Gotowe bibliografie tematyczne / Aerospace Engineering - Propulsion

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Gotowa bibliografia na temat „Aerospace Engineering - Propulsion”

Autor: Grafiati

Data publikacji: 6 września 2023

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Artykuły w czasopismach na temat "Aerospace Engineering - Propulsion"

Isikveren, A. T., A. Seitz, J. Bijewitz, A. Mirzoyan, A. Isyanov, R. Grenon, O. Atinault, J. L. Godard i S. Stückl. "Distributed propulsion and ultra-high by-pass rotor study at aircraft level". Aeronautical Journal 119, nr 1221 (listopad 2015): 1327–76. http://dx.doi.org/10.1017/s0001924000011295.

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AbstractThis technical article discusses design and integration associated with distributed propulsion as a means of providing motive power with significantly reduced emissions and external noise for future aircraft concepts. The technical work reflects activities performed within a European Commission funded Framework 7 project entitled Distributed Propulsion and Ultra-high By-Pass Rotor Study at Aircraft Level, or, DisPURSAL. In this instance, the approach of distributed propulsion includes a Distributed Multiple-Fans Concept driven by a limited number of engine cores as well as one unique solution that integrates the fuselage with a single propulsor (dubbed Propulsive-Fuselage Concept) – both targeting entry-in-service year 2035+. Compared to a state-of-the-art, year 2000 reference aircraft, designs with tighter coupling between airframe aerodynamics and motive power system performance for medium-to-long-range operations indicated potentially a 40-45% reduction in CO2-emissions. An evolutionary, year 2035, conventional morphology gas-turbine aircraft was predicted to be –33% in CO2-emissions.

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Perry, Aaron T., Phillip J. Ansell i Michael F. Kerho. "Aero-Propulsive and Propulsor Cross-Coupling Effects on a Distributed Propulsion System". Journal of Aircraft 55, nr 6 (listopad 2018): 2414–26. http://dx.doi.org/10.2514/1.c034861.

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Gray, Justin S., i Joaquim R. R. A. Martins. "Coupled aeropropulsive design optimisation of a boundary-layer ingestion propulsor". Aeronautical Journal 123, nr 1259 (31.10.2018): 121–37. http://dx.doi.org/10.1017/aer.2018.120.

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AbstractAirframe–propulsion integration concepts that use boundary-layer ingestion (BLI) have the potential to reduce aircraft fuel burn. One concept that has been recently explored is NASA’s STARC-ABL aircraft configuration, which offers the potential for fuel burn reduction by using a turboelectric propulsion system with an aft-mounted electrically driven BLI propulsor. So far, attempts to quantify this potential fuel burn reduction have not considered the full coupling between the aerodynamic and propulsive performance. To address the need for a more careful quantification of the aeropropulsive benefit of the STARC-ABL concept, we run a series of design optimisations based on a fully coupled aeropropulsive model. A 1D thermodynamic cycle analysis is coupled to a Reynolds-averaged Navier–Stokes simulation to model the aft propulsor at a cruise condition and the effects variation in propulsor design on overall performance. A series of design optimisation studies are performed to minimise the required cruise power, assuming different relative sizes of the BLI propulsor. The design variables consist of the fan pressure ratio, static pressure at the fan face, and 311 variables that control the shape of both the nacelle and the fuselage. The power required by the BLI propulsor is compared with a podded configuration. The results show that the BLI configuration offers 6–9% reduction in required power at cruise, depending on assumptions made about the efficiency of power transmission system between the under-wing engines and the aft propulsor. Additionally, the results indicate that the power transmission efficiency directly affects the relative size of the under-wing engines and the aft propulsor. This design optimisation, based on computational fluid dynamics, is shown to be essential to evaluate current BLI concepts and provides a powerful tool for the design of future concepts.

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Bore, C. L. "Some contributions to propulsion theory — Fuel consumption formulae and general range equation". Aeronautical Journal 97, nr 963 (marzec 1993): 118–20. http://dx.doi.org/10.1017/s0001924000025203.

