Browse Topic: Rocket engines

Items (538)

A Mid-Infrared Laser Absorption Sensor for Gas Temperature and Carbon Monoxide Mole Fraction Measurements at 15 kHz in Engine-Out Gasoline Vehicle Exhaust

03-17-01-000201/16/2024

Quantifying exhaust gas composition and temperature in vehicles with internal combustion engines (ICEs) is crucial to understanding and reducing emissions during transient engine operation. This is particularly important before the catalytic converter system lights off (i.e., during cold start). Most commercially available gas analyzers and temperature sensors are far too slow to measure these quantities on the timescale of individual cylinder-firing events, thus faster sensors are needed. A two-color mid-infrared (MIR) laser absorption spectroscopy (LAS) sensor for gas temperature and carbon monoxide (CO) mole fraction was developed and applied to address this technology gap. Two quantum cascade lasers (QCLs) were fiber coupled into one single-mode fiber to facilitate optical access in the test vehicle exhaust. The QCLs were time-multiplexed in order to scan across two CO absorption transitions near 2013 and 2060 cm–1 at 15 kHz. This enabled in situ measurements of temperature and CO

Airlines Electronic Engineering Committee

Letter from the Guest Editors

01-15-02-000809/24/2022

Letter from the Guest Editors

Rajpathak, Dnyanesh, Roboff, Mark, Yu, Huafeng, Biswas, Gautam

Water-Powered Engines Offer Satellite Mobility

TBMG-3835201/01/2021

Spinoff is NASA’s annual publication featuring successfully commercialized NASA technology. This commercialization has contributed to the development of products and services in the fields of health and medicine, consumer goods, transportation, public safety, computer technology, and environmental resources.

Laser Wire Additive Manufacturing System

TBMG-3789110/01/2020

ADDere Additive Manufacturing Waukesha, WI 414-327-0000

Rocket Engine Technology

TBMG-3760909/01/2020

Invocon, Inc. Conroe, TX 281-292-9903

Facility Focus: NASA John C. Stennis Space Center

TBMG-3763509/01/2020

In 1961, when President John F. Kennedy issued his challenge for the United States to send humans to the Moon and back by the end of that decade, a site was needed to test the powerful rocket engines and stages that would propel them on the historic journey. For NASA officials, the rough terrain of Hancock County, Mississippi provided five essentials for testing the large Apollo Program engines and stages: isolation from large population centers, water and road access for transportation, available public utilities, supporting local communities, and a climate conducive to year-round testing.

Machine Learning Enables Rapid Rocket Engine Design

TBMG-3720607/01/2020

Time, cost, and safety prohibit testing the stability of a test rocket using a physical build “trial and error” approach. But even computational simulations are extremely time-consuming. A single analysis of an entire SpaceX Merlin rocket engine, for example, could take weeks or even months for a supercomputer to provide satisfactory predictions.

SMART Solar Sail

TBMG-3720507/01/2020

The SMART (Super Miniaturized Autonomous Reconfigurable Technology) Solar Sail is a deployable, fully autonomous solar sail for use in very fine station-keeping of a spacecraft. The solar sail would be highly deformable from an initially highly compressed configuration, yet also capable of enabling very fine maneuvering of the spacecraft by means of small sail-surface deformations.

Battle Command System

TBMG-3710106/01/2020

Northrop Grumman Corp. Falls Church, VA 703-280-2900

Large Eddy Simulations of Supercritical and Transcritical Jet Flows Using Real Fluid Thermophysical Properties

2020-01-115304/14/2020

In order to understand supercritical jet flows further, well resolved large eddy simulations (LES) of a n-dodecane jet mixing with surrounding nitrogen are conducted. A real fluid thermodynamic model is used to account for the fuel compressibility and variable thermophysical properties due to the solubility of ambient gas and liquid jet using the cubic Peng-Robinson equation of state (PR-EOS). A molar averaged homogeneous mixing rule is used to calculate the mixing properties. The thermodynamic model is coupled with a pressure-based solver to simulate multispecies reacting flows. The numerical model is based on a second order accurate method implemented in the open source OpenFOAM-6 software. First, to evaluate the present numerical model for sprays, 1D advection and shock tube benchmark problems at supercritical conditions are shown. Second, a cryogenic nitrogen injection with a jet velocity of 4.9 m/s into a supercritical nitrogen environment at 4 MPa and room temperature is

