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Thursday, July 23, 2020 | History

1 edition of Image analysis of solid propellant combustion holograms using an imageaction software package found in the catalog.

Image analysis of solid propellant combustion holograms using an imageaction software package

David N. Redman

Image analysis of solid propellant combustion holograms using an imageaction software package

by David N. Redman

  • 82 Want to read
  • 26 Currently reading

Published .
Written in English

    Subjects:
  • Electrical and computer engineering

  • The Physical Object
    Pagination93 p.
    Number of Pages93
    ID Numbers
    Open LibraryOL25461119M

    The QuIP interpreter, a software environment for QUick image processing, uses an interactive scripting language designed to facilitate use by non-expert users, through features such as context-sensitive automatic response completion and integrated documentation. The package includes a number of. Rocket Propulsion Analysis (RPA) is a multi-platform analysis tool intended for use in conceptual and preliminary design (design phases 0/A/B1). For many years rocket propulsion professionals, scientists and students were using command-line MS-DOS or UNIX programs to .

    Removed popup when sim is run with no propellant grains re-wrote logic driving the set max kn feature (so it actually works) bugfix - when using arrows to move up and down in grain grid the grain fields and image were not updating port/throat area ratio label updated to be readable when color changes to alert to possibly unsafe values. Swim is a software information service for the grid built on top of the NASA-developed Pour framework. Software information is periodically gathered from native package managers on FreeBSD, Solaris, and IRIX as well as the RPM, Perl, and Python package managers on multiple platforms.

    Volumetric Loading Fraction, Vf. The ratio of propellant volume Vb to the chamber volume Vc (excluding nozzle) available for propellant, insulation, and restrictors. Using Eq. and Vb = mjp: where I, is the total impulse, Is the specific impulse, and pb the propellant density. A grain has to satisfy several interrelated requirements: 1. Space Propulsion Analysis and Design 1st Edition by Ronald Humble (Author) out of 5 stars 5 ratings. ISBN ISBN Why is ISBN important? ISBN. This bar-code number lets you verify that you're getting exactly the right version or edition of a book. Cited by:


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Image analysis of solid propellant combustion holograms using an imageaction software package by David N. Redman Download PDF EPUB FB2

Implementation of Image Action Plus Software for Image Analysis of Solid Propellant Combustion Holograms [Valerie R. Hockgraver] on *FREE* shipping on qualifying offers.

Implementation of Image Action Plus Software for Image Analysis of Author: Valerie R. Hockgraver. A two-beam holographic scheme consisting of a relay lens and an integral hologram has been used with a Q-switched ruby laser to record high resolution 3-D images and interferograms of the combustion of small ( x 3 x 6 millimeter; x x inch) rocket propellant samples in Cited by: 1.

solid propellant; and finally, calculation of diffusion flame effects that are critical in the combustion of AP/hydrocarbon solid propellants. The capability of modeling premixed combustion using detailed kinetic mecha-nisms has been evolving and successfully applied to solid propellant ingredients based on a one-dimensional approach.

rocket propellant. Commercial software [1] can be used to complete this; also, a mathematical-physical model of the solid propellant rocket motor operation can be built using internal ballistic laws and by considering individual characteristics of the propellant charge, combustion chamber and nozzle dimensions [].Author: Bogdan Zygmunt, Zbigniew Surma, Zbigniew Leciejewski, Krzysztof Motyl, Tomasz Rasztabiga.

Normally, the quality of solid propellant is defined by its grain. Therefore, during the casting process any inclusion, i.e. bubble, air gap and cavity, should not occur.

SIMPLIFIED COMPUTER PROGRAM FOR ANALYSIS OF SOLID-PROPELLANT ROCKET MOTORS Final Report, 15 Dec. - 15 Apr. Unclas (Auburn Univ.) p HC $ CSCL 21H G3/28 EXTENSION OF A SIMPLIFIED COMPUTER PROGRAM FOR ANALYSIS OF SOLID-PROPELLANT ROCKET MOTORS By Richard H. Sforzini Auburn University Auburn, Alabama April.

