The document describes a study that developed an evaluation tool and used multi-objective genetic algorithms to explore the conceptual design of a hybrid rocket launch vehicle. The study aimed to evaluate launch vehicles with hybrid rocket engines and demonstrate multi-disciplinary design optimization. The design method involved using a genetic algorithm with Pareto ranking to optimize objectives of minimizing gross weight and maximizing flight altitude for a single-stage rocket carrying a 40kg payload. The results showed a tradeoff between weight and altitude, with a maximum altitude of around 180km found. One optimal design was compared to an existing solid-fuel rocket, showing the hybrid rocket design had a higher aspect ratio due to longitudinal component placement.
Knowledge Discovery for Hybrid Rocket Conceptual Design Based on Evolutionari...Masahiro Kanazaki
This document discusses using a genetic algorithm to optimize the conceptual design of a hybrid rocket for space propulsion. It provides background on hybrid rocket engines and aircraft design using evolutionary algorithms. It then gives an overview of genetic algorithms and demonstrates their use for multi-objective optimization problems. Finally, it formulates the design problem for a sub-orbital launch vehicle using a hybrid rocket engine and presents results from applying a multi-objective genetic algorithm, including visualizations of the non-dominated solutions and design knowledge discovered.
Airfoil Design for Mars Aircraft Using Modified PARSEC Geometry RepresentationMasahiro Kanazaki
The document describes a study that used computational fluid dynamics and genetic algorithms to optimize airfoil designs for aircraft intended to fly on Mars. The study represented airfoils using a modified PARSEC method and evaluated designs based on their maximum lift-to-drag ratio. The optimization process produced designs with higher lift-to-drag ratios than the baseline design, achieving this through design changes like smaller leading edge radii, increased camber, and more relaxed upper surface pressure recovery. Visualization of the results provided insight into which design parameters most affected lift-to-drag ratio. The study demonstrated an efficient method for exploring unknown airfoil design problems to achieve higher performing designs for Mars aircraft.
MULTI-POINT DESIGN OF A SUPERSONIC WING USING MODIFIED PARSEC AIRFOIL REPRESE...Masahiro Kanazaki
1) The study aimed to perform multi-point aerodynamic design of a supersonic wing using an efficient global optimization methodology.
2) The methodology used a modified PARSEC airfoil representation and kriging model-based genetic algorithm for efficient global optimization.
3) The design explored maximizing lift-to-drag ratio at high and low Mach cruise speeds, finding many potential designs and discovering that camber of the kink and root airfoils most affected performance at high Mach while thickness curvature at kink and root did so at low Mach.
DESIGN PERFORMANCE INVESTIGATION OF MODIFIED PARSEC AIRFOIL REPRESENTATION US...Masahiro Kanazaki
This document summarizes a study investigating the design performance of modified PARSEC airfoil representation methods using genetic algorithms. The study compares the original PARSEC method to two proposed modifications for representing airfoils. The optimizations aim to maximize airfoil thickness and minimize drag coefficient for transonic and low Reynolds number airfoil design problems. Computational fluid dynamics simulations are performed using structured grids and turbulence models. Results show that the modified PARSEC methods improve the aerodynamic performance around the leading edge compared to the original method.
Vortex Dissipation Due to Airfoil-Vortex InteractionMasahiro Kanazaki
1) A numerical simulation was conducted of airfoil-vortex interaction (AVI) for two airfoils to improve a hybrid method for predicting blade-vortex interaction (BVI) noise.
2) The simulation estimated the change in vortex center location and circulation due to sequential AVI. It found that the original vortex was decelerated and moved upward due to induced counter-rotating vortices from the first airfoil.
3) Sound pressure fluctuations were also estimated, finding that the pressure level after the second AVI was lower than after the first due to the increased miss-distance between the vortex and airfoil. This simulation provided data to modify the prescribed wake model used in the hybrid
Multidisciplinary Design Optimization of Supersonic Transport Wing Using Surr...Masahiro Kanazaki
The document summarizes research on the multidisciplinary design optimization of supersonic transport wing concepts. The objectives were to develop an efficient MDO tool for conceptual design of SST wings using low-cost computational fluid dynamics and surrogate modeling. 107 design samples were evaluated for aerodynamic performance, sonic boom levels, and wing weight. 24 non-dominated solutions were identified, with the best designs having thinner root airfoils, larger inboard sweep angles, or modified tail angles compared to a baseline compromised design. Analysis of variance identified key design variables with the most influence on objectives.
Knowledge Discovery for Hybrid Rocket Conceptual Design Based on Evolutionari...Masahiro Kanazaki
This document discusses using a genetic algorithm to optimize the conceptual design of a hybrid rocket for space propulsion. It provides background on hybrid rocket engines and aircraft design using evolutionary algorithms. It then gives an overview of genetic algorithms and demonstrates their use for multi-objective optimization problems. Finally, it formulates the design problem for a sub-orbital launch vehicle using a hybrid rocket engine and presents results from applying a multi-objective genetic algorithm, including visualizations of the non-dominated solutions and design knowledge discovered.
Airfoil Design for Mars Aircraft Using Modified PARSEC Geometry RepresentationMasahiro Kanazaki
The document describes a study that used computational fluid dynamics and genetic algorithms to optimize airfoil designs for aircraft intended to fly on Mars. The study represented airfoils using a modified PARSEC method and evaluated designs based on their maximum lift-to-drag ratio. The optimization process produced designs with higher lift-to-drag ratios than the baseline design, achieving this through design changes like smaller leading edge radii, increased camber, and more relaxed upper surface pressure recovery. Visualization of the results provided insight into which design parameters most affected lift-to-drag ratio. The study demonstrated an efficient method for exploring unknown airfoil design problems to achieve higher performing designs for Mars aircraft.
MULTI-POINT DESIGN OF A SUPERSONIC WING USING MODIFIED PARSEC AIRFOIL REPRESE...Masahiro Kanazaki
1) The study aimed to perform multi-point aerodynamic design of a supersonic wing using an efficient global optimization methodology.
