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Author : Sabri Ahmet Sansoy
Publisher :
ISBN 13 :
Total Pages : 186 pages
Book Rating : 4.:/5 (182 download)
Download or read book Design Optimization of a Transatmospheric Launch Vehicle written by Sabri Ahmet Sansoy and published by . This book was released on 1987 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Douglas James Bayley
Publisher :
ISBN 13 :
Total Pages : 196 pages
Book Rating : 4.:/5 (498 download)
Download or read book Design Optimization of Space Launch Vehicles Using a Genetic Algorithm written by Douglas James Bayley and published by . This book was released on 2007 with total page 196 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Air Force (USAF) continues to have a need for assured access to space. In addition to flexible and responsive spacelift, a reduction in the cost per launch of space launch vehicles is also desirable. For this purpose, an investigation of the design optimization of space launch vehicles has been conducted.
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781720610212
Total Pages : 36 pages
Book Rating : 4.6/5 (12 download)
Download or read book Launch Vehicle Design and Optimization Methods and Priority for the Advanced Engineering Environment written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-03 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: NASA's Advanced Engineering Environment (AEE) is a research and development program that will improve collaboration among design engineers for launch vehicle conceptual design and provide the infrastructure (methods and framework) necessary to enable that environment. In this paper, three major technical challenges facing the AEE program are identified, and three specific design problems are selected to demonstrate how advanced methods can improve current design activities. References are made to studies that demonstrate these design problems and methods, and these studies will provide the detailed information and check cases to support incorporation of these methods into the AEE. This paper provides background and terminology for discussing the launch vehicle conceptual design problem so that the diverse AEE user community can participate in prioritizing the AEE development effort.Rowell, Lawrence F. and Korte, John J.Langley Research CenterLAUNCH VEHICLES; SYSTEMS ENGINEERING; DESIGN OPTIMIZATION; SPACE TRANSPORTATION SYSTEM; RESEARCH AND DEVELOPMENT; MATHEMATICAL MODELS; STOCHASTIC PROCESSES; GENETIC ALGORITHMS; EXPERIMENT DESIGN; CONFIGURATION MANAGEMENT
Author : Mark D. Stevenson
Publisher :
ISBN 13 :
Total Pages : 12 pages
Book Rating : 4.:/5 (742 download)
Download or read book Collaborative Design Environment for Space Launch Vehicle Design and Optimization written by Mark D. Stevenson and published by . This book was released on 2003 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: Like all organizations, the Air Force is interested in conducting its vehicle studies as quickly as possible with as high fidelity an analysis as is feasible and with a proven, repeatable design and analysis process. This research is in support of an approach formulated by engineers at Wright Patterson Air Force Base who seek to integrate design and analysis tools into a collaborative, network-distributed design environment. The benefits of using an integrated design environment to reduce the time and potential errors associated with the transfer of data between design and analysis codes are well documented. This research presents the integration of an initial set of space access and future strike vehicle analysis codes designed to improve the entire conceptual-level design process and documents the advantages of using the tools in a collaborative, network-distributed environment. This paper focuses on the design environment including geometry modeling, object design, discipline interactions, and design tools built for this effort including weight, propulsion, and trajectory analysis.
