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Monday, July 20, 2020 | History

1 edition of A combined optical and collection probe for solid propellant exhaust particle analysis found in the catalog.

A combined optical and collection probe for solid propellant exhaust particle analysis

Timothy J. Eno

A combined optical and collection probe for solid propellant exhaust particle analysis

by Timothy J. Eno

  • 159 Want to read
  • 23 Currently reading

Published by Naval Postgraduate School, Available from the National Technical Information Service in Monterey, Calif, Springfield, Va .
Written in English


Edition Notes

ContributionsNetzer, David Willis, 1939-
The Physical Object
Pagination59 p.
Number of Pages59
ID Numbers
Open LibraryOL25485183M

Solid propellants are an integral part of the structure of solid rockets although their chemical composition and overall configuration are dictated by ballistic requirements. If the propellant is viewed as a material of construction, it must be characterized with respect to mechanical . stress analysis of the sample is used to show that the crack velocity varies - systematically with crack length and load. is-filled withAhe solid propellant charge, which has, a central hole -- ýto have'a multimodal particle distribution in the size range 10 to 7,50 fxm. The smaller crystals tend to be roughly sphericalt whereas the.

Optical Multiwavelength Technique Applied to the Online Measurement of Particle Emissions from system is described that delivers information about particle size and concentration directly from the undiluted exhaust gas. which allows the analysis within a broad concentration range. On-line measurements of the particulate emissions in the Cited by: 6. CiteSeerX - Document Details (Isaac Councill, Lee Giles, Pradeep Teregowda): Abstract- Design and analysis of propellant grain configurations for determination of the grain geometry which is an important and critical step in the design of solid propellant rocket motors, because accurate calculation of grain geometrical properties plays a vital role in performance prediction.

Research Article Multiphase CFD Simulation of Solid Propellant Combustion in a Small Gun Chamber /is particle volume, Reis the solid density, and is propellant linear burning rate which is modeled by Vieille s law (also known a solid propellant mass varies between. g and.g. Oct 03,  · Seminar Slide Deck (PDFMB) Abstract. Recently, Horne, Burnside, Panda, and Brodell, in a paper titled Measurements of Unsteady Pressure Fluctuations in the Near-Field of a Solid Rocket Motor Plume, measured a comprehensive set of acoustic spectra in the near field of a solid propellant astonmartingo.com their experiment, two very different tests were performed; one at high burn and the .


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A combined optical and collection probe for solid propellant exhaust particle analysis by Timothy J. Eno Download PDF EPUB FB2

Exhaust dispersion analysis from large solid propellant rocket motor firing using hysplit model over satish dhawan space centre (sdsc shar).

High performance solid propellant compositions producing halogen-free exhaust products comprised of Ammonium Nitrate and powdered magnesium and optionally containing polyoxypropylene glycol Cited by: Imaging particle analysis is a technique for making particle measurements using digital imaging, one of the techniques defined by the broader term particle size astonmartingo.com measurements that can be made include particle size, particle shape (morphology or shape analysis and grayscale or color, as well as distributions (graphs) of statistical population measurements.

In this work, the plasma plume created by electric solid propellant pulsed microthrusters is investigated using a nude Faraday probe, a triple Langmuir probe, and residual gas analysis.

Solid propellants often contain aluminum particulates in order to increase specific impulse and improve combustion stability.

When one surface of a propellant strand is ignited, a combustion front forms and the nanometer to micrometer-sized metal particulates begin to melt due to the heat released from the reaction of the oxidizer and fuel astonmartingo.com by: EFFECT OF OXIDIZER PARTICLE SIZE ON SOLID- PROPELLANT COMBUSTION STABILITY for Federal Scientific and Technical Information Springfield, Virginia - Price $ EFFECT OF OXIDIZER PARTICLE SIZF: ON SOLID- PROPELLANT COMBUSTION STABILITY The propellant ingredients were combined in a sigma-bladed mixer, trans.

Feb 08,  · Propellant, High Performance Low Cost Solid Propellant Compositions Producing Halogen Free Exhaust US Patent Skip to main content This banner text can have markup. Solid Propellant Chemistry Combustion and Motor Interior Ballistics Preview this book» What people are saying - Write a review.

