The Army is developing hypergolic, liquid and gelled bipropellants for a small, selectable-thrust, liquid rocket engine (LRE) that can power tactical missiles for both current and future combat systems. The use of gel propellants brings the advantages of selectable thrust and the promise of small engine size but also introduces new challenges in combustion control. One of these challenges is th...

This paper deals with the preventive maintenance (PM) scheduling problem of reusable rocket engine (RRE), which is different from the ordinary repairable systems, by genetic algorithm. Three types of PM activities for RRE are considered and modeled by introducing the concept of effective age. The impacts of PM on all subsystems’ aging processes are evaluated based on improvement factor model. T...

RPA (Rocket Propulsion Analysis) is a design tool for the performance prediction of the liquidpropellant rocket engines. RPA is written in Java and can be used under any operating system that has installed Java Runtime Environment (e.g. Mac OS ® X, Sun SolarisTM, MS WindowsTM, any Linux etc). The tool can be used either as a standalone GUI application or as an object-oriented library. This docu...

The possibility of a significant flight range extension guided aerial bomb during climb bombing due to the jet thrust created by solid-propellant rocket engine was considered. By means simulation, comparative analysis equipped (not equipped) with under typical conditions carrier aircraft level and performed. It demonstrated that use engine, whose mass is 20 % bomb’s mass, allows increase horizo...

HPFT HPFTP This paper presents the; theoretical foundation and HPOP application of two univariate failure detection HPOT algorithms to Space Shuttl,; Main Engine (SSME) test LPFP firing data. Both algorithms were applied to data LPOP collected during steady-sutte operation of the engine, m One algorithm, the time s_'.ries algorithm, is based on MCC time series techniques and involves the comput...

The lecture presents an overview of some recent results of the work carried out at Alta on the hydrodynamic design and rotordynamic fluid forces of cavitating turbopumps for liquid propellant feed systems of modern rocket engines. The reduced order models recently developed for preliminary geometric definition and noncavitating performance prediction of tapered-hub axial inducers and centrifuga...

Accurate simulation of radiative heat-transfer effects from the rocket engine exhaust plays an important role for the proper characterization of missile base heat loads. To promote improved radiative transfer solutions, careful attention to the physical flow-field models is paramount. Use of a generalized fluid dynamic model can assist in the close approximation of the actual base heating by so...

The numerical simulation of cryogenic combustion is crucial for a better understanding of the complex physics involved in reactive flows of rocket engines and to help to reduce the development cost of these engines. The focus of this study is set on the oxidizer injection and its dispersion through jet dense core destabilization and atomization or supercritical mixing. Specific models have been...