2) The methodology used a modified PARSEC airfoil representation and kriging model-based genetic algorithm for efficient global optimization.
3) The design explored maximizing lift-to-drag ratio at high and low Mach cruise speeds, finding many potential designs and discovering that camber of the kink and root airfoils most affected performance at high Mach while thickness curvature at kink and root did so at low Mach.
DESIGN PERFORMANCE INVESTIGATION OF MODIFIED PARSEC AIRFOIL REPRESENTATION US...Masahiro Kanazaki
This document summarizes a study investigating the design performance of modified PARSEC airfoil representation methods using genetic algorithms. The study compares the original PARSEC method to two proposed modifications for representing airfoils. The optimizations aim to maximize airfoil thickness and minimize drag coefficient for transonic and low Reynolds number airfoil design problems. Computational fluid dynamics simulations are performed using structured grids and turbulence models. Results show that the modified PARSEC methods improve the aerodynamic performance around the leading edge compared to the original method.
Vortex Dissipation Due to Airfoil-Vortex InteractionMasahiro Kanazaki
1) A numerical simulation was conducted of airfoil-vortex interaction (AVI) for two airfoils to improve a hybrid method for predicting blade-vortex interaction (BVI) noise.
2) The simulation estimated the change in vortex center location and circulation due to sequential AVI. It found that the original vortex was decelerated and moved upward due to induced counter-rotating vortices from the first airfoil.
3) Sound pressure fluctuations were also estimated, finding that the pressure level after the second AVI was lower than after the first due to the increased miss-distance between the vortex and airfoil. This simulation provided data to modify the prescribed wake model used in the hybrid
Multidisciplinary Design Optimization of Supersonic Transport Wing Using Surr...Masahiro Kanazaki
The document summarizes research on the multidisciplinary design optimization of supersonic transport wing concepts. The objectives were to develop an efficient MDO tool for conceptual design of SST wings using low-cost computational fluid dynamics and surrogate modeling. 107 design samples were evaluated for aerodynamic performance, sonic boom levels, and wing weight. 24 non-dominated solutions were identified, with the best designs having thinner root airfoils, larger inboard sweep angles, or modified tail angles compared to a baseline compromised design. Analysis of variance identified key design variables with the most influence on objectives.
Numerical Simulation: Flight Dynamic Stability Analysis Using Unstructured Ba...Masahiro Kanazaki
The document summarizes a numerical simulation of flight dynamic stability analysis using an unstructured Navier-Stokes solver. It investigates the ability of computational fluid dynamics (CFD) to analyze dynamic stability at supersonic flight conditions. The study uses the Standard Dynamics Model configuration and estimates aerodynamic derivatives from computational results to analyze stiffness, damping, and unsteady oscillation characteristics. Grid dependency is also examined using coarse, medium, and fine meshes.
Spectrum-Compliant Accelerograms through Harmonic Wavelet TransformAlessandro Palmeri
This presentation has been delivered at the 11th International Conference on Computational Structures Technology in Dubrovnik (Croatia) on 7th September 2012, and shows how the harmonic wavelet transform can be effectively used: first, to adjust a recorded accelerogram to match a given elastic design spectrum; second, to generate a number of fully non-stationary samples with the same probabilistic features.
TH2.L09.4 - CHARACTERISTIC ANALYSIS OF VEHICLE TARGET IN QUAD-POL RADARSAT-2...grssieee
1) The document analyzes the characteristic backscattering properties of vehicle targets in quad-polarimetric Radarsat-2 SAR images.
2) Experiments at different incidence angles and azimuth angles found significant differences in the radar cross section and polarization components of vehicle targets.
3) Polarization decomposition analysis showed double bounce scattering is an important characteristic for detecting trucks on roads, and vehicles are best detected when oriented parallel to the SAR flight direction.
Welcome to International Journal of Engineering Research and Development (IJERD)IJERD Editor
This document presents a transit time model for short gate length ion-implanted GaAs MESFETs. It develops a 2D analytical model to calculate the potential distribution and electric field in the channel region. Based on this, it derives an expression for transit time by considering the carrier velocity and saturation effects. It also presents an equation for drain current as a function of transit time, doping profile, and other device parameters. Simulation results using MATLAB are shown for Id-Vd characteristics and transit time for different device geometry and material parameters. The model aims to better understand the underlying device physics of optically controlled GaAs MESFETs.
Development of Reliability Analysis and Multidisciplinary Design Optimization...Altair
This document summarizes the capabilities of the RAMDO software for reliability-based design optimization (RBDO). It discusses both sensitivity-based and sampling-based RBDO approaches in RAMDO. It also provides examples of multidisciplinary applications of RAMDO in areas like fatigue analysis, casting process design, vehicle crashworthiness, and more. Several published case studies demonstrate how RAMDO has been used to optimize designs while accounting for input variability and reliability constraints.
This document proposes a modular beamforming architecture for ultrasound imaging that uses FPGA DSP cells to overcome limitations of previous designs. It interleaves the interpolation and coherent summation processes, reducing hardware resources. This allows implementing a 128-channel beamformer in a single FPGA, achieving flexibility like FPGAs but with lower power consumption like ASICs. The design is scalable, allowing a tradeoff between number of channels, time resolution, and resource usage.
goGPS is open source software that improves the accuracy of low-cost GPS devices through real-time kinematic (RTK) positioning and Kalman filtering. It was initially developed through 2007-2009 at the Polytechnic of Milan and Osaka City University. The software provides sub-meter level positioning and is being ported from MATLAB to Java to manage it as a collaborative open source project. goGPS processing will also be offered as a web service to provide accurate positioning from raw GPS data. Future work includes expanding supported signals and sensors and developing hardware to run the software-defined radio front-end.