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The permanent urgency of aircraft design during the author’s career at Hawker Aircraft, a.k.a. British Aerospace Kingston, inhibited publication of his advances of theory. So he collected those on propulsion and presented them to the Royal Aeronautical Society in a lecture “Some Unpublished Contributions to Propulsion Theory” on 11 March 1992. The meeting proposed that the material should be published in full, and F. W. Armstrong helpfully suggested that the best way for future reference would be to divide the material into Technical Notes on related topics, each capable of standing alone. These have been reworked to stand separately, as follows:1)Fuel consumption formulae and the general range equation2)The Stream Force Theorem and applications to propulsion3)Non-isentropic duct flow and the general wake traverse4)Propulsion streamtubes in supersonic flow and the first supercritical intake cowl5)Rotary jet thrust augmenters(a)fallacy of Foa’s theory and correction(b)the jet fan augmenter.

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Seitz, A., D. Schmitt i S. Donnerhack. "Emission comparison of turbofan and open rotor engines under special consideration of aircraft and mission design aspects". Aeronautical Journal 115, nr 1168 (czerwiec 2011): 351–60. http://dx.doi.org/10.1017/s000192400000587x.

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Abstract An integrated parametric model involving the design of propulsion system, airframe and flight mission is presented. Based hereon, the carbon dioxide (CO2) emission characteristics of advanced direct-drive turbofan and open rotor powered aircraft are analysed against pertinent aircraft and propulsion system design parameters. In addition, initial concept-specific trend statements on nitrogen oxides (NOx) as well as propulsor noise emission characteristics are derived. The obtained results contribute to a better understanding of more appropriate aircraft design attributes for advanced system architectures.

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Cusati, Vincenzo, Salvatore Corcione, Fabrizio Nicolosi i Qinyin Zhang. "Improvement of Take-Off Performance for an Electric Commuter Aircraft Due to Distributed Electric Propulsion". Aerospace 10, nr 3 (11.03.2023): 276. http://dx.doi.org/10.3390/aerospace10030276.

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The need for environmentally responsible solutions in aircraft technology is now considered the priority for global challenges related to the limited supply of traditional fuel sources and the potential global hazards associated with emissions produced by traditional aircraft propulsion systems. Several projects, including research into highly advanced subsonic aircraft concepts to drastically reduce energy or fuel usage, community noise, and emissions associated with aviation, are currently ongoing. One of the proposed propulsion concepts that address European environmental goals is distributed electric propulsion. This paper deals with the detailed aerodynamic analyses of a full-electric commuter aircraft with fuel cells, which expects two primary electric motors at the wing tip and eight other electric motors distributed along the wingspan as secondary power sources. The main objective was the numerical estimation of propulsive effects in terms of lift capabilities at take-off conditions to quantify the possible reduction of take-off field length. However, the aircraft was designed from scratch, and therefore a great effort was spent to design both propellers (for the tip and distributed electric motors) and the wing flap. In this respect, several numerical tests were performed to obtain one of the best possible flap positions. This research work estimated a reduction of about 14% of the take-off field length due to only the propulsive effects. A greater reduction of up to 27%, if compared to a reference conventional commuter aircraft, could be achieved thanks to a combined effect of distributed propulsion and a refined design of the Fowler flap. On the contrary, a significant increment of pitching moment was found due to distributed propulsion that may have a non-negligible impact on the aircraft stability, control, and trim drag.

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Ibrahim, K., S. Sampath i D. Nalianda. "Voltage synchronisation for hybrid-electric aircraft propulsion systems". Aeronautical Journal 125, nr 1291 (22.07.2021): 1611–30. http://dx.doi.org/10.1017/aer.2021.56.

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AbstractIncreasing demand for commercial air travel is projected to have additional environmental impact through increased emissions from fuel burn. This has necessitated the improvement of aircraft propulsion technologies and proposal of new concepts to mitigate this impact. The hybrid-electric aircraft propulsion system has been identified as a potential method to achieve this improvement. However, there are many challenges to overcome. One such challenges is the combination of electrical power sources and the best strategy to manage the power available in the propulsion system. Earlier methods reviewed did not quantify the mass and efficiency penalties incurred by each method, especially at system level. This work compares three power management approaches on the basis of feasibility, mass and efficiency. The focus is on voltage synchronisation and adaptation to the load rating. The three methods are the regulated rectification, the generator field flux variation and the buck-boost. This comparison was made using the propulsion system of the propulsive fuselage aircraft concept as the reference electrical configuration. Based on the findings, the generator field flux variation approach appeared to be the most promising, based on a balance of feasibility, mass and efficiency, for a 2.6MW system.

