1 edition of Particle sizing in solid rocket motors found in the catalog.
Particle sizing in solid rocket motors
Douglas Lyle Hovland
Published
1989
by Naval Postgraduate School in Monterey, California
.
Written in
Particle size distribution measurements were made with a Malvern 2600c forward laser light diffraction system across the exhaust nozzle entrance and exhaust plume of a small two-dimensional rocket motor. The solid propellants tested were GAP propellants containing 2.0% and 4.69% aluminum. Surface agglomeration of the aluminum, indicated by the in-motor results, was found to decrease as the motor chamber pressures were increased. At low pressures, increasing the aluminum loading with fixed total solids decreased the mean particle size at the nozzle entrance. Exhaust plume particle size was practically independent of nozzle inlet particle diameters, supporting the critical Weber number particle breakup theory. Initial validation of the Malvern 2600c measurements was accomplished by favorable comparison to exhaust plume particle distribution results obtained using a particle collection probe. Particle sizing; Solid propellant rocket engines; Light scattering; Theses.
Edition Notes
| Statement | Douglas Lyle Hovland |
| Contributions | Naval Postgraduate School (U.S.) |
| The Physical Object | |
|---|---|
| Pagination | vi, 103 p. : |
| Number of Pages | 103 |
| ID Numbers | |
| Open Library | OL25479530M |
A popular application of propellant containing of aluminum powder is as fuel for solid rocket motors (SRMs). The combustion gas contains large amounts of alumina particles, which will worsen the SRM thermal protection system by inducing severe mechanical erosion on the surface of the insulation material exposed directly to the high-temperature and high-velocity gas and solid two-phase ://(ASCE)AS Cyclic loads tests of carbon involute solid rocket motor outer boot ri Rafiq Ahmed Not in Library. Flight motor set L (STSR), final report Plume particle collection and sizing from static firing of solid rocke Jay K. Sambamurthi , 1 book Stanley K. Borowski, 1 book Wayne E. Lundblad, 1 book Lyndon B. Johnson Space
Superlatives are truly in order. While my personal interests lie more along the lines of pyrotechnic rocketry, this book, focused on amateur rocketry, nevertheless was a pleasure to read. The book is exhaustive in its scope and well organized. The reader may explore amateur rocket motor construction in as little or as great depth as › Books › Engineering & Transportation › Engineering. Those who downloaded this book also downloaded the following books: ?Element_ID=
The burning time t b of a particle is a major sizing parameter for practical applications. For instance, in solid rocket motors, this burning time is of high importance since it controls the occurrence of incomplete combustion (if burning time is longer than residence time in the chamber) or the onset of thermoacoustic instabilities [5]. 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
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Audio. An illustration of a " floppy disk. Software. An illustration of two photographs. Particle sizing in solid rocket motors Item Preview remove-circle Particle sizing in solid rocket motors by Douglas Lyle Hovland,Naval Postgraduate School edition, in English Particle sizing in solid rocket motors.
By Douglas Lyle Hovland. Download PDF (6 MB) Abstract. Approved for public release; distribution is unlimitedParticle size distribution measurements were made with a Malvern c forward laser light diffraction system across the exhaust nozzle entrance and exhaust plume of a small two-dimensional rocket Based on a comparison of theoretical calculations and numerous experimental data, the formula is recommended for prediction of the size of aluminum-oxide particles in exhaust plumes of various types of solid rocket motors.
Key words: rocket motor, two-phase flow, aluminum oxide, fragmentation of :// 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 :// The particle mass averaged diameters, d43, measured from the samples for the different motors, ranged from 8 to 11 mu m and were independent of the dart collection surface and the motor burn time.
The measured results agreed well with those calculated using the industry standard Hermsen's correlation within the standard deviation of the Effect of Particle Size Distribution on the Sensitivity of Combustion Instability for Solid Rocket Motors Journal of the Korean Society of Propulsion Engineers, Vol.
19, No. 5 Characterization and Combustion of Aluminum Nanopowders in Energetic Systems 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 and covers a comprehensive range of fluidic nozzle › Engineering › Mechanical Engineering.
