scholarly journals Analytical and preliminary design studies of nuclear rocket propulsion systems. Volume VI. Compilation of hydrogen properties

1961 ◽  
Author(s):  
J.D. Barney ◽  
P.M. Magee
Keyword(s):  
Preliminary Design ◽  
Propulsion Systems ◽  
Design Studies ◽  
Rocket Propulsion ◽  
Nuclear Rocket

scholarly journals Low-Noise Propulsion Systems for Subsonic Transports

1969 ◽  
Author(s):  
James J. Kramer ◽  
Bruce R. Leonard ◽  
Charles E. Feiler
Keyword(s):  
Long Range ◽  
Low Noise ◽  
Preliminary Design ◽  
Propulsion Systems ◽  
Design Studies ◽  
Transport Aircraft ◽  
Range Transport ◽  
Definition Of ◽  
Acoustic Treatment ◽  
Aircraft Data

The authors present a brief review of the preliminary design studies that led to a definition of specifications for a low-noise output turbofan engine for use on long-range subsonic transport aircraft. Data on low-speed fans, with and without acoustic treatment in the fan ducting, indicate that overall noise output of four-engine long-range transport aircraft can be reduced 20 perceived noise decibels by appropriate fan design and the use of nacelle acoustic treatment.

Features of the system approach to safety stand tests of liquid rocket propulsion systems

2020 ◽  
pp. 40-50
Author(s):  
В.А. Бершадский
Keyword(s):  
Basic Concept ◽  
System Approach ◽  
Functional Model ◽  
Industrial Safety ◽  
Propulsion Systems ◽  
Rocket Propulsion ◽  
Effective Application ◽  
Liquid Rocket Propulsion ◽  
Liquid Rocket

Пояснена необходимость разработки и реализации специальных мероприятий при применении системного подхода к безопасности стендовых испытаний двигательных установок ракет. Определена основная концепция промышленной безопасности при стендовых испытаниях кислородно-водородных двигательных установок. Изложено и обосновано содержание специальных мероприятий по безопасности испытаний. Предложена функциональная модель безаварийного проведения испытаний и определены мероприятия для её эффективного применения. It explains the need to develop and implement special measures for a systematic aproach to the safety of stand tests of rocket propulsion systems. The basic concept of industrial safety during stand tests of oxygen-hydrogen propulsion systems is defined. The content of special measures for test safety is described and justified. A functional model of trouble-free testing is proposed and measures for effective application are defined.

Preliminary Design of Hybrid-Electric Propulsion Systems for Emerging UAM Rotorcraft Architectures

2021 ◽  
Author(s):  
Chana Anna Saias ◽  
Ioannis Goulos ◽  
Ioannis Roumeliotis ◽  
Vassilios Pachidis ◽  
Marko Bacic
Keyword(s):  
Electric Propulsion ◽  
Flight Test ◽  
Preliminary Design ◽  
Propulsion Systems ◽  
Rotor Aerodynamics ◽  
Tilt Rotor ◽  
Integrated Methodology ◽  
Hybrid Electric ◽  
Battery Energy ◽  
Optimal Implementation

Abstract The increasing demands for air-taxi operations together with the ambitious targets for reduced environmental impact have driven significant interest in alternative rotorcraft architectures and propulsion systems. The design of Hybrid-Electric Propulsion Systems (HEPSs) for rotorcraft is seen as being able to contribute to those goals. This work aims to conduct a comprehensive design and trade-off analysis of hybrid powerplants for rotorcraft, targeting enhanced payload-range capability and fuel economy. An integrated methodology for the design, performance assessment and optimal implementation of HEPSs for conceptual rotorcraft has been developed. A multi-disciplinary approach is devised comprising models for rotor aerodynamics, flight dynamics, HEPS performance and weight estimation. All models are validated using experimental or flight test data. The methodology is deployed for the assessment of a hybrid-electric tilt-rotor, modelled after the NASA XV-15. This work targets to provide new insight in the preliminary design and sizing of optimally designed HEPSs for novel tilt-rotor aircraft. The paper demonstrates that at present, current battery energy densities (250Wh/kg) severely limit the degree of hybridization if a fixed useful payload and range are to be achieved. However, it is also shown that if advancements in battery energy density to 500Wh/kg are realized, a significant increase in the level of hybridization and hence reduction of fuel burned and carbon output relative to the conventional configuration can be attained. The methodology presented is flexible enough to be applied to alternative rotorcraft configurations and propulsion systems.

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