Author : Veena Savithri Dorairajan
Publisher :
ISBN 13 :
Total Pages : 154 pages
Book Rating : 4.:/5 (328 download)
Download or read book Synthesis of Launch Vehicle Design and Trajectory Optimization written by Veena Savithri Dorairajan and published by . This book was released on 1995 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Paul Andreas Ritter
Publisher :
ISBN 13 :
Total Pages : 178 pages
Book Rating : 4.:/5 (89 download)
Download or read book Optimization and Design for Heavy Lift Launch Vehicles written by Paul Andreas Ritter and published by . This book was released on 2012 with total page 178 pages. Available in PDF, EPUB and Kindle. Book excerpt: The simulation and evaluation of an orbital launch vehicle requires consideration of numerous factors. These factors include, but are not limited to the propulsion system, aerodynamic effects, rotation of the earth, oblateness, and gravity. A trajectory simulation that considers these different factors is generated by a code developed for this thesis titled Trajectories for Heavy-lift Evaluation and Optimization (THEO). THEO is a validated trajectory simulation code with the ability to model numerous launch configurations. THEO also has the capability to provide the means for an optimization objective. Optimization of a launch vehicle can be specified in terms of many different variables. For a heavy lift launch vehicle in this thesis, the goal of optimization is to minimize Gross Lift Off Weight (GLOW). THEO provides the capability to optimize by simulating hundreds of thousands of trajectories for a single configuration through the variation of preset independent variables. The sheer volume of these trajectories provides the means to locate configurations that minimize GLOW. Optimization can also be performed by determining the minimum amount of energy necessary to reach target burnout conditions. The energy requirements are then correlated to the propellant mass which can be used to estimate GLOW. This thesis first discusses the validation of THEO as a simulation program and the properties associated with accurately modeling a trajectory. It then relates how THEO and other developed tools can be utilized to determine a configuration that is optimized to minimize GLOW to orbit for adaptable payload sizes.
Author : National Aeronautics and Space Adm Nasa
Publisher :
ISBN 13 : 9781723852190
Total Pages : 56 pages
Book Rating : 4.8/5 (521 download)
Download or read book Information Flow in the Launch Vehicle Design/Analysis Process written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-09-20 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper describes the results of a team effort aimed at defining the information flow between disciplines at the Marshall Space Flight Center (MSFC) engaged in the design of space launch vehicles. The information flow is modeled at a first level and is described using three types of templates: an N x N diagram, discipline flow diagrams, and discipline task descriptions. It is intended to provide engineers with an understanding of the connections between what they do and where it fits in the overall design process of the project. It is also intended to provide design managers with a better understanding of information flow in the launch vehicle design cycle.Humphries, W. R., Sr. and Holland, W. and Bishop, R.Marshall Space Flight CenterINFORMATION FLOW; DESIGN ANALYSIS; LAUNCH VEHICLES; OPTIMIZATION; SPACECRAFT LAUNCHING; SPACE TRANSPORTATION...
Author : Wade H. Shafer
Publisher : Springer Science & Business Media
ISBN 13 : 1461305993
Total Pages : 411 pages
Book Rating : 4.4/5 (613 download)
Download or read book Masters Theses in the Pure and Applied Sciences written by Wade H. Shafer and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 411 pages. Available in PDF, EPUB and Kindle. Book excerpt: Masters Theses in the Pure and Applied Sciences was first conceived, published, and disseminated by the Center for Information and Numerical Data Analysis and Synthesis (CINDAS) * at Purdue University in 1 957, starting its coverage of theses with the academic year 1955. Beginning with Volume 13, the printing and dissemination phases of the activity were transferred to University Microfilms/Xerox of Ann Arbor, Michigan, with the thought that such an arrangement would be more beneficial to the academic and general scientific and technical community. After five years of this joint undertaking we had concluded that it was in the interest of all con cerned if the printing and distribution of the volumes were handled by an interna tional publishing house to assure improved service and broader dissemination. Hence, starting with Volume 18, Masters Theses in the Pure and Applied Sciences has been disseminated on a worldwide basis by Plenum Publishing Cor poration of New York, and in the same year the coverage was broadened to include Canadian universities. All back issues can also be ordered from Plenum. We have reported in Volume 32 (thesis year 1987) a total of 12,483 theses titles from 22 Canadian and 176 United States universities. We are sure that this broader base for these titles reported will greatly enhance the value of this important annual reference work. While Volume 32 reports theses submitted in 1987, on occasion, certain univer sities do report theses submitted in previous years but not reported at the time.
