Propulsion Technology Research Articles

Futuristic Exploring of Ionic Wind Technology and Wind-Assisted Propulsion in a Comprehensive Journey

This research investigate into the convergence of ionic wind technology and wind-assisted propulsion, presenting a combined approach to enhance propulsion systems in diverse applications. Ionic wind, characterized by electro aerodynamic propulsion, involves the generation of ions through electrostatic fields to induce controlled airflow. Concurrently, wind-assisted propulsion leverages natural wind currents to amplify the thrust of vehicles or devices. Through a systematic investigation, this study aims to unravel the potential benefits, address the associated challenges, and illuminate the synergies emerging from the seamless integration of these innovative propulsion technologies.

Innovations in Laser-Driven Plasma Propulsion Systems for Space Exploration

Laser propulsion has emerged as a promising technology for revolutionizing space exploration by offering rapid and efficient spacecraft propulsion. This paper proposes a novel system that integrates dense corona discharge with electrical mechanisms to significantly enhance the efficiency and effectiveness of laser propulsion. Leveraging plasma physics and laser technology, this system harnesses the synergy between dense plasma and laser-driven propulsion, significantly exceeding the capabilities of conventional systems. Theoretical analysis and computational simulations reveal the potential for increased thrust, improved energy conversion efficiency, and enhanced controllability, paving the way for next-generation spacecraft propulsion technologies.

Bibliometric Study of Life Cycle Analysis Applied to Motor Vehicles

Purpose: Conducting a bibliometric analysis of papers on the Life Cycle Assessment (LCA) of motor vehicles published over the last 20 years. Theoretical framework: Bibliometric analysis, a discipline within scientometrics, uses mathematical and statistical methods to synthesize and evaluate publications, identifying trends and structures in specific research fields. Method: The bibliometric analysis was conducted using data from Scopus and Web of Science, and it assessed the impact and trends of scientific production, correlating keywords to explore connections between themes. Articles from the last two decades were analyzed to quantify the relevance of the studied topic. Results and conclusion: Using the Bibliometrix algorithm in R, 512 published articles were analyzed. The results indicated a significant increase in research output in this field of study, as demonstrated by the substantial growth in the number of published articles and citations. Research implications: This bibliometric study reveals key trends and guides future innovations in the environmental and transportation sectors, highlighting the transition towards more sustainable options. Originality/value: This groundbreaking work provides valuable insights into the life cycle of vehicles with various propulsion technologies, emphasizing the evolution and environmental impacts of electric, hybrid, internal combustion, and fuel cell vehicles.

A Review of the Current Regulatory Framework for Supersonic Civil Aircraft: Noise and Emissions Regulations

The request for faster and greener civil aviation is urging the worldwide scientific community and aerospace industry to develop a new generation of supersonic aircraft, which are expected to be environmentally sustainable, and to guarantee a high level of protection for citizens. The availability of novel propulsive technologies, together with the development of new civil supersonic passenger aircraft configurations and missions, is pushing international authorities to update the regulatory framework to limit nuisances on the ground and the contribution to climate change. Existing ICAO noise and emissions standards are outdated as they were developed in the 1970s and tailored to Concorde, the only SST that has ever operated in Western airspace. This article provides (i) a comprehensive review of current environmental regulations for SST, encompassing noise and pollutant emissions near airports (LTO cycle) as well as CO2 emissions and sonic booms, and (ii) updated information about the ongoing rulemaking activities by ICAO, FAA and EASA. This review clearly highlights the following findings: (i) the need to revise current rules to better fit future SST design, operations and technologies; (ii) the need to introduce new regulations to cover additional aspects, including stratospheric water vapour emissions and ozone depletion; and (iii) the need to support regulatory activities with solid technical bases, fostering cooperation with academia, research centres and industry in R&D projects. Eventually, a practical example of how SST rulemaking activities are supported by the collaborative research H2020 MORE&LESS is reported.

Numerical modelling of stepped helical cooling channels

The automotive industry is in the midst of a radical change of propulsion technology to meet the increasingly stringent limits on emissions and fuel consumption. Electric and hybrid power-trains are progressively replacing their internal combustion counterparts, as they are more efficient, especially in transient operation. In electric and hybrid vehicles effective cooling system operation is of utmost importance as it influences directly the efficiency and power density levels achievable by the power train. Thus, accurate analyses are needed to maximize the thermal performance of these systems. In this work an electric motor cooling jacket, that features a stepped helical geometry, is studied by means of CFD, with a particular focus on the head losses. The periodicity of the cooling channels geometry along the helical development is exploited to reduce the computational domain to a basic periodic module. The flow field is determined by applying a 3D Finite Volume approach, and numerical solutions are obtained by means of a validated incompressible solver. Novel boundary conditions are purposely developed to allow for the coupling of the inlet and outlet patches, which are roto-translated with respect to each other. The sensitivity of integral results on friction losses, with respect to the number of periodic modules included in the model, is investigated. The developed numerical model is employed to obtain a suitable correlation for the equivalent Darcy friction factor as a function of the Reynolds number only. Finally, a first estimation of the total head losses is obtained by using the Darcy Weisbach formula along with the aforementioned friction factor correlation.

