Propulsion System Selection Research Articles

A holistic approach for efficient greener in-space propulsion

This paper presents a comprehensive framework for designing in-space propulsion systems, integrating four criteria: global propulsive performance, environmental impact, cost efficiency, and architectural reliability. The study focuses on the emerging class of Orbital Transfer Vehicles to illustrate the application of this method. By examining the synergistic potential of OTVs and greener propellants, the paper addresses different mission scenarios, including LEO, GEO, and lunar missions, with both scientific and commercial objectives. The proposed framework aims to go beyond traditional cost-centric approaches, offering a more complete evaluation method for early design phases. A case study comparing three liquid bipropellant options, pressure-fed MON-3/MMH, 98%-HTP/RP-1, and self-pressurizing N2O/Ethane, demonstrates the utility of the tool. Findings suggest that scientific missions benefit most from 98%-HTP/RP-1, while traditional propellants remain preferable for cost-driven commercial missions to GEO and the Moon, though greener alternatives are competitive for less demanding LEO missions. This innovative framework aims to guide the selection of propulsion systems to achieve greener space missions, aligning traditional performance figures with environmental responsibility.

Optimizing Propellant Distribution for Interorbital Transfers

The advent of space exploration missions, especially those aimed at establishing a sustainable presence on the Moon and beyond, necessitates the development of efficient propulsion and mission planning techniques. This study presents a comprehensive analysis of chemical and electric propulsion systems for spacecraft, focusing on optimizing propellant distribution for missions involving transfers from Low-Earth Orbit (LEO) to Geostationary Orbit (GEO) and the Lunar surface. Using mathematical modeling and optimization algorithms, we calculate the delta-v requirements for key mission segments and determine the propellant mass required for each propulsion method. The results highlight the trade-offs between the high thrust of chemical propulsion and the high specific impulse of electric propulsion. An optimization model is developed to minimize the total propellant mass, considering a hybrid approach that leverages the advantages of both propulsion types. This research contributes to the field of aerospace engineering by providing insights into propulsion system selection and mission planning for future exploration missions to the Moon, Mars, and Venus.

Decision-making model for propulsion system selection

History it has become evident that the military industry and its thriving action has generated change and development in different areas, and it is to be expected that a project as ambitious as the Strategic Surface Platform - PES focuses on the impact that internal combustion systems can generate in the design, therefore an evaluation model is developed for the selection of the propulsion system of the platform, which was based on the life cycle cost and performance of the main mechanical equipment, providing an additional tool for decision making. The cost side was estimated by breaking down the ROM (Rough Order of Magnitude) acquisition costs, maintenance costs and fuel and lubricant consumption costs, which leaves the performance side evaluated under the technical characteristics, considering the criteria of performance, reliability, delivered power and installation footprint; without leaving aside the mandatory requirements such as IMO TIER III gas emissions, reduction of the acoustic signature and the use of redundancy.

Selection of Propulsion System for Electric Amphibious Bus to Alleviate Traffic Congestion in the Jabodetabek Area

High vehicle growth in Jakarta is not balanced with traffic growth, the level of congestion in Jakarta continues to increase every year. To overcome this congestion, innovation is needed to utilize the river as a means of public transportation. The amphibious bus is an alternative public transportation option in the Jabodetabek area to break congestion. The amphibious bus design must be supported by a propulsion system that can operate on land and water. The amphibious bus propulsion system is a must, according to river conditions and operational requirements. The selection of the drive system is carried out by means of analysis The driving criteria factors needed according to the specifications of the amphibious bus are power, efficiency, size, cost, and maneuverability. These criteria become indicators in determining the type of mover. This study aims to select the prime mover system based on criteria and specification requirements. The selection uses the process hierarchy analysis (AHP) method by giving weight to the criteria for each driver, and type of mover in the water, namely waterjets, azimuth-podded, Paddle Wheels, Cycloidal Propellers and propulsion on land diesel engines, gasoline engines, and electric engines. The results showed that the order of the propulsion selection criteria was propulsion power being the top priority, followed by maneuverability, energy efficiency, cost, operational and investment, and propulsion size and weight. The results of the AHP show that the main options are propulsion systems in water, namely waterjets and diesel engine propulsion systems on land. System Water Jet has a propulsion power of 1000 kW, has high maneuverability, energy efficiency of 85%, and a maximum speed of 60 Km/hour so it can meet the specifications of an amphibious bus drive. For operations on land, the main choice of propulsion system for amphibious buses is a diesel engine with a power of 250 HP and 800 Nm of torque providing strong torque and a wide cruising range. This system has a range of up to 800 km, a maximum speed of 120 km/h, and exhaust emissions of Euro 5.

