Hybrid Propulsion Technology Program: Phase 1 PDF Download

Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781792760242
Category : Science
Languages : en
Pages : 40

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Book Description
A number of booster propulsion system concepts are being considered for the next generation of manned and unmanned space launch vehicles. The one propulsion system concept that has potential for reducing costs with increased safety, reliability, and performance is hybrid propulsion (HP). A HP system may be thought of as a liquid propulsion system with solid fuel or a solid propulsion system with a liquid oxidizer. The liquid propulsion features that are most attractive are the higher specific impulse, clean exhaust, separated propellants, and oxidizer loading just prior to launch. The most attractive solid propulsion features includes low life cycle costs, no rotating machinery, compact size, and a robust case. In addition, a HP system has a robust LO2 tank; provides thrust control for ignition, to alleviate flight loads, and for thrust termination; and uses an inert grain that is not sensitive to anomalies such as cracks, voids, and separations. The object is to develop the technology to enable the application of HP to manned and unmanned space launch vehicles. This program will identify the necessary technology, acquire that technology, and demonstrate that technology. This volume is the executive summary. Schuler, A. L. and Wiley, D. R. NASA-CR-183972, NAS 1.26:183972, GDSS-HPT-89-001-VOL-1 NAS8-37777...

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722284299
Category :
Languages : en
Pages : 24

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Book Description
The study program was contracted to evaluate concepts of hybrid propulsion, select the most optimum, and prepare a conceptual design package. Further, this study required preparation of a technology definition package to identify hybrid propulsion enabling technologies and planning to acquire that technology in Phase 2 and demonstrate that technology in Phase 3. Researchers evaluated two design philosophies for Hybrid Rocket Booster (HRB) selection. The first is an ASRM modified hybrid wherein as many components/designs as possible were used from the present Advanced Solid Rocket Motor (ASRM) design. The second was an entirely new hybrid optimized booster using ASRM criteria as a point of departure, i.e., diameter, thrust time curve, launch facilities, and external tank attach points. Researchers selected the new design based on the logic of optimizing a hybrid booster to provide NASA with a next generation vehicle in lieu of an interim advancement over the ASRM. The enabling technologies for hybrid propulsion are applicable to either and vehicle design may be selected at a downstream point (Phase 3) at NASA's discretion. The completion of these studies resulted in ranking the various concepts of boosters from the RSRM to a turbopump fed (TF) hybrid. The scoring resulting from the Figure of Merit (FOM) scoring system clearly shows a natural growth path where the turbopump fed solid liquid staged combustion hybrid provides maximized payload and the highest safety, reliability, and low life cycle costing. Unspecified Center NAS8-37775...

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724242143
Category :
Languages : en
Pages : 264

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Book Description
A concept design study was performed to configure two sizes of hybrid boosters; one which duplicates the advanced shuttle rocket motor vacuum thrust time curve and a smaller, quarter thrust level booster. Two sizes of hybrid boosters were configured for either pump-fed or pressure-fed oxygen feed systems. Performance analyses show improved payload capability relative to a solid propellant booster. Size optimization and fuel safety considerations resulted in a 4.57 m (180 inch) diameter large booster with an inert hydrocarbon fuel. The preferred diameter for the quarter thrust level booster is 2.53 m (96 inches). As part of the design study critical technology issues were identified and a technology acquisition and demonstration plan was formulated. Jensen, Gordon E. and Holzman, Allen L. and Leisch, Steven O. and Keilbach, Joseph and Parsley, Randy and Humphrey, John Unspecified Center NASA-CR-183953, NAS 1.26:183953, PROJ-2027-FR-VOL-1 NAS8-37778...

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722441067
Category :
Languages : en
Pages : 100

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Book Description
Three candidate hybrid propulsion (HP) concepts were identified, optimized, evaluated, and refined through an iterative process that continually forced improvement to the systems with respect to safety, reliability, cost, and performance criteria. A full scale booster meeting Advanced Solid Rocket Motor (ASRM) thrust-time constraints and a booster application for 1/4 ASRM thrust were evaluated. Trade studies and analyses were performed for each of the motor elements related to SRM technology. Based on trade study results, the optimum HP concept for both full and quarter sized systems was defined. The three candidate hybrid concepts evaluated are illustrated. Schuler, A. L. and Wiley, D. R. Unspecified Center...

