Multidisciplinary and Multi-objective Design Exploration Methodology for Conc...Masahiro Kanazaki
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.
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.
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 and Multi-objective Design Exploration Methodology for Conc...Masahiro Kanazaki
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.
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.
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
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.
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.
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.
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.
Seismic QC & Filtering with GeostatisticsGeovariances
The quality of seismic volumes is critical in building reliable reservoir models. Seismic data are often polluted by acquisition or processing artifacts which may have strong impact on subsequent seismic processing or interpretation. Geostatistics allows filtering efficiently seismic noise and artifacts without modifying the signal.
Geovariances provides solutions from seismic data quality control and filtering to reservoir characterization. This technology is based on geostatistics and all algorithms are available in Isatis, leader in geostatistical software solutions.
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.
Carbon nanotubes have the potential for solid state hydrogen storage if modified with heteroatoms. Theoretical studies show that heteroatoms like nitrogen can facilitate hydrogen activation and storage in carbon nanotubes. For effective storage, heteroatoms must be incorporated geometrically and chemically into the carbon structure. Boron-substituted carbon nanotubes were synthesized using template methods and exhibited up to 2% hydrogen storage capacity, depending on the boron configuration within the nanotube structure. Heteroatom substitution in carbon nanotubes provides a promising approach for developing hydrogen storage materials.
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.
The document summarizes formulations for optimization problems under stochastic dominance constraints. It presents formulations for both first-order and second-order stochastic dominance. For second-order stochastic dominance, it introduces the SSDLP and cSSD formulations. For first-order stochastic dominance, it introduces the FDMIP, cFSD, and FSD formulations. It also discusses solving the resulting mixed integer programs using cutting planes and specialized branching heuristics.
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).
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
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.
1) A class at Washington State University designed and built three sounding rockets with different propulsion systems, including a hybrid rocket system. Each team was given a $3,000 budget.
2) A hybrid rocket combines aspects of solid and liquid fuel rockets. It uses a liquid oxidizer injected into a combustion chamber containing a solid fuel grain, allowing for throttling and restart capabilities.
3) The hybrid rocket used a non-homogeneous fuel grain consisting of HTPB and paraffin wax. The combination provided structural stability from the HTPB and a high regression rate from the wax.
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.
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 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 testing of a 1,500 lbf thrust liquid oxygen/liquid methane rocket engine. The engine was developed through a collaboration between Armadillo Aerospace and NASA and tested at both sea level and simulated altitude conditions. Key findings included:
1) The engine was successfully ignited using both a gas torch and pyrotechnic igniter at sea level and vacuum.
2) Performance data was obtained for the engine using a dual-bell nozzle configuration at altitudes from 90,000 to 50,000 feet.
3) Armadillo Aerospace conducted the first tests of a self-pressurizing liquid oxygen/liquid methane propulsion system, eliminating the need for helium pressurization
Prototech is a technology company with 40 employees that works to create solutions for space travel, green energy production, and other industries. It has expertise in mechanical engineering, fluid dynamics, materials testing, and green energy systems. The company aims to be an attractive partner for developing new technologies through collaboration between its technology, solutions, parts, and services departments.
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.
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.
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.
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.
Seismic QC & Filtering with GeostatisticsGeovariances
The quality of seismic volumes is critical in building reliable reservoir models. Seismic data are often polluted by acquisition or processing artifacts which may have strong impact on subsequent seismic processing or interpretation. Geostatistics allows filtering efficiently seismic noise and artifacts without modifying the signal.
Geovariances provides solutions from seismic data quality control and filtering to reservoir characterization. This technology is based on geostatistics and all algorithms are available in Isatis, leader in geostatistical software solutions.
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.
Carbon nanotubes have the potential for solid state hydrogen storage if modified with heteroatoms. Theoretical studies show that heteroatoms like nitrogen can facilitate hydrogen activation and storage in carbon nanotubes. For effective storage, heteroatoms must be incorporated geometrically and chemically into the carbon structure. Boron-substituted carbon nanotubes were synthesized using template methods and exhibited up to 2% hydrogen storage capacity, depending on the boron configuration within the nanotube structure. Heteroatom substitution in carbon nanotubes provides a promising approach for developing hydrogen storage materials.
