Propulsion Research Papers - Academia.edu (original) (raw)

This paper updates earlier thoughts by the author on a putative propulsion system. The concept was based around static electromagnetic momentum, as expounded in the "Feynman Disk" and experimentally verified by Graham and Lahoz. That said, naïve static electromagnetic momentum schemes to achieve linear translation are defeated by "hidden momentum" mechanisms, so too are simple arrangements just cycling the fields; we shall survey the flaws in their arguments. It may however be possible to achieve linear translation by means of arrangements of torques with a novel mechanism to break the symmetry of forces (or torques) on the second half of the cycle as the field is switched off. At the time of earlier presentation no mechanism could be found to explain the momentum balance for the process but it was believed that momentum was being given to the zero-point of the field. We show that it is possible to dump angular momentum and thence linear momentum to the ground state by standard quantum analysis of the EM field. None of this violates the conservation of momenergy.

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- Engineering, Physics, Theoretical Physics, Electromagnetism
- by Paul Price
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- Cosmology (Physics), Space Propulsion, Propulsion, Gravitational Physics

В монографії викладені теоретичні основи високовольтних техноло-гій у морській електроінженерії, вимоги класифікаційних товариств до морсь-кого високовольтного електроустаткування, основи безпечної експлуатації високовольтного електроустаткування, конструктивні особливості побудови електроенергетичних систем, систем захисту, а також процедури обслугову-вання і тестування електрообладнання напругою вище за 1000 вольт.
Матеріал монографії повністю охоплює вимоги мінімального стан-дарту компетентності Кодексу ПДНВ А-ІІІ/6 щодо підготовки суднових еле-ктромеханіків з компетенції «Експлуатація та технічне обслуговування сило-вих систем з напругою більше ніж 1000 вольт» та А-III/5 щодо підготовки суднових механіків з компетенції «Електрообладнання, електронна апарату-ра і системи управління на допоміжному рівні».
Монографія призначена для науково-педагогічних працівників, які займаються викладанням навчальних курсів з високовольтних технологій, інженерно-технічних працівників, для здобувачів вищої освіти зі спеціальнос-ті 271 «Річковий та морський транспорт» спеціалізацій: 271.03 «Експлуатація суднового електрообладнання і засобів автоматики» та 271.02 «Управління судновими технічними системами і комплексами», а також для суднового інженерно-технічного персоналу, що проходить, за вимогами безпечної екс-плуатації суднового високовольтного електричного устаткування, спеціаль-ний курс High Voltage Safety and Operational Procedures.
Схвалено рішенням Вченої ради НУ «ОМА» від 25.06.2020, Прото-кол № 9.

- by Vitalii Budashko
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- Electrical Engineering, Power Electronics, Propulsion, Electric Power Systems
- by Ian Blake
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- Information Theory, Propulsion, Nonlinear filters, Optimization
- by Rodolfo Bontempo and +1
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- Aerospace Engineering, Fluid Mechanics, Aeronautical Engineering, Aerodynamics
- by harsha kota
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- Mechanical Engineering, Aerospace Engineering, Propulsion
- by Geoffrey Swain
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- Biomimetics, Titanium, Propulsion, Elasticity

hands, arms and feet to the water and the aim in sport is to maximize effective propulsion minimizing energy. In previous studies we recorded propulsive force during tethered swimming and used bubbles to trace the water flow (Arellano et al, 2002, 2006)[1,2]. Vorticity in wakes was seen to be dominant in the best swimmers, whose circulation produced by both hands and feet (eddies or vortex structures) were more regular. When non-steady motions occur Zhukovsky’s condition is not met and unbound vortices are shed at the tips of the hands and feet in a turbulent 3D fashion forming a complex wake

- by Jose M. Redondo
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- Turbulence, Propulsion, Swimming, Bluff body wakes
- by Paul Gradl
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- Materials Science, Manufacturing, Laser, Space Propulsion
- by Luiz Aragao
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- Forestry, Remote Sensing, Spatial Analysis, Climate Change

The prospects for realizing a magnetohydrodynamic (MHD) bypass hypersonic airbreathing engine are examined from the standpoint of fundamental thermodynamic feasibility. The MHD-bypass engine, first proposed as part of the Russian AJAX... more