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James, Anthony. "The Aviation Conference of the Year!" Aerospace Testing International 2018, nr 3 (wrzesień 2018): 86–89. http://dx.doi.org/10.12968/s1478-2774(23)50121-6.

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The 4th Electric & Hybrid Aerospace Technology Symposium will bring together more than 200 engineering experts from aircraft manufacturers, propulsion suppliers, electronics and avionics suppliers, materials companies, aerospace research organizations and others involved in the electrification of aircraft.

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Bae, Yoon-Yeong, i George Emanuel. "Performance of an aerospace plane propulsion nozzle". Journal of Aircraft 28, nr 2 (luty 1991): 113–22. http://dx.doi.org/10.2514/3.45999.

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Falzarano, Jeffrey. "Ship Resistance and Propulsion: Practical Estimation of Ship Propulsive Power". AIAA Journal 56, nr 10 (październik 2018): 4218. http://dx.doi.org/10.2514/1.j057653.

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Rozprawy doktorskie na temat "Aerospace Engineering - Propulsion"

Zhu, Dawei. "Supercirculation Aerodynamic-Propulsion Test Rig Instrumentation Development". Ohio University / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1142542776.

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Gilpin, Matthew R. "High temperature latent heat thermal energy storage to augment solar thermal propulsion for microsatellites". Thesis, University of Southern California, 2016. http://pqdtopen.proquest.com/#viewpdf?dispub=10160163.

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Solar thermal propulsion (STP) offers an unique combination of thrust and efficiency, providing greater total ΔV capability than chemical propulsion systems without the order of magnitude increase in total mission duration associated with electric propulsion. Despite an over 50 year development history, no STP spacecraft has flown to-date as both perceived and actual complexity have overshadowed the potential performance benefit in relation to conventional technologies. The trend in solar thermal research over the past two decades has been towards simplification and miniaturization to overcome this complexity barrier in an effort finally mount an in-flight test.

A review of micro-propulsion technologies recently conducted by the Air Force Research Laboratory (AFRL) has identified solar thermal propulsion as a promising configuration for microsatellite missions requiring a substantial Δ V and recommended further study. A STP system provides performance which cannot be matched by conventional propulsion technologies in the context of the proposed microsatellite ''inspector" requiring rapid delivery of greater than 1500 m/s ΔV. With this mission profile as the target, the development of an effective STP architecture goes beyond incremental improvements and enables a new class of microsatellite missions.

Here, it is proposed that a bi-modal solar thermal propulsion system on a microsatellite platform can provide a greater than 50% increase in Δ V vs. chemical systems while maintaining delivery times measured in days. The realization of a microsatellite scale bi-modal STP system requires the integration of multiple new technologies, and with the exception of high performance thermal energy storage, the long history of STP development has provided "ready" solutions.

For the target bi-modal STP microsatellite, sensible heat thermal energy storage is insufficient and the development of high temperature latent heat thermal energy storage is an enabling technology for the platform. The use of silicon and boron as high temperature latent heat thermal energy storage materials has been in the background of solar thermal research for decades without a substantial investigation. This is despite a broad agreement in the literature about the performance benefits obtainable from a latent heat mechanisms which provides a high energy storage density and quasi-isothermal heat release at high temperature.

In this work, an experimental approach was taken to uncover the practical concerns associated specifically with applying silicon as an energy storage material. A new solar furnace was built and characterized enabling the creation of molten silicon in the laboratory. These tests have demonstrated the basic feasibility of a molten silicon based thermal energy storage system and have highlighted asymmetric heat transfer as well as silicon expansion damage to be the primary engineering concerns for the technology. For cylindrical geometries, it has been shown that reduced fill factors can prevent damage to graphite walled silicon containers at the expense of decreased energy storage density.

Concurrent with experimental testing, a cooling model was written using the "enthalpy method" to calculate the phase change process and predict test section performance. Despite a simplistic phase change model, and experimentally demonstrated complexities of the freezing process, results coincided with experimental data. It is thus possible to capture essential system behaviors of a latent heat thermal energy storage system even with low fidelity freezing kinetics modeling allowing the use of standard tools to obtain reasonable results.