A2 Structure Of Source Models Measurement Methods R Buetikoferahmad bassiouny
The document discusses aircraft noise source modeling. It describes the structure of source models, including sound power level directivity, operation conditions and other parameters. It also discusses different measurement methods that can be used to obtain data for the source models, such as in-flight measurements under operational conditions, arranged in-flight measurements, and analyzing processed data from manufacturers. The measurements require precision tracking and synchronization to attribute sound recordings to specific aircraft types, speeds, thrust settings and other factors.
The document discusses extending the Chemical Tagger natural language processing tool to be more applicable to climate science texts by incorporating climate science controlled vocabularies. It describes adapting the Chemical Tagger, originally designed for chemistry texts, to process abstracts from climate science journals. This includes modifying the tagger's dictionaries and grammars. Web forms and a CIM document viewer are also discussed which can generate and view outputs in the CIM XML format. The document aims to highlight climate science terms in texts to map them to a controlled vocabulary and better populate the CIM framework.
Multi-objective Genetic Algorithm Applied to Conceptual Design of Single-stag...Masahiro Kanazaki
"Multi-objective Genetic Algorithm Applied to Conceptual Design of Single-stage Rocket Using Hybrid Propulsion System" presented at The Eighth China-Japan-Korea Joint Symposium on Optimization of Structural and Mechanical Systems (CJK-OSM).
Conceptual Design and Structural Analysis of Solid Rocket Motor Casingijceronline
This paper is concern with theoretical design of the 100 kg solid rocket motor with predefined values of the burning rate is 100 mm/ sec, specific impulse is 240 sec and chamber pressure is 1000 psi. confined with selection of the material and basic concept of the rocket motor and its aspect during static test. Rocket motor is a highly complex aerospace component that consists of a metal casting, ablative liner and propellant grain. Also to determine the design pressure and burst pressure of a solid rocket motor casing .Preliminary design provided key propulsion outputs that would later be refined and assessed in the final design.
1) A senior capstone team at Portland State University developed a method for rapidly prototyping small bipropellant liquid fuel rocket engines using additive manufacturing.
2) They designed a 500 lbf thrust engine using liquid oxygen and ethanol as propellants, with regenerative cooling channels and a pintle injector.
3) The design process utilized Python Jupyter notebooks to generate parametric equations defining the engine geometry, which allows changing design parameters and quickly generating new geometry files for 3D printing.
IJERA (International journal of Engineering Research and Applications) is International online, ... peer reviewed journal. For more detail or submit your article, please visit www.ijera.com
DESIGN AND ANALYSIS OF HELICOPTER MAIN ROTOR HEADIRJET Journal
This document describes the design and analysis of a helicopter main rotor head. It begins with an abstract that outlines the objectives of modeling and analyzing a helicopter rotor head in SOLIDWORKS and ANSYS software. The introduction provides background on the main components of a helicopter rotor system. The methodology section then details the steps taken, which included designing the rotor head in SOLIDWORKS based on calculations, performing structural and modal analyses in ANSYS, and evaluating different materials. Dimensions of the rotor head are also presented. The document analyzes the rotor head to evaluate stresses, natural frequencies, and fatigue life.
This document discusses CFD analysis of solid fuel scramjet combustors. It begins with an introduction to scramjet engines and reasons for investigating solid fuels. It then reviews previous research on solid fuel scramjet combustor tests and numerical simulations. The computational domain and geometry of the scramjet combustor being modeled is described. Different classifications of solid propellant combustion models are discussed. Finally, the numerical method used in the CFD analysis with the FLUENT software is outlined. The analysis examines non-reacting and reacting flow fields in the combustor with a Mach 2 inlet flow and regression of the solid fuel boundary.
IRJET - Design and Analysis of Connecting Rod using Different MaterialsIRJET Journal
This document describes the design and analysis of a connecting rod using different materials through finite element analysis. The connecting rod was modeled in NX 10 software and analyzed in ANSYS Workbench. Materials analyzed included titanium alloy, beryllium alloy, magnesium alloy, and aluminum 360. ANSYS was used to analyze von mises stress, strain, deformation, factor of safety, and weight reduction for each material. Aluminum alloy was found to have a higher factor of safety, lower weight, lower stress, and was stiffer than forged steel. Fatigue analysis can also determine the lifetime of the connecting rod. The connecting rod was designed, modeled, and analyzed to compare the performance of different materials.
Welcome to International Journal of Engineering Research and Development (IJE...IJERD Editor
This document describes the design optimization of a tipper truck body. Three existing tipper truck body models were modeled and analyzed using finite element analysis software. The analyses found the maximum equivalent stress and total deformation for each model. An optimized model was then developed with reduced weight and stress compared to the original models. The optimized model had a mass of 413.04kg, maximum equivalent stress of 166.01MPa, and maximum deformation of 16.215mm, representing improvements over the original designs. The analyses demonstrated the ability to optimize truck body design for reduced weight and stress.
The document proposes developing a lunar hopper vehicle powered by a nuclear thermal rocket engine. It would take off and land repeatedly to gather soil samples from multiple locations on the moon's surface. An optimization problem is set up in MATLAB to determine the ideal dry mass and mass ratio to maximize the number of landing sites visited. The analysis finds that a design using a SNRE (Small Nuclear Reactor Engine) with a 3500 kg dry mass could achieve up to 28 sample retrievals from sites 5 km apart. A conceptual design of the vehicle is then presented, including subsystem mass budgets and dimensioned drawings. Future work areas are identified to further develop the design.
This document discusses scramjet inlets, which are a critical component of scramjet engines suitable for sustained hypersonic flight. Scramjet inlets must compress supersonic incoming air for combustion while minimizing losses. Different inlet designs achieve varying levels of compression efficiency. The document examines inlet types, desired compression levels, and presents a design example of a 3D scramjet inlet intended to operate between Mach 6-12 for access to space. Key challenges for scramjet inlets include achieving sufficient compression while minimizing shock losses and heating at high flight speeds.
This seminar gives idea about spacecraft propulsion i.e., actually what are different latest modes of propulsion are used in space agency and also the introduction of combustion of propellants.
