bluuebunny/crossref_metadata_2025_split huggingface dataset:
Improving Body Weight, Serum Albumin and Total Protein of Undernourished Rat Model after Milks-Based and Fish-Soy-Based RUTF Intervention
Authors: Fadly K , Rimbawan R , Damayanthi E , Giriwono P E 
Published: July 2024

Abstract
Ready-to-use therapeutic food (RUTF) has been formulated to address severe acute malnourished (SAM) in children under five years old, but its efficacy in undernourished rat models should be assessed before human trials can be conducted. This research examined how RUTF with milk-based and fish-soy-based impacted body weight, serum albumin level, and total protein level in undernourished rats. Using a factorial randomized group design, 31 male Wistar rats were split into three intervention groups: control (standard diet), low protein (5%), and low protein energy (30%) diet restriction. After 21 days of inducing malnutrition, each group received randomly assigned milk-based or fish-soy-based RUTF. The findings revealed that both groups’ body weight, serum albumin, and total protein had significantly improved to normal ranges. Statistical analysis did not show significant differences between the two groups in terms of body weight (p = 0.904), serum albumin (p=0.645), and serum total protein (p=0.504). This study suggests that producing RUTF from local resources such as soybean and fish in Indonesia could improve the nutritional status of undernourished animal models, which can be further studied in human subjects.
Nutritional Profile of Locally Produced Ready-to-Use Therapeutic Food (RUTF) for Severe Acute Malnourished Children in Indonesia
Authors: Rimbawan R , Nasution Z , Griwono P E , Tamimi K , Fadly K 
Published: July 2024

Abstract
Ready-to-use therapeutic food (RUTF) is a lipid-based product used to treat severe acute malnutrition (SAM) in children under five years old without clinical complications. In Indonesia, new RUTF formulas have been created using local protein sources, resulting in milk-based, legumes-based, fish-based, and soy-fish-based RUTFs. Among these, milk-based RUTF was the most preferred and was enhanced with a vitamin and mineral premix to meet WHO, UNICEF, and FAO standards. The nutrient content, including proximate composition, vitamins, minerals, amino acids, and fatty acids, was assessed using standardized methods. Safety was evaluated for mycotoxins, microorganisms, and heavy metals. The results indicated that the nutritional content met RUTF guidelines, with no heavy metal contamination and acceptable levels of mycotoxins and microorganisms. This study suggests that producing safe RUTF from local resources with high nutritional value is feasible and likely to be well-received by the local population, offering sustainable prospects.
Development of a 35 K single-stage coaxial pulse tube cryocooler
Authors: Wang Nailiang , Zhao Miguang , Lei Yilin , Liang Jingtao 
Published: July 2024

Abstract
A high-efficiency, single-stage coaxial pulse tube cryocooler has been developed for the purpose of operating at approximately 35 K, specifically targeting long-wavelength infrared detectors. The present study outlines the design considerations and discusses the optimizations made to the length of the regenerator. By conducting experimental investigations, the prototype of the cooler has successfully achieved a no-load temperature of 24 K. This was accomplished by incorporating an inertance tube and reservoir as the phase-shifter. By incorporating the double-inlet into the phase-shifter, it is possible to attain a lower temperature of 21 K. At present, the current cooler prototype demonstrates a cooling capacity of 2 W at 35 K with an input power of 200 W at a frequency of 37 Hz. Additionally, a comprehensive presentation of the key parameters and performance of the designed PTC is provided.
Using mylar-insulated cryopumping panels to improve vacuum level during warm temperature testing at JSC’s large thermal vacuum facilities
Authors: Gasior B , Owen J , Cui K , Song H , Homan J 
Published: July 2024

Abstract
Johnson Space Center’s Space Environment Simulation Lab (SESL) has both Chamber A, the world’s largest purpose-built thermal vacuum chamber capable of creating deep space conditions, and Chamber B, the largest human rated thermal vacuum chamber. A unique design feature of these chambers is the gaseous helium cryopumping panels within the liquid nitrogen shroud. This shroud is used to bring the chamber to cryogenic temperatures while the cryopumping panels trap gasses on its surface area to create a high vacuum environment of 5*10−6 Torr. In preparation for the James Webb Space Telescope (JWST) flight test, a series of functionals required the chamber to run at higher temperatures, and therefore did not need active cooling from the liquid nitrogen shroud. During testing, cryopumping panels were used to mitigate contamination during this main shroud warm-up. One of the cryopumping panels in Chamber A was covered with several layers of aluminized mylar to thermally protect the zone from the warmed shroud. This strategy was effective and became part of operations during JWST testing. Currently, Chamber B has requests for both commercial and NASA space suit tests at both high and low temperatures to validate thermal models. High temperature tests could benefit from reduced heater demand with an insulated shroud while still sustaining the high vacuum environment provided by the cryopumping panels. This paper will quantitatively define the thermal loads on the panels used in previous Chamber A warm up sequences. Additionally, this report will perform thermal analyses to assess the feasibility of adding layers of aluminized mylar to the cryopumping panels of Chamber B.
The simulation and experiments of a high frequency single stage pulse tube cryocooler with two cooled thermal sinks
Authors: Gao Min , Li Geyang , Feng Tianshi , Yang Bin , Quan Jia , Chen Houlei , Cai Jinghui , Zheng Maowen 
Published: July 2024

Abstract
In the application of infrared detectors, pulse tube cryocoolers are required to provide cooling power at different temperature ranges simultaneously with light weight and compact construction. In this paper, a single stage pulse tube cryocooler was designed to provide cooling power at different temperature ranges with an extra cooled thermal sink placed in the middle of the regenerator. The axial distribution of volume flow and pressure wave of cryocooler with middle heat exchanger and without middle heat exchanger were compared theoretically. To verify the simulation results, a series of experiments were carried out. As a result, the cooling power of cryocoolers with middle heat exchanger was decreased at 80 K, and 0.5 W @ 88.5 K & 0.5 W @ 195.8 K of cooling power was obtained simultaneously at 45 W input power.
Development of a cryogenic stepping motor using high-purity copper wire
Authors: Iida Teruhito , Matsumura Tomotake , Sakurai Yuki , Ghigna Tommaso , Hasebe Takashi , Hoang Thuong Duc , Katayama Nobuhiko , Takaku Ryota , Nakagawa Jun 
Published: July 2024

Abstract
We developed a stepping motor working in a cryogenic environment with minimal heat dissipation from it. While a cryogenic motor is commercially available, a user must prepare a cryogenic environment that can tolerate a large heat dump during the operation. We modified a commercial stepping motor (TAMAGAWA SEIKI CO., LTD) for room temperature usage. The components of the motor were replaced from a conventional electromagnetic wire to 6N high-purity copper and from aluminium chassis to a glass-fibre resign epoxy chassis. The former reduces the Joule heat, and the latter reduces the eddy current. In addition, the bearings have been replaced with ones with a dry lubricant. An iron yoke, a stack of iron core plates, is already introduced in the commercial motor to reduce an eddy current loss, and this was kept from the commercial design. The preliminary experiment was conducted at the temperature of 15 K using a GM cryocooler to estimate the heat dissipation on the motor. The results show that the electrical resistance of the high-purity copper wire at 15 K is 1950 times lower than at room temperature. We measured the total heat dissipation of the motor with the high-purity copper coils and compared it to the conventional one. The measured heat dissipation was reduced by about 40% when the motor rotation speed was 2.25 rpm. The Joule loss of the motor with a high-purity copper wire was about 20 times smaller than the conventional motor due to the reduction of the wire resistance. We also identified that the remaining heat dissipation is dominated by the component proportional to the rotational frequency, i.e., hysteresis or static friction from the bearing. This development was motivated by using a cryogenic stepping motor in a cryogenics space mission with limited active and passive cooling power.
Cooling method for the rotor of a superconducting motor
Authors: Caughley A J , Allpress N , Lumsden G , Rogers Rehn N , Gschwendtner M , Jeong S 
Published: July 2024

Abstract
Electrification has been proposed as a route to decarbonizing air travel. Conventional electric motors are too heavy to achieve the power densities required for aviation so superconducting motors for aircraft are being developed. Superconductors however, work at cryogenic temperatures, which indispensably require a reliable and efficient cooling mechanism with a cryocooler. The Robinson Research Institute is developing a 3 MW superconducting motor using an HTS (High Temperature Superconductor) rotor operating at 50 K and MgB2 running at near 20 K for the stator. The motor is intended to run at a shaft speed of 4500-6000 rpm to directly drive a ducted fan. A key challenge is the removal of heat from a cryogenic spinning rotor to a stationary refrigerator so it can be rejected at ambient temperatures. Previous motors have utilized externally pumped or thermos-syphoned cryogens to cool the rotor, which require complex rotary seals. The aircraft application demands a compact and low weight solution. This paper presents a novel cooling design where a stationary cryocooler’s cold heat exchanger penetrates the rotor, and the relative motion of the two creates a pumping motion for cold helium gas to transfer heat from the rotor to the cryocooler. The sealing is low pressure and at ambient temperature and pressure with a temperature gradient in the helium adjacent to the cryocooler regenerator. Design and CFD modelling of the concept are presented showing the system can generate sufficient cold helium flow to transfer heat from the rotor to the cryocooler with a small temperature difference, resulting in a compact, efficient, and low-weight rotor cooling method.
Thermal Modeling of CryoFILL liquefaction tests
Authors: Kashani A , Yamashita K , Grotenrath R , Hauser D , Balasubramaniam R , Johnson W 
Published: July 2024

Abstract
Proposed NASA missions to Moon and Mars involve producing cryogenic propellant in-situ to reduce launch mass and requirements. One technique for liquefaction of the gases produced through electrochemical processes is to circulate cold gaseous neon or helium through broad area cooling tubes attached to the outside of the propellant tanks. To determine the performance of this liquefaction process tests were conducted at NASA Glenn Research Center in a 2.1 cubic meter tank with a broad area cooling network (CryoFILL). A thermal/fluid model of the tank and its cooling loop is developed in Thermal Desktop. Details of the model and the model predictions and comparison to some of the experimental data from the CryoFILL liquefaction tests are presented here.
Conceptual cryostat design for cryogenic payload suspension studies for the Einstein Telescope
Authors: Koroveshi X , Rapagnani P , Mangano V , Stamm M , Grohmann S 
Published: July 2024

Abstract
The Einstein Telescope (ET) is a third generation gravitational wave detector, combining a low-frequency (LF) and a high-frequency (HF) laser interferometer. Cryogenic operation of ET-LF in the temperature range of 10 K to 20 K is essential to suppress the suspension thermal noise, which dominates the detection sensitivity at frequencies below 10 Hz. This requires suspension materials with high thermal conductivity and low mechanical dissipation at cryogenic temperatures. Two possible suspension concepts are currently considered, using either monocrystalline suspension fibers made of silicon or sapphire, or titanium suspension tubes filled with static He-II. The dissipative behavior of these suspensions is characterized by the mechanical Q-factor. It can be measured by the ring-down method, exciting the suspensions to resonance vibrations on the nanometer scale and analyzing the decay time. For this purpose, a new cryogenic test facility is being planned, allowing the investigation of cryogenic payload suspensions for third-generation gravitational wave detectors. The test cryostat is equipped with a cryocooler and enables real-size studies with various suspension materials and geometries. The future integration of He-II is foreseen to enable He-II filled suspension studies. We describe the scope of experiments and the conceptual design of the test cryostat.
Low-noise thermal shielding around the cryogenic payloads in the Einstein Telescope
Authors: Busch L , Iaquaniello G , Rosier P , Stamm M , Grohmann S 
Published: July 2024