Design and development of an autonomous unmanned aerial vehicle for surface coalmines surveillance

This paper presents a detailed investigation into the development of a specialized unmanned aerial vehicle (UAV) for practical applications in coal mining. The main focus is on enhancing surveillance capabilities, identifying potential hazards, and supporting various coal mine activities. This study initiates with the careful design of a quadcopter, taking into account essential parameters such as VTOL, maneuverability, and hover efficiency. The quadcopter model is meticulously developed to ensure smooth operation under ideal conditions. The design process involves utilizing SolidWorks software to create a robust and optimized quadcopter model. Additionally, the static deformation simulation of the quadcopter is conducted using Ansys software, providing valuable insights into its structural integrity and performance. Dynamic modelling using the Bond Graph Method enables a thorough understanding of the quadcopter’s behavior and informs propulsion system selection. The chosen propulsion system prioritizes maximizing thrust-to-weight ratio to about 2:1, achieving the factor of safety of approximately 4, and ensuring maneuverability. The use of eCalc, an online open-source software, assists in identifying the ideal motor-propeller combination for optimal thrust characteristics. Surveillance and mapping techniques are explored in detail. A step-by-step methodology is proposed for image identification, while mapping is achieved through image stitching and path planning using waypoints. Additionally, volume estimation and vulnerability assessment methods specific to coal mining are discussed.

Design and Experiment of Ecological Plant Protection UAV Based on Ozonated Water Spraying

With the development of pesticide substitution technology, ozonated water has been gradually applied in agricultural plant protection. This paper describes our development of an ecological plant protection unmanned aerial vehicle (UAV) that can produce and spray ozonated water while flying. Firstly, this paper carries out the design of the ozonated water system, including the selection of the ozone generator and the gas-liquid mixing method. Secondly, the conceptual design method of the ecological plant protection UAV is introduced, including total weight estimation, propulsion system selection, layout and structure design, battery modeling, center of gravity evaluation, and control system. Then, static analysis was computed in ANSYS Workbench on the UAV fuselage. Finally, the field test verified that the hovering time of the UAV could reach the design requirement of 10 min when it was fully loaded. The effective spraying width (with a height of 2 m and a speed of 3 m/s) is 5.25 m. The UAV was used to spray ozonated water with a concentration of 17 ppm continuously once a day; on day 7, the control effect could reach 76.4% and the reduction rate of the larvae population was 59.3%. Therefore, spraying ozonated water with a concentration of 17 ppm every day by using the ecological plant protection UAV can effectively control broccoli diamondback moth larvae and achieve the control effect of traditional pesticides (Chlorantraniliprole SC).