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.
The document summarizes formulations for optimization problems under stochastic dominance constraints. It presents formulations for both first-order and second-order stochastic dominance. For second-order stochastic dominance, it introduces the SSDLP and cSSD formulations. For first-order stochastic dominance, it introduces the FDMIP, cFSD, and FSD formulations. It also discusses solving the resulting mixed integer programs using cutting planes and specialized branching heuristics.
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).
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
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.
1) A class at Washington State University designed and built three sounding rockets with different propulsion systems, including a hybrid rocket system. Each team was given a $3,000 budget.
2) A hybrid rocket combines aspects of solid and liquid fuel rockets. It uses a liquid oxidizer injected into a combustion chamber containing a solid fuel grain, allowing for throttling and restart capabilities.
3) The hybrid rocket used a non-homogeneous fuel grain consisting of HTPB and paraffin wax. The combination provided structural stability from the HTPB and a high regression rate from the wax.
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.
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 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 testing of a 1,500 lbf thrust liquid oxygen/liquid methane rocket engine. The engine was developed through a collaboration between Armadillo Aerospace and NASA and tested at both sea level and simulated altitude conditions. Key findings included:
1) The engine was successfully ignited using both a gas torch and pyrotechnic igniter at sea level and vacuum.
2) Performance data was obtained for the engine using a dual-bell nozzle configuration at altitudes from 90,000 to 50,000 feet.
3) Armadillo Aerospace conducted the first tests of a self-pressurizing liquid oxygen/liquid methane propulsion system, eliminating the need for helium pressurization
Prototech is a technology company with 40 employees that works to create solutions for space travel, green energy production, and other industries. It has expertise in mechanical engineering, fluid dynamics, materials testing, and green energy systems. The company aims to be an attractive partner for developing new technologies through collaboration between its technology, solutions, parts, and services departments.
Prototech is a technology company with 40 employees that works to create solutions for space travel, green energy production, and other industries. It has expertise in mechanical engineering, fluid dynamics, materials testing, and green energy systems. The company aims to be an attractive partner for technology development projects through its unique solutions, high expertise, and sustainable values. It works across disciplines like mechanical construction, advanced calculations, and testing to develop solutions for future generations.
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.
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.
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.
This document provides a summary of Ravikiran Anapagaddi's background and qualifications. It includes his contact information, education history, areas of interest, professional experience, projects undertaken, research projects, technical skills, publications, presentations, and training. The document highlights that he has a Master of Technology degree from IIT Madras and a Bachelor of Technology degree from GVP College of Engineering. He has over 5 years of work experience in process engineering and research related to mathematical modeling and simulation of metallurgical processes.
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.
La presentació que Johan Steelant, director de la Divisió d'Anàlisi de Propulsió i Aerotermodinàmica del ESTEC-ESA va fer a Ecotendències Cosmocaixa el 31 de gener de 2012.
This document summarizes Kevin McMahon's presentation on disposal research activities at Sandia National Laboratories. It discusses the various disposal options being considered, including deep boreholes, crystalline host rock, argillite host rock, and salt host rock. It also outlines work supporting these options, such as on dual purpose canisters and regional geology studies. The presentation focuses on the technical challenges of building confidence in multiple repository concepts without site-specific data and developing tools to characterize complex natural and engineered disposal systems.
Ravikiran Anapagaddi provides a resume summarizing his education and work experience in steel process engineering. He received a Master's degree in chemical engineering from IIT Madras and worked as a process engineer and systems engineer developing mathematical models of various steelmaking processes. His work focused on areas like gasification, inclusion behavior, thermodynamic modeling, and developing reduced order models and optimization techniques for steel production processes.
This document is a curriculum vitae for James C. Kuijper, a Senior Consultant specializing in Nuclear Reactor Physics. It lists his education, languages, computer skills, and extensive work experience in nuclear reactor physics and simulation code development since 1988. Notable roles include coordinating an EU project on plutonium and minor actinide management in thermal reactors, teaching nuclear reactor physics courses, and advising on criticality safety for nuclear installations in the Netherlands.