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723148996
Category :
Languages : en
Pages : 118

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Book Description
A concept design study was performed to configure two sizes of hybrid boosters; one which duplicates the advanced shuttle rocket motor vacuum thrust time curve and a smaller, quarter thrust level booster. Two sizes of hybrid boosters were configured for either pump-fed or pressure-fed oxygen feed systems. Performance analyses show improved payload capability relative to a solid propellant booster. Size optimization and fuel safety considerations resulted in a 4.57 m (180 inch) diameter large booster with an inert hydrocarbon fuel. The preferred diameter for the quarter thrust level booster is 2.53 m (96 inches). The demonstration plan would culminate with test firings of a 3.05 m (120 inch) diameter hybrid booster. Jensen, Gordon E. and Holzman, Allen L. and Leisch, Steven O. and Keilbach, Joseph and Parsley, Randy and Humphrey, John Unspecified Center FEED SYSTEMS; HYBRID PROPULSION; OXYGEN SUPPLY EQUIPMENT; ROCKET ENGINES; THRUST; HYDROCARBON FUELS; OPTIMIZATION; PAYLOADS; SAFETY; SOLID PROPELLANTS; VACUUM EFFECTS...

Author: National Academies of Sciences, Engineering, and Medicine
Publisher: National Academies Press
ISBN: 0309440998
Category : Technology & Engineering
Languages : en
Pages : 123

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Book Description
The primary human activities that release carbon dioxide (CO2) into the atmosphere are the combustion of fossil fuels (coal, natural gas, and oil) to generate electricity, the provision of energy for transportation, and as a consequence of some industrial processes. Although aviation CO2 emissions only make up approximately 2.0 to 2.5 percent of total global annual CO2 emissions, research to reduce CO2 emissions is urgent because (1) such reductions may be legislated even as commercial air travel grows, (2) because it takes new technology a long time to propagate into and through the aviation fleet, and (3) because of the ongoing impact of global CO2 emissions. Commercial Aircraft Propulsion and Energy Systems Research develops a national research agenda for reducing CO2 emissions from commercial aviation. This report focuses on propulsion and energy technologies for reducing carbon emissions from large, commercial aircraftâ€" single-aisle and twin-aisle aircraft that carry 100 or more passengersâ€"because such aircraft account for more than 90 percent of global emissions from commercial aircraft. Moreover, while smaller aircraft also emit CO2, they make only a minor contribution to global emissions, and many technologies that reduce CO2 emissions for large aircraft also apply to smaller aircraft. As commercial aviation continues to grow in terms of revenue-passenger miles and cargo ton miles, CO2 emissions are expected to increase. To reduce the contribution of aviation to climate change, it is essential to improve the effectiveness of ongoing efforts to reduce emissions and initiate research into new approaches.

Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 11

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Book Description
This report contains the program plan and background information for the Heavy Vehicle Hybrid Propulsion R and D Program sponsored by the Department of Energy's Office of Heavy Vehicle Technologies. The program is a collaboration between industry and government established for the development of advanced hybrid-electric propulsion technology for urban cycle trucks and buses. It targets specific applications to enhance potential market success. Potential end-users are also involved.

Author: John M. Miller
Publisher: IET
ISBN: 0863419151
Category : Technology & Engineering
Languages : en
Pages : 473

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Book Description
Offering in-depth coverage of hybrid propulsion topics, energy storage systems and modelling, and supporting electrical systems, this book will be an invaluable resource for practising engineers and managers involved in all aspects of hybrid vehicle development, modelling, simulation and testing.

Author: Yuan Zou
Publisher: Springer
ISBN: 3662536730
Category : Technology & Engineering
Languages : en
Pages : 331

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Book Description
This book focuses on the systematic design of architectures, parameters and control of typical hybrid propulsion systems for wheeled and tracked vehicles based on a combination of theoretical research and engineering practice. Adopting a mechatronic system dynamics perspective, principles and methods from the fields of optimal control and system optimization are applied in order to analyze the hybrid propulsion configuration and controller design. Case investigations for typical hybrid propulsion systems of wheeled and tracked ground vehicles are also provided.

Author: Craig B. Kunkle
Publisher:
ISBN:
Category :
Languages : en
Pages : 390

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Book Description
Future advanced propulsion systems require improved control systems for the achievement of maximum overall weapon system effectiveness. Additional closed-loop control and flight-sensitive limiting functions are required to provide the necessary fuel economy and improved system response. The Advanced Hybrid Propulsion System Control Program has provided data necessary to achieve these requirements. The work accomplished during the program is presented. The performance requirements for an advanced turbopropulsion system were determined, and a control system to meet these requirements established. A comparison of fluidic, electronic, and hydromechanical technologies was made. A breadboard hybrid control system was designed, fabricated, and tested to demonstrate an approach for combining the three technologies. Bench tests at 1200 F environmental temperatures and engine evaluation tests were conducted and the results presented.