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A Method For Incorporating Changing Structural Characteristics Due To Propellant Mass Usage In A Launch Vehicle Ascent Simulation
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721778812 Total Pages :28 pages Book Rating :4.7/5 (788 download)
Book Synopsis A Method for Incorporating Changing Structural Characteristics Due to Propellant Mass Usage in a Launch Vehicle Ascent Simulation by : National Aeronautics and Space Administration (NASA)
Download or read book A Method for Incorporating Changing Structural Characteristics Due to Propellant Mass Usage in a Launch Vehicle Ascent Simulation written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-24 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Launch vehicles consume large quantities of propellant quickly, causing the mass properties and structural dynamics of the vehicle to change dramatically. Currently, structural load assessments account for this change with a large collection of structural models representing various propellant fill levels. This creates a large database of models complicating the delivery of reduced models and requiring extensive work for model changes. Presented here is a method to account for these mass changes in a more efficient manner. The method allows for the subtraction of propellant mass as the propellant is used in the simulation. This subtraction is done in the modal domain of the vehicle generalized model. Additional computation required is primarily for constructing the used propellant mass matrix from an initial propellant model and further matrix multiplications and subtractions. An additional eigenvalue solution is required to uncouple the new equations of motion; however, this is a much simplier calculation starting from a system that is already substantially uncoupled. The method was successfully tested in a simulation of Saturn V loads. Results from the method are compared to results from separate structural models for several propellant levels, showing excellent agreement. Further development to encompass more complicated propellant models, including slosh dynamics, is possible. McGhee, D. S. Marshall Space Flight Center NASA/TM-2004-213549, M-1124
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1972 with total page 1070 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book STAR written by and published by . This book was released on 1973 with total page 904 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Fixed-point Framework for Launch Vehicle Ascent Guidance by : Lijun Zhang
Download or read book A Fixed-point Framework for Launch Vehicle Ascent Guidance written by Lijun Zhang and published by . This book was released on 2006 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt: Recent, interests in responsive launch have highlighted the need for rapid and fully automated ascent guidance planning and guidance parameter generation for launch vehicles. This dissertation aims at developing methodology and algorithms for on-demand generation of optimal launch vehicle ascent trajectories from lift-off to achieving targeting conditions outside the atmosphere. The entire ascent trajectory from lift-off to final target point is divided into two parts: atmospheric ascent portion and vacuum ascent portion. The two portions are integrated via a fixed-point iteration based on the continuity condition at the switch point between atmospheric ascent portion and vacuum ascent portion. The previous research works on closed-loop endo-atmospheric ascent guidance shows that the classical finite difference method is well suited for fast solution of the constrained optimal three-dimensional ascent problem. The exploitation of certain unique features in the integration procedure between the atmospheric portion and vacuum portion and the finite difference method, allows us to cast the atmospheric ascent problem into a nested fixed-point iteration problem. Therefore a novel Fixed-Point Iteration algorithm is presented for solving the endo-atmospheric ascent guidance problem. Several approaches are also provided for facilitating the convergence of the fixed-point iteration. The exo-atmospheric ascent portion allows an optimal coast in between the two vacuum powered stages. The optimal coast enables more efficient usage of the propellant. The Analytical Multiple-Shooting algorithm is developed to find the optimal trajectory for this portion. A generic launch vehicle model is adopted in the numerical simulation. A series of open-loop and closed-loop simulations are performed. The results verify the effectiveness, robustness and reliability of the Fixed-Point Iteration (FPI) algorithm and Analytical Multiple-Shooting (AMS) algorithm developed in this research. In comparison to Finite Difference (FD) algorithm, the Fixed-Point Iteration algorithm is more adaptive to the "cold start" case for endo-atmospheric ascent guidance. The simulations also validate the feasibility of the methodology presented in this research in rapid panning and guidance for ascent through atmosphere.
