نتایج جستجو برای: aerospike nozzle

تعداد نتایج: 6415  

1997
J. J. Korte A. O. Salas H. J. Dunn N. M. Alexandrov

A model of a linear aerospike rocket nozzle that consists of coupled aerodynamic and structural analyses has been developed. A nonlinear computational fluid dynamics code is used to calculate the aerodynamic thrust, and a three-dimensional finite-element model is used to determine the structural response and weight. The model will be used to demonstrate multidisciplinary design optimization (MD...

2007
A Zilic Alina A. Alexeenko A. Zilić D. L. Hitt A. A. Alexeenko

In this study, we numerically examine thrust performance of the linear aerospike nozzle micro-thruster for various nozzle spike lengths and flow parameters in order to identify optimal geometry(s) and operating conditions. Decomposed hydrogen-peroxide is used as the monopropellant in the studies. Performance is characterized for different flow rates (Reynolds numbers) and aerospike lengths, and...

2011
Shannon D. Eilers Matthew D. Wilson Stephen A. Whitmore Zachary W. Peterson

Results from numerical and coldow experimental investigations of aerodynamic thrust vectoring on a small-scale aerospike thruster are presented. Thrust vectoring was created by the injection of a secondary uid into the primary ow eld normal to the nozzle axis. The experimental aerospike nozzle was truncated at 57% of its full theoretical length. Data derived from coldow thrust vectoring tests w...

To improve the calculation of the flow properties of an aerospike nozzle, different turbulence models were investigated in this study. The primary shape of the nozzle plug is determined through utilizing an approximate method. The flow field is, then, simulated using the Navier-Stokes equations for compressible flows. The commercial computational fluid dynamics code Fluent is used to simulate t...

2010
Shannon D. Eilers Matthew D. Wilson Stephen A. Whitmore

A system for cold ow testing of an aerospike nozzle has been developed in an e ort to examine the e ectiveness of aerodynamic thrust vectoring and truncated nozzle base bleed. These tests are designed to produce results that will support the design of a system for hot ow testing of the same technologies. Design of a nozzle suitable for testing with reasonable cold-gas mass ow rates and measurea...

2009
Patrick Lemieux

The Department of Mechanical Engineering at the California Polytechnic State University, San Luis Obispo, has developed an innovative program of experimental research and development on hybrid rocket motors (where the fuel and the oxidizer are in different phases prior to combustion). One project currently underway involves the development of aerospike nozzles for such motors. These nozzles, ho...

2010
Patrick Lemieux

The Department of Mechanical Engineering at the California Polytechnic State University, San Luis Obispo, has developed an innovative program of experimental research and development on hybrid rocket motors (where the fuel and the oxidizer are in different phases prior to combustion). One project currently underway involves the development of aerospike nozzles for such motors. These nozzles, ho...

The influence of the plug shape on the performance of an aerospike nozzle thrust force is studied in different back pressure conditions. To generate smooth plug contours, Cubic B-Spline technique is employed. In the current research, basis functions are obtained using Deboor’s relation. The flow field around the aerospike nozzle is investigated implementing various shapes and the best of the ge...

Journal: :International Journal of Research in Engineering and Technology 2014

Journal: :IOP Conference Series: Materials Science and Engineering 2017

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