Propulsion System Design Research Articles

Design optimization of a low-cost three-stage launch vehicle with modular hybrid rocket motors

This article investigates the impact of modular propulsion system design on the performance and cost of a three-stage hybrid rocket. Furthermore, it conducts a multi-objective optimization of unit payload cost, take-off mass, and payload mass ratio, considering factors such as the number of motors and layout considerations. The optimization design scheme for the three-stage hybrid rocket is divided into four cases. In the first case, each stage is equipped with a fixed single motor, and each stage is independently optimized without modular design. The second case considers the use of multiple motors in the first and second stages, still without modular design. The third case also involves multiple motors in the first and second stages, but all motors in each stage have identical parameters except for the nozzle expansion ratio, implementing a modular design. In the fourth case, the number and layout of the motor design method are the same as those in the third case, with independent optimization in the third stage using partial modular design. The results indicate that the unit payload cost of the multi-motor non-modular design case can be reduced by 13.12% compared to the single-motor non-modular design case. Within the modular case, the full modular design case is slightly inferior to the partial modular design case. Based on the above data, it can be concluded that the first and second stages of modular rockets offer the best performance and the lowest cost.

Study on Design of Hybrid Diesel-Electric Motor Propulsion System for Eco-Tourism Boat

Indonesia as a maritime country has extraordinary marine tourism potential. On the other hand, the development of eco-tourism boats is still limited. The objective of this study is to investigate the design of diesel-electric hybrid propulsion system for a tourist boat with capacity of 10 passengers. The design of eco-tourism boats considers a trimaran hull using hybrid diesel-electric motor propulsion with an overall length of 12 meters and a block coefficient of 0.4. The performance of the proposed eco-tourism boat was investigated by a simulation model to obtain the required power and stability criteria. The simulation result shows the proposed eco-tourism boat can achieve the desired service speed of 13 knots with the required power is 390 kW.

Design of E-Cycle Drivetrain Configuration Using MATLAB

This research explores the comprehensive dynamics of electric bicycles, focusing on the intricate interplay of rolling resistance, gradient resistance, aerodynamic resistance, and acceleration resistance. Through detailed analysis and mathematical formulations, the study aims to provide insights crucial for optimizing the design and efficiency of electric bicycle propulsion systems. By understanding the various resistive forces affecting performance, engineers and researchers can contribute to the ongoing evolution of sustainable urban mobility solutions Within this research, an in-depth examination unfolds, delving into the nuanced dynamics of electric bicycles. The spotlight is on the complex interaction between rolling resistance, gradient resistance, aerodynamic resistance, and acceleration resistance.

Tri-objective optimal design of a hybrid electric propulsion system for a polar mini-cruise ship

The environmental impact, economic considerations, and passenger comfort of hybrid electric propulsion systems (HEPSs) are significantly influenced by the design phase. However, a design method solely focused on minimizing annual fuel consumption may inadvertently lead to increased life-cycle cost and decreased annual pure-electric sailing time. To address this issue, this paper presents a tri-objective optimization design method to achieve an optimal trade-off among the objectives for a polar mini-cruise ship. First, a scalable mathematical model is established for a hybrid diesel engines/batteries/shore power propulsion system. Then, a refined, rule-based energy management strategy is developed to control the power flow among energy sources. Next, a tri-objective optimization model with detailed descriptions of objectives, variables, constraints, and method is formulated. Finally, the performances of three optimal designs, obtained through tri-objective optimization, single-objective optimization, and conventional heuristics, are compared through simulations based on a typical real-world navigation case. The results highlight the clear advantages of the proposed method over the other two methods. Furthermore, sensitivity analysis underscores that the parameters of the diesel engine, battery, and gear ratio exert a greater impact on HEPS performances than other factors.

Techno-Economic Analysis of Combined Gas and Steam Propulsion System of Liquefied Natural Gas Carrier

Various combinations of ship propulsion systems have been developed with low-carbon-emission technologies to meet regulations and policies related to climate change, one of which is the combined gas turbine and steam turbine integrated electric drive system (COGES), which is claimed to be a promising ship propulsion system for the future. The objective of this paper is to perform a techno-economic and environmental assessment of the COGES propulsion system applied to liquefied natural gas (LNG) carriers. A propulsion system design for a 7500 m3 LNG carrier was evaluated through the thermodynamics approach of the energy system. Subsequently, carbon emissions and environmental impact analyses were carried out through a life cycle assessment based on the power and fuel input of the system. Afterwards, a techno-economic analysis was carried out by considering the use of boil-off gas for fuel and additional income from carbon emission incentives. The proposed propulsion system design produces 1832 kilowatts of power for a service speed of 12 knots with the total efficiency of the system in the range of 30.1%. The results of the environmental evaluation resulted an overall environmental impact of 10.01 mPts/s. The results of the economic evaluation resulted in a positive net present value and a logical payback period for investment within 8 years of operation. The impact of this result shows that the COGES has a promising technological commercial application as an environmentally friendly propulsion system. Last, for the economy of the propulsion system, the COGES design has a positive net present value, an internal rate return in the range of 12–18%, and a payback period between 6 and 8 years, depending on the charter rate of the LNG carrier.