Author : Mohammed Abdulmalek Aldheeb
Publisher :
ISBN 13 :
Total Pages : 374 pages
Book Rating : 4.:/5 (957 download)
Download or read book Optimization of Micro Air Launch Vehicle for Micro and Nano Satellite written by Mohammed Abdulmalek Aldheeb and published by . This book was released on 2012 with total page 374 pages. Available in PDF, EPUB and Kindle. Book excerpt: Air launch vehicles provide a prominent solution for low cost launch of micro and nano satellites with much less launching constraints as compared to ground launch. In this research, evolutionary optimization techniques is used to design a micro air launch vehicle (MALV) which is specifically designed for very small payloads. To perform the optimization, a two-step design optimization algorithm is developed. In the first step, a preliminary design optimization of the air launch vehicle is performed to determine its design and performance parameters. In the second step, a trajectory optimization is performed to determine optimal trajectory and estimate the velocity losses of the designed vehicle. For the first step, a preliminary design model is developed for air launch vehicles. This model is used to calculate the masses, dimensions and performance parameters of the air launch vehicle. The inputs for this model are the payload mass; launching velocity losses due to drag, steering and gravity; and initial guess values for the vehicle specific impulses and inert mass fractions. Given these values, mission analysis and preliminary design is performed to determine, for each stage of the vehicle, the geometric and performance parameters taking into consideration some important inputs such as thrust to weight ratio, length to diameter ratio, chamber pressure, type of propellant and structure materials. For the second step, a 3 degree-of-freedom trajectory simulation model is developed. The inputs of this model are the masses and performance parameters obtained from vehicle design and a predetermined set of angles of attack. Angles of attack are used to steer the vehicle along its trajectory using aerodynamic forces. The coefficients of lift and drag are obtained using Missile DATCOM, which calculates the aerodynamic coefficients within the flight envelope of the vehicle. Two evolutionary optimization techniques are used for the optimization of the air launch vehicle trajectory and design; namely particle swarm optimization (PSO) and differential evolution (DE). These techniques were selected for their ability to handle large design spaces with many dimensions while making no assumptions about the design problem itself. The optimization problem is formulated with the vehicle initial mass taken as the objective function. A set of design variables are used in vehicle design, which are thrust to weight ratio, length to diameter ration, exit area to rocket diameter ratio, chamber pressure and velocity fraction for each stage. The micro air launch vehicle is designed to launch a 20-kg payload into a 400-km circular polar orbit after release from mother plane at 12-km with initial velocity of 300 m/s. Realizing the important role of the fairing mass on vehicle performance, a geometric method is used to estimate the fairing mass for micro air launch vehicle. The estimation gives fairing mass between 8 kg and 12 kg. Using PSO, the optimal micro air launch vehicle initial mass achieved is 1287 kg and the maximum payload mass is 20.7 kg for 12-kg fairing mass. When the 8-kg fairing mass is assumed, the initial mass achieved is reduced to 1267 kg and the maximum payload mass is reduced to 20.64 kg. DE is used to solve the same optimization problem with 8-kg fairing mass for comparison with PSO. The initial mass obtained from DE using fairing mass of 8 kg is 1267 kg and payload mass is 20.61 kg. Therefore, both evolutionary techniques give very close optimal results for the same objective functions and same design variables.
Author : Donald P. Legalley
Publisher : Academic Press
ISBN 13 : 1483270823
Total Pages : 433 pages
Book Rating : 4.4/5 (832 download)
Download or read book Re-Entry and Vehicle Design written by Donald P. Legalley and published by Academic Press. This book was released on 2014-05-12 with total page 433 pages. Available in PDF, EPUB and Kindle. Book excerpt: Ballistic Missile and Space Technology, Volume IV: Re-Entry and Vehicle Design focuses on the advancements of processes, methodologies, and technologies involved in re-entry and vehicle design, including hypersonics, material structures, propulsion, and communications. The selection first offers information on the pyrolysis of plastics in a high vacuum arc image furnace and aerothermodynamic feasibility of graphite for hypersonic glide vehicles. Discussions focus on aerothermochemical behavior of graphite, transient heat conduction, equilibrium glide trajectory, and apparatus and pyrolysis procedure. The text then takes a look at an engineering analysis of the weights of ablating systems for manned reentry vehicles and trajectories of lifting bodies entering planetary atmospheres at shallow angles. The manuscript ponders on propulsive control of atmospheric entry lifting trajectories, re-entry engineering mechanics, and rocket casing behavior predicted by laboratory tests. Topics include description of testing program, full-scale casing results, camera design, theoretical correlation, approximate thrust vector optimization, and propellant weight estimation. The selection is a dependable reference for astronauts and researchers interested in re-entry and vehicle design.