Finally, a technological road map is provided listing extant technological concerns and potential solutions. Improvements in container design and an increased understanding of convective coupling efficiency will ultimately enable both high temperature latent heat thermal energy storage and a new class of high performance bi-modal solar thermal spacecraft.

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Eilers, Shannon Dean. "Development of the Multiple Use Plug Hybrid for Nanosats (Muphyn) Miniature Thruster". DigitalCommons@USU, 2013. https://digitalcommons.usu.edu/etd/1726.

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The Multiple Use Plug Hybrid for Nanosats (MUPHyN) prototype thruster incorporates solutions to several major challenges that have traditionally limited the deployment of chemical propulsion systems on small spacecraft. The MUPHyN thruster offers several features that are uniquely suited for small satellite applications. These features include 1) a non-explosive ignition system, 2) non-mechanical thrust vectoring using secondary fluid injection on an aerospike nozzle cooled with the oxidizer flow, 3) a non-toxic, chemically-stable combination of liquid and inert solid propellants, 4) a compact form factor enabled by the direct digital manufacture of the inert solid fuel grain. Hybrid rocket motors provide significant safety and reliability advantages over both solid composite and liquid propulsion systems; however, hybrid motors have found only limited use on operational vehicles due to 1) difficulty in modeling the fuel flow rate 2) poor volumetric efficiency and/or form factor 3) significantly lower fuel flow rates than solid rocket motors 4) difficulty in obtaining high combustion efficiencies. The features of the MUPHyN thruster are designed to offset and/or overcome these shortcomings. The MUPHyN motor design represents a convergence of technologies, including hybrid rocket regression rate modeling, aerospike secondary injection thrust vectoring, multiphase injector modeling, non-pyrotechnic ignition, and nitrous oxide regenerative cooling that address the traditional challenges that limit the use of hybrid rocket motors and aerospike nozzles. This synthesis of technologies is unique to the MUPHyN thruster design and no comparable work has been published in the open literature.

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Collie, Wallis Vernon. "Design and Analysis of an Unmanned Aerial Vehicle Propulsion System with Fluidic Flow Control Inside a Highly Compact Serpentine Inlet Duct". NCSU, 2003. http://www.lib.ncsu.edu/theses/available/etd-11282003-145453/.

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The benefits of highly compact serpentine inlet ducts extend from reductions in overall aircraft weight to higher survivability, as well as allow the aircraft designer greater flexibility in propulsion system integration. Unfortunately, due to the extreme wall curvature, these ducts result in significant flow distortion and total pressure losses at the engine face. It has been shown that active flow control in the form of micro-fluidic vortex generators significantly helps to reduce these losses. To date, these systems have only been tested in a laboratory setting in which items such as flow control air supply, system and subsystem size, weight, and location are not major factors. Subscale unmanned aerial vehicles provide a real world test bed to help overcome these constraints at a lower cost and lower risk as compared to full scale aircraft testing. This work presents the design, integration, testing, and analysis of an unmanned aerial vehicle?s propulsion system that implements fluidic flow control inside a highly compact serpentine inlet duct in order to reduce engine face distortion and increase propulsion system performance.

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Armstrong, Isaac W. "Development and Testing of Additively Manufactured Aerospike Nozzles for Small Satellite Propulsion". DigitalCommons@USU, 2019. https://digitalcommons.usu.edu/etd/7428.

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Automatic altitude compensation has been a holy grail of rocket propulsion for decades. Current state-of-the-art bell nozzles see large performance decreases at low altitudes, limiting rocket designs, shrinking payloads, and overall increasing costs. Aerospike nozzles are an old idea from the 1960’s that provide superior altitude-compensating performance and enhanced performance in vacuum, but have survivability issues that have stopped their application in satellite propulsion systems. A growing need for CubeSat propulsion systems provides the impetus to study aerospike nozzles in this application. This study built two aerospike nozzles using modern 3D metal printing techniques to test aerospikes at a size small enough to be potentially used on a CubeSat. Results indicated promising in-space performance, but further testing to determine thermal limits is deemed necessary.

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Marklund, Hanna. "Supersonic Retro Propulsion Flight Vehicle Engineering of a Human Mission to Mars". Thesis, Luleå tekniska universitet, Rymdteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-75820.