Route Planning Based on Parallel Optimization in the Air-Ground Integrated Network

Recent advancement in propulsion technologies to reduce the need for travel or increase the share of sustainable unmanned devices has accelerated the shift toward sustainable transport. To achieve the optimization of route planning in the air-ground integrated network (AGIN), we design an optimization strategy of accompanying graph navigation for unmanned devices, which aims to reduce the power consumption and <inline-formula xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink"> <tex-math notation="LaTeX">$CO_2$</tex-math> </inline-formula> gas emissions. The optimization of accompanying graph navigation is composed of three strategies, namely, the navigation based on the complete maps, the navigation based on the partitioned maps, and the navigation without maps. We propose a Two-tiered Grid (TG) index and Distributed AGIN Navigation (DAN) to navigate on partitioned maps. The top layer of the TG-index is composed of the border vertices of the global road network, which reflects the overall traffic conditions of the global road network and provides coarse-grained navigation routes. The bottom layer is a grid index composed of subgraphs, which reflects traffic conditions in local areas and provides fine-grained navigation routes. The navigation optimization is implemented in several segments, which can be run by multi-processors and realize rapid response to a large number of concurrent queries.

Numerical Prediction of Aerodynamic Noise for a Propeller-wing Configuration and an Investigation of Pitch Effect

Driven by the sustainable and eco-friendly vision of aviation, Distributed Electric Propulsion (DEP) technology has received much attention for its high aerodynamic efficiency. Simultaneously, lower noise emissions from DEP configurations are desired and therefore it is important to investigate the aerodynamic noise features, which include but are not limited to the noise generation mechanism and the effect of propeller-propeller/wing interactions. This paper focuses on a numerical approach, which is suitable for industrial practice, for predicting the aerodynamic noise of propeller-wing configurations. A generic DEP configuration is employed, consisting of a Mejzlik 2-blade propeller installed on the leading edge of a NACA0018 airfoil. A hybrid method of computational aeroacoustics has been performed in the present simulations, where aeroacoustics in the near field is solved by coarse-grid compressible large-eddy simulations and then the acoustic far field is calculated by the Ffowcs-Williams Hawkings analogy. The influence of grid resolution is studied based on Pope's criterion M and satisfactory results are achieved at a moderate mesh count as compared to the experimental measurements. Further simulations are conducted to investigate the effect of propeller pitch on the aerodynamic performance, noise generation and propeller-wing interactions.

Propulsion Control and Autonomous Systems: Advancements, Challenges, and Prospects

This research paper explores the dynamic intersection of propulsion control and autonomous systems, shedding light on the evolving landscape of propulsion technologies integrated with advanced autonomous capabilities. The integration of these two domains has the potential to revolutionize various industries, including aerospace, automotive, maritime, and space exploration. This paper provides an in-depth analysis of the current state of propulsion control and autonomous systems, highlights key advancements, addresses challenges, and outlines potential future directions for research and development.

Ground testing of Al-polyurethane shape memory polymer sail material under pulsed light exposure

This article presents a study on design and testing of space sails using Al-polyurethane Shape memory polymer. The properties of the polymer are simulated and tested in the design phase, and the results are compared with the fabricated sail, which is considered nominal. The efficiency of the polyurethane sail is found to be approximately 86.5%. The controllability of the sail is enhanced using a heating system that uses light rays to heat the polymer at specific control spots. The relative deflection at these spots causes a deviation in solar momentum, resulting in a controlled displacement of the sail. This control system is found to be 42% more efficient than conventional vane-type deflection systems. The paper also presents the fabrication of a ground testing apparatus designed to test the sail specimen in laboratory conditions. The apparatus is capable of producing a vacuum chamber pressure up to −400 mm/Hg and includes a magnetic levitation platform with strong permanent magnets to neglect local gravitational effects. The platform provides support for fixing the solar sail frame made from carbon fiber composite material. The testing apparatus consists of a 1000-W halogen light source with intensity ranges of approximately 200,000 lux. Sail material with a reflective surface is exposed to controlled luminance under vacuum conditions to measure the deflection of the sail. Deflection values are recorded by means of a resistance type strain gauge and strain indicator arrangement. Plotting deflections with time period gives the acceleration of the sail inside the test apparatus. A coolant chamber with a ceramic base is also provided to reduce temperature effects inside the vacuum chamber. In conclusion, this study presents a promising approach for the design and testing of solar sails using shape memory polymer and a ground testing apparatus. The results of this research can contribute to the development of more efficient and versatile solar sail technology for fuel-free aerospace propulsion.