- by John Cole
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- Mechanical Engineering, Aerospace Engineering, Thermodynamics, Magnetohydrodynamics
- by Amir-Homayoun Javadi
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- Motion Planning, Propulsion, Stability, Path planning
- by Steven Oleson and +3
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- Mechanical Engineering, Aerospace Engineering, Propulsion, Electric Propulsion
- by Y. Young
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- Engineering, Vibrations, Multiphase Flow, Vibration

Climate change is a serious threat to the environment and socioeconomic globally. Climate change is caused by natural processes and due to human activities that have resulted in long-term climate fluctuations and even globally over the past few decades, the climate has experienced a fairly rapid rise in average temperatures. Climate change is mainly caused due to ozone depletion which results in changes in greenhouse effect conditions. The International Maritime Organization (IMO) has adopted standards to reduce sulfur pollution from ships. The majority of naval warships today use conventional mechanical propulsion systems where the power from the main propulsion is transmitted to the propeller through gearboxes. The ships owned by the Navy almost all still use conventional thrust systems with diesel engine starters. With a conventional support system. The latest innovation in the support system that has been carried out, namely on the United States Navy warship TAKE-1 (the destroyer ship), whereby changing the support system from conventional to electricity with the concept of Integrated Fully Electric Propulsion (IFEP) can reduce fuel use by 10% to 25%. IFEP application if applied to ships of the Navy, will obtain a very large benefit in overcoming environmental problems namely reducing air pollution.
Keywords: Integrated Fully Electric Propulsion (IFEP); Concept on Navy ships

- by Antariksa Sudikno
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- Mechanical Engineering, Propulsion, Electricity, CO2 emissions

The conference proceedings contained theses of the papers presented at the plenary and sectional meetings of the Scientific and Methodological Conference "Actual Problems of Ship Electроengineering, Electromechanics and Radioelectronics" held on December 15-16, 2015 at the National University "Odessa Maritime Academy".
The topics of the conference cover the following scientific and methodological directions: energy saving in marine energy, technical operation of modern electrical equipment and ship management systems, energy efficiency and reliability of electromechanical systems, information security, optimization of the operation of radio electronic devices and systems.

Ecuador es un país con una economía emergente, el
cual está comenzando a establecer una plataforma de
investigación en diferentes áreas de la tecnología. En
este marco, la industria aeroespacial se ve como un
campo prometedor de investigación, debido a las numerosas
ventajas para los servicios de vigilancia, transporte,
infraestructura, comunicaciones, entre otros.
Para mantener a la industria de la aviación en un
camino de desarrollo sostenible y favorecer el crecimiento
de esta en diversas áreas, es necesario crear
nuevos sistemas de propulsión los cuales presenten
beneficios en términos de consumo de combustible, reducción
de emisiones y ruidos. En este ámbito, nuevas
tecnologías como PTeD, BLI y HTS exhiben ventajas
potenciales para mejorar el desempeño de las aeronaves.
En el siguiente trabajo se utiliza un enfoque
paramétrico para presentar una revisión de estas tecnologías
y se examinan los beneficios que pueden
brindar en términos de consumo energético. También
se resaltan los desafíos que se necesitan vencer para
poder implantar esta tecnología en aeronaves.

- by Paul Gradl
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- Engineering, Mechanical Engineering, Aerospace Engineering, Materials Science
- by OMAR YAAKOB and +1
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- Propulsion, Propeller, Ship Hydrodynamics, Fishing Technology
- by Rupert Young
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- International Cooperation, Space Technology, Space Science, Propulsion
- by Catherine Tinsley
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- Organizational Learning, Risk Management, Market Research, Risk Taking

ABSTRACT The paper presents an analysis of performances for studied electrical machine designed for the propulsion of a special electric vehicle. This special vehicle is an electric scooter, usually used by people with physical disabilities. This particular electric scooter can be used by elders as well, offering them greater mobility, since, due to their physical health they are becoming more isolated in society. The electrical machine under study in this paper is axial flux permanent magnet synchronous machine. The analysis of the studied machine will be made analytically, numerically and experimental. The obtained results of the proposed solution will be related to a special electric scooter, powered by a dc motor, bought from the market.

