The thrust vector control problem for an upper-stage rocket with propellant slosh dynamics is considered. The control inputs are defined by the gimbal deflection angle of a main engine and a pitchingmoment about the center of mass of the spacecraft. The rocket acceleration due to themain engine thrust is assumed to be large enough so that surface tension forces do not significantly affect the p...

Because of its strong oxidizing properties, high density, low-toxicity and environmentally friendly decomposition products, concentrated hydrogen peroxide has regained popularity as a propellant in many rocket applications. The MEMS-based MIT micro-rocket engine is one such application where 98% liquid hydrogen peroxide and JP7 are proposed as a propellant combination. Like other micro-thruster...

Title of Document: FLOW AND ATOMIZATION CHARACTERISTICS OF CRYOGENIC FLUID FROM A COAXIAL ROCKET INJECTOR Vivek Gautam, Ph.D., 2007 Directed By: Professor, Ashwani K. Gupta, Department of Mechanical Engineering High thrust-to-weight ratio and consistent performance over a range of operating conditions make cryogenic rocket engines one of the best options for space propulsion. However, future sp...

A model of a linear aerospike rocket nozzle that consists of coupled aerodynamic and structural analyses has been developed. A nonlinear computational fluid dynamics code is used to calculate the aerodynamic thrust, and a three-dimensional finite-element model is used to determine the structural response and weight. The model will be used to demonstrate multidisciplinary design optimization (MD...

Future reusable launch vehicles will depend on new propulsion technologies to lower system operational costs while maintaining adequate performance. Recently, a number of vehicle systems utilizing rocket-based combinedcycle (RBCC) propulsion have been proposed as possible low-cost space launch solutions. Vehicles using RBCC propulsion have the potential to combine the best aspects of airbreathi...