Analysis of simulated dynamic loads of a ship propulsion system of a non-conventional power system

Unconventional approaches to propulsion system design are increasingly being explored to meet increasing demands for efficiency, environmental performance and reliability. This article focuses on the analysis of simulated dynamic loads on the propulsion system of ships equipped with unconventional power systems - reformed methanol fuel cells (RMFCs). The analysis is aimed at understanding the performance of these systems under dynamic maritime conditions, assessing their performance and identifying potential challenges and benefits associated with them (including military ones). According to military assumptions, an undeniable benefit is the minimization of the ship's physical fields and its independence from the base (i.e., in the future, obtaining hydrogen from seawater electrolysis).

Tailbeat perturbations improve swimming efficiency by reducing the phase lag between body motion and the resulting fluid response.

Understanding how animals swim efficiently and generate high thrust in complex fluid environments is of considerable interest to researchers in various fields, including biology, physics, and engineering. However, the influence of often-overlooked perturbations on swimming fish remains largely unexplored. Here, we investigate the propulsion generated by oscillating tailbeats with superimposed rhythmic perturbations of high frequency and low amplitude. We reveal, using a combination of experiments in a biomimetic fish-like robotic platform, computational fluid dynamics simulations, and theoretical analysis, that rhythmic perturbations can significantly increase both swimming efficiency and thrust production. The introduction of perturbations increases pressure-induced thrust, while reduced phase lag between body motion and the subsequent fluid dynamics response improves swimming efficiency. Moreover, our findings suggest that beneficial perturbations are sensitive to kinematic parameters, resolving previous conflicts regarding the effects of such perturbations. Our results highlight the potential benefits of introducing perturbations in propulsion generators, providing potential hypotheses for living systems and inspiring the design of artificial flapping-based propulsion systems.

Mission-Oriented Electrified Aircraft Propulsion System Design and Verification Using Model-Based Systems Engineering

Abstract The concept of electrified aircraft propulsion (EAP) has garnered substantial attention and investigation due to its potential for mitigating fuel consumption, emissions, and noise. Present studies mainly concentrate on point design rather than systematic design space exploration. This paper considers the attainment of prescribed mission objectives as a paramount evaluation criterion and proposed a mission-oriented design and verification method based on model-based systems engineering (MBSE). Instead of using a general modeling language, this method develops a domain-specific metamodel library for EAP based on six meta-metamodels. A Mission-Operational-Functional-Logical-Physical (MOFLP) modeling methodology is provided to standardize EAP design process. Furthermore, the modeling process is integrated with the verification process by executable verification script. A case study about skydiving mission is conducted to verify the effectiveness of this method. The case results corroborate the utility of this method in the generation of an initial EAP solution. Such initial solution can serve as a fundamental benchmark for iterative design.

The analysis of electromagnetic maxwell nanofluid flow over an axisymmetric cylindrical surface using artificial neural networks for active and passive control

ABSTRACT This work presents a novel approach to active and passive control of fluid flow on a stretching cylinder, considering the collective effects of electromagnetism, and chemical reactivity. The Maxwell fluid flow over the stretched surface of a cylinder is responsible for the improvement in heat transfer. The proposed methodology leverages the power of Artificial Neural Networks (ANN) to effectively manipulate and optimize fluid flow behavior in this complex system. By integrating ANN into the control strategy, we achieve enhanced propulsion system design and optimization capabilities, enabling improved performance around cylinders. Additionally, insights into the interconnection of electromagnetic effects and heat sources provide valuable implications for thermal management systems, where understanding and controlling fluid flow behavior are essential for efficient heat transfer. The design approach for addressing different aspects of the fluid problem consists of a sequence of operations, which encompass training, testing, and validation using a reference dataset. Furthermore, visual representations are employed to portray the flow model parameters concerning momentum, energy, and concentration profiles, effectively illustrating the results of the investigation, all of which are closely aligned with each other on average 10−8.