Materials science applications of HPC can help address challenges in developing new materials by enabling high-throughput screening of thousands of potential candidates using computational modeling. This reduces the time and cost of research and development compared to experimental methods alone. Examples discussed include identifying catalysts for fuel cells and optimizing electrolytes for lithium ion batteries through automated quantum chemistry calculations on large supercomputers.
Similar to Multi-Disciplinary Conceptual Design of Multi-Stage Hybrid Rocket using Genetic Algorithm and Data Mining Technique (20)
Lecture on “Aerodynamic design of Aircraft” in University of Tokyo 21st December, 2015. Optimization techniques, data-visualization and their applications are inclusive.
This document summarizes research on the design optimization of a launch vehicle concept using a clustered hybrid rocket engine for future space transportation. The researchers developed a design methodology for a launch vehicle with clustered hybrid rocket engines and investigated combinations of unit engines. Their objectives were to maximize payload to gross weight ratio and minimize gross weight. They defined four design cases and used multi-objective genetic algorithms and data visualization techniques to optimize the design variables. The results showed that a design with optimized engines for each stage performed best by avoiding excess unburnt fuel from shared engines across stages. Future work could further reduce unburnt fuel and improve payload ratio.
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Multi-Disciplinary Conceptual Design of Multi-Stage Hybrid Rocket using Genetic Algorithm and Data Mining Technique
1. 1
6th EUROPEAN CONGRESS ON COMPUTATIONAL METHODS IN APPLIED SCIENCES AND
ENGINEERING, the University of Vienna, Austria, September 10-14, 2012.
MULTI-DISCIPLINARY CONCEPTUAL DESIGN OF
MULTI-STAGE HYBRID ROCKET USING GENETIC
ALGORITHM AND DATA MINING TECHNIQUE
○Masahiro Kanazaki
Tokyo Metropolitan University
Yosuke Kitagawa
Tokyo Metropolitan University
Koki Kitagawa
Japan Aerospace Exploration Agency
Masaki Nakamiya
Kyoto University
Toru Shimada
Japan Aerospace Exploration Agency
2. 2
Contents
• Background
• Objectives
• Design methods
– Evaluation procedure of hybrid rocket engine (HRE)
– Multi-objective Genetic Algorithm (MOGA)
– Analysis of Variance (ANOVA)
– Self-organizing Map (SOM)
• Formulation (Design problem for LV with HRE)
– Design variables
– Objective functions
• Results
– Design and visualization results
– Design knowledge
• Conclusions
3. 3
Background
Rockets presently used for space
transportation
Solid-propellant rocket engine
Advantage:・Simple mechanism and construction
・Easy to maintain the propellant
Disadvantage:・Inability to stop combustion after it is ignited
・Low specific impulse (Isp)
・Environment issues
(caused by ammonium perchlorate (NH4ClO4),
and aluminum oxide (Al2O3))
Liquid-propellant rocket engine
Advantage : ・Ability to stop/restart combustion
・High specific impulse (Isp)
Disadvantage:・Complex mechanism and construction
・Difficulty to store low temperature propellant
・Risk of explosion
4. 4
Background
What is hybrid rocket?
• Hybrid Rocket Engine(HRE) :
propellant stored in two kinds of phases
It can adopt the beneficial features of both the liquid
and solid rockets. SpaceShipTwo
Advantage of HRE
Simple construction and mechanism
Ability to stop/restart combustion
Lower cost
HEAT-II
Expectation for private space transportation
Virgin Galactic:SpaceShipTwo
Copenhagen Suborbitals :HEAT-II for “TychoBrahe” launching
⇒HRE are introduced.
Research working group in ISAS/JAXA.
→Plan of ground test for 5kN class HRE.
5. 5
Background
HRE research working group (HRErWG)
・Mainly single port type fuel
rport (t ) a Goxi t
・Several studies are carried out.
n
(combustion, measurement, simulation,
and design optimization)
fuel
rport (t ) a Goxi t
n
Important empirical expression for several combustion
techniques.
rport (t ) a Goxi t
n
Index n and coefficient a are empirically summarized for each
combustion techniques.