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A manned Mars mission will require a substantial increase in landed mass compared to previous robotic missions, beyond the capabilities of current Entry Descent and Landing, EDL, technologies, such as blunt-body aeroshells and supersonic disk-gap-band parachutes. The heaviest payload successfully landed on Mars to date is the Mars Science Laboratory which delivered the Curiosity rover with an approximate mass of 900 kg. For a human mission, a payload of magnitude 30-50 times heavier will need to reach the surface in a secure manner. According to the Global Exploration Roadmap, GER, a Human Mission to Mars, HMM, is planned to take place after year 2030. To prepare for such an event several technologies need maturing and development, one of them is to be able to use and accurately asses the performance of Supersonic Retro Propulsion, SRP, another is to be able to use inflatable heat shields. This internal study conducted at the European Space Agency, ESA, is a first investigation focusing on the Entry Descent and Landing, EDL, sequence of a manned Mars lander utilising an inflatable heatshield and SRP, which are both potential technologies for enabling future landings of heavy payloads on the planet. The thesis covers the areas of aerodynamics and propulsion coupled together to achieve a design, which considers the flight envelope constraints imposed on human missions. The descent has five different phases and they are defined as circular orbit, hypersonic entry, supersonic retropropulsion, vertical turn manoeuvre and soft landing. The focus of this thesis is on one of the phases, the SRP phase. The study is carried out with the retro-thrust profile and SRP phase initiation Mach number as parameters. Aerodynamic data in the hyper and supersonic regime are generated using Computational Fluid Dynamics, CFD, to accurately assess the retropropulsive performance. The basic concept and initial sizing of the manned Mars lander builds on a preliminary technical report from ESA, the Mission Scenarios and Vehicle Design Document. The overall optimisation process has three parts and is based on iterations between the vehicle design, CFD computations in the software DLR-Tau and trajectory planning in the software ASTOS. Two of those parts are studied, the vehicle design and the CFD,to optimise and evaluate the feasibility of SRP during the descent and test the design parameters of the vehicle. This approach is novel, the efficiency and accuracy of the method itself is discussed and evaluated. Initially the exterior vehicle Computer Aided Design, CAD, model is created, based on the Mission Scenarios and Vehicle Design Document, however updated and furthered. The propulsion system is modelled and evaluated using EcosimPRO where the nozzle characteristics, pressure levels and chemistry are defined, and later incorporated in the CAD model. The first iteration of the CFD part has an SRP range between Mach 7 and 2, which results in an evaluation of five points on the trajectory. The thrust levels, the corresponding velocity, altitude and atmospheric properties at those points can then be evaluated and later incorporated in ASTOS. ASTOS, in turn, can simulate the full trajectory from orbit to landing including the CFD data of the SRP phase. Due to time limitation only one iteration of the vehicle design and the SRP range was completed. However, the goals of the study were reached. A first assessment of SRP in Mars atmosphere has been carried out, and the aerodynamic and propulsive data has been collected to be built on in the future. The results indicate that the engines can start at a velocity of Mach 7. They also show consistency with similar studies conducted in Earths atmosphere. The current vehicle design, propulsion system and SRP range can now be furthered, updated and advanced in order to optimise the different descent phases in combination with future results from ASTOS.

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Connolly, Joseph. "Aero-Propulso-Elastic Analysis of a Supersonic Transport". The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1543337967878799.

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Chamberlain, Britany L. "Additively-Manufactured Hybrid Rocket Consumable Structure for CubeSat Propulsion". DigitalCommons@USU, 2018. https://digitalcommons.usu.edu/etd/7285.

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Three-dimensional, additive printing has emerged as an exciting new technology for the design and manufacture of small spacecraft systems. Using 3-D printed thermoplastic materials, hybrid rocket fuel grains can be printed with nearly any cross-sectional shape, and embedded cavities are easily achieved. Applying this technology to print fuel materials directly into a CubeSat frame results in an efficient, cost-effective alternative to existing CubeSat propulsion systems. Different 3-D printed materials and geometries were evaluated for their performance as propellants and as structural elements. Prototype "thrust columns" with embedded fuel ports were printed from a combination of acrylonitrile utadiene styrene (ABS) and VeroClear, a photopolymer substitute for acrylic. Gaseous oxygen was used as the oxidizer for hot-fire testing of prototype thrusters in ambient and vacuum conditions. Hot-fire testing in ambient and vacuum conditions on nine test articles with a combined total of 25 s burn time demonstrated performance repeatability. Vacuum specific impulse was measured at over 167 s and maximum thrust of individual thrust columns at 9.5 N. The expected ΔV to be provided by the four thrust columns of the consumable structure is approximately 37 m/s. With further development and testing, it is expected that the consumable structure has the potential to provide a much-needed propulsive solution within the CubeSat community with further applications for other small satellites.