User Review - Flag as inappropriate. This book is full of information. I cant buy as it has very high price.I want to get it free online. Analysis of the GasPermeation Layer. Basic Solution and 5/5(1). Sep 14,  · Solid Propellant Chemistry Combustion and Motor Interior Ballistics (Progress in Astronautics & Aeronautics) [Professor Vigor Yang, Thomas B Brill, Wu-Zhen Ren, Paul Zarchan] on astonmartingo.com *FREE* shipping on qualifying offers.

Yang (mechanical engineering, Pennsylvania State U.), Brill (chemistry and chemical engineering, U. of Delaware) and Ren (propellants and explosives4/5(1). An optical system is described for measuring the burning rate of solid propellant strands. It consists of a bomb equipped with quartz windows, an objective, a photo diode array and a data acquisition and processing unit.

A Simultaneous observation of the burning in possible by. texts All Books All Texts latest This Just In Smithsonian Libraries FEDLINK (US) Genealogy Lincoln Collection. Books to Borrow. Top American Libraries Canadian Libraries Universal Library Community Texts Project Gutenberg Biodiversity Heritage Library Children's Library.

Open Library. Grain configurations for solid propellant rockets are classified by relative web thickness and mean vector direction of burning surface into a topological continuum.

This ranges from the thin web Author: John S. Billheimer, F. Wagner. Composite solid propellant is prepared using tri-modal Ammonium perchlorate (AP) containing coarse, fine and ultrafine fractions of AP with average particle size (APS)40 and 5 μm respectively, in various compositions and their rheological, mechanical and burn rate characteristics are astonmartingo.com by: 1.

This paper presents the procedure of uniaxial mechanical characterization of composite solid rocket propellant based on hydroxy-terminated polybutadiene (HTPB), whose mech-anical properties strongly depend on temperature, strain rate, natural aging and accum-ulated damage.

A method of processing data is presented in order to determine time-tem. Spectral Studies of Solid Propellant Combustion IV: Absorption and Burn Rate Results for M43, XM39, and M10 Propellants [M. Teague] on astonmartingo.com *FREE* shipping on qualifying astonmartingo.com: M.

Teague. Solid Propulsion Technology and Development Proven Technology for a New Era of Applications. Analysis, Test Marshall, the hub of solids, is the recognized NASA center for solid propul - This extinguishable solid propellant technology could be used on small in-space propulsion projects, allowing.

May 20,  · Abstract. The measurement of solid propellant burning rates using ultrasound requires the simultaneous acquisition and analysis of ultrasonic signals and pressure data simultaneously in a wide range of pressure values during the process of propellant astonmartingo.com by: 6.

32 Lalith V. Kakumanu et al.: Combustion Study of Composite Solid Propellants Containing Metal Phthalocyanines composite solid propellants. Combustion study of solid propellants containing various contents of MPcs have been investigated and an effort has been made to obtain detailed.

A solid composite propellant consisting of 7% to 15% of a carboxyl-terminated butadiene polymer binder, 66% to 82% of ammonium perchlorate, greater than 0% to 18% of aluminum and greater than 0% to 8% of n-butyl ferrocene as a burning rate catalyst, the ingredient amounts being in weight per cent, and wherein the particle size of the ammonium perchlorate is greater than 0 but less than 3 Cited by: An analysis of launch vehicle Gross Lifloff Weight (GLOW) using high energy density atomic propellants with solid particle feed systems was conducted.

The analyses covered several propellant combinations, including atoms of aluminum (Ai), boron (B), carbon (C), and hydrogen (H) stored in a solid cryogenic particle, with a cryogenic.

NASA has given the solid propellant performance prediction and analysis. Based upon this the performance of the solid propellant rocket motor the design is done by considering the loads that are going to act on the solid rocket motor casing.

The effectiveness of this process is predicted and assessedAuthor: P. Mahesh Babu, G. Bala Krishna, B Siva Prasad.The Analysis of Unfired Propellant Particles by Gas Chromatography-Mass Spectrometry: A Forensic Approach Shiona Croft iii 67$7(0()2 5,*,1$/$ 87++,3 The work contained in this thesis has not been previously submitted to meet requirements for an award at this or any other higher education institution.

To the.Multiscale modeling of solid propellants: From particle packing to failure analysis by Matousˇ and Geubelle [21].

The mechanical ing of an idealized propellant are presented, showing the ability of the proposed multiscale scheme to relate the dam.