combustion behaviour investigation of solid fuels using a micro-sized hybrid rocket motor Article (PDF Available) in International Journal of Energetic Materials and Chemical Propulsion 7(3) book specialized in solid propellant performance prediction capturing in supersonic-high temperature flows for the use in solid rocket motors plume. of Alumina Particulate in Solid Booster. New Method to Determine the Velocities of Particles on a Solid Propellant Surface in a Solid Rocket Motor Use of aluminized composite solid propellants and submerged nozzles are common in solid rocket motors (SRM). Due to the generation of slag, which injects into a combusted gas flow, a two-phase flow pattern is one of the main flow Cited by: -A continuing investigation is being conducted to develop techniques which can be used to obtain quantitative data that can be used to relate solid rocket propellant composition and operating environment to the behavior of solid par-ticulates within the grain port and exhaust nozzle. The techniques employedAuthor: R G Cramer, R J Edington, D E Faber, K J Graham, B J Hansen.
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. It comprehensively covers a range of fluidic nozzle throats in solid rocket motors and is richly illustrated. Abstract. Unstable motions must be anticipated as a possible\ud problem in solid-propellant rocket motors;\ud the characteristics of an instability depend primarily\ud on the geometry of the motor and composition\ud of the imeldaclyde.com: F. E. C. Culick. Development of an intrusive technique for particles collection in rockets plume. An intrusive technique for particles capturing in supersonic-high temperature flows to be used in solid rocket motors plume characterization is proposed. due to the condensation of chlorine and moisture on solid particulate suspended in the atmosphere Cited by: 1. This chapter discusses the solid propellant combustion and internal ballistics of motors. The combustion of a solid propellant is characterized by the way its surface regresses once it begins to burn. The burning rate is the distance traveled by the flame front per unit of time, measured normally to the burning imeldaclyde.com by:
Metron employees represent the best and brightest in their fields of expertise. This includes recognized innovators such as Kristine L. Bell, Thomas L. Corwin, Roy L. Streit and world renowned scientists, such as Lawrence D. Stone. The objective of this study, as related to the overall High Energy Solid Propellant Combustion Efficiency Program, is the development of an understanding of the combustion and performance of solid double-base propellants containing metal and metal-hydride fuels by a chemical and physical analysis of their particulate exhaust products. Read chapter 4 Review of Candidate Alternative Technologies: The U.S. military has a stockpile of approximately , tons of excess, obsolete, or unser. A CFD Investigation of Multiple Burner Ignition and Flame Propagation with Detailed Chemistry and Automatic Meshing. Motor Scale and Propellant Geometry Effects on Pressure Oscillations in Aft-Finocyl Solid Rocket Motors. View Section, Effect of Semi-Molten Particulate on Tailored Thermal Barrier Coatings for Gas Turbine Engine. View.