Inscrição na biblioteca: Guest
Portal Digital Begell Biblioteca digital da Begell eBooks Diários Referências e Anais Coleções de pesquisa
International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.28 SNIP: 0.421 CiteScore™: 0.9

ISSN Imprimir: 2150-766X
ISSN On-line: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2015011502
pages 29-56

EFFECT OF FLIGHT AND MOTOR OPERATING CONDITIONS ON INFRARED SIGNATURE PREDICTIONS OF ROCKET EXHAUST PLUMES

Robert Stowe
Defence Research and Development Canada, Quebec City, Quebec, Canada, G3J1X5
Sophie Ringuette
Defence R&D Canada-Valcartier, Quebec City, Quebec G3J1X5, Canada
Pierre Fournier
Defence Research and Development Canada, Quebec City, Quebec, Canada, G3J1X5
Tracy Smithson
Defence Research and Development Canada, Quebec City, Quebec, Canada, G3J1X5
Rogerio Pimentel
Defence Research and Development Canada, Quebec City, Quebec, Canada, G3J1X5
D. Alexander
Martec, Limited, 1888 Brunswick St., Suite 400, Halifax, NS, B3J 3J8, Canada
Richard Link
Martec Limited, Halifax, Nova Scotia, Canada, G3J1X5

RESUMO

A computationally efficient methodology based on computational fluid dynamics (CFD) has been developed to predict the flow field and infrared signatures of rocket motor plumes. Because of the extreme environment in the plume and the difficulties in taking measurements of motors inflight, it has been partially validated with temporally- and spatially resolved imaging spectrometer data from the static firings of small flight-weight motors using a non-aluminized composite propellant. Axisymmetric simulations were carried out for a variety of motor burn time, flight velocity, altitude, and modeling parameters to establish their effects on the results. By extrapolating the axisymmetric CFD output into three dimensions, images of the rocket plume as seen by an infrared sensor outside the computational domain were also created. The CFD methodology correctly predicted the afterburning zone downstream of the nozzle, and good agreement for its location was obtained with the imaging spectrometer data. It also showed that flight velocity and altitude have substantial effects on the size, shape, and infrared emissions of the plume. Smaller effects on plume properties were predicted for different motor burn times, but indicated that more experimental data of greater temporal and spatial resolution of single static firings are required to better validate the CFD plume prediction methodology.


Articles with similar content:

DIFFUSION FLAME STRUCTURE OF HNF SANDWICHES
International Journal of Energetic Materials and Chemical Propulsion, Vol.5, 2002, issue 1-6
Jeroen Louwers, G. G. M. Stoffels, Dirk J.E.M. Roekaerts, G. M. H. J. L. Gadiot
A NOVEL RADIATIVE HEAT FLUX MEASUREMENT TECHNIQUE FOR COMBUSTION PRODUCTS FLOWING IN SOLID ROCKET MOTORS
International Journal of Energetic Materials and Chemical Propulsion, Vol.12, 2013, issue 3
Ryan W. Houim, Matthew J. Degges, Peter J. Ferrara, J. E. Boyer, Kenneth K. Kuo, Heath T. Martin, Andrew C. Cortopassi
EROSIVE BURNING IN SOLID PROPELLANT ROCKET MOTORS
Energy and the Environment, 1998, Vol.0, 1998, issue
Mehmet Ali Ak, Huseyin Vural, T. Gudu
APPROPRIATENESS OF BURNING RATE MEASURING TECHNIQUE WITH THE MEASURING CONDITIONS AND REQUESTED DATA
International Journal of Energetic Materials and Chemical Propulsion, Vol.17, 2018, issue 4
Ondrej Vodochodsky, Ahmed Maraden, Robert Matyas, Petr Stojan
LARGE EDDY SIMULATION OF A LEAN PREMIXED LOW SWIRL BURNER
TSFP DIGITAL LIBRARY ONLINE, Vol.6, 2009, issue
Lars-Erik Eriksson, Mohammad Irannezhad