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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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All sourcesNASA NTRSDOE OSTI
NASA NTRS2017

Evolution of Fundamental Technologies for Future Electrified Aircraft

Gradual progression of electric and hybrid electric aircraft from small planes to large planes will require technology advances in multiple areas, which include energy storage, electrical machines, power transmission, power electronics, control systems, materials, thermal management, and multi-scale modeling tools. Advances in both fundamental research and applied interdisciplinary research will be required to realize the goals for future electric and hybrid electric aircraft. The presentation will provide an overview of long-range research and technology needs for the next thirty years and how evolution of several early stage technologies will influence the development of electrified aircraft in the future.

Germany↗
NASA NTRS2018

Insights into Space Solar Cell Durability Using SPICE Simulation Seeded by Current-Voltage Characteristics Parametrized Using the Lambert W Special Function

We developed and validated an automated routine for the fitting of I-V curve data to the single diode model according to an exact analytical solution. Our fitting routine was validated to show good noise immunity and high accuracy usingsimulated values from LTSPICE. We are thus able to automate parameter extraction from a dataset or arbitrary size. This parameterization allows for better simulation of performance of real cells and arrays and provides utility for a host of applications relevant to space arrays. We will use this methodology to determine the array performance of radiated cells over time, and simulate the performance of the arrays with bypass diodes and power electronics.

Solar Cell↗
NASA NTRS2019

Electrified Aircraft Propulsion Systems: Potential Failure Modes and Failure Mitigation Strategies

Electrified aircraft propulsion (EAP) systems hold great potential for the reduction of aircraft fuel burn, emissions, and noise. Currently, NASA and other organizations are actively working to identify and mature technologies necessary to bring EAP designs to reality. A requirement for the development of any civil aircraft and its systems is to ensure that potential hazards in the design are identified and appropriately mitigated to ensure that the system is safe. During aircraft development, a system safety assessment that consists of a functional hazard assessment is conducted to identify all potential failure conditions of each function, and classify those failures according to the severity of their effects on the aircraft or its occupants. The more severe a function's failure condition classification, the greater the development assurance level required for the function to ensure that the probability of the hazard is acceptably low. Today, aircraft engines and their control systems receive type certificate approval as a stand-alone system to signify their airworthiness. However, the complex coupling and distributed nature of EAP designs are expected to place added challenges on the certification of these systems. This presentation will provide an initial high-level review of the potential failure modes and hazards posed by a generic EAP system along with potential mitigation strategies for those failures. The EAP system is assumed to be a hybrid design consisting of gas turbine engines, mechanical drives, electric machines, power electronics and distribution systems, energy storage devices, and motor driven propulsors. The functionality provided by each of these EAP subsystems will be discussed along with the potential failure modes they may encounter. This will include a discussion of coupled failure effects, where a fault in one EAP subsystem effects the operation of other subsystems in the architecture. Next, potential failure mitigation strategies are discussed including both software-based and hardware-based mitigation strategies. The presentation will conclude with an example evaluation of the potential failure modes and mitigation strategies for a concept EAP system proposed by NASA.

Simon, Donald L.↗
NASA NTRS2019

Long-Duration Venus Lander Development

One of the most intriguing planets in our solar system for both solar system and extra-solar system science is Venus. Venus is the planet most similar to Earth in several key ways and many believe Venus-like planets are more common around other suns than are Earth-like planets. Therefore scientific understanding of our sister planet is a high priority. However, the hostile environmental conditions at the surface coupled with thick acid clouds and dense atmosphere have made understanding this planet very challenging. Remote sensing of surface features and near surface environments is very limited. The hostile environment has also limited the ability of landers to survive, in fact the longest living asset survived just over two hours. Even after over 50 years of attempts to explore Venus, many key measurements, especially near the surface, are still in the future. NASA has begun to undertake steps to overcome the technical challenges and is developing the capability for sustained operations and science return from this important body. For example, recent technology advances in high temperature sensors, electronics, power, and other systems have been funded and this, combined with the new capabilities to replicate Venus conditions on Earth, are changing the outlook for Venus surface exploration.