This document summarizes Robert White's qualifications for an aerospace engineering position. It includes his education background with a B.S. in Aerospace Engineering and minor in Electrical Engineering from Purdue University. It outlines relevant skills and work experience, including internships modifying balloon and robot camera systems. It also details involvement in student engineering projects including a bucket elevator excavator for a lunar mining robot and cargo lander designs for a moon base project.
This paper discusses the processes involved in the additive manufacturing of a regenerative and film-cooled liquid rocket engine with a thrust of 10 kN using Inconel 718, while detailing validation techniques. A description of the objectives and design constraints provide the context and motivations. Computational Fluid Dynamics (CFD) models were developed and provided the expected pressure and thermal regimes under regenerative and film cooling. Additionally, Finite Element (FE) models were used to predict the capabilities of the engine structure. A description of 3D printing methods highlights the benefits and limitations of the technology, specifically the influence the design of liquid rocket engines. A pintle injector is used, printed as a separate, easily removable and replaceable component. Issues related to overhangs, surface roughness, and shrinkage; aspects related to post-print processing and the need to minimize machining are discussed. Results from the CT scans of the engine and its components are presented. The paper also outlines the series of tests that will be performed on this engine to verify its performance and provide design basis for future works. This engine will be used to power the reusable flight vehicle that is under development at the Kyushu Institute of Technology in Japan. The student-led Liquid Propulsion Laboratory at the University of Southern California is responsible for the work detailed below.
Numerical Simulation: Flight Dynamic Stability Analysis Using Unstructured Ba...Masahiro Kanazaki
The document summarizes a numerical simulation of flight dynamic stability analysis using an unstructured Navier-Stokes solver. It investigates the ability of computational fluid dynamics (CFD) to analyze dynamic stability at supersonic flight conditions. The study uses the Standard Dynamics Model configuration and estimates aerodynamic derivatives from computational results to analyze stiffness, damping, and unsteady oscillation characteristics. Grid dependency is also examined using coarse, medium, and fine meshes.
Spectrum-Compliant Accelerograms through Harmonic Wavelet TransformAlessandro Palmeri
This presentation has been delivered at the 11th International Conference on Computational Structures Technology in Dubrovnik (Croatia) on 7th September 2012, and shows how the harmonic wavelet transform can be effectively used: first, to adjust a recorded accelerogram to match a given elastic design spectrum; second, to generate a number of fully non-stationary samples with the same probabilistic features.
TH2.L09.4 - CHARACTERISTIC ANALYSIS OF VEHICLE TARGET IN QUAD-POL RADARSAT-2...grssieee
1) The document analyzes the characteristic backscattering properties of vehicle targets in quad-polarimetric Radarsat-2 SAR images.
2) Experiments at different incidence angles and azimuth angles found significant differences in the radar cross section and polarization components of vehicle targets.
3) Polarization decomposition analysis showed double bounce scattering is an important characteristic for detecting trucks on roads, and vehicles are best detected when oriented parallel to the SAR flight direction.
Welcome to International Journal of Engineering Research and Development (IJERD)IJERD Editor
This document presents a transit time model for short gate length ion-implanted GaAs MESFETs. It develops a 2D analytical model to calculate the potential distribution and electric field in the channel region. Based on this, it derives an expression for transit time by considering the carrier velocity and saturation effects. It also presents an equation for drain current as a function of transit time, doping profile, and other device parameters. Simulation results using MATLAB are shown for Id-Vd characteristics and transit time for different device geometry and material parameters. The model aims to better understand the underlying device physics of optically controlled GaAs MESFETs.
Development of Reliability Analysis and Multidisciplinary Design Optimization...Altair
This document summarizes the capabilities of the RAMDO software for reliability-based design optimization (RBDO). It discusses both sensitivity-based and sampling-based RBDO approaches in RAMDO. It also provides examples of multidisciplinary applications of RAMDO in areas like fatigue analysis, casting process design, vehicle crashworthiness, and more. Several published case studies demonstrate how RAMDO has been used to optimize designs while accounting for input variability and reliability constraints.
This document proposes a modular beamforming architecture for ultrasound imaging that uses FPGA DSP cells to overcome limitations of previous designs. It interleaves the interpolation and coherent summation processes, reducing hardware resources. This allows implementing a 128-channel beamformer in a single FPGA, achieving flexibility like FPGAs but with lower power consumption like ASICs. The design is scalable, allowing a tradeoff between number of channels, time resolution, and resource usage.
goGPS is open source software that improves the accuracy of low-cost GPS devices through real-time kinematic (RTK) positioning and Kalman filtering. It was initially developed through 2007-2009 at the Polytechnic of Milan and Osaka City University. The software provides sub-meter level positioning and is being ported from MATLAB to Java to manage it as a collaborative open source project. goGPS processing will also be offered as a web service to provide accurate positioning from raw GPS data. Future work includes expanding supported signals and sensors and developing hardware to run the software-defined radio front-end.
A2 Structure Of Source Models Measurement Methods R Buetikoferahmad bassiouny
The document discusses aircraft noise source modeling. It describes the structure of source models, including sound power level directivity, operation conditions and other parameters. It also discusses different measurement methods that can be used to obtain data for the source models, such as in-flight measurements under operational conditions, arranged in-flight measurements, and analyzing processed data from manufacturers. The measurements require precision tracking and synchronization to attribute sound recordings to specific aircraft types, speeds, thrust settings and other factors.
The document discusses extending the Chemical Tagger natural language processing tool to be more applicable to climate science texts by incorporating climate science controlled vocabularies. It describes adapting the Chemical Tagger, originally designed for chemistry texts, to process abstracts from climate science journals. This includes modifying the tagger's dictionaries and grammars. Web forms and a CIM document viewer are also discussed which can generate and view outputs in the CIM XML format. The document aims to highlight climate science terms in texts to map them to a controlled vocabulary and better populate the CIM framework.
Multi-objective Genetic Algorithm Applied to Conceptual Design of Single-stag...Masahiro Kanazaki
"Multi-objective Genetic Algorithm Applied to Conceptual Design of Single-stage Rocket Using Hybrid Propulsion System" presented at The Eighth China-Japan-Korea Joint Symposium on Optimization of Structural and Mechanical Systems (CJK-OSM).