The primary function of a propellant grain is to produce combustion products at a prescribed flowrate defined by: where p is the propellant mass density, A b is the burning area, and r is the propellant burn rate.

A complete discussion on burn rate is provided in the Propellant Burn Rate web page. The total burning area consists of all. The capability of modeling premixed combustion using detailed kinetic mechanisms has been evolving and successfully applied to solid propellant ingredients based on a one-dimensional approach.

Much of the early work was performed at by: Production, Characterization, and Combustion of Nanoaluminum in Composite Solid Propellants. solid propellant rockets, guns, explosives, thermites, etc. analysis of the bright fi eld. Solid Hydrogen Experiments for Atomic Propellants: Image Analyses Bryan Palaszewski Glenn Research Center, Cleveland, Ohio Prepared for the 37th Joint Propulsion Conference and Exhibit cosponsored by the AIAA, ASME, SAE, and ASEE Salt Lake City, Utah, JulyNational Aeronautics and Space Administration Glenn Research Center January   Addeddate Identifier Solid_propellant_processing_factors_in_rocket_motor_design Identifier-ark ark://t1tf3v07v Ocr ABBYY FineReader Solid propellant rocket motors are the most widely used propulsion systems for military applications that require high thrust to weight ratio for relatively short time intervals.

Very wide range of magnitude and duration of the thrust can be obtained from solid propellant rocket motors by making some small changes at the design of the rocket motor. 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.

formance of a given propellant and propellant-geometry can be determined. The currently used software, GDP[1], is able to calculate the performance and burn behavior in detail. Yet, it does not provide fast analysis or a basis for optimizations of the propellant geometry, also known as the grain Size: 4MB.

Addeddate Identifier Solid_Propellant_Engineering Identifier-ark ark://tmv3m Ocr ABBYY FineReader Pages Ppi Scanner. On this slide, we show a schematic of a solid rocket engine. Solid rocket engines are used on air-to-air and air-to-ground missiles, on model rockets, and as boosters for satellite launchers.

In a solid rocket, the fuel and oxidizer are mixed together into a solid propellant which is packed into a solid cylinder. A hole through the cylinder serves as a combustion chamber. Propellant stock photos and images () Best Match Fresh.

Refine. Back Page of 9 Next. Display Mode. Liquid propellant and solid examples. Take off physics forces. Stock Image by normaals 1 / 23 Fuel Nozzle Stock Image by Gudella 2 / 5 Gas Station Road Sign.

The liquid oxygen and hydrogen tanks hold over million litres of propellant to power the rocket's core stage that is comprised of four RS engines and two solid rocket boosters. Integrated Simulation of Solid Propellant Rockets William A.

Dick Managing Director 4 April C e n t e r f o r S i m u l a t i o n o f A d v a n c e d R o c k e t s U n i v e r s i t y o f I l l i n o i s a t U r b a n a - C h a m p a i g n © Board of Trustees of the University of Illinois ©. The user may run the analysis 3 times without restarting the software.

To continue with evaluation, the application has to be restarted. After restart, the application does not open the last used configuration file automatically. If needed, the user has to open it explicitly. Solid rocket motor internal ballistics simulation using different burning rate models 51 For many double-base propellants, also referred to as smokeless powders, it was established that the burning rates obey a relationship known as Vieille’s or Saint Robert’s empirical law, represented by .Solid Rocket Motor (SRM) based solid propellant.

This project focus on and discusses the study of optimum design based SRM characteristics including the methods of the optimum design selection and fabrication, analysis using COSMOS and static thrust fundamental of solid File Size: 1MB.Windows Software.

Combustion and propellant simulation tools: PROPEP - Author: unknown - click to download (k Platform: DOS) Expanded data file () for the PROPEP program. Includes entries for Dextrose, Sorbitol, Charcoal, Asphalt, and Paraffin. (23k) From Richard Nakka's Experimental Rocketry Web Site.