Kremic, Tibor↗
NASA NTRSDate not supplied

Electrified Aircraft Propulsion Systems: Gas Turbine Control Considerations for the Mitigation of Potential Failure Modes and Hazards

This paper provides a high-level review of the potential failure modes and hazards to which electrified aircraft propulsion (EAP) systems are susceptible, along with potential gas turbine control-based strategies to assist in the mitigation of those failures. To introduce the types of failures that an EAP system may experience, a generic EAP system is considered, consisting of gas turbine engines, mechanical drives, electric machines, power electronics and distribution systems, energy storage devices, and motor driven propulsors. The functionality provided by each of these EAP subsystems is discussed, along with their potential failure modes, and possible strategies for mitigating those failures. To further illustrate the role of gas turbine controls in mitigating EAP failure modes, an example based on a simulated EAP concept aircraft proposed by NASA is given. The effects of failures are discussed, along with turbomachinery control strategies, including reversionary control modes, and control limit logic.

Donald L Simon↗
NASA NTRSDate not supplied

Convergent Aeronautics Solutions (CAS) High Voltage Hybrid Electric Propulsion (HVHEP) Activity

Overview of Convergent Aeronautics Solutions (CAS) High Voltage Hybrid Electric Propulsion (HVHEP) activity. CAS HVHEP activity demonstrated feasibility of variable frequency, variable high voltage power system using doubly fed electric machines (DFM), and provided 90% reduction in power electronic weight for 35 megawatt system. DFM enables multi-phase (9) ac operation, with enhanced control and integrated protection methods for improved safety through minimization of fault energy.

CAS↗
NASA NTRS2021

Electrified Aircraft Propulsion Systems: Gas Turbine Control Considerations for the Mitigation of Potential Failure Modes and Hazards

This paper provides a high-level review of the potential failure modes and hazards to which electrified aircraft propulsion (EAP) systems are susceptible along with potential gas turbine control-based strategies to assist in the mitigation of those failures. To introduce the types of failures that an EAP system may experience, a generic EAP system is considered consisting of gas turbine engines, mechanical drives, electric machines, power electronics and distribution systems, energy storage devices, and motor driven propulsors. The functionality provided by each of these EAP subsystems is discussed along with their potential failure modes and possible strategies for mitigating those failures. To further illustrate the role of gas turbine controls in mitigating EAP failure modes, an example based on a simulated EAP concept aircraft proposed by NASA is given. The effects of failures are discussed, along with turbomachinery control strategies, including reversionary control modes, and control limit logic

Electrified Aircraft Propulsion↗
NASA NTRSDate not supplied

Development and Qualification Status of the Electric Propulsion Systems for the NASA PPE Mission and Gateway Program

NASA is charged with landing the first American woman and next American man on the South Pole of the Moon and establishing sustainable lunar exploration by the end of the decade. To meet this challenge, NASA’s Gateway will develop and deploy critical infrastructure required for operations on the lunar surface and that enables a sustained presence on and around the moon. NASA’s Power and Propulsion Element (PPE), the first planned element of NASA’s cis-lunar Gateway, leverages prior and ongoing NASA and U.S. industry investments in high-power, long-life solar electric propulsion technology investments. NASA awarded a PPE contract to Maxar Technologies to provide a 50 kW-class SEP spacecraft that meets Gateway’s needs, aligns with industry’s heritage spacecraft buses, and allows extensibility for NASA’s Mars exploration goals. Maxar’s PPE concept design, is based on their high heritage, modular, and highly reliable 1300-series bus architecture. The electric propulsion system features three 12 kW Advanced Electric Propulsion (AEPS) thrusters from Aerojet Rocketdyne and four BHT-6000 thrusters from Busek. Maxar-provided power electronics and xenon flow controllers from Moog are utilized in both the 12kW and 6kW electric propulsion strings on the spacecraft. The paper will present overviews of NASA’s Gateway and the PPE Project, status of the development and qualification activities for the two electric propulsion system, and the planned implementation of PPE electric propulsion system as keystone of NASA’s Gateway. The PPE spacecraft is currently heading into the Critical Design Review, with the qualification and flight electric propulsion hardware fabrication already initiated and significant progress being made toward planned qualifications in support of the planned PPE spacecraft co-manifest launch in 2024.

Electric Propulsion↗
NASA NTRSDate not supplied

Development and Qualification Status of the Electric Propulsion Systems for the NASA PPE Mission and Gateway Program