Conceptual Design and Structural Analysis of Solid Rocket Motor Casingijceronline
This paper is concern with theoretical design of the 100 kg solid rocket motor with predefined values of the burning rate is 100 mm/ sec, specific impulse is 240 sec and chamber pressure is 1000 psi. confined with selection of the material and basic concept of the rocket motor and its aspect during static test. Rocket motor is a highly complex aerospace component that consists of a metal casting, ablative liner and propellant grain. Also to determine the design pressure and burst pressure of a solid rocket motor casing .Preliminary design provided key propulsion outputs that would later be refined and assessed in the final design.
1) A senior capstone team at Portland State University developed a method for rapidly prototyping small bipropellant liquid fuel rocket engines using additive manufacturing.
2) They designed a 500 lbf thrust engine using liquid oxygen and ethanol as propellants, with regenerative cooling channels and a pintle injector.
3) The design process utilized Python Jupyter notebooks to generate parametric equations defining the engine geometry, which allows changing design parameters and quickly generating new geometry files for 3D printing.
IJERA (International journal of Engineering Research and Applications) is International online, ... peer reviewed journal. For more detail or submit your article, please visit www.ijera.com
DESIGN AND ANALYSIS OF HELICOPTER MAIN ROTOR HEADIRJET Journal
This document describes the design and analysis of a helicopter main rotor head. It begins with an abstract that outlines the objectives of modeling and analyzing a helicopter rotor head in SOLIDWORKS and ANSYS software. The introduction provides background on the main components of a helicopter rotor system. The methodology section then details the steps taken, which included designing the rotor head in SOLIDWORKS based on calculations, performing structural and modal analyses in ANSYS, and evaluating different materials. Dimensions of the rotor head are also presented. The document analyzes the rotor head to evaluate stresses, natural frequencies, and fatigue life.
This document discusses CFD analysis of solid fuel scramjet combustors. It begins with an introduction to scramjet engines and reasons for investigating solid fuels. It then reviews previous research on solid fuel scramjet combustor tests and numerical simulations. The computational domain and geometry of the scramjet combustor being modeled is described. Different classifications of solid propellant combustion models are discussed. Finally, the numerical method used in the CFD analysis with the FLUENT software is outlined. The analysis examines non-reacting and reacting flow fields in the combustor with a Mach 2 inlet flow and regression of the solid fuel boundary.
IRJET - Design and Analysis of Connecting Rod using Different MaterialsIRJET Journal
This document describes the design and analysis of a connecting rod using different materials through finite element analysis. The connecting rod was modeled in NX 10 software and analyzed in ANSYS Workbench. Materials analyzed included titanium alloy, beryllium alloy, magnesium alloy, and aluminum 360. ANSYS was used to analyze von mises stress, strain, deformation, factor of safety, and weight reduction for each material. Aluminum alloy was found to have a higher factor of safety, lower weight, lower stress, and was stiffer than forged steel. Fatigue analysis can also determine the lifetime of the connecting rod. The connecting rod was designed, modeled, and analyzed to compare the performance of different materials.
Welcome to International Journal of Engineering Research and Development (IJE...IJERD Editor
This document describes the design optimization of a tipper truck body. Three existing tipper truck body models were modeled and analyzed using finite element analysis software. The analyses found the maximum equivalent stress and total deformation for each model. An optimized model was then developed with reduced weight and stress compared to the original models. The optimized model had a mass of 413.04kg, maximum equivalent stress of 166.01MPa, and maximum deformation of 16.215mm, representing improvements over the original designs. The analyses demonstrated the ability to optimize truck body design for reduced weight and stress.
The document proposes developing a lunar hopper vehicle powered by a nuclear thermal rocket engine. It would take off and land repeatedly to gather soil samples from multiple locations on the moon's surface. An optimization problem is set up in MATLAB to determine the ideal dry mass and mass ratio to maximize the number of landing sites visited. The analysis finds that a design using a SNRE (Small Nuclear Reactor Engine) with a 3500 kg dry mass could achieve up to 28 sample retrievals from sites 5 km apart. A conceptual design of the vehicle is then presented, including subsystem mass budgets and dimensioned drawings. Future work areas are identified to further develop the design.
This document discusses scramjet inlets, which are a critical component of scramjet engines suitable for sustained hypersonic flight. Scramjet inlets must compress supersonic incoming air for combustion while minimizing losses. Different inlet designs achieve varying levels of compression efficiency. The document examines inlet types, desired compression levels, and presents a design example of a 3D scramjet inlet intended to operate between Mach 6-12 for access to space. Key challenges for scramjet inlets include achieving sufficient compression while minimizing shock losses and heating at high flight speeds.
This seminar gives idea about spacecraft propulsion i.e., actually what are different latest modes of propulsion are used in space agency and also the introduction of combustion of propellants.
This document summarizes Robert White's qualifications for an aerospace engineering position. It includes his education background with a B.S. in Aerospace Engineering and minor in Electrical Engineering from Purdue University. It outlines relevant skills and work experience, including internships modifying balloon and robot camera systems. It also details involvement in student engineering projects including a bucket elevator excavator for a lunar mining robot and cargo lander designs for a moon base project.
This paper discusses the processes involved in the additive manufacturing of a regenerative and film-cooled liquid rocket engine with a thrust of 10 kN using Inconel 718, while detailing validation techniques. A description of the objectives and design constraints provide the context and motivations. Computational Fluid Dynamics (CFD) models were developed and provided the expected pressure and thermal regimes under regenerative and film cooling. Additionally, Finite Element (FE) models were used to predict the capabilities of the engine structure. A description of 3D printing methods highlights the benefits and limitations of the technology, specifically the influence the design of liquid rocket engines. A pintle injector is used, printed as a separate, easily removable and replaceable component. Issues related to overhangs, surface roughness, and shrinkage; aspects related to post-print processing and the need to minimize machining are discussed. Results from the CT scans of the engine and its components are presented. The paper also outlines the series of tests that will be performed on this engine to verify its performance and provide design basis for future works. This engine will be used to power the reusable flight vehicle that is under development at the Kyushu Institute of Technology in Japan. The student-led Liquid Propulsion Laboratory at the University of Southern California is responsible for the work detailed below.
