Methane (CH4) is a promising rocket fuel for various future space mission scenarios. It has advantages in terms of cost, performance, and environmental friendliness. Currently, there no clear definition on standards specifications liquefied methane or similar liquids such as natural gas (LNG) their use fuel. However, those regulations are necessary the commercial, safe, proper operation engines...

Abstract The typical methods for predicting rocket engine noise were comprehensively illustrated. Simultaneously including some modification, implement environmental prediction of any number, position via programming. For instance, in a liquid engine, field the double was predicted, results which compared with experimental data. We then evaluated advantages and disadvantages different analyzed ...

A low-power microwave arjet thruster was studied using ammonia gas as propellant. The purpose of the project was to generate ammonia plasma using a 7.5 GHz magnetron and a cylindrical cavity thruster, which is resonant in the TM001 mode [1]. The desired pressure was atmospheric or above while generating a thrust of roughly 20mN and an Isp of about 500s operating at low power (<100 kW). Introduc...

The objective of this work is to develop deep theoretical methods that are based on the solution of the integral boundary layer equations for investigating film cooling in liquid rocket engine. The integral model assumes that heat is transferred from hot free stream gas to the liquid film both by convection and radiation. The mass is transferred to the free srteam gas by the well-known blowing ...

This note describes a web-based tool for storm analysis using multiple data sets developed for use in research of thunderstorms and forecasting applications. The tool was developed for users to monitor atmospheric changes along the path of storm systems. It demonstrates the use of the Thematic Real time Environmental Data Distributed Services (THREDDS) being developed by University Corporation ...

This paper reports the results of initial efforts to apply the System Sensitivity Analysis (SSA) optimization method to the conceptual design of a single-stage-to-orbit (SSTO) launch vehicle. SSA is an efficient, calculus-based MDO technique for generating sensitivity derivatives in a highly multidisciplinary design environment. The method has been successfully applied to conceptual aircraft de...

Lateral nozzle forces are known to cause severe structural damage to any new rocket engine in development. Currently there is no fully coupled computational tool to analyze this fluid/structure interaction process. The objective of this study was to develop a fully coupled aeroelastic modeling capability to describe the fluid/structure interaction process during the transient nozzle operations....