・Swirling oxidizer type HRE with polypropylene fuel
・Glycidyl Azide Polymer(GAP) fuel
rport (tfuel a Goxi t
・WAX (paraffin) ) n
6. 6
Background
Difficulty of hybrid rocket design
Solid rocket:Preliminary mixed solid propellant
Liquid rocket:Control of mass flow of fluid propellant
→ Easy to maintain a constant oxidizer massand fuel
mass 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 too much 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
7. 7
Objectives
• Development of the evaluation tool for conceptual
design of launch vehicle (LV) with HRE
– Evaluation based on the empirical model
• Multi-disciplinary design exploration for concept of
three stage LV
– Solutions of multi-objective problem obtained by MOGA
– Knowledge discovery using data mining
8. 8
Flow chart of HRE evaluation
Calculation of engine specifications
- fuel size, time variation of O/F, Design variables
pressure of combustion chamber, etc.. ・ Initial value of oxidizer mass flow
・Initial value of O/F
Estimation of structural weight ・Coefficient a of regression rate
・Combustion chamber, Oxidizer tank, ・Initial value of mass flux of oxidizer
Pressurizing tank, nozzle ・Combustion time
・ Initial pressure of combustion chamber
・ Initial pressure of pressurizing tank
Engine specifications ・Aperture ratio of nozzle
Thrust by NASA-CEA* *NASA Chemical Equilibrium with Applications
(Gordon, S., et al, “Computer Program for Calculation
of Complex Chemical Equilibrium Compositions and
Trajectory Applications I. Analysis,” NASA RP-1311, 1994.)
No Kosugi, Y., Oyama, A., Fujii, K., and Kanazaki, M.: Multidisciplinary
t>combustion time?
and Multi-objective Design Exploration Methodology for Conceptual
Yes Design of a Hybrid Rocket, AIAA 2011-1634a, 2011.
Altitude, velocity, .. after mth stage combustion
9. 9
Flight Sequence
Ignition of 3rd stage
Separation of 2nd stage
Coasting
Target altitude
(perigee 250km)
Separation
of 1st stage
Launch
10. 10
Design exploration
Heuristic search:Multi-objective genetic algorithm
(MOGA)
Inspired by evolution of life
Selection, crossover, mutation
Searching global non-dominated
NSGA2 is employed.
BLX0.5 for cross over
Arbitral evaluation
Minimize f1
Minimize f2
Ranking by NSGA2 Crossover (BLX-α)
Flowchart of GA
11. 11
Design methods
Knowledge management1
Integrate
Analysis of Variance
One of multi-valiate analysis for quantitative information
The main effect of design variable xi:
i ( xi ) y( x1 ,....., xn )dx1 ,..., dxi 1 , dxi 1 ,.., dxn
ˆ
variance
where:
y( x1 ,....., xn )dx1 ,....., dxn
ˆ
μ1
Total proportion to the total variance:
i xi dxi
2
pi
y ( x1 ,....,xn ) dx1 ...dxn
2
ˆ
where, εis the variance due to design variable xi.
Proportion (Main effect)
12. 12
Design methods
Knowledge management2
Self-organizing map for qualititative information
– Proposed by Prof. Kohonen
– Unsupervised learning
– Nonlinear projection algorithm from high to two dimensional map
Design-objective
Multi-objective Each cell represents vector which has
same number of components as input.
Two-dimensional map
(Colored by an component, N component plane, for N
dimensional input.)
Multi-dimensional data *modeFrontier ®v4.0 is used.
13. 13
Design space
a can control by changing intensity of the oxidizer swirling.*( r a Gon )
* Hikone,S., et al, “Regression Rate Characteristics and Combustion Mechanism of Some Hybrid Rocket Fuels ,”Asian Joint Conference on
Propulsion and Power 2010.
14. 14
Design Problem
Design target: Design of three-stage rocket which can deliver micro-satellites
to the Sun-synchronous orbit (SSO) (perigee is 250km, apogee is 800km)
Objective functions
• maximize Payload mass/Gross mass (Mpay/Mtot)
• minimize Gross mass (Mtot)
Constraints
• After combustion of third stage,
Height > 250km
Angular momentum > 52413.5km2/s
-0.5deg. < Flight path angle < 0.5deg.