The Selection of Propeller and Primary Engine Matching of A 30 GT Fishing Vessel (Case Study KM Inka Mina 759)

Reducing fuel consumption and carbon emissions in the development of ship propulsion systems following the required Energy Efficiency Design Index (EEDI) has become a concern for the fishing industry as determined by the International Maritime Organization (IMO). This study analyzes the suitability of using a 30 GT fishing vessel propeller and propulsion engine for optimum efficiency. The analysis focuses on developing a propulsion system selection model, studying the characteristics of the ship's resistance, loading propellers, and selecting the appropriate engine. The propeller-engine matching procedure predicts the propeller and engine suitability. Furthermore, the Analytic Hierarchy Process (AHP) method determines the suitability level for the propeller and diesel engine. The results showed the highest level of suitability for the Yanmar 6CH-HHTEC engine versus the A.30X34 type propeller with 31.7%. Then the Deutz BF06M1013MC engine versus the B.30X28 propeller type, the Yuchai YC6A170C engine versus the B30X28 propeller type, and the Volvo D7ATA engine versus the B30X28 propeller type with percentages of 26.6%, 26.4%, and 15.3%, respectively. The high level of SP2 selection is due to the propulsion system having minimal noise levels, dimensions, and engine weight but having maximum power.

A technological assessment of electrical motors for e-rickshaws

"India is one of the prominent manufacturers in the automobile industry with 30 Million of vehicles production rate. Most of vehicles manufactured in India utilize internal combustion power drive methodology. Additionally, pollutions, global warming, conventional fuels exhaustion and loss of building materials are the major concerns associated with IC engine technology. Electric drive technology has the potential to mitigate these issues. Three-wheeled (3-W) battery powered rickshaws/vehicles are primarily employed for public conveyance in the metropolitan cities of India. The motor (propulsion) is a vital component of 3-W battery powered rickshaw. But, selection of appropriate propulsion system for 3-W rickshaw is crucial step. In the present study, an exertion has been prepared to assess the correct propulsion system for 3-W battery powered vehicle in Indian contest. "

Analysis of inland waterway vessel propulsion by criterion efficiency, ecology and safety

The paper analyses the propulsion systems of inland waterway vessels according to the criteria of economic efficiency, ecology and safety. The professional experience of the authors and their expert knowledge indicate that always the increase of safety level as well as ecological solutions are realized at the expense of economic efficiency. Therefore, arguing for the result of such analysis, the features of water bodies, port infrastructure and elements which should influence the selection of propulsion systems, features of various types of power and fuels with their energy value guaranteeing the swimming range were described. Types of propulsion systems were characterized and a model of selection of propulsion system to the type of sailing was presented. The analysis presented in the article is necessary for a reliable assessment of the accuracy of the selection of the propulsion system for the actual conditions of operation of sea and inland waterway vessels, i.e. for the type of the vessel and its suitability to perform operational tasks on specific waterways.

Analysis of the selection of the auxiliary drive system for a special purpose hybrid rail vehicle

Strict emission standards mean that the internal combustion engines used in means of transport must meet the standards for the emission of harmful compounds. For this reason, there is an increase in the use of alternative sources of propulsion, including rail transport. The article presents unconventional solutions of drive systems in rail vehicles using hybrid systems and fuel cells. The concept of the realizing project of a special-purpose rail vehicle, which is to be able to be driven from three different sources, was presented. Considerations concerning the selection of the internal combustion propulsion system, which is to be used as an auxiliary in the vehicle, are described. The possibilities of installing the power unit on the vehicle were also presented.

Evaluation and Comparison of Hybrid Wing VTOL UAV with Four Different Electric Propulsion Systems

Electric propulsion technology has attracted much attention in the aviation industry at present. It has the advantages of environmental protection, safety, low noise, and high design freedom. An important research branch of electric propulsion aircraft is electric vertical takeoff and landing (VTOL) aircraft, which is expected to play an important role in urban traffic in the future. Limited by battery energy density, all electric unmanned aerial vehicles (UAVs) are unable to meet the longer voyage. Series/parallel hybrid-electric propulsion and turboelectric propulsion are considered to be applied to VTOL UAVs to improve performances. In this paper, the potential of these four configurations of electric propulsion systems for small VTOL UAVs are evaluated and compared. The main purpose is to analyze the maximum takeoff mass and fuel consumption of VTOL UAVs with different propulsion systems that meet the same performance requirements and designed mission profiles. The differences and advantages of the four types propulsion VTOL UAV in the maximum takeoff mass and fuel consumption are obtained, which provides a basis for the design and configuration selection of VTOL UAV propulsion system.