Ningegowda, B M, Rahantamialisoa, Faniry, Zembi, Jacopo, Pandal, Adrian, Im, Hong G., Battistoni, Michele

Effects of Engine Speed on the Performance at Extreme Vehicle Driving Conditions

2019-36-029701/13/2020

Nowadays, improvements in engine fuel economy and reduction in pollutant emissions have been much discussed. Downsizing and downspeeding are methods widely used in the automotive market, used to increase internal combustion engine efficiency. Fuel consumption is commonly measured through a specific cycle that could differ between countries. Federal Test Procedure (FTP-75) for Latin America and New European Driving Cycle (NEDC) for Europe are some examples. These cycles include normal driving conditions, low vehicle load and mild environmental conditions. The style of gear shifting is one of the main factors affecting fuel efficiency and performance of motor vehicles. At extreme diving conditions, parameters like coolant and air charge temperature could reach limit durability values of the system. In order to avoid knocking and maintain structural reliability, it becomes mandatory to control the engine speed. An increase in engine speed reduces engine load requirements and thus

Thomaz, Fabrício, Baeta, José Guilherme Coelho

Metallization for SiC Semiconductors

TBMG-3570412/01/2019

Scientists at NASA’s Glenn Research Center have developed and patented improved ohmic contacts, and a fabrication method for them, that will speed the production of silicon carbide (SiC) sensors and electronics that operate in high-temperature, harsh environments.

Phase-Change Coating Absorbs Heat from Rockets, Pipes, and Beer

TBMG-3544611/01/2019

Spinoff is NASA's annual publication featuring successfully commercialized NASA technology. This commercialization has contributed to the development of products and services in the fields of health and medicine, consumer goods, transportation, public safety, computer technology, and environmental resources.

Celebrating the 50th Anniversary of Apollo 11: Getting There, To a New Era of Space Exploration

TBMG-3474507/01/2019

For the first time in a generation, NASA is building a human spacecraft for deep-space missions that will usher in a new era of space exploration. A series of increasingly challenging missions awaits, and this new spacecraft will take astronauts farther than they’ve gone before, including to the Moon and Mars.

LED Lighting Improves Efficiency and Imaging

TBMG-3439705/01/2019

Rocket engine testing requires a lot of light since all tests are filmed with high-speed cameras to monitor performance; however, those cameras have to adjust to the bright plume from a firing engine, which would black out the rest of the image. Traditionally, that light has been provided by metal halide bulbs.

A Target Cascading Method Using Model Based Simulation in Early Stage of Vehicle Development

2019-01-083604/02/2019

In the early stages of vehicle development, it is important for decision makers to understand a feasible constraint region that satisfies all system level requirements. The purpose of this paper is to propose a target cascading method to solve for a feasible design region which satisfies all constraints of the system based on model based simulation. In this method, the feasible design region is explored by using both global optimization methods and active learning techniques. In optimization problems, the inverse problem for understanding feasibility for specific designs is defined and solved. To determine the objective functions of the inverse problem, an index representing the achievement level of constraints from system requirements is introduced. To predict feasible regions in the specific design space, a surrogate model of minimized values of the index is trained by using a kriging model. Training data of the surrogate model is sequentially generated based on the expected

Shintani, Kohei, Abe, Atsuji, Yamamoto, Yasushi

Interoperable Intelligent Controllers for Process Management and Control Networks

TBMG-3392903/01/2019

NASA Johnson Space Center developed reprogrammable and interchangeable electronic controllers that can attach to a system or subsystem wirelessly or through plug-and-play capability. Originally designed to work with rocket engines, this technology can control different systems and subsystems. This smart controller recognizes which system it is communicating with once connected to the network and loads the appropriate application to perform the required function in the system. The device enables a common set of spares and can talk to other devices of its kind by relaying information and instructions to other controllers. A prototype can be easily developed using low-cost solutions such as Raspberry Pi to demonstrate functionality.

Integrated Multiphysics and Advanced Diagnostics

TBMG-3283209/01/2018

The objective of this effort was to design, fabricate, integrate, and fly a nuclear thermal rocket without having to build massive ground test facilities. Furthermore, this nuclear rocket would be inspected internally without having to disassemble it. Another aim here was to predict the reliability for a 15-to-20-year lifetime for a surface nuclear power plant essential for supplying power to explorers on the Moon or Mars, all without having to build and test a full-scale reactor. If the performance of these systems could be predicted, one could establish the impact of manufacturing tolerances on the operations of these systems.

