Design, fabrication and testing Nitrous Oxide feeding system of a hybrid rocket motor

Space access is more important than ever. Over the years, the aerospace industry market has expanded at the expense of demand for launch servi:es, such as the orbiting of communication satellites, but also due to the growing interest in space tourism and the dismantling of the space shuttle. Currently, most small countries can build small satellites, but most cannot afford to launch one by themselves . Hybrid rocket propulsion technology also shows promise for the next gereration of sounding rockets and especially for the launch of small payload. this study was conducted to determine the vessel's strength of pressure, piping and bulkhead (FEM and pressure test). In addition, the design of oxidizer tank, control valves, bulk heads and injector nozzle is also carried out. From the literature review, nitrous oxide oxidizer was coosen as an oxidizer am the milti-flow injector was used to counter the probems of using hazardous oxidizer material. The objective of this study is to design, fabricate and test N20 reservoir (oxidizer tank, injector) and controller. In this case, an experiment method was use to determine the multi-flow pattern of the injector. Finite Element Analysis (FEA) is one of the tools to perform analysis pressure of the vessel piping and bulkhead. The second objective is to design and install the Data Acquisition (DAQ) System for hybrid rocket system. A software program was developed to collect data from the test bed. This thesis proposes to devek>p an oxidizer tbw control system To do tlm, an oxidizer test bed was built in the labaratory, whi;h consists of all the components in an actual rocket engine. Using this apparatus, the behaviour of nitrous oxide in the system was analysed, including the characterization of the oxidizer flow control valve and the response of the system to various parameters. This aim, to contribute to building a hybrid rocket motor which could eventually be used to power scientific rockets that are being built in support of propulsion research activities at the National Defence University of Malaysia (NDUM). The main aim of the study was to design and build the oxidizer system for the present UPNM hybrid rocket motor to be capable of a flight-viable hybrid rocket motor. The key finding are the design, development and testing of oxidizer (nitrous oxide) system of a hybrid rocket motor was successfully achieved. Next the firing test results (pressure, temperature and thrust) are successfully recorded by the DAQ system with self-pressurizing nitrous oxide delivery system provide a more realistic oxidizer for the liquefying fuel (stearic acid). The oxidizer feed and injection system have allowed for a complete design.