- by Florin Jurca and +1
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- Propulsion, Power Generation, Magnetic Flux

The paper offers an analytical formulation of the two errors embodied in the momentum theory. The first one originates from to the use of the differential form of the axial momentum equation and the second one from the linearisation of the tangential velocity terms. Both errors are evaluated comparing the axial velocity at the disk as predicted by the momentum theories with that one obtained thorough a semi-analytical actuator disk method based on the exact solution of the flow. Several cases characterised by different values of the thrust and advance coefficient are analysed, and the range of validity of the momentum theories is discussed in depth.

- by Rodolfo Bontempo and +1
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- Mechanical Engineering, Hydrodynamics (Physics), Wind Energy, Aeronautical Engineering

The major objective of the present work is to study the thermal profile for a considered turbine Blade without Thermal Barrier Coating. Then, the thermal profile of the same blade with Thermal Barrier Coating is studied. A ceramic TBC coating like Yttria-stabilized Zirconia or SiC matrix composite is used as the coating for the turbine blade profile. Through extensive CFD analysis using NUMECA, the CFD tool used to generate and simulate the flow over the turbine blade, the objective is carried out. Flow behaviors over the two turbine blades and the data obtained post simulation are compared and the the effectiveness of the Thermal Barrier Coating is observed.

- by Hari Goutham Krishna and +2
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- Aerospace Engineering, GAS TURBINE, Propulsion, Computational Fluid Dynamics (CFD) modelling and simulation

The main task of the conference is to develop scientific and creative activity of students, graduate students and young scientists, involve them in solving current scientific and technical problems in the transport industry, discuss a wide range of new scientific and practical results of modern innovations and technologies in maritime and inland water transport. tasks of modern science, the formation of a single scientific and educational space, the establishment of scientific links between young scientists.

- by Vitalii Budashko
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- Electrical Engineering, Transportation Engineering, Education, Electronics

One of the most advantages of hybrid vehicles is that the wasted braking energy can be captured and reused during driving cycle. In this paper, a regenerative braking system for hydraulic hybrid vehicles is investigated. Based on... more

- by chou chou
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- Computer Science, Propulsion, Fluids, Regenerative Braking
- by Hiroyuki Ohsaki
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- Engineering, Materials Science, Finite element method, Propulsion

This is a particular section of the author's propulsion lab (group) project of which the author contributed the most in the making of the report. In general, the calculations that have been made in the consideration of the rocket aerodynamics can be differentiated into two different approaches – static & dynamics. The static takes into account the first moments, centroids & center of gravity. Whereas, the dynamics consists of peak height, the velocity of rocket, the time lapse, drag equation, the nozzle thrust & dynamic pressure. Nonetheless, most of the equations have been considered with few assumptions made. It is for certain that any possible discrepancy is inevitable in this particular section in comparison of the actual results obtained. Lastly, the results obtained are as follows: centre of gravity = 19 cm upward with respect to the nozzle-end; centre of pressure = 5 cm upward with respect to the nozzle-end; peak height = 33.69 cm; instantaneous velocity = 25.71 m/s; time of free-falling = 2.62 s; time of upward motion = 2.38 s; drag = 1.21 N; instantaneous nozzle thrust = 608.4 N; and dynamic pressure = 397.9 Pa.

- by Akmal Hafizi
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- Mechanical Engineering, Aerospace Engineering, Aerodynamics, Rocket Propulsion
- by Chand John
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- Mechanical Engineering, Biomedical Engineering, Biomechanics, Modeling