High Strength Elevated Temperature Bolting Practice

ARP700B (Historical)08/23/2018

This SAE Aerospace Recommended Practice (ARP) provides general information on the design and installation of threaded fasteners in high strength and high temperature applications in propulsion systems. Some of the more common definitions of fastener terminology are also provided.

E-25 General Standards for Aerospace and Propulsion Systems

Freeform Channel Close-Out for High-Performance Heat Exchangers

TBMG-2884005/01/2018

Large-scale liquid rocket engines with regeneratively cooled nozzles will enable reliable and reduced-cost access to space. The coolant that circulates through the internal channels within the nozzle helps maintain adequate wall temperatures to prevent failure, and is contained under high pressure. It has been a challenge to affordably manufacture the intricate nozzle channels and close-out of these channels. As such, NASA has leveraged cladding and additive manufacturing technology to build the nozzle liner and outer jacket that closes out the channels within, and contains the high-pressure coolant fluid. The new capability reduces the time to fabricate the nozzle and allows for real-time inspection during the build. It has been demonstrated on a series of different alloys, hot-fire testing is nearly complete, and micrograph examination has verified that the bonds are reliable with little deformation to the coolant channels. The technology provides new opportunities to manufacture

Exploring the Potential of Combustion on Titan

01-11-01-000204/07/2018

Significant attention has been focused on Mars due to its relative proximity and possibility of sustaining human life. However, its lack of in-situ sources of energy presents a challenge to generate needed energy on the surface. Comparatively, Titan has a nearly endless source of fuel in its atmosphere and lakes, but both are lacking in regards to their oxidizing capacity. The finding of a possible underground liquid ammonia-water lake on Titan suggests that oxygen might actually be within reach. This effort provides the first theoretical study involving a primary energy generation system on Titan using the atmosphere as a fuel and underground water as the source for the oxygen via electrolysis from wind generated electricity. Thermodynamic calculations and use of chemical kinetics in a zero-dimensional Homogeneous Charge Compression Ignition (HCCI) engine model demonstrate that is indeed possible to operate an internal combustion engine on the surface of Titan while providing heat for

Depcik, Christopher

Non-Catalytic Ignition System for High-Performance Advanced Monopropellant Thrusters

TBMG-2873204/01/2018

Anon-catalytic pyrotechnic ignition system was developed for advanced green monopropellant systems operating with hydroxylammonium nitrate (HAN)-based monopropellant AF-M315E. This technology will provide increased performance and new operating regimes for future NASA missions that employ green propulsion systems. The non-catalytic ignition system is a critical component for future high-thrust, in-space rocket engines that utilize AF-M315E, offering longer thruster life and faster startup than catalytic engines. This work demonstrated the pyrotechnic ignition system in proof-of-concept hot-fire tests showing AF-M315E combustion in a workhorse thruster in a laboratory environment.

Efficient Packaging Process for One-Piece Deployable Thin Membrane

TBMG-2854003/01/2018

NASA’s Marshall Space Flight Center is building a small CubeSat that uses an 85-m2 solar sail deployed from a central location to capture the push of photons from the Sun as its propulsion source. To integrate this sail into the CubeSat, NASA inventors have developed a new method for folding and packaging the thin membrane.

Cryogenic and Non-Cryogenic Liquid Level Instrument

TBMG-2818501/01/2018

NASA’s Marshall Space Flight Center has developed a unique prototype for measuring the liquid level in a tank, employing a novel process. The technology can operate in a wide range of environments, including high and low temperatures and pressures, and is simpler and less expensive than other optical sensing techniques. The instrument also provides far greater accuracy and faster results in cryogenic conditions than typical cryogenic liquid metering methods. It is ideal for cryogenic and non-cryogenic ground tank metering applications, and zero-gravity systems that include stratification or settling techniques.

Novel Design of an Orifice Control Element

TBMG-2800612/01/2017

An orifice element is commonly used in liquid rocket engine test facilities either as a flow metering device, a damper for acoustic resonance, or to provide a large reduction in pressure over a very small distance in the piping system. The orifice as a device is largely effective in stepping down pressure; however, it is also susceptible to a wake-vortex instability that generates pressure fluctuations that propagate downstream and interact with other elements of the test facility, resulting in structural vibrations. Exacerbating the situation in cryogenic test facilities is the possibility of the formation of vapor clouds when the pressure in the wake falls below the vapor pressure, leading to cavitation. Cavitation has the potential for highamplitude fluctuations that can cause catastrophic damage to a facility.