Time- and Energy-Saving Potentials of Efficient Urban Air Mobility Airspace Structures

Novel electric propulsion technology has given rise to thinking about urban air mobility in a new way with its expected high degree of operational flexibility. The designs of electric vertical takeoff and landing configurations are determined by their mission profile, which we found to be oversimplified at many points in the current scientific literature. There is a gap of understanding in how mission profiles impact travel time and energy demand. In this paper, we review various mission designs, formulate a five-segment flight profile (including vertical ascent, climb, cruise, descent, and vertical approach), and apply it on a fleet level of up to 200,000 urban air mobility trips. The demand data originate from the Upper Bavaria region study, OBUAM. In a sensitivity study, we vary the cruise altitude, the height of the vertical flight segments, and the climb and descent angles for two vehicle configurations: a fixed-wing tilt-rotor concept, and a multicopter concept. The main findings for the fixed-wing concept are that the height of the vertical flight segments and the cruise altitude should be as low as possible, and small climb angles (below 7 deg) should be avoided. The multicopter concept, however, is penalized by fast forward flight while being comparatively insensitive to both the cruise altitude and height of the vertical flight segments. Furthermore, we found a tradeoff between time- and energy-optimal flights with the a energy-optimized climb/descent angle at around 10 deg.

An Overview of Current Challenges and Emerging Technologies to Facilitate Increased Energy Efficiency, Safety, and Sustainability of Railway Transport

This article presents a review of cutting-edge technologies poised to shape the future of railway transportation systems, focusing on enhancing their intelligence, safety, and environmental sustainability. It illustrates key aspects of the energy-transport-information/communication system nexus as a framework for future railway systems development. Initially, we provide a review of the existing challenges within the realm of railway transportation. Subsequently, we delve into the realm of emerging propulsion technologies, which are pivotal for ensuring the sustainability of transportation. These include innovative solutions such as alternative fuel-based systems, hydrogen fuel cells, and energy storage technologies geared towards harnessing kinetic energy and facilitating power transfer. In the following section, we turn our attention to emerging information and telecommunication systems, including Long-Term Evolution (LTE) and fifth generation New Radio (5G NR) networks tailored for railway applications. Additionally, we delve into the integral role played by the Industrial Internet of Things (Industrial IoT) in this evolving landscape. Concluding our analysis, we examine the integration of information and communication technologies and remote sensor networks within the context of Industry 4.0. This leveraging of information pertaining to transportation infrastructure promises to bolster energy efficiency, safety, and resilience in the transportation ecosystem. Furthermore, we examine the significance of the smart grid in the realm of railway transport, along with the indispensable resources required to bring forth the vision of energy-smart railways.

Investigation on unsteady thermal process of NEPE propellant based on an refined chemical kinetic model

This study presents a sophisticated investigation into the intricate heat and mass transfer mechanisms of NEPE composite propellant under realistic rocket motor conditions, with particular emphasis on the rapid depressurization effects. To accomplish this, we have developed an innovative particle packing algorithm coupled with a novel semi-global kinetics model. By integrating detailed chemical kinetics models for Ammonium perchlorate (AP) oxidizing powders, Cyclotetramethylene tetranitramine (HMX) oxidizing powders, and Nitroglycerin/1,2,4-Butane triol trinitrate (NG/BTTN) fuel-binder, we have constructed a meso-scale model of NEPE propellant based on comprehensive experimental data. Furthermore, a refined 9-step kinetic mechanism has been incorporated into the meso-scale model, along with a pressure drop model that accurately captures the intricate gas reaction domain. The predicted parameters of NEPE propellant have been meticulously compared with experimental results, demonstrating a remarkable level of agreement. Moreover, meticulous analyses have been carried out to investigate the complex thermal processes exhibited by this composite propellant under the challenging conditions of rapid depressurization combustion. These analyses primarily focus on unraveling the dynamic evolution of the gas-solid phase and the underlying thermal regression mechanism of the solid phase. Notably, our findings reveal intriguing temporal changes in local heat flux feedback spikes throughout the entire depressurization process, owing to the intricate topology structure of NEPE propellant, which comprises multiscale oxidizing micro-particles embedded within a fuel-binder matrix. This research significantly enhances our understanding of the thermal behavior and performance characteristics of NEPE composite propellant, thereby paving the way for future advancements in rocket propulsion technology.