• Rocket aspect ratio < 20
• Radius of nozzle exit < Radius of rocket
• Area of grain port > 2・(Area of nozzle throat)
Combustion type
• Swirling oxidizer type engine
• Oxidizer:LOX, Fuel:WAX (FT-0070)
15. 15
Result
MOGA exploration
Optimum direction
• Trade-off between objective functions
• Mpay/Mtot of “Epsilon rocket” planed by JAXA is about 1.3%
⇒Lower cost than existent LVs
16. 16
Selected Design from Non-dominated Solutions
Selected rocket size
Length of rocket [m] 20.8
Diameter of rocket [m] 1.46
Aspect ratio of rocket [-] 14.3
1st stage 2nd stage 3rd stage
Length [m] 8.22 6.57 6.06
Diameter [m] 1.45 1.46 1.07
Gross mass [ton] 8.07 4.09 0.70
Structural mass [ton] 1.78 0.49 0.10
Structural mass ratio [%] 22.1 11.9 14.5
20.8
8.22 6.57 6.06
1.35 1.36 0.97
1.46
What kind of design can be high performance?
1.21 2.18 3.21 1.61 2.29 1.06 2.11 1.11 2.06 0.35 0.99 0.64 2.02
⇒Design knowledge discovery by means of data mining
17. 17
Knowledge discovery
Contribution ratio estimated by analysis of variance
Mtot Mpay/Mtot
• dv1, 9 (oxidizer mass flow ratios of 1st and 2nd stages) influence on Mtot.
• dv6, 14 (combustion pressure of 1st and 2nd stages) influence on Mpay/Mtot.
• dv1, 9, 17 (oxidizer mass flow ratios of all stages) influence on Mpay/Mtot.
– dv17 (oxidizer mass flow ratio of 3rd stage) remarkably influences on Mpay/Mtot.
⇒ Design of the engine for 3rd stage is important for low cost rocket.
18. 18
Knowledge discovery
• SOM visualization
• Trade-off between Mpay/Mtot and Mtot
• LV which can deriver high Mpay can not
always achieve high Mpay.
– Mpay maximization is not always explore high
efficient LV.
19. 19
Knowledge discovery
• Selection of design variables based on similarity of SOMs’ colored
map and contribution ratios by ANOVA.
• dv3, 11, 19 (coefficient a of regression rate) are also checked.
r 0 a Go 0
n
20. 20
Knowledge discovery
• Comparison among objective functions and design variables
dv5 dv6
dv1
2.420
139.5 56.01
To obtain higher Mpay/Mtot
60.4 46.01 1.900
• Moderate value of dv5(Combustion time of 1st stage)
dv9
dv14
1.600
dv17
3.677
18.30
• Smaller dv6, 14 (Pressure of combustion chamber of 1st and 2nd stage)
• Moderate value of dv1(Oxidizer mass flow of 1st stage)
• Larger dv9, 17(Oxidizer mass flow of 2nd and 3rd stage)
1.215 1.710
9.36
21. 21
Knowledge discovery
• Coefficient a of regression rate
r 0 a Go 0
n
To obtain higher Mpay/Mtot
• Lower regression rate at 1st stage
• Moderate a at 2nd stage
• Higher regression rate at 3rd stage
22. 22
Conclusions
Design exploration of multi-stage launch vehicle with
hybrid rocket engines
Empirical expression based evaluation of HRE
• Engine size, Thrust, Structure, and Flight
Global Exploration employing MOGA
• Type of HRE using FT0070 fuel with swirling oxidizer for all stages
• Trade-off between total mass ratio and payload-total mass ratio
Design knowledge using ANOVA and SOM
• Oxidizer mass flow of 1st and 2nd stages have predominant effect to
total mass.
• Pressure of combustion chamber of 1st and 2nd stages influence on
payload-total mass ratio
• Knowledge about what kind of engine design is promising for each stage.
Further study: Design exploration of LV which has different fuel in
each stage to found out better solution.
23. 23
Acknowledgement
• 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.