Book Synopsis Solid Propellant Grain Structural Integrity Analysis by : James S. Noel
Download or read book Solid Propellant Grain Structural Integrity Analysis written by James S. Noel and published by . This book was released on 1973 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measured and Predicted Longitudinal Vibrations of a Liquid Propellant Two-stage Launch Vehicle by : Robert R. Clary
Download or read book Measured and Predicted Longitudinal Vibrations of a Liquid Propellant Two-stage Launch Vehicle written by Robert R. Clary and published by . This book was released on 1970 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental and analytical program was conducted to investigate the longitudinal vibration properties of a two-stage full-scale launch vehicle loaded with various amounts of simulated propellants. A two-dimensional finite-element mathematical model formulated from vehicle physical parameters and experimental results was the basis for free-and forced-vibration analyses. Good agreement was obtained between the measured and predicted responses. Vector-response plots enhanced the interpretation of experimental and forced-vibration analytical results. Proper identification and correlation of the modes required a knowledge of the accelerations along the length of the vehicle, accelerations of specific components such as the engines and the turbopump, and pressures at the top and bottom of the propellant tanks.
Book Synopsis Launch Vehicle Design Process: Characterization, Technical Integration, and Lessons Learned by : J. C. Blair
Download or read book Launch Vehicle Design Process: Characterization, Technical Integration, and Lessons Learned written by J. C. Blair and published by . This book was released on 2001 with total page 264 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720363767 Total Pages :60 pages Book Rating :4.3/5 (637 download)
Book Synopsis A Procedure for Structural Weight Estimation of Single Stage to Orbit Launch Vehicles (Interim User's Manual) by : National Aeronautics and Space Administration (NASA)
Download or read book A Procedure for Structural Weight Estimation of Single Stage to Orbit Launch Vehicles (Interim User's Manual) written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-29 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is an interim user's manual for current procedures used in the Vehicle Analysis Branch at NASA Langley Research Center, Hampton, Virginia, for launch vehicle structural subsystem weight estimation based on finite element modeling and structural analysis. The process is intended to complement traditional methods of conceptual and early preliminary structural design such as the application of empirical weight estimation or application of classical engineering design equations and criteria on one dimensional "line" models. Functions of two commercially available software codes are coupled together. Vehicle modeling and analysis are done using SDRC/I-DEAS, and structural sizing is performed with the Collier Research Corp. HyperSizer program.Martinovic, Zoran N. and Cerro, Jeffrey A.Langley Research CenterSTRUCTURAL WEIGHT; SINGLE STAGE TO ORBIT VEHICLES; MATHEMATICAL MODELS; USER MANUALS (COMPUTER PROGRAMS); LAUNCH VEHICLES; FINITE ELEMENT METHOD; LOADS (FORCES); ITERATION; MASS RATIOS
Book Synopsis Fundamentals of Rocket Propulsion by : DP Mishra
Download or read book Fundamentals of Rocket Propulsion written by DP Mishra and published by CRC Press. This book was released on 2017-07-20 with total page 364 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book follows a unified approach to present the basic principles of rocket propulsion in concise and lucid form. This textbook comprises of ten chapters ranging from brief introduction and elements of rocket propulsion, aerothermodynamics to solid, liquid and hybrid propellant rocket engines with chapter on electrical propulsion. Worked out examples are also provided at the end of chapter for understanding uncertainty analysis. This book is designed and developed as an introductory text on the fundamental aspects of rocket propulsion for both undergraduate and graduate students. It is also aimed towards practicing engineers in the field of space engineering. This comprehensive guide also provides adequate problems for audience to understand intricate aspects of rocket propulsion enabling them to design and develop rocket engines for peaceful purposes.
Book Synopsis Influence of Structure and Material Research on Advanced Launch Systems' Weight, Performance, and Cost by : J. A. Boddy
Download or read book Influence of Structure and Material Research on Advanced Launch Systems' Weight, Performance, and Cost written by J. A. Boddy and published by . This book was released on 1968 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Information Flow in the Launch Vehicle Design/Analysis Process by :
Download or read book Information Flow in the Launch Vehicle Design/Analysis Process written by and published by . This book was released on 1999 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Improved Analytic Longitudinal Response Analysis for Axisymmetric Launch Vehicles. Volume I - Linear Analytic Model by :
Download or read book Improved Analytic Longitudinal Response Analysis for Axisymmetric Launch Vehicles. Volume I - Linear Analytic Model written by and published by . This book was released on 1965 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes an improved linear analytical model and A digital program developed for the calculation of axisymmetric launch vehicle steady-stage response to applied axisymmetric sinusoidal loads. The detailed computer programming manual for the digital program is contained in Volume II of this report. In the evaluation of launch vehicle behavior, it is necessary to study the response of the entire vehicle to a wide variety of dynamic loadings to insure the structural integrity and stability of the system. Much effort has already gone into the development of techniques to calculate the vehicle response to lateral and longitudinal loadings using distributed and lumped spring -mass models and techniques for theoretical and empirical modeling of the vehicle behavior. However, experimental data indicate that these procedures are unsatisfactory in several respects. For example, accurate representation of important structural shell characteristics and realistic coupling of the fluids with the detailed structural behavior of tank walls and bulkheads are omitted.