IRJET- Research Review on Field of Exhaust Manifold DesignIRJET Journal
This document summarizes research on exhaust manifold design for spark ignition engines to reduce emissions. It reviews 12 previous studies that used various approaches like modeling, CFD analysis, and experimental testing to optimize exhaust manifold geometry. The studies evaluated parameters like back pressure, exhaust velocity, thermal performance, and emissions. The document identifies gaps in the literature around limited research on different manifold geometries and their effects. It concludes by setting objectives for further research to conduct a comparative study of manifold designs to address exhaust emission problems.
ENERGICO: A Revolutionary Software Design Tool for Gas Turbine Combustor and ...Reaction Design
ENERGICO is a complex system-design simulation tool that works by applying detailed chemistry technology to solve the toughest gas-turbine engineering problems related to emissions reduction and stability. By using ENERGICO to model and test new combustor designs, companies can save millions in gas turbine development costs and substantially reduce time-to-market when compared to traditional physical prototype testing.
This report summarizes the preliminary design of the EcoBobcat DEP19 aircraft, which uses distributed electric propulsion (DEP) with 14 propellers powered by turbo-electric generators. The design team selected epoxy sheet molding compound (carbon fiber) as the primary material. An estimated empty weight of 3,200 kg was calculated based on comparable aircraft. A novel "looped-back wing" concept is proposed, with the main wing looping back to attach near the tail, powered by superconducting motors. Performance analysis shows the aircraft meets all competition requirements with a range over 3,500 km, endurance over 8 hours, and a climb rate of 513 m/min. Structural analysis confirmed the wing can
Geoffrey Wardle has over 40 years of experience in air and space research and development. His career began in 1982 with designing coatings to protect rocket engine parts from corrosion for the LEROS liquid fuel rocket engine. In the 1980s and early 1990s, he conducted structural qualification testing for components of Eurofighter Typhoon and developed test methodologies at establishments including RAE Farnborough and BAe. Currently, he is researching advanced composite airframe technologies and supersonic bomber design using simulation tools from his graduate studies.
Vikram Mane is seeking a position that provides opportunities for continuous learning and contributing to organizational goals. He has over 7 years of experience as a Design Engineer working on projects for companies like Tech Mahindra, Bombardier Aerospace, and Mitsubishi Heavy Industries. Some of his project experiences include designing a retractable landing gear system, tolerance analysis of aircraft wings, and creating CAD models for MRJ aircraft components. Vikram has strong skills in stress analysis, kinematics, design for manufacturing, and using tools like CATIA. He is a quick learner with good communication and teamwork abilities.
Finite Element Analysis of Solar impulse aircraftAdarsh Agrawal
The presentation discussed about the Finite Element Analysis that was done on the famous solar impulse aircraft which was one of those projects that was funded by Google. The presentation includes information about the project and how the aircraft came into being.
Authors: Adarsh Agrawal, Gunjan Javaria and Vaibhav Mahawar
IRJET- Review on Methodology of Furnace Burner Design for Thermal Power Plant...IRJET Journal
This document discusses the design optimization of furnace burners in thermal power plants using computational fluid dynamics (CFD). It begins by introducing thermal power plants and the importance of designing efficient, clean and economical combustion systems. It then discusses using CFD to analyze key burner parameters like velocity, angle, size and configuration to maximize mixing efficiency and combustion. The goal is to determine the most cost-effective combination of parameters. CFD analysis can provide insights to improve flame stability and reduce emissions and losses compared to experimental testing alone.
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Multidisciplinary and Multi-objective Design Exploration Methodology for Conceptual Design of a Hybrid Rocket
1. Infotec@Aerospace 2011
I@A-89 Evolutionary Design of Intelligent Systems AIAA-2011-1634
Multidisciplinary and Multi-objective Design Exploration
Methodology for Conceptual Design of a Hybrid Rocket
Yukihiro Kosugi
Tokyo Metropolitan University (TMU)
Akira Oyama
Japan Aerospace Exploration Agency
Kozo Fujii
Japan Aerospace Exploration Agency
Masahiro Kanazaki
Tokyo Metropolitan University (TMU)
2. Contents 2
Background
Objectives
Design method
Evaluation procedure of LV with HRE
Multi-objective Genetic Algorithm (MOGA)
Scatter Matrix Plot (SPM)
Design problem for LV with HRE
Design variables
Objective functions
Results
Design results
Visualization of non-dominated solutions
Design knowledge
Conclusions
3. Background1 Rockets presently used for space transportation 3
Solid-propellant rocket engine
Advantage:・Simple mechanism and construction
・Easy to maintain the propellant
Disadvantage:・Low specific impulse (Isp)
・Inability to stop combustion after it is ignited
・Environment issues
(caused by ammonium perchlorate (NH4ClO4),
and aluminum oxide (Al2O3))
Liquid-propellant rocket engine
Advantage :・High specific impulse (Isp)
・Ability to stop/restart combustion
Disadvantage:・Complex mechanism and construction
・Risk of explosion
・Difficulty to store low temperature propellant
4. Background2 What is hybrid rocket? 4
Hybrid Rocket Engine(HRE) : propellant stored in two kinds of phases
It can adopt the beneficial features of both the liquid and solid rockets.
Solid fuel + Liquid oxidizer :
Advantage of HRE
・Simple construction and mechanism
・Higher specific impulse (ISP) than solid rocket engine
・Ability to stop/restart combustion
・Low environmental impact and low cost
5. Background4 Design of HRE 5
Solid rocket:Premixing type solid propellant
Fuel rocket:Mass flow control of fluid propellant
→ Easy to maintain a constant oxidizer and mass -
fuel ratio (O/F) and to get a stable thrust
HRE:The mixture of fuel and oxidizer is initiated after ignition.