Ion Electric Propulsion System Design Considerations for Beam Sparkle

Ion Electric Propulsion System Design Considerations for Beam Sparkle

Design and analysis of a novel underwater vector propulsion system based on 2SPS+SP/SPR parallel propelling mechanism

Due to the dual function of propulsion and manipulation, vector propulsion systems (VPSs) have recently become an emerging research hotspot. The 3-DOF parallel mechanism (PM) has been proven to be significant advantageous in underwater VPSs. However, the current design is mostly dominated by a three-limb propelling mechanism, and its stiffness remains to be improved. In the present research, a novel VPS based on a three-actuated limb and one-passive limb parallel propelling mechanism is proposed. Firstly, a kinematic model is studied, taking into account the terminal coupling relationships overlooked in previous studies; the independent parameters in the kinematic model correspond to the yaw and pitch angles of an underwater robot propelled by the VPS. Secondly, a mechanism inversion method for obtaining all singularity configurations is proposed to solve the singularity problem of the parallel propelling mechanism proposed herein. Finally, motion simulations are performed to verify the feasibility, effectiveness, and accuracy of the proposal. These simulations provide some pitch/yaw adjustment references for improving the VPS propulsion efficiency.

A method for an efficiency and weight-optimised preliminary design of a hydrogen-powered fuel cell-based hybrid-electric propulsion system for aviation purposes

There is a worldwide effort to advance the usage of zero-emission propulsion systems for aircraft. Due to their high thermodynamic efficiency and the fact that they produce no CO2\\documentclass[12pt]{minimal} \\usepackage{amsmath} \\usepackage{wasysym} \\usepackage{amsfonts} \\usepackage{amssymb} \\usepackage{amsbsy} \\usepackage{mathrsfs} \\usepackage{upgreek} \\setlength{\\oddsidemargin}{-69pt} \\begin{document}$$\ extrm{CO}_{2}$$\\end{document} and NOx\\documentclass[12pt]{minimal} \\usepackage{amsmath} \\usepackage{wasysym} \\usepackage{amsfonts} \\usepackage{amssymb} \\usepackage{amsbsy} \\usepackage{mathrsfs} \\usepackage{upgreek} \\setlength{\\oddsidemargin}{-69pt} \\begin{document}$$\ extrm{NO}_{x}$$\\end{document} emissions, hydrogen-powered fuel cells are becoming increasingly popular for aviation purposes. However, fuel cell systems suffer from lower power density and higher cooling requirements when compared to conventional propulsion systems. Harnessing the high potential requires an optimised design of the whole propulsion system and its heat management system. This paper aims to present a method for the preliminary design and dimensioning of a fuel cell-based hybrid-electric propulsion system, which respects the limits of the heat management system and is weight and efficiency optimised. Thermodynamic models of the whole propulsion system are a crucial element to enable further investigations. Such a model has been developed, which is suitable for unsteady simulations of the propulsion and the heat management system performance of a short-range four-seater aircraft. A parameter study of the design parameters has been performed to display their impact on the system mass, the overall efficiency and the total hydrogen consumption. These results enable the identification of an overall optimised configuration. The study indicates that fuel cell-only configurations with an oversized fuel cell stack are beneficial for the analysed aircraft and flight mission.

The effects of distributed electric propulsion on the aerodynamics of a regional aircraft wing

A study is performed to comprehensively evaluate the aerodynamic performance of a regional aircraft designed for short-haul flights, with a particular focus on the effects of distributed electric propulsion (DEP) on aerodynamic performances. This effort aligns well with a core objective of the Clean Aviation program to decrease carbon emissions within the aviation sector. To address this challenge, we propose a concept that considers incorporating electric motors to complement the conventional propulsion system of a regional aircraft wing. These electric motors have the capability to draw power from either the traditional turboprop engine or exclusively from an on-board electrical generator, providing an innovative pathway for emissions reduction. The central focus of this study revolves around a detailed examination of the aerodynamic efficacy with respect to the placement of engines within the wing. It seeks to ascertain whether optimal aerodynamic efficiency is achieved through the adoption of a greater number of smaller-diameter motors, characterized by reduced power output to the shaft. Alternatively, the study explores the prospect of employing a reduced number of motors, each possessing larger diameters and correspondingly augmented power output. While a larger motor size may intuitively suggest superiority in terms of thrust, it remains imperative to meticulously evaluate the potential influence of the associated drag factor. This research contributes to the growing body of knowledge in the realm of aviation by shedding light on the intricate interaction between aerodynamic efficiency and power output in the context of propulsion system design.

ANALYSIS OF FOREIGN EXPERIENCE OF DUAL USE SOLID ROCKET MOTORS

In countries, such as the United States, China, India, France, Israel and many others, solid-propellant rocket engine technologies are used not only in military missiles, but also in launch vehicles of the rocket and space industry. Such an approach of dual application of technologies makes it possible to introduce and develop new innovative solutions to increase the degree of unification of related technologies. One of the most important factors influencing the efficiency of using solid propellant rocket engines in space programs is the cost of solid rocket propellants and propulsion system components. For this reason, a high degree of unification of solid fuel products for various purposes is aimed at ensuring a high utilization of the industry’s production capacities, which can significantly reduce prices for materials, fuel and the design of propulsion systems as a whole. The analysis confirmed that the creation of launch vehicles based on rocket engines of solid fuel for military missiles naturally leads to a reduction in the time and costs for the development of such products, a reduction in technical risks and an increase in the reliability of the technologies used.