This book, a translation of the French title Technologie des Propergols Solides, offers otherwise unavailable information on the subject of solid propellants and their use in rocket propulsion. The fundamentals of rocket propulsion are developed in chapter one and detailed descriptions of concepts are covered in the following :// SOLID ROCKET COMPONENTS AND MOTOR DESIGN This is the last of four chapters on solid propellant rockets.
We describe the key inert components of solid propellant rocket motors, namely the motor case, nozzle, and igniter case, and then discuss the design of motors. Although the thrust vector control mechanism is also a component of many rocket eringcom/Data/Engineering/aeronautical_engineering/Rocket_Propulsion.
Plume Particle Collection and Sizing from Static Firing of Solid Rocket Motors Jay K. Sambamurthi* NASA / Marshall Space Flight Center Huntsville, Alabama Thermal radiation from the plume of any solid rocket motor, containing aluminum as one of the propellant ingredients, is mainly from the microscopic, hot Plume particle collection and sizing from static firing of solid rocket motors.
By Jay K. Sambamurthi. (% scaled version of the RSRM) motors and the horizontally fired RSRM motor has been demonstrated. The particle mass averaged diameters, d43, measured from the samples for the different motors, ranged from 8 to 11 mu m and were PDF | OnI.
Parsons and others published Coupled Simulations of Solid Rocket Motors | Find, read and cite all the research you need on ResearchGate /_Coupled_Simulations_of_Solid_Rocket_Motors.
Get this from a library. Plume particle collection and sizing from static firing of solid rocket motors. [Jay K Sambamurthi; United States. National Aeronautics and Space Administration.] Agglomerate Sizing in Aluminized Propellants Using Digital Inline Holography and Traditional Diagnostics.
Study of aluminum particle combustion in solid propellant plumes using digital in-line holography and imaging pyrometry. Combustion of Aluminum Particles in Solid Rocket :// Sincehe has worked at FMC Corporation, concentrating on solid rocket exhaust gas management, ablative, and intumescent materials with applications to missile launching systems.
His specialty is in solid‐propellant combustion modeling, particle sizing in rocket exhaust plumes, and thermal analyses of solid rocket nozzles and :// In a solid rocket motor (SRM) using aluminized composite solid propellant and a submerged nozzle, a two-phase flow needs to be investigated by both experiment and computation.
The boundary conditions for the ejecting particles constrain their trajectories, hence these affect the two-phase flow calculations, and thus significantly affect the In the present investigation, various factors and trends, related to the usage of two or more sets of inert particles comprised of the same material (nominally aluminum) but at different diameters for the suppression of axial shock wave development, are numerically predicted for a composite-propellant cylindrical-grain solid rocket motor.
The limit pressure wave magnitudes at a later reference Particulate matter are sized in the exhaust nozzle and plume of small rocket motors of varying geometry to assess the effects of the expansion process on particle size. Both converging and converging-diverging nozzles are considered, and particle sizing is accomplished at pressures of up to MPa with aluminum loadings of and :// Snecma Moteurs, Rocket Motors Division, through its subsidiaries Europropulsion and G2P, is the prime contractor for developing the solid propellant rocket motors of Ariane 5 launchers and of the French deterrence force.
Snecma Moteurs also develops thermal protection systems for reentry vehicles and bodies, and spatial :// and CFD Session/.
particle field could then be used to obtain the particle concentration [Ref. 4]. The apparatus used in these investigations, while accurate for small rocket motors in a controlled laboratory environment, would probably be greatly effected by vibrations caused by larger motors Nanomaterials in Rocket Propulsion Systems covers the fundamentals of nanomaterials and examines a wide range of innovative applications, presenting the current state-of-the-art in the g with a chapter on nano-sized energetic materials, the book examines metal nanoparticles-based fuels, ballistic modifiers, stabilizers and catalysts as the components of rocket :// use as a fuel is widespread from large scale solid rocket boosters to hobbyist rocket motors.
Aluminum powder raises the specific impulse (I sp) through the product molecular weights and increased flame temperature [1]. It also suppresses high-frequency combustion instabilities through viscous particle ?article=&context=open_access_theses.