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Bertuzzi, Alberto. "Microcontroller based flow control for spacecraft electric propulsion". Master's thesis, Alma Mater Studiorum - Università di Bologna, 2018.

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Cheney, Liam Jon. "Development of Safety Standards for CubeSat Propulsion Systems". DigitalCommons@CalPoly, 2014. https://digitalcommons.calpoly.edu/theses/1180.

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The CubeSat community has begun to develop and implement propulsion systems. This movement represents a new capability which may satisfy mission needs such as orbital and constellation maintenance, formation flight, de-orbit, and even interplanetary travel. With the freedom and capability granted by propulsion systems, CubeSat providers must accept new responsibilities in proportion to the potential hazards that propulsion systems may present. The Cal Poly CubeSat program publishes and maintains the CubeSat Design Specification (CDS). They wish to help the CubeSat community to safety and responsibly expand its capabilities to include propulsive designs. For this reason, the author embarked on the task of developing a draft of safety standards CubeSat propulsion systems. Wherever possible, the standards are based on existing documents. The author provides an overview of certain concepts in systems safety with respect to the classification of hazards, determination of required fault tolerances, and the use of inhibits to satisfy fault tolerance requirements. The author discusses hazards that could exist during ground operations and through launch with respect to hazardous materials and pressure systems. Most of the standards related to Range Safety are drawn from AFSPCMAN 91-710. Having reviewed a range of hypothetical propulsion system architectures with an engineer from Range Safety at Vandenberg Air Force Base, the author compiled a case study. The author discusses many aspects of orbital safety. The author discusses the risk of collision with the host vehicle and with third party satellites along with the trackability of CubeSats using propulsion systems. Some recommendations are given for working with the Joint Functional Component Command for Space (JFCC SPACE), thanks to the input of two engineers who work with the Joint Space Operations Center (JSpOC). Command Security is discussed as an important aspect of a mission which implements a propulsion system. The author also discusses End-of-Life procedures such as safing and de-orbit operations. The orbital safety standards are intended to promote “good citizenship.” The author steps through each proposed standard and offers justification. The author is confident that these standards will set the stage for a dialogue in the CubeSat community which will lead to the formulation of a reasonable and comprehensive set of standards. The author hopes that the discussions given throughout this document will help CubeSat developers to visualize the path to flight readiness so that they can get started on the right foot.

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Książki na temat "Aerospace Engineering - Propulsion"

Theory of aerospace propulsion. Waltham, MA: Academic Press, 2012.

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Greatrix, David R. Powered Flight: The Engineering of Aerospace Propulsion. London: Springer London, 2012.

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Chamis, C. C. Computational simulation for concurrent engineering of aerospace propulsion systems. [Washington, DC: National Aeronautics and Space Administration, 1992.

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N, Singhal Surendra, i United States. National Aeronautics and Space Administration., red. Computational simulation for concurrent engineering of aerospace propulsion systems. [Washington, DC: National Aeronautics and Space Administration, 1992.

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Angelino, G. Modern Research Topics in Aerospace Propulsion: In Honor of Corrado Casci. New York, NY: Springer New York, 1991.

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Bose, Tarit. Airbreathing Propulsion: An Introduction. New York, NY: Springer New York, 2012.

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Joint Propulsion Conferences: 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. [Place of publication not identified]: [publisher not identified], 2012.

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Joint Propulsion Conferences: 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. [Place of publication not identified]: [publisher not identified], 2010.

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Xian jin hang tian tui jin ji shu. Beijing: Guo fang gong ye chu ban she, 2012.

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Space, Technology &. Applications International Forum (2004 Albuquerque N. M. ). Space Technology and Applications International Forum--STAIF 2004: Held in Albuquerque, NM, 8-11 February 2004. Melville, N.Y: American Institute of Physics, 2004.