The effect of propulsion system design on the response of the novel yoke–bell–clapper system with a proportional–integral controller

This article focuses on the influence of the propulsion mechanism design on the transient and steady-state response of the yoke–bell–clapper system with a proportional–integral controller. The analysis is made using the mathematical model validated in our previous paper. Three different propulsion system designs are considered. Analyzed cases are compared and assessed, taking into account the launching time of the system, additional loads in the supports, and final steady-state response. The subject of the analysis contributes to the topic devoted to the dynamic interaction between the bells and their supporting structures that is recently widely considered by the scientific community.

Effects of different paddling motion patterns and flexibility on hydrofoil propulsion performance

A bi-directional fluid-solid interaction method is used to simulate the “8” shape motion of the hydrofoil of a bionic penguin. The feasibility of the numerical simulation method is verified by building an experimental platform. The effects of the forward and backward paddling motion (no front and back F0, symmetrical F1, and asymmetrical F2) and the flexibility (high, medium, and low flexibility intervals) on the propulsion performance are considered. The results show that the best propulsion performance is obtained in the medium and low flexibility ranges for F0 and F1 and the medium flexibility range for F2. At the same flexibility, F0 achieves the best propulsive efficiency but the lowest average and peak instantaneous thrust coefficients, and as the amplitude of motion increases, the propulsive efficiency decreases and the average and peak instantaneous thrust coefficients increase; for similar input power, F2 can achieve higher peak instantaneous thrust coefficients. The vortex and pressure fields under different parameters are analyzed through post-processing further to explain the reasons for the differences in propulsion performance. The findings of the study are of great significance for the unraveling of the hydrofoil propulsion mechanism and the optimal design of future hydrofoil propulsion systems.

Integrated Design and Flight Validation of Solar-Powered Unmanned Aerial Vehicle (UAV) Structure and Propulsion System

The development of solar-powered unmanned aerial vehicles (UAVs) primarily focuses on enhancing the efficiency of the propulsion system to minimize energy consumption during the conversion of valuable solar energy. However, due to the unique nature of UAV propulsion systems, there is limited cross-reference ability among existing solar-powered UAV systems. This paper proposes an integrated design approach for the propulsion system and UAV structure. Based on this approach, an overall design is conducted for the solar-powered UAV, including initial design goals and performance parameters. Aerodynamic layout design and performance estimation are carried out, and a prototype is fabricated and assembled for flight testing validation. The results demonstrate the significant importance of this approach in improving the efficiency of the solar-powered UAV propulsion system.

Design and analysis of liquid hydrogen-fueled hybrid ship propulsion system with dynamic simulation

In this study, we examine a liquid hydrogen (LH2)-fueled hybrid ship propulsion system (HSPS) consisting of an LH2 fuel gas supply system (FGSS), a polymer electrolyte membrane fuel cell (PEMFC), and battery systems. The LH2-HSPS is analyzed through three dynamic simulations, representing different PEMFC outputs, for a 2-MW-class tugboat. During transient states of LH2 FGSS, hydrogen temperature changes from 11 to 41 °C at the LH2 vaporizer outlet. Dynamic simulations considering hydrogen temperature tolerance in the PEMFC system show interruptions of power generation during 1–5 s. In Case 3, where the PEMFC system provides all propulsive power, an energy capacity of 310–1860 kWh is calculated with maximum C-rates of 1C–6C. The average power consumption of the balance of plant in the PEMFC system is 43.64, 27.51, and 44.06 kW for Cases 1–3, respectively. Finally, the battery system's thermal management is well performed for all cases.

Oxidation induced emissivity variations of the Haynes 25 alloy at high temperatures

Haynes 25 alloy is used in the design of propulsion systems for spacecrafts and it can constitute a space debris at the end of life of the mission. All the thruster combustion chambers and nozzles are manufactured with Haynes 25 alloy and the thrusters used storable monopropellant hydrazine. During the atmospheric reentry of thruster pieces at high velocity, the Haynes 25 alloy is submitted to high temperatures in an extreme environment with atomic oxygen. This is why the high temperature oxidation of Haynes 25 was studied, in air plasma conditions in the temperature range 1000–1700 K. Moreover, as emissivity is an important parameter to know for the heat transfer, the spectral directional emissivity was measured on several samples surfaces: pristine, pre-oxidized in air plasma and in situ oxidized in air. The high temperature oxidation of Haynes 25 is moderate up to 1500 K and above an important mass loss occurred up to 1700 K (around 40 mg/cm2), that is the determined melting temperature. The emissivity of pristine Haynes 25 is vey low, around 0.20 at 1350 K and it increases with oxidation up to 0.85–0.90 at 1600 K.

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.