Hagemann, G., Frey, M.: Shock pattern in the plume of rocket nozzles: needs for design consideration. Shock Waves 17(6), 387-395 (2008)Hagemann, G., Frey, M., 2008, "Shock Pattern in the Plume of Rocket Nozzle: Needs for Design Con- sideration", Shock Waves, Vol. 17, pp.387...
Solid propellant rocket nozzle design and validation using Finite Difference Method and CFD techniqueThe objective of the present work is to compare a set of results of flow behavior inside the nozzle and in the following atmospheric discharge zone, obtained using different computational techniques. ...
Keywords Nozzle design · Method of characteristics · Shape optimization · Compressible flow · Surrogate-based optimization 1 Introduction The universe and the vastness of space have always been one of the greatest mysteries known to mankind. As time passed and technology evolved, ...
rendering, and collaborative CAD modeling functions in Fusion 360. He has worked closely with his fellow student team members, including Rodrigo Yurazcek (nozzle design and CFD simulations), Manuela Becerra (engine propellant chemicals), and Isabella Crespo and Osheit Chang (coding and flight simula...
The side-load character strongly depends on the nozzle design, and is a key feature for the nozzle's mechanical structure layout. It is shown especially for the VULCAIN and VULCAIN 2 nozzle, how specific shock patterns evolve during transients, and how - by the nozzle design - undesired flow...
The structure consists of a sandwich of three micromachined silicon substrates: nozzles, igniters and propellant chambers. The thrust force issued from the combustion of the solid propellant ranges from 1 mN to a few mN. Just by geometrical and dimensional considerations, it is possible to adapt...
lateral loads may be induced. The sideload character strongly depends on the nozzle design, and is a key dimensional load for the nozzle’s mechanical structure. It is shown especially for the VULCAIN and VULCAIN 2 nozzle, how specific shock pattern evolve during transients, and how - by the...
Thermal Fluid System Design: Rocket Engine Layout – Cycle Calculation Nozzle Design & Cooling Turbopump Secondary Flow Systems Propellant Pipelines Generative Turbomachinery Design & Analysis: Oxidizer & Fuel Pump Design & Analysis Subsonic and Supersonic Turbine Design & Analysis ...
Specifically, the application of reduced-order flowfield solvers to a rocket's thrust controller design is explored. A quasi-one-dimensional supersonic convergent-divergent nozzle with varying backpressure is used as a model problem. Treating the nozzle flow as one-dimensional, the reduced-order ...
Nozzles tend to be either two- or three-dimensional. Heat transfer characteristics, particularly in the throat, where the peak heat flux occurs, are not well understood. Heat transfer predictions for these small thrusters have been made with one-dimensional analysis such as the Bartz equation or...