NASA is charged with landing the first American woman and next American man on the South Pole of the Moon and establishing sustainable lunar exploration by the end of the decade. To meet this challenge, NASA’s Gateway will develop and deploy critical infrastructure required for operations on the lunar surface and that enables a sustained presence on and around the moon. NASA’s Power and Propulsion Element (PPE), the first planned element of NASA’s cis-lunar Gateway, leverages prior and ongoing NASA and U.S. industry investments in high-power, long-life solar electric propulsion technology investments. NASA awarded a PPE contract to Maxar Technologies to provide a 50 kW-class SEP spacecraft that meets Gateway’s needs, aligns with industry’s heritage spacecraft buses, and allows extensibility for NASA’s Mars exploration goals. Maxar’s PPE concept design, is based on their high heritage, modular, and highly reliable 1300-series bus architecture. The electric propulsion system features three 12 kW Advanced Electric Propulsion (AEPS) thrusters from Aerojet Rocketdyne and four BHT-6000 thrusters from Busek. Maxar-provided power electronics and xenon flow controllers from Moog are utilized in both the 12kW and 6kW electric propulsion strings on the spacecraft. The paper will present overviews of NASA’s Gateway and the PPE Project, status of the development and qualification activities for the two electric propulsion system, and the planned implementation of PPE electric propulsion system as keystone of NASA’s Gateway. The PPE spacecraft is currently heading into the Critical Design Review, with the qualification and flight electric propulsion hardware fabrication already initiated and significant progress being made toward planned qualifications in support of the planned PPE spacecraft co-manifest launch in 2024.

Electric Propulsion↗
NASA NTRS2024

Space Rated High Voltage Plasma Generating Supply

The use of plasma for in-situ resource utilization (ISRU) applications (such as water treatment, acid production, plant seed activation, biofilm sanitization, or waste gasification) is an active area of research at the KSC Applied Chemistry Lab (ACL). The generation of plasma for experimentation has thus far been done with lab-rated power supplies which are unsuitable for space applications, and no suitable supply is readily available for purchase. This project tackled the development of a low TRL prototype 500 W power supply intended for generating plasma in space. The design was based on similar power electronic circuits used for electric propulsion systems and was adapted for use in ISRU applications. This technology will enable KSC’s plasma-based ISRU related technologies to be demonstrated in the space environment.

Nathaniel Cain↗
DOE OSTI2016

Systems Integration Fact Sheet

This fact sheet is an overview of the Systems Integration subprogram at the U.S. Department of Energy SunShot Initiative. The Systems Integration subprogram enables the widespread deployment of safe, reliable, and cost-effective solar energy technologies by addressing the associated technical and non-technical challenges. These include timely and cost-effective interconnection procedures, optimal system planning, accurate prediction of solar resources, monitoring and control of solar power, maintaining grid reliability and stability, and many more. To address the challenges associated with interconnecting and integrating hundreds of gigawatts of solar power onto the electricity grid, the Systems Integration program funds research, development, and demonstration projects in four broad, interrelated focus areas: grid performance and reliability, dispatchability, power electronics, and communications.

solar energy, systems integration, sunshot initiat↗
DOE OSTI2016

A Closer Look at a Stronger Titanium

An improved titanium alloy – stronger than any commercial titanium alloy currently on the market – gets its strength from the novel way atoms are arranged to form a special nanostructure. For the first time, researchers at Pacific Northwest National Laboratory have been able to see this alignment and then manipulate it to make it even stronger. Using powerful electron microscopes and a unique atom probe imaging approach at EMSL, the Environmental Molecular Sciences Laboratory, a DOE Office of Science User Facility located at PNNL, they were able to peer deep inside the alloy’s nanostructure to see what was happening.

36 MATERIALS SCIENCE↗
DOE OSTI2016

Progress & Frontiers in PV Performance

PowerPoint slides for a presentation given at Solar Power International 2016. Presentation includes System Advisor Model (SAM) introduction and battery modeling, bifacial PV modules and modeling, shade modeling and module level power electronics (MLPE), degradation rates, and PVWatts updates and validation.

14 SOLAR ENERGY↗
DOE OSTI2017

Alternative High-Performance Motors with Non-Rare Earth Materials, Final Publishable Report