Study and Assessment of Propulsion Systems of Three-Wheeled Electric Powered Rickshaw in India

India is one of the prominent manufacturers in the automobile industry with 30 Million of vehicles production rate. Most of vehicles manufactured in India utilize internal combustion power drive methodology. Additionally, pollutions, global warming, conventional fuels exhaustion and loss of building materials are the major concerns associated with IC engine technology. Electric drive technology has the potential to mitigate these issues. Three-wheeled (3-W) battery powered rickshaws/vehicles are primarily employed for public conveyance in the metropolitan cities of India. The motor (propulsion) is a vital component of 3-W battery powered rickshaw. But, selection of appropriate propulsion system for 3-W rickshaw is crucial step. In the present study, an exertion has been prepared to assess the correct propulsion system for 3-W battery powered vehicle in Indian contest.

Investigating behavior of VLCC ship’s diesel engine on handling stormy waters

The behavior of ship engine encountering stormy waters with different sea wavelengths has been investigated. In this study, a mathematical model is developed using governing equations for various parts of the ship, that is the hull, engine, power transmission shafts from the engine to the propeller also the propeller of the ship itself were implemented in MATLAB/ Simulink software environment. The model consists of the torsional vibrations of the transmission shafts; this enables a more accurate analysis of the engine behavior which is the source of power generation in the ship's propulsion system. The simulation results showed that the wavelength of sea waves has a significant effect on the dynamic performance of the engine. In this research, the effect of different ratios of wavelength to ship length (λ/LPp ) including 0.5, 1, 1.5 and 2 in violent stormy sea conditions with a wave height of 11.5 m and wind speed of 28.5 m/s has been investigated. The results showed that with the exception of λ/LPp of 1.5, at another ratios of λ/LPp , changes in engine performance parameters such as torque, fuel and air consumption, CO2 emission and power are decreasing with increasing wavelength. Most variations in engine speed are related to λ/LPp of 2. The results showed that by reducing the wavelength, the period of oscillations is reduced. As the ratio of wavelength to ship length increases, the number of oscillating points in the engine behavior increases and the lowest number of oscillating points can be seen at λ/LPp of 1.5. This study highlights the importance of effects of sea wavelengths as one of the most important physical parameters of the sea which should not be ignored in the design phase of the ship propulsion system and engine selection.

Selection of Optimal Air Independent Propulsion System using Forced Decision Matrix

A project management decision tool viz., forced decision matrix (FDM) is implemented in this paper towards identification of a suitable optimal air independent propulsion (AIP) system for submerged vehicles. FDM is utilised in order to handle the trade-off from amongst multiple propulsion technologies. FDM is based on multi-attribute utility theory used extensively in decision analysis situations involving persuasive multiple alternatives. The efficiency and effectiveness of this methodology to tackle complex solutions is elaborated in this paper with appropriate calculations. A rational decision-making procedure is evolved using the FDM in order to select the best suited AIP technology for a submerged vehicle. It is inferred that FDM is an effective and potential tool towards identification of best suitable solution in a multi-option environment.

Development of a microthrust balance and ion beam measurement system: Characterizing a dual-mode thruster for spacecraft