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Części książek na temat "Aerospace Engineering - Propulsion"

"Rocket Propulsion". W Aerospace Engineering Pocket Reference, 309–24. CRC Press, 2015. http://dx.doi.org/10.1201/b18185-27.

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"Air- Breathing Propulsion". W Aerospace Engineering Pocket Reference, 299–308. CRC Press, 2015. http://dx.doi.org/10.1201/b18185-26.

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Ilyes, Ghedjatti, Yuan Shiwei i Wang Haixing. "Perspective Chapter: Effect of Laser Key Parameters on the Ignition of Boron Potassium Nitrate with a Changing Working Distance". W Hypersonic and Supersonic Flight - Advances in Aerodynamics, Materials, and Vehicle Design [Working Title]. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.107915.

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The need to realize more effective ignition systems and exploit their full potential in aerospace propulsion applications has led to significant developments in laser and power systems. This work aims to investigate experimentally and describe mathematically the effectiveness of laser systems based on varying key parameters and their related effects on the sensitivity, ignition threshold, and combustion performance of boron potassium nitrate, then to define the key variables with the most significant influence on the overall system. Understanding the physics and chemistry behind the combined system of laser power source and optics system, and the considered medium as well as the interaction in between, led to a better apprehension of how an optimal and viable solution can be achieved in terms of ignition delays, burning times, and combustion temperatures, considering laser wavelength, power and energy densities, and the focal length displacement over a changing working distance. This is of paramount importance when operating amid difficult conditions in aerospace propulsion applications or during outer space missions, particularly those involving manned missions, not only in terms of performance and efficiency but also safety, engineering, and economic feasibility.

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Streszczenia konferencji na temat "Aerospace Engineering - Propulsion"

CHAMIS, C., i S. SINGHAL. "Computational simulation of concurrent engineering for aerospace propulsion systems". W Aerospace Design Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-1144.

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Figueroa, Fernando, i Carolyn R. Mercer. "Advancing Sensor Technology for Aerospace Propulsion". W ASME 2002 International Mechanical Engineering Congress and Exposition. ASMEDC, 2002. http://dx.doi.org/10.1115/imece2002-33180.

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NASA’s Stennis Space Center (SSC) and Glenn Research Center (GRC) participate in the development of technologies for propulsion testing and propulsion applications in air and space transportation. Future transportation systems and the test facilities needed to develop and sustain them are becoming increasingly complex. Sensor technology is a fundamental pillar that makes possible development of complex systems that must operate in automatic mode (closed loop systems), or even in assisted-autonomous mode (highly self-sufficient systems such as planetary exploration spacecraft). Hence, a great deal of effort is dedicated to develop new sensors and related technologies to be used in research facilities, test facilities, and in vehicles and equipment. This paper describes sensor technologies being developed and in use at SSC and GRC, including new technologies in integrated health management involving sensors, components, processes, and vehicles.

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FAROKHI, SAEED. "System design aspects of propulsion education in aerospace engineering curricula". W 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2256.

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Habashi, G. W., T. Krepec i T. S. Sankar. "Teaching Aircraft Propulsion Engineering to Meet Industry's Needs in Montreal". W Aerospace Atlantic Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1993. http://dx.doi.org/10.4271/931392.

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Smith, Jeffrey L. "Concurrent Engineering in the Jet Propulsion Laboratory Project Design Center". W Aerospace Manufacturing Technology Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/981869.

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PARKMAN, D. "Recovery concepts for propulsion and avionics components". W Aerospace Engineering Conference and Show. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1810.

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Millar, Richard C. "A Systems Engineering Approach to PHM for Military Aircraft Propulsion Systems". W 2007 IEEE Aerospace Conference. IEEE, 2007. http://dx.doi.org/10.1109/aero.2007.352840.

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Naoumov, Viatcheslav, Viktor Kriukov i Airat Abdullin. "Chemical Kinetics Software System for the Propulsion and Power Engineering". W 41st Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-854.

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SCHUTZENHOFER, L., H. MCCONNAUGHEY i P. MCCONNAUGHEY. "Role of CFD in propulsion design - Government perspective". W Aerospace Engineering Conference and Show. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1825.

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SINGH, RAJENDRA, i DONALD HOUSER. "Engineering science research issues in high power density transmission dynamics for aerospace applications". W 29th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-2299.

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