Combustion occurs in the boundary layer diffusion flame.
→ Because O/F is decided in this part of combustion process, the solid fuel
geometry and the supply control of the oxidizer have to be optimally
combined.
⇔With excessive mass flow of oxidizer, the
rocket achieves higher thrust, but structural
weight should be heavier .
Importance to find optimum fuel geometry and oxidizer supply
⇒Multi-disciplinary design which is considered propulsion,
structure and trajectory
6. Background5 Meta-heuristics approach in aircraft design 6
Evolutionary Algorithm based Design Exploration
Application of Mitsubishi Regional Jet (MRJ)
Targets
•Wing design
•High-lift Airfoil design
•Nacelle chine design
Design Exploration
•Genetic Algorithm
•Surrogate model
•Data mining
・Chiba, K., Obayashi, S., Nakahashi, K., and Morino, H., "High-Fidelity Multidisciplinary Design Optimization of Aerostructural Wing
Shape for Regional Jet," AIAA Paper 2005-5080, AIAA 23rd Applied Aerodynamics Conference, Toronto, Canada, June 2005.
・Kanazaki, M., and Jeong, S., “High-lift Airfoil Design Using Kriging based MOGA and Data Mining,” The Korean Society for
Aeronautical & Space Sciences International Journal, Vol. 8, No. 2, pp. 28-36, November 2007.
・Kanazaki, M., Yokokawa, Y., Murayama, M., Ito, T., Jeong, S., and Yamamoto, K., “Nacelle Chine Installation Based on Wind Tunnel
Test Using Efficient Design Exploration,” Transaction of Japan Society and Space Science, Vol.51, No. 173, pp. 146-150, November
2008. … etc.
Design Exploration is also expected in MDO for hybrid rocket.
7. Objectives of this study 7
Development of the evaluation tool for concept of
launch vehicle (LV) with HRE
Evaluation based on the empirical model
Demonstration of multi-disciplinary design using
genetic algorithm
Conceptual design of single stage surrounding
rocket which achieves low gross weight and high
flight altitude
Knowledge discovery using data mining
8. Design method1 evaluation1 8
Overview of the evaluation procedure
Input variable Output variable
* Mass flow of oxidizer [kg/s] * Flight altitude [km]
* Fuel length [m] * Gross weight [kg]
* Port radius of fuel [m] * Total oxidizer weight [kg]
* Combustion time [s] * Total fuel weight [kg]
* Pressure of combustion chamber [MPa] * Nozzle length [m]
* aperture ratio of nozzle [-] * Combustion chamber length [m]
* Oxidizer tank length [m]
* Rocket radius [m]
* Rocket aspect ratio [-]
* Nozzle throat area [m2]
* Thrust at ignition [kN]
* Initial oxidizer mass flux [kg/m2s]
* History of flight, thrust, and
combustion chamber pressure
9. Design method2 evaluation2 9
O/F and thrust power estimations
Underlined variables are part of the design parameters.
moxi t
O F (t )
m fuel t
rport (t ) a Goxi t
n
Mass of vaporized fuel: m fuel t 2rport t L fuel fuel rport (t )
A
NASA-CEA
t
rport (t ) rport (0) rport ( )d
0
T t T m propue Pe Pa Ae
m prop (t ) moxi (t ) m fuel (t )
fuel
t
moxi t
= mass flow of oxidizer m prop t
= mass flow of propellant rport (t ) rport (0) rport ( )d
m fuel t
= mass flow of fuel 0
Peh = pressure in the combustion chamber
Lfuel = length of fuel Pe = pressure at nozzle exit
ρfuel = density of fuel (constant) Pa = pressure of atmosphere at flight altitude
rport = radius of fuel port ue = velocity at nozzle exit
T(t) = thrust ηT λ = momentum loss coefficient at nozzle exit by friction (<1)
= total thrust loss coefficient by deflection of propellant at nozzle exit (<1)
10. Design method3 evaluation3 10
Weight and length estimations
Mtot is estimated by the sum of the components’ weight
moxi t dt
tburn
M tot M engine M pay M ex M oxi
0
m fuel t dt
tburn
M engine M oxi M fuel M res M ch M fuel
0
2
M ex M engine M res Vres
3
Ltot is one and a half times as long as HRE for including payload. M ch Vch
tburn = combustion time
Moxi = mass of total oxidizer
Mfuel = mass of total fuel
Mres = mass of the oxidizer tank
Mch = mass of the combustion chamber The sketch of the oxidizer tanks. The sketch of the nozzles.
Vres = integrated volume of material for the oxidizer tank
Vch = integrated volume of material for the combustion chamber
Mtot = gross weigh Ltot = total length of the rocket
Mengine = engine weight Lch = length of the combustion chamber (=Lfuel)
Mpay = payload weight Lres = length of the oxidizer tank
Mex = weight of other equipments Lnozzle = length of the nozzle
11. Design method4 evaluation4 11
Trajectory prediction S-520: JAXA’s surrounding solid propellant rocket
Equation of motion
T t Dt
at g
M tot t
D(t) = total drag at time t
Friction drag coef. of outer surface of the rocket
A(t) = acceleration at time t
0.455
C D f , Design (t ) g = gravitational acceleration
log 10 Re2.58 1 0.144M
2 0.65 Dp, Design(t)
Df, Design(t)
=
=
pressure drag at time t
friction drag at time t
Pressure drag coeff. based on S-520 flight data Re = Reynolds number
S wet ,S 520 CDp, Design(t) = pressure drag coefficient at time t
C D p , Design (t ) C D,S 520 (t ) C D f ,S 520 (t ) CDf, Design(t) = friction coefficient drag at time t
S ref ,S 520 CDp, S-520(t) = pressure drag coefficient of the solid rocket S-520
D p , Design (t ) qS ref , DesignC D p ,S 520
CDf, S-520(t) = friction drag coefficient of the solid rocket S-520 a
D
q = dynamic pressure
f , Design (t ) qS wet , DesignC D f , Design
Sref, Design = area of cross section of the designed rocket
Swet Design = wetted area of cylinder of the designed rocket
D(t ) D p , Design (t ) D f , Design (t ) Sref, S-520 = area of cross section of the solid rocket S-520
Swet S-520 = wetted area of cylinder of the solid rocket S-520
The aerodynamic effect of the rocket length and diameter can be evaluated.