There is a rapid progression toward spacecraft miniaturization due to the prospect of reduced launch costs, the requirement for satellite constellations, and the integration of microelectromechanical systems (MEMS). Satellite propulsion is required for increased mission flexibility and orbital debris mitigation, but down-scaling of such devices has proven non-trivial. Some electrostatic thrusters are both challenging and promising given their increase in performance with small geometry, but the relatively low thrust produced through ion acceleration limits their mission applicability. For this reason, it may be desirable to produce thrusters that are able operate across a wide range of specific impulses, depending on maneuver time, thrust bit requirements, and several other factors that influence propulsion system selection. At RAPPEL, a bimodal thruster that can operate at high specific impulse with electrospray propulsion or high thrust using cold gas expansion has been developed. Inevitably, such a propulsion system comes with complications related to performance characterization. A novel and economical data acquisition system has been established to measure the performance of both modes in high vacuum. For the cold gas mode, a torsional thrust balance was built in-house to measure thrust levels between 1−15mN, and can be easily modified for lower ranges. The natural frequency of the thrust stand was measured to be 5.6Hz. The vacuum system sustained pressures below 5mbar while the cold gas nozzle operated, and 1.3×10−5mbar during electrospray operation. A 3-D printed linear cold gas nozzle was used to validate the thrust stand. Its thrust was close to 9mN at a mass flow rate of 20mg/s of nitrogen, producing a specific impulse of just under 45s. Due to the noise present in thrust stand measurements at the sub-mN force-level produced by electrosprays, the thrust stand was built to also accommodate a complementary ion beam current measurement system. The power processing unit, used to generate square-wave ±2500V signals using optodiodes, was built to operate a bipolar ionic liquid ion source (ILIS). The rise and fall times of the push/pull switch were close to 1ms and 30ms, respectively. The electrical power system used to operate the electrospray and measure its performance is examined in detail, followed by the results from validation of both data acquisition systems.

Optimising the engine-propeller matching for a liquefied natural gas carrier under rough weather

Dual-fuel Diesel engines have become the most interesting alternative for liquefied natural gas carriers (LNGCs) since they are able to use boil-off gas as fuel. However, there is a lack of studies about the optimisation of propulsion system selection considering weather conditions in an integrated approach. Thus, the present work aims to provide a comprehensive approach to perform the optimisation of engine-propeller matching for an LNGC under rough weather. A weather condition was included in the assessment of total resistance and thereby affected the propeller’s open water efficiency, shaft speed and brake power. Constraints were included to the approach in order to avoid propellers that could present issues concerning strength, cavitation and vibration. A differential evolution optimisation algorithm was applied to minimise the fuel expenditure of propulsion for a round trip. The case study was designed using an LNGC with cargo capacity of 175,000 m3 sailing in laden condition from Lake Charles to Tokyo Bay, via Panama Canal, and returning in ballast. All suitable matchings for 5346 propellers were found in 2.8 h and over 28% of them were constrained. The method has shown gains up to 19% of fuel expenditure reduction. The required brake power was approximately 20% higher for rough weather than for still water. Therefore, the approach used here has shown a significant gain and highlighted the value of exploring a broad range of propellers and engines in an integrated manner, as well as considering the weather condition.

Type selection and design of hybrid propulsion system of ship

Hybrid propulsion system is a new type of dynamic form. It has the characteristic structural complexity and the diversity of operating conditions. Due to the different vessel functions, different sailing areas or different control performance requirements of the ship, types of hybrid propulsion systems are not the same. In this paper, 6000HP platform supply vessel is an example. Hybrid propulsion the system is selected by the fuzzy comprehensive evaluation method.

Comparison of COGES and Diesel-Electric Ship Propulsion Systems

Diesel-electric ship propulsion is a frequent shipowners choice nowadays, especially on passengerships. Despite many diesel engines advantages, their primary disadvantage is emission of pollutants. As environmental standards become more stringent, the question of optimal alternative to diesel-electric propulsion arises. COGES (COmbined Gas turbine Electric and Steam) propulsion system is one of the proposals for alternative propulsion system, primarily due to significant reduction of pollutant emissions. On the other hand, gas turbines have higher specific fuel consumption in comparison with diesel engines what represents their noticeable disadvantage. However, some analyzes suggested that COGES propulsion system could be still cost-effective in comparison to diesel-electric propulsion, particularly on passenger ships where higher initial investment can be compensated by increasing the number of passenger cabins. This paper shows a comparison of above mentioned propulsion systems, which can be useful for the optimal ship propulsion system selection

