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 new facility has been built at the University of Michigan to study shear coaxial combusting gas-gas injection in a rocket combustion chamber. This facility, capable of chamber pressures of 10 atmospheres, is used to obtain a better understanding of the complex fluid dynamics and combustion processes found in rocket combustion chambers and to provide data to assess NASA’s computational fluid d...

Three examples of response surface modeling with CFD are presented for combined cycle propulsion components. The examples include a mixed-compression-inlet during hypersonic flight, a hydrogen-fueled scramjet combustor during hypersonic flight, and a ducted-rocket nozzle during all-rocket flight. Three different experimental strategies were examined, including full factorial, fractionated centr...

To calculate the trajectory of a rocket by use of a digital computer, the equations of the motion of the rocket should be solved step-by-step with respect to short intervals of time. Hence, the problem is essentially to solve the differential equations and thus there is no particular difficulty in the procedure. In a previous paper, the fundamental programming for the Runge-Kutta integration me...

This paper investigates the use of structured H∞ control for aerodynamic descent phase a reusable rocket. A unified strategy attitude and position is proposed verified. The architecture controller, together with observed performance are discussed. Results presented CALLISTO, rocket demonstrator jointly developed by DLR, JAXA CNES.

Purpose – To provide a broad understanding of knowledge management and how to successfully implement knowledge management. Design/methodology/approach – Using a wide range of technical, business and knowledge management-specific sources to explain the value and importance of knowledge management and the relative simplicity of the concept, the paper is divided into sections providing a definitio...

Thermo-acoustic combustion instability is a problem that has been researched for decades as it is a precursor to sudden catastrophic failure. Meanwhile, the demand for rocket engines that are able to maintain stable combustion over a wider range of thrust levels is increasing. One injector design utilized in Russia and Asia that has demonstrated stable throttling ability is the liquid-liquid co...

BACKGROUND In the ROCKET AF (Rivaroxaban-Once-daily, oral, direct Factor Xa inhibition Compared with vitamin K antagonism for prevention of stroke and Embolism Trial in Atrial Fibrillation) trial, marked regional differences in control of warfarin anticoagulation, measured as the average individual patient time in the therapeutic range (iTTR) of the international normalized ratio (INR), were as...

HE analysis and design of rocket propulsion systems largely relies on full-scale prototype development and testing. Computational simulation techniques have the potential to assist in the design process if accurate physical models are available. The objective of this study is to address this issues by assessing the predictive capability of three different modeling approaches to simulate the rea...