Electric drive systems, which include electric machines and power electronics, are a key enabling technology for advanced vehicle propulsion systems that reduce the petroleum dependence of the transportation sector. To have significant effect, electric drive technologies must be economical in terms of cost, weight, and size while meeting performance and reliability expectations. The goal of the project is to develop traction motors that reduce or eliminate the use of rare-earth materials and meet the DoE specifications for such a traction motor. This is accomplished by evaluating and developing multiple motor topologies in conjunction with advanced materials. Eight non-permanent magnet motor topologies and two reduced or non-rare earth motor topologies are analyzed and compared using a common set of requirements. Five of the motors are built and tested to validate the analysis. This paper provides a detailed quantitative comparison of the different machine topologies that reduce or eliminate rare-earth materials. Conclusions are drawn from the analysis and test data to show the tradeoffs related to selecting each of the motor topologies with the hope of providing practicing engineers and researchers in the field enough guidelines for choosing the “optimum” machine topology that suits their applications and set of performance requirements. Four materials technologies were investigated for their ability to enable a reduced rare earth electric motor. Two of the technologies were soft magnetic materials, one was a non-rare-earth containing permanent magnet technology, and the last was an insulation material. These processing and performance of these materials were first demonstrated in small coupons. The coupon tests justified proceeding to larger scale processing for two of the materials technologies: 1) a dual-phase soft magnetic material for use in rotor laminates and 2) a high temperature insulation material for use as a slot liner in the stator. The dual phase soft magnetic material was produced at a scale sufficient to build and test a sub-scale motor prototype. The high temperature insulation material was first evaluated in a series of “statorettes” before being demonstrated in the stator of one of the full-scale motor prototypes. Testing of the dual phase material revealed issues with process variability in larger production volumes that are being addressed in a subsequent project. The performance of the high-temperature slot liner insulation was demonstrated during the operation of a full-scale prototype. Furthermore, the insulation material was shown to survive aging tests of 2000 hours and 280 °C and 800 hours at 300 °C. This program provides analysis and data to accelerate the introduction of hybrid electric vehicles into the U.S. road vehicle fleet and bring the added benefits of reduced fuel consumption and environmental impacts

33 ADVANCED PROPULSION SYSTEMS↗
DOE OSTI2018

UTEMPRA - Unitary Thermal Energy Management for Propulsion Range Augmentation

Key hurdles to achieving wide consumer acceptance of battery electric vehicles (BEVs) are weather-dependent drive range, higher cost, and limited battery life. These translate into a strong need to reduce a significant energy drain and resulting drive range loss due to auxiliary electrical loads the predominant of which is the cabin thermal management load. Studies have shown that thermal subsystem loads can reduce the drive range by as much as 45% under ambient temperatures below -10 degrees C. Often, cabin heating relies purely on positive temperature coefficient (PTC) resistive heating, contributing to a significant range loss. Reducing this range loss may improve consumer acceptance of BEVs. The authors present a unified thermal management system (UTEMPRA) that satisfies diverse thermal and design needs of the auxiliary loads in BEVs. Demonstrated on a 2015 Fiat 500e BEV, this system integrates a semi-hermetic refrigeration loop with a coolant network and serves three functions: (1) heating and/or cooling vehicle traction components (battery, power electronics, and motor), (2) heating and cooling of the cabin, and (3) waste energy harvesting and re-use. The modes of operation allow a heat pump and air conditioning system to function without reversing the refrigeration cycle to improve thermal efficiency. The refrigeration loop consists of an electric compressor, a thermal expansion valve, a coolant-cooled condenser, and a chiller, the latter two exchanging heat with hot and cold coolant streams that may be directed to various components of the thermal system. The coolant-based heat distribution is adaptable and saves significant amounts of refrigerant per vehicle. Also, a coolant-based system reduces refrigerant emissions by requiring fewer refrigerant pipe joints. The authors present bench-level test data and simulation analysis and describe a preliminary control scheme for this system.

33 ADVANCED PROPULSION SYSTEMS↗
DOE OSTI2019

Solar Research Spotlight: Systems Integration

This Solar Energy Technologies Office fact sheet provides an overview of the systems integration subprogram, which funds research and development projects in five broad, interrelated focus areas: planning and operation, solar plus X, power electronics, sensing and communication, and codes and standards.

Solar Energy Technologies Office fact sheet, syste↗
DOE OSTI2017

Cost, Supply Chain, and Manufacturing Competitiveness Issues Related to SiC-Based Variable Frequency Drives for Industrial Motor Applications

A significant fraction of industrial energy use is attributable to motor-driven systems. The use of silicon carbide (SiC) in industrial motor drives can improve efficiency and, in certain applications footprint, balance-of-system cost, and other performance metrics compared to systems using traditional silicon (Si) devices. However, adoption of these drives is currently low. Barriers to adoption include the conservative nature of the market, a lack of public sources quantifying the value proposition of technology, and supply chain issues. We present a regional bottom-up cost analysis of SiC-based power modules and variable frequency drives, as well as an analysis of the global supply chain and current status of manufacturing. These results highlight possible opportunities and challenges for potential adopters of this technology, manufacturers currently in the SiC power electronics space or looking to expand into it, and policymakers seeking to understand how to increase the adoption of these energy-efficient systems or influence where they are manufactured.

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATI↗