Author : Michael J. Steffens
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (89 download)
Download or read book A Combined Global and Local Methodology for Launch Vehicle Trajectory Design-space Exploration and Optimization written by Michael J. Steffens and published by . This book was released on 2014 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Trajectory optimization is an important part of launch vehicle design and operation. With the high costs of launching payload into orbit, every pound that can be saved increases affordability. One way to save weight in launch vehicle design and operation is by optimizing the ascent trajectory. Launch vehicle trajectory optimization is a field that has been studied since the 1950's. Originally, analytic solutions were sought because computers were slow and inefficient. With the advent of computers, however, different algorithms were developed for the purpose of trajectory optimization. Computer resources were still limited, and as such the algorithms were limited to local optimization methods, which can get stuck in specific regions of the design space. Local methods for trajectory optimization have been well studied and developed. Computer technology continues to advance, and in recent years global optimization has become available for application to a wide variety of problems, including trajectory optimization. The aim of this thesis is to create a methodology that applies global optimization to the trajectory optimization problem. Using information from a global search, the optimization design space can be reduced and a much smaller design space can be analyzed using already existing local methods. This allows for areas of interest in the design space to be identified and further studied and helps overcome the fact that many local methods can get stuck in local optima. The design space included in trajectory optimization is also considered in this thesis. The typical optimization variables are initial conditions and flight control variables. For direct optimization methods, the trajectory phase structure is currently chosen a priori. Including trajectory phase structure variables in the optimization process can yield better solutions. The methodology and phase structure optimization is demonstrated using an earth-to-orbit trajectory of a Delta IV Medium launch vehicle. Different methods of performing the global search and reducing the design space are compared. Local optimization is performed using the industry standard trajectory optimization tool POST. Finally, methods for varying the trajectory phase structure are presented and the results are compared.
Author : U. M. Schoettle
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Performance Optimization of an Airbreathing Launch Vehicle by a Sequential Trajectory Optimization and Vehicle Design Scheme written by U. M. Schoettle and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Benjamin Christopher Rush
Publisher :
ISBN 13 :
Total Pages : 98 pages
Book Rating : 4.:/5 (27 download)
Download or read book A Nonlinear Programming Model for Optimization of Launch Vehicle Design Parameters to Obtain Minimum Cost written by Benjamin Christopher Rush and published by . This book was released on 1966 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : J. C. Blair
Publisher :
ISBN 13 :
Total Pages : 264 pages
Book Rating : 4.:/5 (317 download)
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 : Jason Maxwell King
Publisher :
ISBN 13 :
Total Pages : 97 pages
Book Rating : 4.:/5 (773 download)
Download or read book Risk Quantification and Reliability Based Design Optimization in Reusable Launch Vehicles written by Jason Maxwell King and published by . This book was released on 2010 with total page 97 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Chong Hun Kim
Publisher : Lulu.com
ISBN 13 : 0615165117
Total Pages : 676 pages
Book Rating : 4.6/5 (151 download)
Download or read book Commercial Satellite Launch Vehicle Attitude Control Systems Design and Analysis (H-infinity, Loop Shaping, and Coprime Approach) written by Chong Hun Kim and published by Lulu.com. This book was released on 2007 with total page 676 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book is written for aerospace engineers who have completed their BS degree and are interested in the design and analysis of rocket attitude control systems. It introduces a new approach to the design, characterized by its robustness. Current LV attitude control systems are designed based on classical SISO control theory, and they lack robustness. The theory used here truly offers a technique that enables us to design control systems that are reasonably insensitive to math modeling errors and can withstand disturbances such as gust, and in addition it doesn’t need external states estimator, such as Kalman filtering. Extensive simulation results, which demonstrate the effectiveness of this approach, are presented in this book. Basic rocket theory and a concept of H-infinity control system design technique are explained for those who are new in these fields of study.
Author : Dietrich E. Koelle
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Cost-optimized Launch Vehicle Design written by Dietrich E. Koelle and published by . This book was released on 1992 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