Purpose Pollutant emissions and energy management for vehicles are subjects well debated during nowadays. Current regulations concern all energy conversions from fuel to energy to wheel, taking into account all the possibilities for improving existing solutions to developing new innovative ones. The benefits coming from fuel conversion efficiency are addressing the immediate and specific needs for reducing fossil fuel consumption, greenhouse gasses and engine internal losses. The research purpose consists in finding new innovative solutions in order to reduce the energy losses and to increase power density for engines. Design/Methodology/Approach Several research activities confirmed the existence of some efficient engines already tested and produced. Different design solutions were used without including solutions for recovering heat, but obtaining 52% Brake Mean Efficiency and highly increased compression ratio. The fuel cell technology based on hydrogen utilization was considered by many specialists as the future global technology to be used on engines. The proposed researched engine is able to reach high internal pressure, high compression ratio and partially recovering energy losses as thermal losses from the exhaust gasses, the cooling system and the incomplete combustion. Based on the Patent RO130861, the researched engine has several design solutions. Starting from a double-state supercharged engine that reveals high compression ratio and high power density, an opposed pistons engine comes with several improvements: ultra-low noise and vibration level, reduced NOx, limited heat exchange, fuel economy, compact and robust shape. The hybrid engine is dedicated to hybrid powertrains and as the range extender for electric powertrains, being an easy to integrate and less expensive solution. Findings The researched approaches took into account the usage of different working fluids (water, liquid nitrogen, liquid air), but some of them are not able to facilitate the heat recovering. The opposed pistons engine has long expansion similar to the Atkinson cycle and two different places, the engine cylinder and the auxiliary cylinder. The auxiliary cylinder works as a pneumatic two-stroke engine. The hybrid engine used as range extender can be modular and easy to handle as a portable unit, its weight being almost 24 kg, offering the possibility to be used independently. The researched engine can be used as part of the power plants to generate electricity for backup system especially.

- by Liviu Giurca
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- Mechanical Engineering, Thermal Engineering, Combustion, Internal Combustion Engines
- by Yasser Kh
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- Propulsion, Propeller, Blades
- by Sravankumar Kota
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- Aerospace Engineering, Propulsion, Space Engineering, Deep Space Propulsion

One of the principal limitations of long duration human spaceflight beyond cis-lunar orbit is the lack of refuelling capabilities on distant planets resulting in the reliance on conventional non-cryogenic, propellants produced on Earth. If one could develop a reliable propulsion system operating on propellants derived entirely of ingredients found on nearby planetary bodies, then not only could mission duration be extended, larger amounts of payload could be ferried to and from the destination and eventually the cost of transporting propellant ingredients from Earth could be reduced, if not eliminated. Metal powder, in particular, aluminium burns energetically with oxygen and affords an impressive exothermic reaction that can be utilised for propulsive force. The oxidiser component of an aluminium powder based propellant can be in the form of pure oxygen, air, steam or a compound such as ammonium perchlorate (AP) making it ideal for terrestrial applications. So much so, that aluminium powder as a fuel has been investigated intermittently for over sixty years for military applications such as to propel torpedoes using an oxidiser in the form of steam produced by drawing in seawater, ram-air as an oxidiser for air-launched ram jet missiles and AP in powder form which when combined and ignited with aluminium powder results in combustion which can deliver a propulsive force suitable for long range surface-to-surface missiles. In terms of space applications , the logic of employing oxygen/aluminium metal powder as an in-situ resource utilisation (ISRU) propulsion concept is due to the fact that the propellant combination are constituent chemicals that can be found on numerous planetary bodies and thus existing research could be adapted and enhanced for possible employment in space based systems. Therefore the technological readiness level is not as complex as if one were to develop an entirely new propulsion system. Living off the land to realise extended duration residency on extra-terrestrial bodies of interest is not exactly a revelation. Metal powder propulsion systems have been addressed intermittently since the Second World War, initially in the field of underwater propulsion where research in the application of propelling torpedoes continues until this day. During the post war era, researchers attempted to utilise metal powders as a fuel for ram jet applications in missiles. The 1960's and 1970's saw additional interest in the use of 'pure powder' propellants, i.e. fluidised metal fuel and oxidiser, both in solid particulate form. Again the application was for employment in space-constrained missiles where the idea was to maximise the performance of high energy density powder propellants in order to enhance the missile's flight duration. Metal powder as possible fuel was investigated for in-situ resource utilisation propulsion systems post-1980's where the emphasis was on the use of gaseous oxygen or liquid oxygen combined with aluminium metal powder for use as a " lunar soil propellant " or carbon dioxide and magnesium metal powder as a " Martian propellant ". Albeit aluminium metal powder propellants are lower in performance than cryogenic and Earth storable propellants, the former does have an advantage inasmuch that the propulsion system is generic, i.e. it can be powered with chemicals mined and processed on Earth, the Moon and Mars. Thus, due to the potential refuelling capability, the lower performing aluminium metal powder propellant would effectively possess a much higher change in velocity (∆V) for multiple missions than the cryogenic or Earth storable propellant which is only suitable for one planet or one mission scenario, respectively. This paper reviews existing metal powder propulsion systems, while emphasising the option of oxygen/aluminium metal powder as a propellant, in order to highlight the potential of this near-term concept.

