid variants for space
applications. A number of unit configuration types involving single
and multi-temperature stages is included. The performance range
varies from milliwatts of cooling at 4K to 10`s of watts at 150K. The
objectives for this survey are to provide a hardware summary of
available units from several U.S. manufacturers including the heritage
and maturity level suitable for space use in payloads and instruments.
Listed in the summary are life test and flight hours, environmental test
levels, size, and electronics controller capabilities as well as load
curves and specific power as a function of temperature.
C1-O-03 Endurance Evaluation of Long-Life Space
Cryocoolers at AFRL- An Update
J. Sutliff, W. Scheirer, E. Pettyjohn, T. Roberts,
AFRL/VSSS.
The Air Force Research Lab (AFRL) in conjunction with various
defense contractors has developed several long-life cryocooler
designs. These cooler include the NGST HEC, the Raytheon PSC, the
Ball 6020, and the Ball 35-60K. They represent different technologies
including pulse tube and Stirling cycle. The coolers operating times
range from the NGST HEC which has been running 28,000 hours to
the TRW 6020 which has been operating for more that 69,000 hours.
Endurance evaluation attempts to describe the long-life potential of
these machines with a complete demonstration of these machines
being 5-10 years of constant operational life in an environment
designed to simulate the conditions of space. The testing hopes to
show any wear out, fatigue, or electronic malfunction so that
cryocoolers will continue to improve their long-life potential.
Endurance testing also quantifies the performance degradation over
time to help determine needs of future satellites. Data presented
indicates that certain degradation patterns exist in these cryogenic
refrigerators which will pose a challenge for their long term use in
multi-year missions.
C1-O-04 Air Liquide Space Pulse Tube Cryocoolers
T. Trollier, J. Tanchon, J. Buquet, A. Ravex, P.
Crespi, Air Liquide Advanced Technology Division,
AL/DTA, Sassenage, France.
Thanks to important development efforts completed and partial ESA
funding, AL/DTA is now in position to propose two Pulse Tube
cooler systems in the 40-80K temperature range for coming Earth
Observation missions such as MTG, Sentinel 3, etc… The two pulse
tube coolers thermo-mechanical units are yet qualified against
environmental constraints.
In addition to these two Pulse Tube cooler systems, a 20-50K multistage
low temperature Pulse Tube cooler is currently under
development for future Scientist Missions such as Xeus, Darwin, etc..
The paper presents the current status of each of the three thermomechanical
units and associated cooler drive electronics.
C1-O-05 High Performance Pulse Tube Cryocoolers
J.R. Olson, P. Champagne, E. Roth, B. Evtimov, T.C.
Nast, Lockheed Martin ATC.
Lockheed Martin’s Advanced Technology Center (LM-ATC) has
been developing pulse tube cryocoolers for more than ten years.
Recent innovations include successful testing of four-stage coldheads,
no-load temperatures below 4 K, and the recent development of a
high-efficiency compressor.
This paper discusses the predicted performance of single and multiple
stage pulse tube coldheads driven by our new 5 kg “M5Midi”
compressor, which is capable of 90% efficiency with 200W input
power, and a maximum input power of 1000W. This compressor
retains the simplicity of earlier LM-ATC compressors: it has a
moving magnet and an external electrical coil, minimizing organics in
the working gas and requiring no electrical penetrations through the
pressure wall. Motor losses were minimized during design, resulting
in a simple, easily-manufactured compressor with state-of-the-art
motor efficiency.
The predicted cryocooler performance is presented as simple
formulae, allowing an engineer to include the impact of a highlyoptimized
cryocooler into a full system analysis. Performance is
given as a function of the heat rejection temperature and the cold tip
temperature and cooling load. A discussion of the optimum number
of coldhead stages will be given. We will also discuss a novel
configuration where the compressor operates with no heat rejection,
allowing very flimsy attachment to the satellite so as to minimize
exported vibration.
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