A study of model-based systems engineering (MBSE) applied to a small-lift launch facility is presented. The research uses Systems Modeling Language (SysML) products and functional diagrams to document the ground systems on a launch pad servicing a small class payload (0-2 tons). With the projected growth in launch cadence of small-lift rockets in the coming decade, there is a need to design increasingly complex launch systems with greater efficiency. The potential improvements in project communication, quality, and productivity are explored by developing a model following the ISO/IEC 15288 technical process framework and the International Council on Systems Engineering (INCOSE) Object-Oriented Systems Engineering Method (OOSEM) methodology. The stakeholder requirements are defined and analyzed to provide traceability to individual systems and subsystems. An architecture is proposed by generating engineering artifacts such as piping and instrumentation drawings. The concepts are verified and validated by performing engineering trade studies concentrated on the pneumatic and fuel subsystems.
A parametric study of a novel turbojet engine with an auxiliary combustion chamber, nicknamed the TurboAux engine is presented. The TurboAux engine is conceived as an extension of a turbojet engine with an auxiliary bypass annular combustion chamber around the core stream. The study presented in this article is motivated by the need to facilitate clean secondary burning of fuel at temperatures higher than conventionally realized from air exiting the low-pressure compressor. The parametric study is initiated by performing a simple optimization analysis to identify optimal 'fan' pressure ratios for a series of conventional lowbypass turbofan engines with varying bypass ratios (0.1 to 1.5). The fan pressure ratios for corresponding bypass ratios are chosen for studying varying configurations of the TurboAux engine. The article is presented in two phases-(i) Phase I presents the simulations carried out to arrive at an optimal configuration of a TurboAux engine and it formulation, (ii) Phase II presents simulations and results to compare the performance of a low-bypass turbofan engine to the TurboAux engine. The formulation and results are an attempt to make a case for charter aircrafts and efficient close-air-support aircrafts.
A parametric study of a novel turbofan engine with an auxiliary high-pressure bypass (AHPB) is presented. The underlying motivation for the study was to introduce and explore a configuration of a turbofan engine which could facilitate clean secondary burning of fuel at a higher temperature than conventionally realized. The study was also motivated by the developments in engineering materials for high-temperature applications and the potential utility of these developments. The parametric study is presented in two phases. Phase I presents a schematic of the turbofan engine with AHPB and the mathematics of the performance parameters at various stations. The proposed engine is hypothesized to consist of three streams—core stream, low-pressure bypass (LPB) stream, and the AHPB or, simply, the high-pressure bypass (HPB) stream. Phase II delves into the performance simulation and the analysis of the results in an ideal set-up. The simulation and results are presented for performance analysis when (i) maximizing engine thrust while varying the LPB and AHPB ratios, and (ii) varying the AHPB ratio while maintaining the LPB ratio constant. The results demonstrate the variations in performance of the engine and a basis for examining its potential utility for practical applications.
His research interests include design & development of pico-, nano-& micro-satelllites (PN-MSats) for atmospheric research and technology advancement. He has collaborated with NASA Goddard Space Flight Center to conduct research in the field of small satellites. He is actively pursuing support from NASA, AFRL, NSF and other organizations supporting research in aerospace engineering. Most recently, he has proposed (NSF) to develop a 6U CubeSat in collaboration with University of Florida, NASA and Maryland Aerospace Inc to advance the understanding of upper atmospheric composition. Through support from Rockwell Collins, he has initiated the development of an Amateur Radio Station on the Tuskegee University campus. The station is envisioned to support the ground system needs of a CubeSat program at Tuskegee University and impart hands on communication skills for the students of College of Engineering. Dr. Asundi actively publishes in the above fields and mentors/supports undergraduate research in his department. Dr. Asundi also serves on the PhD committee of Bungo Shiotani, a graduate student at University of Florida, to research the project life cycle of CubeSat systems. His research interests include the following: • Small Satellites (CubeSat) Design & Development • Spacecraft Attitude Determination & Control • Autonomous Systems Design & Development • Systems Engineering for Small Satellites • Vehicle Health Monitoring
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