Sequential/Simultaneous Multi-Metallized Nanocomposites (S2M2N)

TBMG-2798712/01/2017

NASA Langley Research Center has developed a method to create Sequential/Simultaneous Multi-Metallized Nanocomposites (S2M2N) via supercritical fluid (SCF) sequential or simultaneous multi-metal infusion. The SCF infusion process provides deep impregnation of metal nanoparticles into a variety of materials, including those with challenging topographies and complex structures. The resulting multi-metallized nanocomposites can possess high electrical conductivity, permittivity, permeability, wear resistance/anti-penetrant, and radiation shielding along with high toughness.

Effect of High Frequency Acoustic Field on Atomization Behavior of Ethanol and Kerosene

2017-01-231810/08/2017

Combustion instability often occurs inside the combustion chamber of aero engine. Fuel atomization and evaporation, one of the controlling processes of combustion rate, is an important mechanism of the combustion instability. To tackle combustion instability, it challenges a deep understanding of the underlying mechanism of fuel atomization and evaporation. In this paper, acoustic field was established to simulate the pressure oscillation. Transient spray images of ethanol and kerosene were recorded using high-speed camera. The obtained images were processed by MATLAB to extract and analyze the related data. Spatial fuel atomization characteristics was analytically examined by multi-threshold image method to analyze the effect of the high frequency acoustic field on the fuel break-up and disintegration. The results show that the half spray cone angle on the side with speaker is suppressed by the presence of the imposed acoustic field compared with the case without speaker

Jia, Xiaoxu, Huang, Zhong, Ju, Dehao, Huang, Zhen, Lu, Xing-cai

Numerical Analysis on the Injection and Atomization Characteristics of Diesel Surrogates at Engine Conditions

2017-01-230610/08/2017

Recently, the shortage of fossil resources contributes to strict regulations of environmental protection. The research on the high efficiency and low emission of engines becomes an important direction all over the world. Technologies like high injection pressure, high levels of supercharging and higher levels of back pressure have come into application. Increasing the injection pressure and average cylinder pressure results in that parts of the spray can experience transcritical and supercritical regimes. In this paper, we established a surrogate fuel composed of n-Hexadecane, HMN and 1-Metylnaphthalene, to analyze the injection and atomization of diesel surrogate fuel with large eddy simulation (LES) in a cubic calculation region with high temperature and high pressure environment. The injection pressure was fixed to 150MPa, and the 900-K temperature and the 6-MPa pressure represented the ambient condition in constant volume vessel which is supercritical with respect to No.2 diesel

Sun, Xiaochuan, Li, Xiang, Huang, Zhong, Ju, Dehao, Lu, Xing-cai, Han, Dong, Huang, Zhen

Application of Solid State Welding and Superplastic Forming to Aerospace Vehicles

2017-01-214809/19/2017

In this paper, manufacturing of launcher structural components with superplastic forming (SPF) and solid state welding technologies is presented with several examples. Some of high strength aerospace alloys, like aluminum, titanium and superalloys, are known to have superplasticity so that complex shapes of aerospace components can be produced with this technology. A combination of superplastic forming and solid state welding processes produces lighter and stiffer components than one manufactured with conventional machining and welding. Solid state welding is an attractive method to weld materials without melting where mechanical properties are important since the welding interface is homogeneous without liquid phases. The results includes aluminum and titanium tanks cryogenic application, a scaled combustion chamber with duplex stainless steel and copper alloy, and lightweight aluminum-copper-lithium cylinder manufactured by superplastic forming and diffusion bonding or friction stir

Lee, Ho-Sung

Multi-Pulse Motor (MPM) for Use with Electric Solid Propellants (ESP)

TBMG-2753809/01/2017

The purpose of this work was to create a safe, green, controllable solid rocket motor that can be pulsed a number of times with electricity to control the ignition and extinguishment times to produce a required thrust or impulse bit. The innovation features an Electric Solid Propellant (ESP). The key problem is that the geometry of the ESP grain changes because of the evolution of the propellant to exhaust gases, but a closed electrical circuit is required to keep the electrical power applied to the grain and continue burning. The chamber pressure is utilized in the multi-pulse motor (MPM) design to ensure electrical contact is retained during the pulsing event.