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1998 with total page 988 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Feasibility of SCRAMJET Technology for an Intermediate Propulsive Stage of an Expendable Launch Vehicle by : Michael D. Schafer
Download or read book Feasibility of SCRAMJET Technology for an Intermediate Propulsive Stage of an Expendable Launch Vehicle written by Michael D. Schafer and published by . This book was released on 2002 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: The single largest contributor to the cost of pulling objects into space is that of the launch portion. The currently available chemical rockets are only capable of specific impulse (Isp) values on the average of 300-350 seconds, with a maximum of 450 seconds. In order to improve the performance of the current families of launch vehicles, it is necessary to increase the performance of the rocket motors, and conversely the amount of propellant/ oxidizer carried. The purpose of this thesis was to determine the feasibility of employing SCRAMJET technology for an intermediate propulsive stage of an expendable launch vehicle. This was motivated by the fact that SCRAMJETS offer a very high propulsive efficiency when compared to conventional chemical rockets. The incorporation of a SCRAMJET engine into the configuration stack' of an expendable launch vehicle, offers the promise of increased payload mass fraction or an increase in the number of attainable orbital profiles. Analytical tools were developed using open-source software to identify launch trajectories for the SCRAMJET-enabled rocket configurations, and to determine how these would differ from conventional launch profiles. The effects of incremental increases in configuration lift and drag coefficients due to the SCRAMJET stage was analyzed. It was determined that incorporation of SCRAMJET Technology into an expendable rocket configuration offered marked improvement in performance, reduction in total launch weight, and increase operational flexibility when compared to a similarly sized conventional chemical rocket.
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781723760976 Total Pages :32 pages Book Rating :4.7/5 (69 download)
Book Synopsis Study Task for Determining the Effects of Boost-Phase Environments on Densified Propellants Thermal Conditions for Expendable Launch Vehicles by : National Aeronautics and Space Adm Nasa
Download or read book Study Task for Determining the Effects of Boost-Phase Environments on Densified Propellants Thermal Conditions for Expendable Launch Vehicles written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-17 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A thermodynamic study has been conducted that investigated the effects of the boost-phase environment on densified propellant thermal conditions for expendable launch vehicles. Two thermodynamic models were developed and utilized to bound the expected thermodynamic conditions inside the cryogenic liquid hydrogen and oxygen propellant tanks of an Atlas IIAS/Centaur launch vehicle during the initial phases of flight. The ideal isentropic compression model was developed to predict minimum pressurant gas requirements. The thermal equilibrium model was developed to predict the maximum pressurant gas requirements. The models were modified to simulate the required flight tank pressure profiles through ramp pressurization, liquid expulsion, and tank venting. The transient parameters investigated were: liquid temperature, liquid level, and pressurant gas consumption. Several mission scenarios were analyzed using the thermodynamic models, and the results indicate that flying an Atlas IIAS launch vehicle with densified propellants is feasible and beneficial but may require some minor changes to the vehicle.Haberbusch, Mark S. and Meyer, Michael L. (Technical Monitor)Glenn Research CenterROCKET PROPELLANTS; PROPELLANT TANKS; FUEL TANK PRESSURIZATION; PRESSURIZING; THERMODYNAMICS; SIMULATION; ATLAS CENTAUR LAUNCH VEHICLE; DENSIFICATION; TRAJECTORY ANALYSIS
Download or read book AIAA 85-0899 - AIAA 85-0950 written by and published by . This book was released on 1985 with total page 618 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Tech Briefs written by and published by . This book was released on 1994 with total page 348 pages. Available in PDF, EPUB and Kindle. Book excerpt:
