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    <title>Transport Research International Documentation (TRID)</title>
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    <copyright>Copyright © 2026. National Academy of Sciences. All rights reserved.</copyright>
    <docs>http://blogs.law.harvard.edu/tech/rss</docs>
    <managingEditor>tris-trb@nas.edu (Bill McLeod)</managingEditor>
    <webMaster>tris-trb@nas.edu (Bill McLeod)</webMaster>
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      <title>Transport Research International Documentation (TRID)</title>
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      <title>Electromagnetic Field Analysis and Design of a Single-Phase
     Full-Bridge Power Converter for Electric Vehicle Range Extender</title>
      <link>https://trid.trb.org/View/2083645</link>
      <description><![CDATA[This paper takes the single-phase full-bridge power converter of the power                     generation system of the free-piston engine of the incremental electric vehicle                     (EV) as the research object. By establishing the three-dimensional (3D)                     electromagnetic radiation simulation model of the power converter, the                     electromagnetic radiation field of the power converter is simulated and analyzed                     by using the equivalent excitation source method. The shielding and suppression                     effect of the power converter shell on the far-field radiated electromagnetic                     field and its influence on the internal electromagnetic field are analyzed. The                     shielding cover of the radiation source and sensitive source of the power                     converter is designed, and the effectiveness of the electromagnetic radiation                     shielding device for shielding the radiation source and sensitive source is                     discussed. The simulation results show that the shell of the power converter can                     effectively shield the far-field radiation so that the external radiation field                     intensity is reduced below the standard value. The designed shielding device of                     the radiation source and the sensitive source can effectively reduce the                     radiation intensity at the position of the sensitive chip in the near-field area                     and satisfy the working conditions of the device.]]></description>
      <pubDate>Wed, 14 Dec 2022 11:17:12 GMT</pubDate>
      <guid>https://trid.trb.org/View/2083645</guid>
    </item>
    <item>
      <title>Study on the Influence of the Magnetic Field and the Induced Electrical Field in Human Bodies by EV/PHEV Wireless Charging Systems</title>
      <link>https://trid.trb.org/View/1834758</link>
      <description><![CDATA[Wireless charging systems for electric vehicles (EVs) and plug-in hybrid electric vehicles (PHEVs) employing the resonant magnetic coupling method and using induction coils have been intensively studied in recent years. Since this method requires kW class high power to be transmitted using resonant magnetic coupling in the high frequency range, it is necessary to pay attention to the leakage of the magnetic field generated by the coil current, and to its influence on surrounding objects, particularly human bodies. Noting that acceptable values for human body exposure to electromagnetic fields have previously been issued by the International Commission on Non-Ionizing Radiation Protection (ICNIRP) as guidelines, we have developed a method for predicting product compliance with those guidelines at the basic design development stage. This method calculates the magnetic field generated by the induction coil current and predicts the value of the electric field induced in the human body. Once we calculate the surrounding magnetic field of the vehicle, this method makes it possible to evaluate induced electric field values when a human body is present in various locations. Using this method, we analyzed the magnetic field distribution and electric field of a 3.7 kW charging system operating at a resonant frequency of 85 kHz while taking into consideration induction coil positions under, at the rear, at the center, and in front of the vehicle. The results show that the induced electric field in the human body is much smaller than the basic restrictions imposed by the ICNIRP guidelines.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:38:33 GMT</pubDate>
      <guid>https://trid.trb.org/View/1834758</guid>
    </item>
    <item>
      <title>Temperature Estimation of Turbocharger Working Fluids and Walls under Different Engine Loads and Heat Transfer Conditions</title>
      <link>https://trid.trb.org/View/1828892</link>
      <description><![CDATA[Turbocharger performance maps, which are used in engine simulations, are usually measured on a gas-stand where the temperatures distributions on the turbocharger walls are entirely different from that under real engine operation. This should be taken into account in the simulation of a turbocharged engine. Dissimilar wall temperatures of turbochargers give different air temperature after the compressor and different exhaust gas temperature after the turbine at a same load point. The efficiencies are consequently affected. This can lead to deviations between the simulated and measured outlet temperatures of the turbocharger turbine and compressor. This deviation is larger during a transient load step because the temperatures of turbocharger walls change slowly due to the thermal inertia. Therefore, it is important to predict the temperatures of turbocharger walls and the outlet temperatures of the turbocharger working fluids in a turbocharged engine simulation.         In the work described in this paper, a water-oil-cooled turbocharger was extensively instrumented with several thermocouples on reachable walls. The turbocharger was installed on a 2-liter gasoline engine that was run under different loads and different heat transfer conditions on the turbocharger by using insulators, an extra cooling fan, radiation shields and water-cooling settings. The turbine inlet temperature varied between 550 and 850 °C at different engine loads.         The results of this study show that the temperatures of turbocharger walls are predictable from the experiment. They are dependent on the load point and the heat transfer condition of the turbocharger. The heat transfer condition of an onengine turbocharger could be defined by the turbine inlet temperature, ambient temperature, oil heat flux, water heat flux and the velocity of the air around the turbocharger. Thus, defining the heat transfer condition and rotational speed of the turbocharger provides temperatures predictions of the turbocharger walls and the working fluids. This prediction enables increased precision in engine simulation for future work in transient operation.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:36:54 GMT</pubDate>
      <guid>https://trid.trb.org/View/1828892</guid>
    </item>
    <item>
      <title>Expandable Habitat Technology Demonstration for Lunar and Antarctic Applications</title>
      <link>https://trid.trb.org/View/1816265</link>
      <description><![CDATA[NASA's vision for Space Exploration includes a long term human presence on the surface of the moon and missions to Mars. In support of these missions, habitation structures will be developed to support operations in these challenging gravitational environments and maximize safety and comfort to the crew. One class of structures that is under study is expandable structures because of their mass and stowed volume efficiency. These structures follow the natural paradigm of exploration that has been observed for centuries. An expandable technology demonstration unit has been constructed and is being tested in the lunar analog environment of Antarctica, over several years. The habitat has yielded test data regarding transport and deployment, sensor integration, reconfigurability, habitability, performance in harsh environments, radiation shielding and dust mitigation. Data from these tests is being used by NASA to support lunar architecture studies. Performance data from this work is also being studied by the National Science Foundation (NSF) Office of Polar Programs (OPP) to determine if this class of structures can improve mission efficiency in polar exploration.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:33:20 GMT</pubDate>
      <guid>https://trid.trb.org/View/1816265</guid>
    </item>
    <item>
      <title>Lunar Concrete Radiation Shielding Production for Primary Lunar Base</title>
      <link>https://trid.trb.org/View/1813179</link>
      <description><![CDATA[This research analyzes potential methods to construct concrete radiation shielding for primary lunar habitats by In-Situ Resource Utilization (ISRU) before crew arrival on the Moon, considering the following key factors:              The concrete shielding production process and necessary facilities are shown in this paper. Moreover, mass and power budgets are estimated based on assumptions from today's research status.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:32:55 GMT</pubDate>
      <guid>https://trid.trb.org/View/1813179</guid>
    </item>
    <item>
      <title>Thermal Testing of the Herschel EPLM STM</title>
      <link>https://trid.trb.org/View/1813134</link>
      <description><![CDATA[The Herschel Extended Payload Module (H-EPLM) consists of the cryostat, the telescope, and the sunshield and solar generator. Within the cryostat, a 2367 l superfluid helium tank and its gas, evaporating via a passive phase separator, provide the required heat sinks at four staggered temperature levels from 1.7 to 15 K to the focal plane units of three scientific instruments. The helium gas is then used to cool three thermal radiation shields inside the cryostat vacuum vessel before being vented to space. In the frame of the EPLM qualification program, cryogenic / thermal tests were performed on EPLM Structural / Thermal Model (STM) level at ambient conditions and in the Large Space Simulator (LSS) facility in Noordwijk, NL. Mass and thermal dummies were integrated in the STM instead of the respective flight parts for the instruments’ focal plane and local oscillator units, the telescope and the sunshield / solar generator. This paper presents the test setup, measured data and evaluation results.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:32:53 GMT</pubDate>
      <guid>https://trid.trb.org/View/1813134</guid>
    </item>
    <item>
      <title>MarsCruiserOne</title>
      <link>https://trid.trb.org/View/1813100</link>
      <description><![CDATA[Based on a study of a Mobile Pressurized Laboratory (MPL) concept made during the European Mars Mission Architecture Study conducted for ESA, further design development of the laboratory and interior functional layout of the rover has been performed. This includes volume optimization, wheel system and geometry, interior layout and functional zoning, airlock placement and ergonomics, radiation protection, ergonomic detailing of habitation functions like sleep, kitchen, hygiene, ergonomics of work environment for driver, glove box, laboratory and storage systems and spatial flexibility and adaptability. The large wheel concept proposed in the ESA study to maximize habitable volume is further investigated. Additionally, omni-directional wheels have been introduced to the design to improve the vehicle's manoeuvrability. The inclusion of new design features led to a decision to rename the concept, MarsCruiserOne (MCO). The paper describes the design of the MCO.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:32:52 GMT</pubDate>
      <guid>https://trid.trb.org/View/1813100</guid>
    </item>
    <item>
      <title>Improvement of Risk Assessment from Space Radiation Exposure for Future Space Exploration Missions</title>
      <link>https://trid.trb.org/View/1813068</link>
      <description><![CDATA[Protecting astronauts from space radiation exposure is an important challenge for mission design and operations for future exploration-class and long-duration missions. Crew members are exposed to sporadic solar particle events (SPEs) as well as to the continuous galactic cosmic radiation (GCR). If sufficient protection is not provided the radiation risk to crew members from SPEs could be significant. To improve exposure risk estimates and radiation protection from SPEs, detailed evaluations of radiation shielding properties are required. A model using a modern CAD tool ProE™, which is the leading engineering design platform at NASA, has been developed for this purpose. For the calculation of radiation exposure at a specific site, the cosine distribution was implemented to replicate the omnidirectional characteristic of the 4π particle flux on a surface. Previously, estimates of doses from SPEs to the blood forming organs (BFO) were made using an average body-shielding distribution for the bone marrow based on the computerized anatomical man (CAM) model. The development of an 82-point body-shielding distribution at BFOs made it possible to estimate the mean and variance of SPE doses in the major active marrow regions. Use of the detailed distribution of bone marrow sites and implementation of the cosine distribution of particle flux is shown to provide improved estimates of acute and cancer risks from SPEs.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:32:52 GMT</pubDate>
      <guid>https://trid.trb.org/View/1813068</guid>
    </item>
    <item>
      <title>Structural and Radiation Shielding Properties of Non-parasitic, Multi-functional Microporous Carbon for Aerospace Applications</title>
      <link>https://trid.trb.org/View/1813032</link>
      <description><![CDATA[AFR, Inc. is developing a multifunctional Carbon material that, in addition to excellent radiation shielding characteristics, is appropriate for certain energy storage applications. As an excellent Hydrogen gas sorbent, it increases the usable storage capacity of a gas cylinder by ∼25% at 3500 PSI and by ∼150% at 500 PSI. Our ongoing NASA Langley funded study shows that when a sorbent-filled tank is charged with hydrogen, it provides shielding superior to polyethylene against most types of ionizing particles. Even as hydrogen is consumed, the carbon and tank ensure that significant radiation shielding capability is maintained. In addition to storing hydrogen, the carbon material also displays considerable strength. In this paper, we explore some of its mechanical properties that show this material is very versatile and highly multifunctional.         Vastly improved radiation shielding is a clear requirement for a potential manned mission to Mars or a long-duration base on the surface of the Moon. However, current shielding technologies are predicated upon systems dedicated solely to the task of shielding. Such single-use material adds substantially to the mass, and therefore expense, of space operations, without otherwise helping to accomplish mission objectives.         One approach to remedy these conflicting constraints is to modify other ship (or EVA suit) systems to maximize their radiation shielding properties, while still serving their primary purposes. Our carbon sorbent material takes this approach. Its performance in this key energy system application is excellent and the carbon itself is a better radiation shield against GCR's and SEP's than the excess Aluminum it can replace. As we explore its mechanical properties, additional functional roles such as micrometeorite protection or some structural applications may emerge.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:32:50 GMT</pubDate>
      <guid>https://trid.trb.org/View/1813032</guid>
    </item>
    <item>
      <title>MicroDosimeter iNstrument (MIDN) on MidSTAR-I</title>
      <link>https://trid.trb.org/View/1808853</link>
      <description><![CDATA[The goal of this project is to develop and test in space a solid-state microdosimeter to directly assess astronaut risk to an unknown mixed radiation field. The instrument is rugged, has low power (< 1.25W), has low mass, and utilizes low voltages (± 5V). A microdosimeter can determine in real time dose equivalent in sieverts which is the regulatory quantity used to evaluate risk and limits of radiation exposure. The lineal energy spectrum that it measures can be multiplied by lineal-energy-dependent regulatory quality factors to determine dose equivalent. An early version of the instrument (MIDN on MidSTAR-I) has been designed and built for inclusion in the MidSTAR-1 USNA student built satellite to be launched in late fall 2006. The instrument is now undergoing test and minor modifications. The DoD Space Experiment Review Board (SERB) has also identified the MIDN instrument as a candidate for inclusion on the International Space Station as an express rack payload for radiation shielding studies.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:26:48 GMT</pubDate>
      <guid>https://trid.trb.org/View/1808853</guid>
    </item>
    <item>
      <title>Passive Radiation Shielding Investigations in Low Earth Orbit and in an Accelerator</title>
      <link>https://trid.trb.org/View/1808717</link>
      <description><![CDATA[Crews of future exploration missions will be exposed for long time to a unique powerful mix of cosmic radiation. Starting from REMSIM study for ESA, we are focusing on short and long term shielding experiments aboard ISS (ESCHILO, ALTCRISS, SOFOCLE) by comparing the materials used in inflatable structures with the typical rigid materials used in current spacecraft, and optimizing and validating the radiation shielding solutions in LEO. To assess shielding strategies, tests in flight are always supported by calculations and laboratory experiments. The paper reports descriptions and available results of the above experiments.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:26:47 GMT</pubDate>
      <guid>https://trid.trb.org/View/1808717</guid>
    </item>
    <item>
      <title>Standardized Radiation Shield Design Method: 2005 HZETRN</title>
      <link>https://trid.trb.org/View/1808716</link>
      <description><![CDATA[Research committed by the Langley Research Center through 1995 resulting in the HZETRN code provides the current basis for shield design methods according to NASA STD-3000 (2005). With this new prominence, the database, basic numerical procedures, and algorithms are being re-examined with new methods of verification and validation being implemented to capture a well defined algorithm for engineering design processes to be used in this early development phase of the Bush initiative. This process provides the methodology to transform the 1995 HZETRN research code into the 2005 HZETRN engineering code to be available for these early design processes. In this paper, we will review the basic derivations including new corrections to the codes to insure improved numerical stability and provide benchmarks for code verification.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:26:47 GMT</pubDate>
      <guid>https://trid.trb.org/View/1808716</guid>
    </item>
    <item>
      <title>Radiation Shielding and Mechanical Strength Evaluations of Non-parasitic, Multi-functional Microporous Carbon for Aerospace Applications</title>
      <link>https://trid.trb.org/View/1808697</link>
      <description><![CDATA[AFR, Inc. is developing a multifunctional Carbon material that, in addition to excellent radiation shielding characteristics, is appropriate for certain energy storage applications. As an excellent Hydrogen gas sorbent, it increases the usable storage capacity of a gas cylinder by ∼25% at 3500 PSI and by ∼150% at 500 PSI. Our ongoing NASA Langley funded study shows that when a sorbent-filled tank is charged with hydrogen, it provides shielding superior to polyethylene against most types of ionizing particles. Even as hydrogen is consumed, the carbon and tank ensure that significant radiation shielding capability is maintained.         Vastly improved radiation shielding is a clear requirement for a potential manned mission to Mars or a long-duration base on the surface of the Moon. However, current shielding technologies are predicated upon systems dedicated solely to the task of shielding. Such single-use material adds substantially to the mass, and therefore expense, of space operations, without otherwise helping to accomplish mission objectives.         One approach to remedy these conflicting constraints is to modify other ship (or EVA suit) systems to maximize their radiation shielding properties, while still serving their primary purposes. Our carbon sorbent material takes this approach. Its performance in this key energy system application is excellent and the carbon itself is a better radiation shield against GCR's and SEP's than the excess Aluminum it can replace.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:26:47 GMT</pubDate>
      <guid>https://trid.trb.org/View/1808697</guid>
    </item>
    <item>
      <title>Thermal Conductivity Testing of Radiation Shielding Materials for Use as Thermal Insulation</title>
      <link>https://trid.trb.org/View/1808663</link>
      <description><![CDATA[The Vision for Space Exploration (VSE) requires vehicles and crew systems designs that include space radiation shielding and protection. Astronauts venturing beyond low Earth orbit (LEO) outside the protection of the Earth's geomagnetic field will be exposed to a much harsher radiation environment due to the potential for solar particle events (SPE). Additionally, long duration missions will subject the crew to higher doses of galactic cosmic rays (GCR). The incorporation of radiation shielding technology into sub-system elements will be crucial to the success of future vehicle designs. One area where radiation shielding may be incorporated is the thermal insulation. As with current crew systems, thermal protection will be a key element in the design. Incorporating radiation shielding into thermal protection systems may be possible by using polymer spheres in place of traditional multi-layer insulation (MLI). By using spheres manufactured from hydrogen rich polymers, which are known to provide a level of shielding against SPE and GCR, the complexity of a system can b e reduced. Using a packed bed of spheres as insulation also allows for the possibility to operate in a w ea k vacuum such as that found on Mars. Under a Phase 1 SBIR contract with the Marshall Space Flight Center (MSFC), a thin heater test apparatus was developed and various polymer sphere samples were tested in both high vacuum and low pressure gas for determination of effective thermal conductivity. The results show that there is potential in the use of polymer spheres as an insulation system.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:26:47 GMT</pubDate>
      <guid>https://trid.trb.org/View/1808663</guid>
    </item>
    <item>
      <title>Alternative Physical and System Architectures for Membrane Based Advanced Regenerative Space Life Support System Water Processing</title>
      <link>https://trid.trb.org/View/1808653</link>
      <description><![CDATA[This study introduces new concepts in the function and placement of membrane based water treatment processes in Exploration Life Support (ELS) System design. These differences are in both form and function and have the potential to radically alter the current paradigms of thought within the ELS research community with regards to the limitations of conventional membrane water treatment. More importantly, they have the potential to change the placement of water processing by quite literally moving it “out of the box”, or in the case of ELS, the standard rack volume. Two possible systems, extremely small scale personal urine treatment and recycle (CEV Lightweight Contingency Water Treatment) and a similar but scaled up habitat wall embedded membrane water treatment pouch, are used to demonstrate the concepts involved.         This work presents current membrane technology as an engineered material that can utilize a number of different treatment system architectures to achieve quite different treatment outcomes, when compared to traditional pressure fed membrane element based systems. Also, in treating membranes as an engineered material in integrative habitat and water processing design, other issues can be addressed by the water processor. Of particular interest is integrating water processing into radiation shielding (water wall) and flexible structural (zero pressurized volume mass metric) design. This makes the concepts covered of particular relevance to the radiation shielding designer and space architect, as well as the physical water treatment designer.]]></description>
      <pubDate>Thu, 09 Dec 2021 10:26:46 GMT</pubDate>
      <guid>https://trid.trb.org/View/1808653</guid>
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