Combustion Characteristics of Hydrocarbon Droplets Induced by Photoignition of Aluminum Nanoparticles

TBMG-2738108/01/2017

In the study of combustion characteristics of liquid rocket fuels, it is customary to either study the combustion of liquid fuel droplets or the combustion of fuel sprays. However, the two are closely related to each other, because in a typical rocket combustion chamber, the burning of droplets, droplet clusters, and fuel sprays occur simultaneously.

Measuring Propellant Stress Relaxation Modulus Using Dynamic Mechanical Analyzer

TBMG-2738008/01/2017

Structural analysis of solid rocket motors is challenging for several reasons, but the most important of these is the complex behavior of the propellant. The mechanical response of a solid propellant is time and temperature dependent. The complexity of the mathematical analysis of the propellant depends on the loading conditions, but for some loading situations, the linear viscoelasticity assumption is reasonable. In particular, linear viscoelasticity is perhaps the most appropriate material behavior description for use in the simulations of stresses related to storage conditions. Typically, simulations use a viscoelastic model in the form of a Prony series and a Williams–Landel–Ferry (WLF) equation. The parameters in these models are derived from stress relaxation experiments, making the stress relaxation experiment a key viscoelastic test, analogous to the tensile test for linear elastic materials.

Measuring Propellant Stress Relaxation Modulus Using Dynamic Mechanical Analyzer

17AERP08_0606/01/2017

New testing technique requires less material, gives more accurate results. Air Force Research Laboratory (AFMC), Edwards Air Force Base, California Structural analysis of solid rocket motors is challenging for several reasons, but the most important of these is the complex behavior of the propellant. The mechanical response of a solid propellant is time and temperature dependent. The complexity of the mathematical analysis of the propellant depends on the loading conditions, but for some loading situations, the linear viscoelasticity assumption is reasonable. In particular, linear viscoelasticity is perhaps the most appropriate material behavior description for use in the simulations of stresses related to storage conditions. Typically, simulations use a viscoelastic model in the form of a Prony series and a Williams-Landel-Ferry (WLF) equation. The parameters in these models are derived from stress relaxation experiments, making the stress relaxation experiment a key viscoelastic test

Combustion Characteristics of Hydrocarbon Droplets Induced by Photoignition of Aluminum Nanoparticles

17AERP08_0706/01/2017

Test methodology allows analysis of combustion dynamics for subscale rocket injectors under super critical conditions. Air Force Research Laboratory (AFMC), Edwards Air Force Base, California In the study of combustion characteristics of liquid rocket fuels, it is customary to either study the combustion of liquid fuel droplets or the combustion of fuel sprays. However, the two are closely related to each other, because in a typical rocket combustion chamber, the burning of droplets, droplet clusters, and fuel sprays occur simultaneously. The study of droplet burning is mostly focused either on single suspended droplets or free droplets, usually in a free fall. In either case, the conditions regarding the combustion of a single fuel droplet deviates from what is expected in typical liquid rocket engines (LREs). This not only concerns the chamber pressure and the temperature that is usually much lower in a typical droplet study, but also the droplet ignition process and the related

ELECTRIC ROCKETS AND THE FUTURE OF SATELLITE PROPULSION

17MEIP06_0406/01/2017

Humans have been using rocket propulsion for almost a millennium, starting with Chinese rockets and “fire arrows” in the 13th century and continuing to the modern era's powerful Space Shuttle and Falcon rockets. For most of that history, rockets have been chemically fueled, but in the past century scientists and engineers have also experimented with electric rockets, also known as ion engines or ion propulsion systems. Rather than using chemical reactions to create heat and accelerate a propellant, electric rockets use electromagnetic or electrostatic fields acting on charged ions of propellant, speeding them up and shooting them out, away from the vehicle, producing thrust. The electrical energy to generate these fields comes from the sun, from batteries, or both.

Low Solidity Vaned Diffuser (LSVD) Design for Improvement of Pressure Recovery

TBMG-2685205/01/2017

Many pump vaned diffuser designs are based on existing airfoil designs, with little attention given to the vane leading edge. There is a need for a vaned diffuser leading edge that helps resist flow separation and the resultant poor diffuser pressure recovery. Diffusers in pumps are often working with an incompressible fluid that makes potential flow methodologies — which have incompressibility as a boundary condition — attractive. The potential flow-based free-streamline analysis methods have been known to improve the aerodynamics of varied components at high incidence angles, such as diffusers, jet engine nacelles, and liquid rocket engine turbopump inducers.