- by Abdul M Ismail
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- Space Propulsion, Rocket Propulsion, Propulsion

Median Paired Fin Propulsion used by fishes like knife fish, has the potential to replace current energy inefficient underwater propulsion systems. This paper quantizes the efficiency of a fin mechanism based on its ability to incorporate a large number of undulations. Characteristic ellipses of a mechanism were defined, based on which two algorithms were defined to measure the capabilities of the mechanism. The available workspace of the mechanism was optimized to accommodate the undulation requirements of the robot based on the formulations. Further, the distortion effect on the waveform was identified and the optimization was redefined to obviate its possibility while in operation.

- by Ajith Anil Meera
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- Engineering, Mechanical Engineering, Robotics, Marine Biology
- by Bala Ji
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- Propulsion, Jet Engines

This paper focuses on the calculation methodology of the thrust of a ACHEON propulsion system, which is based on Coanda effect deflection of thrust. It defines a calculation methodology based on integral equations. The proposed methodology allows an effective calculation of the performances and the force applied on the airplane by such a propulsion system. It will also allow an effective design of the nozzle system and will implement also internal elements with an accurate definition of frictional losses. Outstanding results have been obtained together with general rules for implanting ACHEON propulsion inside an aircraft.

- by Michele Trancossi
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- Aerospace Engineering, Design, Computational Fluid Dynamics, Fluid Mechanics

Additive Manufacturing (AM) of metals is a processing technology that has significantly matured over the last decade. For liquid propellant rocket engines, the advantages of AM for replacing conventional manufacturing of complicated and expensive metallic components and assemblies are very attractive. AM can significantly reduce hardware cost, shorten fabrication schedules, increase reliability by reducing the number of joints, and improve hardware performance by allowing fabrication of designs not feasible by conventional means. The NASA Marshall Space Flight Center (MSFC) has been involved with various forms of metallic additive manufacturing for use in liquid rocket engine component design, development, and testing since 2010. The AM technique most often used at the NASA MSFC has been powder-bed fusion or selective laser melting (SLM), although other techniques including laser directed energy deposition (DED), arc-based deposition, and laser-wire cladding techniques have also been used to develop several components. The purpose of this paper is to discuss the various internal programs at the NASA MSFC using AM to develop combustion devices hardware. To date at the NASA MSFC, combustion devices component hardware ranging in size from 100 lbf to 35,000 lbf have been designed and manufactured using SLM and deposition-based AM processes, and many of these pieces have been hot-fire tested. Combustion devices component hardware have included thrust chamber injectors, injector components such as faceplates, regeneratively-cooled combustion chambers, regeneratively-cooled nozzles, gas generator and preburner hardware, and augmented spark igniters. Ongoing and future developments for combustion devices have also included design of components sized for boost-class engines. Several design and hot-fire test iterations have been completed on these subscale and larger scale components, and a summary of these results will be presented as well.

- by Paul Gradl
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- Engineering, Mechanical Engineering, Aerospace Engineering, Manufacturing

Additive manufacturing is increasing in prevalence and importance across many industries. This tutorial will provide a thorough introduction to the technologies involved, the typical manufacturing process, and common design considerations... more

Additive manufacturing is increasing in prevalence and
importance across many industries. This tutorial will provide a
thorough introduction to the technologies involved, the typical
manufacturing process, and common design considerations using
this new technology.

- by Paul Gradl
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- Manufacturing, Systems Engineering, Lean Manufacturing, Space Propulsion
- by Paul Gradl
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- Materials Science, Manufacturing, Systems Engineering, Lean Manufacturing
- by Yasser Kh
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- Space Propulsion, Rocket Propulsion, Propulsion, AEROSPACE PROPULSION
- by L Caveny
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- Mechanical Engineering, Aerospace Engineering, Propulsion
- by John Evans
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- Propulsion, AEROSPACE PROPULSION, Airbag propulsion
- by Victor Vilnrotter
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- A Priori Knowledge, Propulsion, Antenna arrays, Spatial Information
- by Venkatesh Re
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- Mechanical Engineering, Aerospace Engineering, Aeronautical Engineering, Propulsion