12. Design method5 design method1 12
Heuristic search:Multi-objective genetic algorithm
(MOGA)
Inspired by evolution of life
Selection, crossover, mutation
Global search
Pareto-ranking method
Ranking of designs for multi-objective function
Sub-population
Individual
Individual
Island model
Migration
Sub-population
(a) (b)
Hiroyasu, T., Miki, M. and Watanabe, S., “The New Model of Parallel
Genetic Algorithm in Multi-Objective Optimization Problems (Divided Range
Multi-Objective Genetic Algorithm),” IEEE Proceedings of the Congress on
Evolutionary Computation 2000, Vol. 1, pp. 333-340, 2000.
13. Design method6 design method2 13
Scatter Plot Matrix (SPM)
→For the design problem investigation
a Scatter plot of avs.b
b
Correlation of avs.b
c
d
SPM arranges two-dimensional scatter plots among attribute values like a matrix
・The present SPM shows scatter plots on the upper triangular, and
correlation coefficient on the lower triangular (Software R is used for statistical
computing and graphics.)
14. Design problem for LV with HRE1 14
Swirling oxidizer type HRE
Proposed by Yuasa, et al.
Swirling oxidizer is supplied into the fuel.
Polypropylene is employed as a fuel.
rport t 0.0826Goxi
This expression was
0.55 provided by Prof. Yuasa.
regression rate against the mass flux of the oxidizer
Yuasa, S., et al, “Fuel Regression Rate Behavior in Swirling-Oxidizer-Flow-Type Hybrid Rocket Engines,” Proc 8th International
Symposium on Special Topics in Chemical Propulsion, No. 143, 2009.
15. Design problem for LV with HRE 15
Design target
the surrounding rocket with assuming that the 40kg payload is carried
Design variables (6)
Lower Upper
Mass flow of oxidizer [kg/s](dv1) 1.0 30.0
Fuel length [m] (dv2) 1.0 10.0
Port radius of fuel [m] (dv3) 0.01 0.30
Combustion time [s] (dv4) 10.0 40.0
Pressure of combustion chamber [MPa] (dv5) 3.0 6.0
aperture ratio of nozzle [-](dv6) 5.0 8.0
Objective functions (2)
Minimize Gross weight, Wgross
Maximize Maximum flight altitude Hmax
16. Results1 Sampling results by MOGA
16
MOGA result colored by rocket’s aspect ratio (length/diameter)
After 100 generation started with 64 individuals
Non-dominated solutions
The solutions for which Hmax is greater
than 150 km have a larger Wgross than the
solutions for which Hmax is less than 150
km.
To achieve high flight altitude, the rocket’s
aspect ratio becomes high.
Optimum direction
-There is trade-off between Wgross and Hmax.
-Maximum Hmax is about 180km.
- The rocket considered here is suitable for the sub-orbital flight around 100km altitude.
17. Results2 Comparison with JAXA’s S-210
17
S-210 Des1
Flight altitude [km](H) 110.0 108.2
Gross weight [kg](W) 260.0 334.0
Payload weight [kg] 40.0 40.0
Payload weight/gross weight 0.154 0.120
Fuel length [m] 5.2 8.5
Fuel diameter [mm] 210.0 210.0
Rocket’s aspect ratio [-] 24.8 40.5
-Comparison with sub-orbital solid rocket S-210
which flight about altitude 100km
-Aspect ratio of the HRE rocket was larger than that
of the S-210, because the oxidizer tank and the solid
fuel are placed longitudinally in the rocket.
-Wpey/Wgross of the designed rocket was less than
www.isas,jaxa,jp
that of the S-210. → Pch is supposed to be constant
during the combustion process
18. Results3 Visualization of non-dominated solution by SPM
18
dv3(port diameter in the fuel) of non-
dominated solutions becomes less.
→ better volumetric efficiency and
slender chamber
There are correlation among dv1(mass
flow of oxidizer), dv2(fuel length), and two
objective functions.
The rockets’ aspect ratio and the Acc_max
are correlative relation.
19. Results4 Design knowledge from non-dominated solution
19
There is a trade-off between the minimization of the gross
weight and the maximization of the flight altitude.
The designed rockets achieve a higher flight altitude by
reducing the aerodynamic drag and by employing a higher
aspect ratio.
The rockets which is lower oxidizer mass flow, the
diameter of the combustion chamber becomes smaller. As
this result, the weight of the combustion chamber
decreases.
The rocket with HRE, which achieves a higher flight
altitude and lower weight, tends to be long and narrow in
the present MDO problem
20. Conclusions 20
Development of the design tool for concept of LV) with HRE
Evaluation based on the empirical model
Evaluation module (cygwin script) is open to the public,
http://bit.ly/hmBYgB.
English manual will be also uploaded in this April-May. This
uploading will announced in twitter, (@tmu_craft_desig #hre).
Knowledge discovery of multi-disciplinary design for a LV with
HRE
High aspect ratio rocket is better for the present design problem.
With heavier mass of the oxidizer, the rocket’s gross weight becomes
heavier.
Future work:
The sophisticate of the evaluation tool.
Consideration of the pressure time variation of the combustion chamber.
Structural type for realistic rocket.
Conceptual design of orbital rocket for microsat launch
21. Acknowledgement 21
We thank members of the hybrid rocket engine
research working group in ISAS/JAXA for giving
their experimental data and their valuable advices.
This paper and presentation was supported by
ISAS/JAXA.
Thank you very much for your kind attention.