407 standards codes for aircraft fuel servicing and the ISO AS/EN 9100 Series of standard codes for aerospace, aviation and defense systems, that we in-cooperated in the modeling and simulation. Data collection was a vital stage of the project, in which I analyzed several standardization organization codes for aerospace engineering technologies, including the These codes assisted me in designing the combustion process, speed optimization, ensuring low losses at suitable temperature ranges and more so made the product industrially compatible. I gathered customer specifications from the users of this product from where I made notes on some input parameters. Finally I collected data from user manuals, datasheets and databases for related fuel combustion simulations that assisted me on the parameter inputs for the model. I then drafted the functional flow diagram for the scramjet engine in different stages as in the following figure. Figure 2. Cavity Based Scramjet Combustion Engine Schematic Diagram I then designed the system step by step, by deriving the structural model for the combustion engine including the supersonic intake, the diffuser, flame stabilizer, kerosene combustor and the nozzle. From the data collected, I specified the materials for each with high strength, light weight and less sensitive to temperature changes. I then computed the chemical reaction for the mass of the kerosene required for one cycle and thus the capacity of the tank depending on the flight time and Mach 5 speed.
407 standards codes for aircraft fuel servicing and the ISO AS/EN 9100 Series of standard codes for aerospace, aviation and defense systems, that we in-cooperated in the modeling and simulation. Data collection was a vital stage of the project, in which I analyzed several standardization organization codes for aerospace engineering technologies, including the These codes assisted me in designing the combustion process, speed optimization, ensuring low losses at suitable temperature ranges and more so made the product industrially compatible. I gathered customer specifications from the users of this product from where I made notes on some input parameters. Finally I collected data from user manuals, datasheets and databases for related fuel combustion simulations that assisted me on the parameter inputs for the model. I then drafted the functional flow diagram for the scramjet engine in different stages as in the following figure. Figure 2. Cavity Based Scramjet Combustion Engine Schematic Diagram I then designed the system step by step, by deriving the structural model for the combustion engine including the supersonic intake, the diffuser, flame stabilizer, kerosene combustor and the nozzle. From the data collected, I specified the materials for each with high strength, light weight and less sensitive to temperature changes. I then computed the chemical reaction for the mass of the kerosene required for one cycle and thus the capacity of the tank depending on the flight time and Mach 5 speed.
CDR-Report-Sample-for-Aeronautical-Engineer-PDF.docx