Particulate sizing in a solid-propellant rocket motor using light scattering techniques
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Particulate sizing in a solid-propellant rocket motor using light scattering techniques

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Published .
Written in English

Subjects:

  • Aeronautics

Book details:

The Physical Object
Pagination65 p.
Number of Pages65
ID Numbers
Open LibraryOL25479539M

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Particulate Sizing in a Solid Propellant Rocket Motor Using Light Scattering Techniques by Kevin G. Horton Captain Canadian Armed Forces BENG, Royal Miiitary College of Canada, Submitted in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE IN ENGINEERING SCIENCE from the NAVAL POSTGRADUATE SCHOOL June Author Author: Kevin G. Horton.   An illustration of an open book. Books. An illustration of two cells of a film strip. Video An illustration of an audio speaker. Particle sizing in a solid propellant rocket motor using a light scattering technique. Particle sizing in a solid propellant rocket motor using a light scattering technique. by Keith, Michael G. Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection Particle sizing in a solid rocket motor using the measurement of scattered light. Particulate sizing in a solid-propellant rocket motor using light scattering techniques. was conducted to determine the feasibility of introducing particles of a known mean diameter into a small solid propellant rocket motor and measuring the change in mean diameter across the exhaust nozzle. particle sizing.

across the nozzle of a small solid propellant rocket motor. Particle size was determined using light scattering techniques. The present optical components limit the lower measurable particle size to approximately three microns. During the investigation, spurious light was detected in the motor optical path. It was determined that transient pressure. PARTICLE SIZING IN A SOLID-PROPELLANT ROCKET MOTOR USING SCATTERED LIGHT MEASUREMENTS 12 PERSONAL AUTHOR(S) Rosa, John S. 1a TYPE OF REPORT 13b TIME COVERED DATE OF REPORT (Year, Month, Day) IS PAGE COUNT Engineer Thesis FROM TO , December 89 16 SUPPLEMENTARY NOTATION 17 I CQSATI CODES SUBJECT TERMS . Solid propellant rocket boosters release metal oxide particulate in the atmosphere, as a result of the combustion of the aluminum powder contained in the energetic material. AE Rocket Propulsion Extinction/Termination • Motor will burn itself out when –no propellant left –amount of propellant (surface area) remaining is insufficient to keep pressure at sustainable level • Motor can extinguish if sudden depressurization (dp/dt) –flame suddenly lifts farther from surface; remaining thermal.

An investigation into the behavior of aluminized solid propellant combustion in a two-dimensional windowed rocket motor was conducted using holographic techniques. An experimental determination of the combustion-chamber aluminum oxide particle-size distribution for the Ariane 5 Solid Rocket Booster is carried out. A subscale motor using a helium injection technique for quenching the reaction products is designed, manufactured and tested. A 30 percent helium-mass flow rate injection close to the head-end of the combustion chamber is found to give an. An illustration of an open book. Books. An illustration of two cells of a film strip. Video An illustration of an audio speaker. Measurement of particle size distribution in a solid propellant rocket motor using light scattering. Item Preview remove-circle.   Particle Sizing by Laser Light Scattering. Review of Principles of Optical Techniques for Particle Size Measurements. 23 August Motor and plume particle size measurements in solid propellant micromotors. Measured particulate behavior in a subscale solid propellant rocket motor.