This kind of SRM which with the structure of tangential multi-nozzle consists of a combustion chamber, propellant charge, 4 tangential nozzles, ignition device, etc. The study on spinning solid rocket motor ( SRM) which used as power plant of twice throwing structure of aerial submunition was introduced. Sĭesign and Experimental Study on Spinning Solid Rocket Motor Wong.34 Solid Rocket Nozzle Design Summary," in 4th AIAA Propulsion Joint Specialist Conference, Cleveland, OH, 1968.
Laboratory, Edwards, CA Abstract In a solid rocket motor ( SRM), when the aluminum based propellant combusts, the fuel is oxidized into alumina (Al2O3.34Chemical Erosion of Refractory-Metal Nozzle Inserts in Solid - Propellant Rocket Motors," J. Study of Liquid Breakup Process in Solid Rocket Motor Nozzle The steady state flowfield results indicate pocketing erosion is not directly initiated by a steady state gas dynamics phenomenon. From the two and three dimensional flowfield calculations presented it can be concluded that there is no evidence from these results that steady state gas dynamics is the primary mechanism resulting in the nozzle pocketing erosion experienced on SRM nozzles 8A or 17B. The flow in the nozzle/case joint region is characterized by low magnitude pressure waves which travel in the circumferential direction. This perfect gas, viscous analysis, provided a steady state solution for the core region and the flow through the nozzle, but indicated that unsteady flow exists in the region under the nozzle nose and near the flexible boot and nozzle/case joint. A three dimensional 3.5 deg gimbaled nozzle flowfield solution was developed for the aft segment and nozzle at t = 9 sec motor burn time. The t = 85 sec solution indicates that the aft segment forward inhibitor stub produces vortices with are shed and convected downwards. Two dimensional axisymmetric solutions were developed at t = 20 and t = 85 sec motor burn times. These perfect gas, viscous solutions for the high performance motor characterize the flow in the aft segment and nozzle of the booster. Two and three dimensional internal flowfield solutions for critical points in the Space Shuttle solid rocket booster burn time were developed using the Lockheed Huntsville GIM/PAID Navier-Stokes solvers. High performance Solid Rocket Motor ( SRM) submerged nozzle/combustion cavity flowfield assessmentįreeman, J.
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