Abstract
The Einstein Telescope (ET) is a planned third-generation gravitational-wave detector that includes a low-frequency (LF) and a high-frequency (HF) laser interferometer. Cryogenic operation of ET-LF is imperative for exploiting the full scientific potential of ET, with mirrors operated at temperatures of 10 K to 20 K in order to reduce the thermal noise. Thermal shielding around the optics is essential to support the cooldown process and to decrease the heat load. Additionally in steady-state operation, mechanical vibrations must be kept to an absolute minimum in order to limit noise contributions from scattered light.
We present a cooling concept for a thermal shield surrounding the cryogenic optics of ET-LF, which considers rapid cooldown and low vibration in steady-state operation. During cooldown, cooling tubes enable the flow of supercritical helium, driving the shield temperature decrease by forced convection. For steady-state operation, the shield cooling mechanism is converted to static heat conduction in He-II within the same tubes. A first mechanical model is presented that fulfills the thermal and vibrational requirements. Thermal characteristics of the shield are demonstrated by means of analytical and numerical modeling results. Modal and dynamic analyses are performed to obtain natural frequencies and transfer functions.
SPHEREx payload thermal architecture and analysis
Authors: Moore B , Bolton D , Penanen K , Susca S 
Published: July 2024

Abstract
The SPHEREx (Spectro-Photometer for the History of the Universe, Epoch of Reionization, and Ices Explorer) is an all-sky spectral survey in a Sun-synchronous low earth orbit. It measures spectrum in the near infrared band from 0.75 µm to 5 µm. To achieve this wavelength coverage, the instrument has two focal plane arrays, both passively cooled at <55 K (mid-wave infrared) and <80 K (short-wave infrared). Additionally, the instrument requires no moving parts for spectral resolution, relying instead on spacecraft-controlled pointing. A thermally isolating structure and a set of V-groove radiators reduce the heat flow conducted and radiated from the spacecraft bus. The thermal system also blocks the incident solar flux and earth radiation from reaching the sensitive cryogenic instrument while still allowing substantial pointing flexibility. The combination of passive cryogenic cooling and survey requirements in a sun exposed low earth orbit environment presents a challenge for the thermal design. This paper will discuss the SPHEREx payload overall thermal architecture, bounding thermal environments, the component thermal design, and analysis of on-flight performance.
Development of switchless thin-plate sorption compressor and miniaturized check valves for 5 K J- T cooler
Authors: Bae Junhyuk , Kim Bokeum , Jeong Sangkwon 
Published: July 2024

Abstract
The cell of the sorption compressor developed in this paper has a thin-plate shape to accelerate the pressure swing by reducing the heating and cooling periods. Its width, height and thickness are 100 mm, 100 mm and 4.6 mm, respectively. Two identical cells filled with 22.8 g of charcoal mass are operated alternately to generate and maintain significant pressure difference for the 5 K J-T cooler with the pre-cooling temperature of 15 K. The designed nominal pressure of the high-pressure and the low-pressure parts of the J-T cooler are 1000 kPa and 196 kPa, respectively. The mass flow rate and the pressure gradient of the thin-plate sorption compressor with commercial check valves are measured experimentally. As the performance of the compressor, COP of the compressor is estimated and compared with the compressor of previous researches. Furthermore, to reduce leakage rate and thermal inertia of check valves in the compressor, miniaturized check valve is specially designed and fabricated to replace the commercial valve. When the flow direction is reversed in the valve, the leakage is passively prevented by contacting two metal surfaces at low temperature (30 K). The essential parts of the valve are critically miniaturized to reduce the overall thermal inertia of the compressor system. The cracking pressure and the leakage rate of the developed check valve and the commercial check valve are measured to compare.
Effects of working fluid on performance of 4.5 K JT cooler
Authors: Chen W , Moore B , Petach M ,   The
Published: July 2024

