Integrating the Preliminary Design Modeling of Solid Propellant, Monopropellant, Bipropellant, and Hybrid Propulsion Systems

Author(s):  
Charles Taylor
Author(s):  
M Benatmane ◽  
B Salter

With the ever tightening of budgets and legislation, new vessel builds are facing tough times.  The future maritime industry requires more efficient vessels to minimise ship operational costs with cleaner technologies that meet stringent environment regulations, reduce greenhouse gas emissions, specifically carbon emissions. Emissions reduction continues to be high on the agenda for the marine industry, it is responsible for about 2.5 percent of global greenhouse emissions1 and is under great pressure to reduce its environmental impact. With pressure comes the opportunity to incentivize innovation, developments and implementation of energy efficient measures, both design and operational. Naval propulsion systems are no different from other industries, and the industry is exploring ways to optimise propulsion and electrical power generation systems architecture for better performance and efficiency. Electric technology plays a leading role. The paper will: Provide a brief overview about the hybrid propulsion concept, with key electrical, mechanical qualities and issues. Describe different designs configurations and performances of hybrid propulsion systems from demonstrated and operational systems in the commercial and naval world. Cover the lessons learnt in technologies and controls used on such systems. Examine future architectures including energy storage and explore the benefits and the flexibility these can bringto the hybrid propulsion sphere.


2015 ◽  
Vol 4 (2) ◽  
pp. 67-72 ◽  
Author(s):  
Самойлов ◽  
M. Samoylov ◽  
Бурцев ◽  
S. Burtsev ◽  
Симаков ◽  
...  

The influence of the circuitry of the hybrid power plant short and medium haul aircraft on their fuel efficiency and environmental characteristics have been investigated. Directions of improvement of traditional patterns of power plants of aircraft on the example of PD-14 engine were analyzed. It has been shown that the use of turbojet engines and traditional schemes operating on aviation kerosene, will not allow to fulfill the demands made by the International Civil Aviation Organization (ICAO) to perspective plane 2025–2035. The analysis of the three schemes hybrid propulsion systems has been performed. It has been shown that using the presented hybrid propulsion systems of alternative fuels can reduce CO2 emissions by 19% to 20% compared with conventional turbojet engines, which run on kerosene TS-1. It has been shown that this fuel efficiency is increased by 2–3%, and the total mass of the power plant increases of 6 to 16%.


Author(s):  
Chana Anna Saias ◽  
Ioannis Goulos ◽  
Ioannis Roumeliotis ◽  
Vassilios Pachidis ◽  
Marko Bacic

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.


2013 ◽  
pp. 163-199
Author(s):  
Lino Guzzella ◽  
Antonio Sciarretta

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