Constellations and platoons of small satellites can offer an assortment of benefits over larger, single function spacecraft. The strict mass, volume, and power limitations of small satellites will require unique micro-technologies to help develop efficient propulsion systems for maneuvering. The Free Molecule Micro-Resistojet (FMMR) has been analyzed and tested in this study to determine its ap...

An internal ballistics model has been developed for performance prediction of a solid propellant rocket motor. In this model a 1-D unsteady Euler equation with source terms is considered. The flow is assumed as a non-reacting mixture of perfect gases with space and time varying thermo physical properties. The governing equations in the combustion chamber are solved numerically by using the Steg...

An unprecedented combination of high propellant fraction and small size is required for affordable-scale Mars return, regardless of the number of stages, or whether Mars orbit rendezvous or in-situ propellant options are used. Conventional space propulsion technology is too heavy, even without structure or other stage subsystems. The application of launch vehicle design principles to the develo...

This year’s efforts were devoted to extending the Rocstar version 3 rocket simulation package in several mission-critical areas: time zooming, surface propagation, and mesh modification. These capabilities were verified and applied to several large-scale simulations, including slumping in the Titan, complete propellant burn-out in a tactical motor, and substantial propellant burn-back in the RS...

A method for the simulation of flows involving a disperse particle phase and a rarefied gas is extended for increased accuracy and efficiency in modeling the high altitude plume flow from a solid propellant rocket. First, a procedure is presented so that calculations involving the interphase transfer of momentum and energy may be avoided in regions where these calculations will have negligible ...

A space transportation infrastructure is described that utilizes propellant depots to support all foreseeable missions in the Earth-Moon vicinity and deep space out to Mars. The infrastructure utilizes current expendable launch vehicles such as the Delta IV Heavy, Atlas V, and Falcon 9, for all crew, cargo, and propellant launches to orbit. Propellant launches are made to a Low-Earth-Orbit (LEO...

This work describes the modeling and control of a proposed actuation system that is capable of pressurizing a chamber volume via the catalytic decomposition of a liquid monopropellant controlled by a binary on/off propellant valve. Two design configurations of the actuation system are presented and common portions of both are energetically modeled. The parameters of the resulting dynamic model ...