Elliptical Orbit Design Based on Air-Breathing Electric Propulsion Technology in Very-Low Earth Orbit Space

Very-low Earth orbit (VLEO) space below 200 km is essential for high-quality communications and near-Earth space environment detection. Due to the significant atmospheric drag, orbital maintenance is required for spacecraft staying here. Based on air-breathing electric propulsion (ABEP) technology, this paper analyzed the orbital boundary conditions of the spacecraft under the constraints of parameters including slenderness ratio, thrust-to-power ratio, drag coefficient, and effective specific impulse. The energy balance is the key constraint for low VLEO orbits, which is determined by the drag coefficient, slenderness ratio, and thrust-to-power ratio. Under the existing technical conditions, the lowest circular orbit (along the terminator) is about 170 km. An elliptical orbital flight scheme is also analyzed to reach a 150 km perigee. A half-period control method was proposed based on the on–off control method for the elliptical orbit, which could enable the spacecraft to maintain a stable 150–250 km elliptical orbit.

A multi-objective variable-specific impulse maneuvers optimization methodology

The problem of optimizing variable-specific impulse electric propulsion maneuvers is presented, proposing a novel multi-objective methodology for the computation of near-optimal planetocentric solutions. The methodology relates a parameter expressing the instantaneous maneuvering efficiency, or thrust effectivity, with the specific impulse through an arbitrary parametric function. The parameters of this function are determined by a multi-objective genetic algorithm, which minimizes propellant consumption and maneuver duration. The study includes the analysis of several scenarios, with the results demonstrating that the methodology can be successfully employed in the context of space mobility of small satellites. The findings reveal that variable-specific impulse maneuvers can achieve improvements exceeding 17% in both propellant mass and maneuver duration compared to a constant-specific impulse case. Consequently, the resultant Pareto fronts showcase enhanced trade-offs and more favorable solutions for the optimization problem. The results highlight the significance of this optimization methodology for electric propulsion technologies with throttling capabilities, particularly in systems with near-constant propulsive efficiency.

Experimental demonstration of forced initiation of kerosene oblique detonation by an on-wedge trip in an ODE model

The first free-jet experiment of a kerosene-fueled oblique detonation engine, conducted in a large-scale hypersonic shock tunnel, is reported in this paper. A novel initiation-control technique using a small on-wedge trip is proposed to overcome the initiation issue of oblique detonation waves (ODWs) encountered when liquid hydrocarbon fuel is used. The results show that the kerosene-fueled ODW fails to initiate within the length-limited combustor without the trip but is successfully initiated when the trip is used, which demonstrates the effectiveness of the proposed initiation-control method. The feasibility of kerosene-fueled oblique detonation propulsion technology is also demonstrated.Novelty and significance statement The feasibility of liquid-hydrocarbon-fueled oblique detonation propulsion technology was demonstrated by performing free-jet shock tunnel experiments of a kerosene-fueled oblique detonation engine. To address the initiation issue of oblique detonation waves encountered when liquid hydrocarbon fuel such as kerosene is used, a novel but simple initiation-control technique was proposed and experimentally validated. Stabilized oblique detonation waves were implemented in the combustor, and the detailed flow structures of different oblique detonation combustion modes were clarified. The proposed technique and the results provide significant reference to the future development of oblique detonation engines.

REVIEW OF SOUTH-KOREAN PATENT SOLUTIONS ON MODULAR PROPULSIVE CHARGES FOR 155 mm ARTILLERY MUNITIONS

Five patent descriptions of South Korean in-ventions on modular artillery propulsive charges and their basic elements creating such propulsive charges used in 155mm artillery ammunition, were presented. Above inventions were filed to the Korean Intellectual Property Office in years 1992-2019. Three inventions deal with central ignition systems situated inside the modular propulsive charges, and a first of the remaining two relates to double-base smokeless powder charges surrounding the central ignition systems and the second to construction of combustible containers of the modular charges. Presented inventions describe material parameters, geometry of particular elements of the propulsive modules and technologies of their manufacture. ballistics,chemical technology,modular propulsive charges for 155 mm howitzer munitions,central ignition systems,combustible tubes,smokeless powders,combustible containers,Korean inventions

A brief overview on iron oxide nanoparticle synthesis, characterization, and applications