Green Monopropellant Secondary Payload Propulsion System

TBMG-2683505/01/2017

Small satellites, launched as secondary payloads, are increasingly being fielded. Advances in liquid rocket propulsion that enhance the on-orbit maneuverability, increase the on-orbit life, and decrease the time between identified need for and deployment of such spacecraft are of great value. Replacing the nearly ubiquitous yet toxic hydrazine propellant with AF-M315E produces higher specific impulse and density specific impulse, resulting in improved overall velocity change capability and increased on-orbit life.

A Modular Apparatus and Method for Attaching Multiple Devices

TBMG-2664604/01/2017

Scientists at NASA's Glenn Research Center have received several patents for fabrication methods that speed the production of silicon carbide (SiC) sensors and electronics, reduce fabrication costs, and enable advanced semiconductor functionality at temperatures greater than 600 °C. Glenn has developed a method for fabricating ultra-thin SiC microstructures using a dopant selective reactive ion etching (DSRIE) technique that can create extremely thin diaphragms (approximately 2 microns), increasing sensor sensitivity and resolution. In addition, Glenn has developed a modular protective packaging that allows SiC-based electronic devices to survive and operate reliably at very high temperatures. These innovations improve the real-time monitoring of high-temperature harsh environments, such as jet and rocket engines, allowing faster response times and more accurate readings.

Electric Rockets and the Future of Satellite Propulsion

TBMG-2667904/01/2017

Cooling Solution Helps NASA Get Closer to Mars

TBMG-2664804/01/2017

Cold conditioning system Aggreko Houston, TX 281-985-8200

Electric Rockets and the Future of Satellite Propulsion

17AERP04_0304/01/2017

Experimental Measurements and Computations for Clarifying Nearly Complete Air-Insulation Obtained by the Concept of Colliding Pulsed Supermulti-Jets

2017-01-103003/28/2017

In our previous papers, a new concept of a compressive combustion engine (Fugine) was proposed based on the collision of pulsed supermulti-jets, which can enclose the burned gas around the chamber center leading to an air-insulation effect and also a lower exhaust gas temperature due to high single-point compression. In order to examine the compression level and air-insulation effect as basic data for application to automobiles, aircraft, and rockets, a prototype engine based on the concept, i.e., a piston-less prototype engine with collision of bi-octagonal pulsed multi-jets from fourteen nozzles, was developed. Some combustion results [Naitoh et al. SAE paper, 2016] were recently reported. However, there was only one measurement of wall temperature and pressure in the previous report. Thus, in this paper, more experimental data for pressures and temperatures on chamber walls and exhaust temperatures, are presented for the prototype engine. First, pressure over 0.6MPa was measured on

Konagaya, Remi, Oyanagi, Susumu, Kanase, Takuto, Tsuchiya, Jumpei, Ayukawa, Ken, Kinoshita, Kodai, Mikoda, Junya, Fujita, Hirotaka, Naitoh, Ken

‘NOT JUST A STUDENT CLUB’

17MOMP03_0103/01/2017

How the University of Toronto Aerospace Team (UTAT) came to redefine the mission and structure of the design team WITH OVER 100 ACTIVE MEMBERS working on everything from quadcopters to astrobiology satellites, sounding rockets to fixed-wing drones, professional conferences to policy research, I often forget that the University of Toronto Aerospace Team (UTAT) is “just” a student club. UTAT's beginnings trace back to 2004, when a handful of engineering students who enjoyed building RC planes and sharing the occasional beer on Friday came together. For nearly nine years, UTAT focused on aircraft-until in 2012 a small group of UTAT-ers wondered what more could be done. Soon, a rocket project was added, educational and professional outreach activities began snowballing, a space systems division and aerial robotics division were formed, and sponsors became increasingly bubbly about UTAT's growth.