Abstract
NASA is considering a “probe” class mission with a far-infrared imaging and spectroscopy space telescope. A critical technology need for this mission is an efficient, high capacity, low-temperature cryocooler with low exported vibrations to enable its cryogenic instruments to achieve exquisite sensitivity and low internal noise to observe far distant faint cosmic sources. This paper discusses the design of a 4.5 K hybrid cooler consisting of a pulse tube precooler and a JT stage. The JT stage uses 3He as its working fluid to achieve a low cooling temperature of 4.5 K. The cooler will build on the JWST MIRI spare flight cooler, using existing TRL 9 component and subsystem hardware technologies. The paper will discuss the cooler configuration, thermodynamic design, predicted performance, and sensitivity to operating conditions. The impact of pressure drops and thermal ineffectiveness in the JT stage recuperators are discussed and compared to those in the MIRI cooler. Finally, test results for MIRI Development Model (DM) compressor with 4He are presented. Test data include compressor volumetric flow rates and power inputs at different pressure ratios and piston stroke lengths. The DM compressor test results and flight compressor test data collected during MIRI spare flight cooler acceptance testing both indicate that the 4.5 K cooler will be able to meet the cooling requirement of 48 mW at 4.5 K and 230 mW at 18 K with a significant margin.
Performance of a single-stage mixed refrigerant miniature Joule Thomson cryocooler operating at 90-100 K for space applications
Authors: Murthy V V S , Padmanabhan P , Venkatarthnam G 
Published: July 2024

Abstract
The performance of a closed-cycle miniature Joule Thomson (J-T) cryocooler operating with zeotropic mixtures is presented in this work. The system can provide refrigeration between 90-100 K and meet a heat load of 1 to 3 W. A miniature variable-speed rotary piston compressor is used in the present version. A coiled tubes-in-tube heat exchanger with an effectiveness greater than 95% is used. The details of the system and its performance are presented in this paper.
Further experimental work in mixed gas Joule-Thomson cryocooling
Authors: Detlor J , Pfotenhauer J , Nellis G 
Published: July 2024

Abstract
Miniature Joule-Thomson (JT) cryocoolers are attractive for many applications due to their small size and resulting fast cool-down time. Finned-tube heat exchangers are one of the most widely used heat exchanger for miniature JT cryocoolers. The basic configuration, known as a Giauque-Hampson (GH) or coiled tube heat exchanger, involves the high-pressure stream flowing through a finned-tube that is helically coiled upon a cylindrical core while the low-pressure return stream flows over the fins in the annular space created by the core and the inner diameter of a shell. The experimental work in this study aimed to gain insight into thermal characteristics of the shell-side of a GH heat exchanger by developing a test facility capable of measuring the two-phase heat transfer coefficient (htc) for this flow at operating conditions of interest to mixed-gas JT (MGJT) cryocooling. The capabilities of the test facility were demonstrated and measurements of the two-phase htc of the mixed gas on the shell-side of the GH heat exchanger prototype revealed that the shell side is the dominant thermal resistance for these operating conditions, even though the fins provide a larger surface area.
Characterization testing of the Air Liquide large pulse tube cryocooler (LPTC)
Authors: McKinley I M , Hummel C D , Johnson D L , Rodriguez J I 
Published: July 2024

Abstract
An Air Liquide large pulse tube cryocooler (LPTC) was parametrically performance tested for cold tip temperatures between 30 K and 200 K and heat rejection temperatures between 0°C and 40°C. The testing utilized a single off-the-shelf power supply to drive the compressor motors in parallel. The effect of compressor temperature and pulse tube inclination angle are also presented. In addition, the exported forces were measured at ambient conditions and the results are shown and discussed.
Characterization testing of the Thales LPT9310-HP cryocooler
Authors: McKinley I M , Hummel C D , Mueller B W , Johnson D L , Rodriguez J I 
Published: July 2024

Abstract
Two Thales LPT9310-HP commercial off-the-shelf (COTS) cryocoolers were parametrically performance tested for cold tip temperatures between 50 K and 250 K and heat rejection temperatures between 0°C and 40°C. Both coolers had identical transfer line configurations. The test results revealed small unit-to-unit thermodynamic performance variation. They are compared to test results of a COTS LPT9310 cooler with the same transfer line configuration. The effect of compressor temperature and pulse tube inclination angle are also discussed. In addition, the off-state heat leak as a function of inclination angle is presented. Finally, the feasibility of using a single LPT9310-HP COTS cooler in a two-stage configuration is discussed.