Aeronautical Engineering

Gas Dynamics by Klaus Oswatitsch

By Klaus Oswatitsch

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But there are limits to the gains to be made in this way, due to the fundamental properties of the ingredients. It is possible that another second or two of Is can be achieved by better processing techniques or the use of additives to improve processing success or mechanical properties. But significant growth in solid rocket performance will depend on the availability and proper formulation of new ingredients. Materials such as nano-Aluminum, AlH3 , CL-20, ADN, energetic binders, and alternative binder systems based on poly-DCPD have been shown to give higher performance in some formulations, but they have not been incorporated in many standard systems, due to cost issues, uncertainty about suitability under some conditions, and incomplete development of the specific formulation techniques required.

2 A Tentative Plan of EMGI Development The medium- and long-term goals of EMGI are to achieve the “demand design” and complete digitized fabrication of advanced EM through theoretical computation and digital simulation. The present goal of EMGI is to establish EM innovation, including high-flux computation platform, high-flux fabrication and examination platform, as well as materials database. These basic establishments are linked up with existing integrated computational materials project, and multi-subject intercrossing and syncretizing are realized, so that the process from discovery to application of EM can be speeded up.

Discusses why and how hybrid propulsion can make a dedicated, economic, lightweight satellite launcher possible. In this context, up-to-date technologies being developed in Japan on new fuels like low-melting temperature (LT) fuels and on swirlingoxidizer-flow-type (SOFT) hybrid rockets are described. T. DeLuca et al. CFD computations and visualization diagnostics of the internal ballistics and flow characteristics in hybrid rockets. A second paper by Park et al. discusses the role of internal flow dynamics in determining regression rate and low-frequency combustion instability (LFI) in hybrid rocket combustion.

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