Approximate Nonlinear Analysis Of Solid Rocket Motors And T Burners Volume Ii Computer Program Userss Manual PDF Download
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| Author | : E. A. Powell |
| Publisher | : |
| Total Pages | : 361 |
| Release | : 1977 |
| Genre | : |
| ISBN | : |
Download Approximate Nonlinear Analysis of Solid Rocket Motors and T-Burners. Volume II. Computer Program Users's Manual Book in PDF, ePub and Kindle
Volume II of this report is a user's manual for the computer programs based on the approximate and 'exact' nonlinear axial-mode combustion instability analyses developed in Volume I. This volume contains a description of all the main programs and subroutines used in these instability programs, as well as descriptions of the inputs needed to operate the programs and the outputs generated. Sample cases are given to facilitate checkout of the programs. The FORTRAN IV source code for each of the programs is also given. (Author).
| Author | : |
| Publisher | : |
| Total Pages | : 1160 |
| Release | : 1986 |
| Genre | : Aeronautics |
| ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, ePub and Kindle
| Author | : E. A. Powell |
| Publisher | : |
| Total Pages | : 209 |
| Release | : 1977 |
| Genre | : |
| ISBN | : |
Download Approximate Nonlinear Analysis of Solid Rocket Motors and T-Burners. Volume I. Analysis and Results Book in PDF, ePub and Kindle
An approximate theory based on the Galerkin method was developed to describe the nonlinear behavior of axial-mode combustion instability in solid-propellant rocket motors and T-burners. For motors with linear combustion driving and linear particle damping (gasdynamic nonlinearities only), growth rates, limiting amplitudes and waveforms were in reasonable agreement with available 'exact' numerical solutions and experimental data. For T-burners the predicted limiting amplitudes were considerably higher than the experimentally measured values. To assess the importance of combustion nonlinearities, a heuristic nonlinear combustion response model was introduced into the approximate analysis. REsults obtained with both the approximate model and the 'exact' analysis showed that nonlinear combustion effects may be important for moderate amplitudes and may account for pulsed instabilities in some cases. The higher Reynolds number correction to the Stokes Drag Law was also included in both the approximate and 'exact' analyses. Results show that nonlinear particle effects become increasingly important as particle size and/or frequency increases. Also, particle nonlinearities may have a significant effect on optimum particle size for maximum damping and may account for pulsed instabilities in some cases. (Author).
| Author | : |
| Publisher | : |
| Total Pages | : 70 |
| Release | : 1972 |
| Genre | : |
| ISBN | : |
Download Numerical Analysis of Nonlinear Longitudinal Combustion Instability in Metalized Propellant Solid Rocket Motors. Volume 2. Computer Program User's Manual Book in PDF, ePub and Kindle
The present report is part of a two volume set which describes a nonlinear solid rocket motor instability analysis and computer program. This volume of the set describes the computer program and serves as a user's manual.
| Author | : |
| Publisher | : |
| Total Pages | : 1062 |
| Release | : 1978 |
| Genre | : Research |
| ISBN | : |
Download Government Reports Annual Index Book in PDF, ePub and Kindle
Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.
| Author | : |
| Publisher | : |
| Total Pages | : 546 |
| Release | : 2003 |
| Genre | : Airplanes |
| ISBN | : |
Download 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit July 20-23, 2003, Huntsville, Alabama: 03-4650 - 03-4699 Book in PDF, ePub and Kindle
| Author | : Jay N. Levine |
| Publisher | : |
| Total Pages | : 107 |
| Release | : 1974 |
| Genre | : |
| ISBN | : |
Download Nonlinear Analysis of Solid Rocket Combustion Instability Book in PDF, ePub and Kindle
The report describes, and serves as a user's manual, for the Ultrasystems Nonlinear Longitudinal Solid Rocket Motor Instability Program. The program solves the one dimensional, two-phase, time dependent equations of motion using the Rubin and Burstein finite difference method. This program has been structured in a user oriented manner, and is designed to be used as a general tool for engineering analysis of solid rocket motor longitudinal instability. This volume contains a description of all of the subroutines and program functions used in the instability program. A dictionary of all of the variables contained in blank, or labeled, commons is also included. Descriptions of the input required to operate the program, the output generated, and the logical units utilized are presented; followed by a sample case which serves to illustrate the text, as well as providing a method for checking out the program.
| Author | : |
| Publisher | : |
| Total Pages | : 1022 |
| Release | : 1979 |
| Genre | : Science |
| ISBN | : |
Download Government Reports Announcements & Index Book in PDF, ePub and Kindle
| Author | : Jay N. Levine |
| Publisher | : |
| Total Pages | : 187 |
| Release | : 1974 |
| Genre | : |
| ISBN | : |
Download Nonlinear Analysis of Solid Rocket Combustion Instability Book in PDF, ePub and Kindle
The primary objective of the current effort was to improve the utility, efficiency and accuracy of the previously developed nonlinear longitudinal combustion instability program. A finite difference procedure has been substituted for the method of characteristics solution of the governing equations of motion. The range of allowable motor and grain geometries has been greatly extended. In addition, the two-phase analysis has been extended to multiple particle sizes. A comparison with data from a small laboratory pulse motor has demonstrated that the present nonlinear model is capable of quantitatively predicting limiting amplitude when the combustion response of the propellant is adequately characterized. The program has also been modified to make it applicable to T-burners. A vent model which accounts for acoustic radiation losses has been developed. Separate nonlinear particle damping and uncoupled nonlinear combustion response studies have been carried out. (Modified author abstract).
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 586 |
| Release | : 2018-08-04 |
| Genre | : |
| ISBN | : 9781724704665 |
Download User's Manual for Rocket Combustor Interactive Design (Roccid) and Analysis Computer Program. Volume 2 Book in PDF, ePub and Kindle
The appendices A-K to the user's manual for the rocket combustor interactive design (ROCCID) computer program are presented. This includes installation instructions, flow charts, subroutine model documentation, and sample output files. The ROCCID program, written in Fortran 77, provides a standardized methodology using state of the art codes and procedures for the analysis of a liquid rocket engine combustor's steady state combustion performance and combustion stability. The ROCCID is currently capable of analyzing mixed element injector patterns containing impinging like doublet or unlike triplet, showerhead, shear coaxial and swirl coaxial elements as long as only one element type exists in each injector core, baffle, or barrier zone. Real propellant properties of oxygen, hydrogen, methane, propane, and RP-1 are included in ROCCID. The properties of other propellants can be easily added. The analysis models in ROCCID can account for the influences of acoustic cavities, helmholtz resonators, and radial thrust chamber baffles on combustion stability. ROCCID also contains the logic to interactively create a combustor design which meets input performance and stability goals. A preliminary design results from the application of historical correlations to the input design requirements. The steady state performance and combustion stability of this design is evaluated using the analysis models, and ROCCID guides the user as to the design changes required to satisfy the user's performance and stability goals, including the design of stability aids. Output from ROCCID includes a formatted input file for the standardized JANNAF engine performance prediction procedure. Muss, J. A. and Nguyen, T. V. and Johnson, C. W. Unspecified Center NASA-CR-187110, NAS 1.26:187110 NAS3-25556; RTOP 582-01-21...