Study of Formulating Conserved Scalar Equations for Turbulent Reactive Flows with General Species Mass- Diffusion Coefficients for Utilization in Flamelet Models

TBMG-2616501/01/2017

The modeling of turbulent reactive flows is a subject of contemporary research. Current turbulent-reaction models cannot account for realistic complexities such as distinct species mass-diffusion coefficients. Under the assumption of a single, constant, mass-diffusion coefficient, a conserved-scalar equation is typically derived in turbulent reactive flows by taking the difference between chemical-species conservation equations having opposite reaction rates (in the sense that the reactant has an opposite reaction rate to the product), thereby creating an equation devoid of reaction terms. Assuming the reaction regions are very thin and are merely contorted by turbulence, chemistry and turbulence can be decoupled, and the evolving statistics of the conserved scalar describe the reaction progression. No such equation has yet been derived for distinct mass-diffusion coefficient cases where the single coefficient is now replaced by a full matrix. Considering that mass diffusion is

NASA's Software Answers Big Questions About Space and Earth

TBMG-2606312/01/2016

NASA’s next-generation Space Launch System (SLS) for deep space exploration consists of four RS-25 liquid rocket engines and two five-segment solid rocket boosters (SRBs). At ignition, the SRBs create a significant over-pressure event, known as the Ignition Over-Pressure (IOP) event. The IOP event experienced in the first space shuttle flight (STS-1) in 1981 damaged the space shuttle orbiter and motivated significant design changes to the launch pad at NASA’s Kennedy Space Center. The RS-25 liquid rocket engines aboard the SLS, along with the SRBs, also create a very significant acoustic environment that, if not mitigated, can harm the SLS launch vehicle. An Ignition Over-Pressure/Sound Suppression (IOP/SS) water system was developed to reduce the amplitude of both the IOP event and the acoustic environment caused by the firing of the RS-25 engines and the SRBs.

Uncertainty of In-Flight Thrust Determination

AIR1678B (Current)10/22/2016

This document defines and illustrates the process for determination of uncertainty of turbofan and turbojet engine in-flight thrust and other measured in-flight performance parameters. The reasons for requiring this information, as specified in the E-33 Charter, are: determination of high confidence aircraft drag; problem rectification if performance is low; interpolation of measured thrust and aircraft drag over a range of flight conditions by validation and development of high confidence analytical methods; establishment of a baseline for future engine modifications. This document describes systematic and random measurement uncertainties and methods for propagating the uncertainties to the more complicated parameter, in-flight thrust. Methods for combining the uncertainties to obtain given confidence levels are also addressed. Although the primary focus of the document is in-flight thrust, the statistical methods described are applicable to any measurement process. The E-33 Committee

E-33 In Flight Propulsion Measurement Committee

Magnetostrictive Pressure Regulating System

TBMG-2551410/01/2016

NASA’s Marshall Space Flight Center has developed a set of unique magnetostrictive (MS) technologies for utilization in pressure regulation and valve systems. By combining MS-based sensors with a newly designed MS-based valve, Marshall has developed an advanced MS regulator. This innovative approach provides both a regulator and a valve with rapid response times. In addition, the components are lightweight, compact, highly precise, and can operate over a wide range of temperatures and pressures. A prototype of the MS valve has been developed and NASA is seeking partners for licensure of this novel technology.

Seeing Closer and Clearer with NASA Imaging Technology

TBMG-2553810/01/2016

NASA’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer (OSIRIS-Rex) spacecraft launched on September 8 to the near-Earth asteroid Bennu to harvest a sample of surface material and return it to Earth for study. But before the science team selects a sample site, they can find out a bit about Bennu’s elemental make-up.

Eddy-Current-Minimizing Flow Plug for Use in Flow Conditioning and Flow Metering

TBMG-2551010/01/2016

Innovators at NASA’s Marshall Space Flight Center have developed a suite of prototype fluid plug technologies with an array of capabilities for fluid flow metering, mixing, and conditioning. Each innovation within this suite is based upon a core technology that has no moving parts, is simple to manufacture, and provides high reliability and efficiency. Also, the base fluid plug technology can be modified with very few or no hardware changes to achieve the desired effect or combination of mixing, metering, and conditioning capabilities depending on the application.

Actuation System Data Summary for Missiles and Launch Vehicles

AIR1855A (Current)09/28/2016

This SAE Aerospace Information Report (AIR) includes all missile and launch vehicle actuation systems, including electrohydraulic, electropneumatic, and electromechanical types. The data for many systems are not complete. As more information becomes available, periodic updates will be issued to complete existing data sheets and to add new ones. An index by type of vehicle and by type of actuation system is included. The actual data sheets in the body of the report are organized in alphabetical order.

A-6B1 Hydraulic Servo Actuation Committee

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