Hematite (α-Fe2O3), magnetite (Fe3O4), and maghemite (γ-Fe2O3) are only a few of the polymorphic forms of iron oxide, a mineral component. Hematite and maghemite, solid propulsion technology nanoparticulate materials, perform exceptionally well during the thermal degradation of ammonium perchlorate. Due to their larger particle size, more active sites, and increased surface area, which encourages more gas adsorption during thermal oxidation reactions, metallic iron oxide nanoparticles have an enhanced catalytic impact. Currently, a variety of techniques, including co-precipitation, sol–gel, microemulsion, and thermal decomposition, can be used to create metallic iron nanoparticles. The literature contains information on these synthetic processes, but there is a dearth of information on nanoparticulate oxides and the methods used to characterise them. The methods for generating nanoparticulate iron oxides, the key features of the various characterization techniques, as well as information regarding the breakdown properties of these nanomaterials are presented in this concise review based on scientific papers, containing data from the last two decades. Transmission electron microscopy, scanning electron microscopy, X-ray powder diffraction, and Fourier transform infrared spectroscopy can all be used to describe the morphologies and structures of iron oxides. Physical adsorption techniques are typically used to determine the textural qualities.

Sunflower mission concept for high-altitude earth observation in LEO via nanosatellite with pyramidal solar sail

Solar sails are an attractive technology for propellant-free propulsion, especially in small satellites with tight power and mass budgets. Several recent missions have shown promising applications of solar sails for nanosatellite orbital control in low Earth orbit (LEO). They enable easier access to and removal from high-altitude orbits. Since solar radiation pressure produces torques in addition to forces, a solar sail can also be used for low-power attitude control. Few missions have exploited this effect. In response, this paper proposes a new nanosatellite mission concept, only achievable by combined orbit-attitude control via solar sail: the sunflower mission, for high-altitude wide-area Earth observation. A realistic sail design meeting the mission requirements is obtained via parametric analysis and comprehensive review of past missions. A pyramid-shaped sail is proposed for the mission, and its advantages and drawbacks are analysed. The dynamics are evaluated using a high-fidelity numerical simulator with all relevant physical perturbations in LEO. The imaging objectives are successfully achieved over a multi-year duration. The sail also provides propellant-free orbit insertion from a low-altitude launch orbit, and fast de-orbit at end-of-life. It uses less power and has a smaller stowed size than several competitor technologies for orbit-attitude control of LEO nanosatellites.

AI-Integrated Mechanical Engineering Solutions for Next-Gen Rocket Propulsion Systems

The integration of Artificial Intelligence (AI) into the field of mechanical engineering has heralded a new era of innovation and efficiency, particularly in the realm of next-generation rocket propulsion systems. This abstract explores the transformative impact of AI in the development and optimization of rocket propulsion technologies, highlighting its potential to revolutionize the aerospace industry. AI-powered mechanical engineering solutions have emerged as a game-changer in the design and manufacturing of rocket propulsion systems. Through advanced machine learning algorithms and predictive analytics, AI can significantly enhance the efficiency of the development process. By analyzing vast datasets of historical performance data, AI can identify patterns and correlations that human engineers might overlook. This allows for the creation of propulsion systems that are not only more powerful but also safer and more reliable. AI plays a pivotal role in the optimization of rocket engines. Traditional optimization methods often require extensive computational resources and time-consuming simulations. AI, on the other hand, leverages neural networks and genetic algorithms to rapidly iterate through design possibilities, resulting in propulsion systems that are finely tuned for maximum performance and fuel efficiency. This not only reduces development costs but also accelerates the time-to-market for next-gen rocket propulsion systems. Safety is paramount in rocket propulsion systems, and AI offers innovative solutions in this regard as well. AI algorithms can continuously monitor and analyze sensor data during rocket launches, quickly identifying anomalies and potential issues.[1] This real-time monitoring allows for immediate corrective actions, reducing the risk of catastrophic failures and ensuring the safety of crewed and uncrewed missions. AI-integrated mechanical engineering solutions enable autonomous maintenance and diagnostics of propulsion systems. Through predictive maintenance models, AI can predict when components are likely to fail and schedule maintenance activities accordingly. This proactive approach not only extends the lifespan of propulsion systems but also minimizes downtime and operational disruptions.

A Review of Machine Translation Techniques and Proposal to Automatic Translation of Videos

Translation of videos including propulsion technology videos has been one of the toughest jobs to do during the eLearning development process. We have tried it earlier by involving mostly manual work and found it to be tiresome. After the fast evolution of Machine learning and Natural language processing techniques, it is feasible now to do the translation involving and inculcating intelligent techniques in the process. We have reviewed the technologies and techniques and presenting it in this paper.