Analytic Hierarchy Process Approach for Selection of Ship Propulsion System – Case Study

The selection of appropriate propulsion system is one of the most critical decisions in the design and development of a successful ship production environment. During such decision making process which essentially involves qualitative and quantitative multi-criteria selection, a tradeoff between tangible and intangible factors is essential to select the best amongst the equals. In this case study, the design team was tasked to select suitable propulsion system for a ship under design. The team uses analytical decision making tool, such as Analytic Hierarchy Process (AHP) in this case, to arrive at a informed decision. The team could compare many non-comparable but interlinked parameters like technical parameters, cost, time, vulnerability etc using AHP. The team could also harness the expertise of team within the arrived consensus decision. This study illustrates that the decision arrived through analytical methods tend to be accurate and practical than an intuitive decision. Keywords: Analytic Hierarchy Process (AHP), Propulsion system selection, Multi criteria decision making. I. Introduction The process of ship design begins with an amalgamation of a numerous ideas from all the stakeholders. While the ship designer plays a vital role to translate these into an engineering possibility keeping in mind the compliance to parameters like safety, environment and the role, most of the times, various requirements and characteristics conflict with each other. It is desirable, initially, to place a few rigid constraints on the design as possible. However, there can be incompatibilities because some characteristics have a variety of interdependencies with other characteristics and so only by careful analysis it is possible to determine the full implications of setting a requirement i.e. essential condition. This paper explores the variety of interactions that occur between elements of propulsion system and outlines few of the consequences of trade off. In this case study, an attempt is also made to highlight major imponderables that could arise during the design process, selection process and the possible implications of certain actions using a broadly defined model. The case of Multi Criteria Decision Making (MCDM) of 'selection of propulsion plant' is unique in nature and a suitable analytic method is required to facilitate the designer to select the best option which can meet all the Staff Requirements (SR). The Analytic Hierarchy Process (AHP) 1 is one such tool which suits this MCDM process involving several decision makers with different conflicting objectives to arrive at a consensus decision. In this case study, a design team has been tasked to select an appropriate propulsion system for a medium cargo ship of following key SR :- (a) Principal particulars: - Length Overall: 150-160m, Beam Max: 14-15m, Mean Draft: 5.0m, Standard Displacement: around 8000 Ton, Nominal Speed : 25 knots, Endurance: 5500 Nautical Miles(minimum). Helicopter capability : Capability for landing only of weight of 11 T (Max). (b) All machinery and systems selections to meet Safety of Life at Sea (SOLAS) conventions and regulations issued by International Maritime Organisation(IMO). (c) Use of 'all electrical system' (electric ship) has been ruled out due to various constraints. Ship propulsion system criteria The performance requirements of a ship during the design phase guides the type and combination of the propulsion arrangement selected. There will be certain criteria/characteristics associated with a particular propulsion system which helps refining the available choices for the associated systems and to an extent also the type of hull. The important criteria/characteristics considered for the ship under design table are:-

Electric Propulsion System Selection Process for Interplanetary Missions

The disparate design problems of selecting an electric propulsion system, launch vehicle, and flight time all have significant im pact s on the cost and robustness of a mission. The effects of these system choices combine into a single optimization of the total mission cost , where t he design constraint is a req uired spacecraft neutral (non -electric pro pulsion) mass . C ost optimal systems are designed for a range of mass margins to examine how the optimal design varies with mass growth . The resulting cost -optimal designs are compared with results generated via m ass optimization methods. Additional optimizations with continuous system param eters address the impact on mission cost due to discrete set s of launch vehicle, power, and specific impulse . The examined mission set comprises a near -Earth asteroid sample return, multiple main belt asteroid rendezvous , comet rendezv ous, comet sample return, and a mission to Saturn .