3 edition of Cold-flow study of low frequency pressure instability in hybrid rocket motors found in the catalog.
Cold-flow study of low frequency pressure instability in hybrid rocket motors
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va
Written in English
|Other titles||Cold flow study of low frequency pressure instability in hybrid rocket motors.|
|Statement||Rhonald M. Jenkins.|
|Series||[NASA contractor report] -- NASA-CR-204348., NASA contractor report -- NASA CR-204348.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
Providing additional study material, this book offers comprehensive coverage for students of aerospace engineering. Catalog no. K, July , pp. ISBN: , $ / £ CCF loading basically involves high frequency low amplitude fluctuations (micro-cycles) embedded in low frequency high amplitude cycles (macro-cycles). A multi-scale technique has been used, which is based on separating the scale of interest (space/time) into a .
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Title: Experimental Study of a Cold Flow Radial Turbine Author: Robert Richardson Marshall Created Date: ZAuthor: Richardson Robert Marshall. Most fans are powered by electric motors, but other sources of power may be used, including hydraulic motors and internal combustion engines Asus M52N Battery. Fans produce air flows with high volume and low pressure, as opposed to compressors which produce high pressures at a comparatively low volume.
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Get this from a library. Cold-flow study of low frequency pressure instability in hybrid rocket motors: final report, NASA-PO HD, NASA Marshall Space Flight Center.
[Rhonald M Jenkins; United States. National Aeronautics and Space Administration.]. The ballistic properties and propulsion efficiency of a hybrid lab rocket scale with N of thrust were evaluated in the pressure of MPa with. Instabilities and pressure oscillations in solid rocket motors* 1 Article in Aerospace Science and Technology 7(3) April with Reads How we measure 'reads'.
Another instability mechanism relying on the intrinsic hydrodynamic instability of the boundary layer which develops over the propellant burning surface also leads to significant pressure oscillations.
The first and second acoustic modes are excited during SRM operation, however the first is the stronger by: 5. A Preliminary Analysis of Low Frequency Pressure Oscillations in Hybrid Rocket Motors 31st AIAA/ASME/SAE/ASEE Joint Propulsion Conference, San Diego, CA, Paper No.
Cited by: A numerical study of pressure oscillation generated in Solid Rocket Motors (SRM) is presented.
Attention is focused on the effect of the cavity located in the vicinity of the nozzle on the flow–acoustic coupling and therefore on the consequent pressure by: 6.
Cold Flow Propulsion Test Complex Pulse Testing Description When the propellants in a liquid rocket engine burn, the rocket not only launches and moves in space, it causes forces that interact with the vehicle itself. When these interactions occur under specific conditions, the vehicle’s structures and components can become unstable.
One. Close Drawer Menu Close Drawer Menu Menu. Home; Journals. AIAA Journal; Journal of Aerospace Information Systems; Journal of Air Transportation; Journal of Aircraft; Journal of Guidance, Control, and Dynamics. Investigation of Low Frequency Combustion Instability in a Dump Combustor.
Qin Fei, He Guoqiang, Experimental Cold Flow Characterization of a Swirl Coaxial Injector Element. Chad Eberhart, Design and Analysis of Hybrid Rocket Launch.
heat exchange and pressure drop enhanced by violent sloshing (english) high-frequency pressure measurements for unstart detection in scramjet isolators. donbar, proof-of-concept testing of a sustained vortex-flow configuration for hybrid. Fluidic Nozzle Throats in Solid Rocket Motors Kan Xie, Xinmin Chen, Junwei Li, Yu Liu This book focuses on the performance and application of fluidic nozzle throats for solid rocket motors, discussing their flow details and characterization performance, as well as the influence of the particle phase on their performance.
Filed under: Gas-lubricated bearings Film thickness measurement for spiral groove and Rayleigh step lift pads self-acting face seals / (Washington, D.C.: National Aeronautics and Space Administation, Scientific and Technical Information Branch ; [Springfield, Va. Gangwar S., Bhanja D., Biswas A.
Cost, reliability and stability of a stand-alone hybrid renewable energy system - a case study on a lecture building with low load factor. Publisher: American Institute of Physics (AIP), Journal of Renewable and Sustainable Energy (SCIE) 7, (), Citations: 5.
In the present work the aerodynamic performances of an innovative rotor blade row have been experimentally investigated. Measurements have been carried out in a large scale low speed single stage cold flow facility at a Reynolds number typical of aeroengine cruise, under nominal and off-design conditions.
The time-mean blade aerodynamic loadings have been Cited by: 1. Instability is a natural phenomenon observed for a long time on all the engines, from the pressure recording: instead of being stable (with a little random component due to the noise), pressure exhibits an oscillation well organized around a frequency, or possibly around several frequencies to form a non-harmonic unsteady signal.
Cold-Flow Study of Hybrid Rocket Motor Flow Electrostatic Ion Cyclotron Instability Due to a Nonuniform Electric Field Perpendicular to the External Magnetic LOW PRESSURE NUCLEAR THERMAL ROCKET CONCEPT (LPNTR).pdf.
Response to the propellant burning rate to pressure (pressure coupling) has been proved (measured and explained). essentially the transient phases (ignition and operation end) and the instability. their validation by experiments is still very poor.
p RMP is a complex parameter. function of the oscillation frequency. p is the steady state. Quasi 1-D Numerical Analysis of Combustion Instability in Hybrid Rocket Motor Incorporating Boundary Layer Lags View Section, Experimental and Analytical Investigation of Effect of Pressure on Regression Rate of Axial-Injection End-Burning Hybrid Rockets.
Library of Congress Cataloging-in-Publication Data (Revised for vol. 8) NASA historical data book. (NASA SP- ) Vol. 1 is a republication of NASA historical data book, –/ Jane Van Nimmen and Leonard C.
Bruno. Vol. 8 in series: The NASA historical data book series. Includes bibliographical references and indexes. Full text of "NASA Technical Reports Server (NTRS) Solid rocket thrust vector control" See other formats. PDF; PDF; Print; Help NASA SBIR/STTR Program Support For questions about the NASA SBIR/STTR solicitations, the proposal preparation and electronic submission process, and other program related areas, please contact the NASA SBIR/STTR Program Support Office.
Phone: Email: [email protected] NASA SBIR/STTR Program Support is .History Hybrid rocket development can be traced back to the ‟s; around the same time as many basic developments in solid and liquid rockets were taking place. Solid rocket motors were the first to be studied due to the early development of gunpowder.
These solid motors used powder charges to achieve combustion.Hybrid motors are a type of chemical propulsion option that utilize propellants stored in two different phases, typically a solid fuel and a liquid or gaseous oxidizer.
For a small-satellite, a hybrid system would be better suited for rapid, large Delta-v maneuvers than electric thrusters.