Sizing and Optimization of Novel General Aviation Vehicles and Propulsion System Architectures

2018 ◽  
Author(s):  
Gokcin Cinar ◽  
Yu Cai ◽  
Imon Chakraborty ◽  
Dimitri N. Mavris
Keyword(s):  
Propulsion System ◽  
General Aviation ◽  
System Architectures

Methodology to qualify marine electrical propulsion system architectures for platform supply vessels

2018 ◽  
Vol 8 (2) ◽  
pp. 152-165 ◽  
Author(s):  
Srinivasarao Kamala ◽  
Priyesh J. Chauhan ◽  
Sanjib K. Panda ◽  
Gary Wilson ◽  
Xiong Liu ◽  
...  
Keyword(s):  
Propulsion System ◽  
System Architectures ◽  
Electrical Propulsion

scholarly journals X-57 Power and Command System Design

2017 ◽  
Author(s):  
Sean Clarke ◽  
Matthew Redifer ◽  
Kurt Papathakis ◽  
Aamod Samuel ◽  
Trevor Foster
Keyword(s):  
Power Distribution ◽  
Electric Propulsion ◽  
High Speed ◽  
New Technologies ◽  
Propulsion System ◽  
General Aviation ◽  
Efficiency Gain ◽  
Critical Systems ◽  
Electric Power Distribution ◽  
Entire Vehicle

This paper describes the power and command system architecture of the X‑57 Maxwell flight demonstrator aircraft. The X-57 is an experimental aircraft designed to demonstrate radically improved aircraft efficiency with a 3.5 times aero-propulsive efficiency gain at a “high‑speed cruise” flight condition for comparable general aviation aircraft. These gains are enabled by integrating the design of a new, optimized wing and a new electric propulsion system. As a result, the X‑57 vehicle takes advantage of the new capabilities afforded by electric motors as primary propulsors. Integrating new technologies into critical systems in experimental aircraft poses unique challenges that require careful design considerations across the entire vehicle system, such as qualification of new propulsors (motors, in the case of the X-57 aircraft), compatibility of existing systems with a new electric power distribution bus, and instrumentation and monitoring of newly qualified propulsion system devices.

scholarly journals Development of a Lumped Parameter Model for an Aeronautic Hybrid Electric Propulsion System

Aerospace ◽  
2018 ◽  
Vol 5 (4) ◽  
pp. 105 ◽  
Author(s):  
Emma Frosina ◽  
Adolfo Senatore ◽  
Luka Palumbo ◽  
Giuseppe Di Lorenzo ◽  
Ciro Pascarella
Keyword(s):  
Electric Propulsion ◽  
Combustion Engine ◽  
Propulsion System ◽  
General Aviation ◽  
Lumped Parameter Model ◽  
Engine Exhaust ◽  
Electric Propulsion System ◽  
Lumped Parameter ◽  
Hybrid Electric ◽  
The University

This paper describes a case study for applying a hybrid electric propulsion system for general aviation aircraft. The work was performed by a joint team from the Centro Italiano Ricerche Aerospaziali (CIRA) and the Department of Industrial Engineering of the University of Naples Federico II. The use of electric and hybrid electric propulsion for aircraft has gained widespread and significant attention over the past decade. The driver of industry interest has principally been the need to reduce the emissions of combustion engine exhaust products and noise; however, studies have revealed the potential for overall improvement in the energy efficiency and mission flexibility of new aircraft types. The goal of the present study was to demonstrate the feasibility of aeronautic parallel hybrid electric propulsion for light aircraft, varying mission profiles and electric configurations. Through the creation and application of a global model with AMESim® software, in which every aspect of the components chosen by the industrial partners can be represented, some interesting studies were carried out. The numerical model used was more complete and more accurate compared to some others available in the literature. In particular, it was confirmed that, for particular missions, integrating state-of-the-art technologies provides notable advantages for aircraft hybrid electric propulsion for light aircraft.

Emission comparison of turbofan and open rotor engines under special consideration of aircraft and mission design aspects

2011 ◽  
Vol 115 (1168) ◽  
pp. 351-360 ◽  
Author(s):  
A. Seitz ◽  
D. Schmitt ◽  
S. Donnerhack
Keyword(s):  
Aircraft Design ◽  
Propulsion System ◽  
Mission Design ◽  
Design Parameters ◽  
Emission Characteristics ◽  
Direct Drive ◽  
Noise Emission ◽  
System Architectures ◽  
Design Attributes ◽  
Open Rotor

Abstract An integrated parametric model involving the design of propulsion system, airframe and flight mission is presented. Based hereon, the carbon dioxide (CO2) emission characteristics of advanced direct-drive turbofan and open rotor powered aircraft are analysed against pertinent aircraft and propulsion system design parameters. In addition, initial concept-specific trend statements on nitrogen oxides (NOx) as well as propulsor noise emission characteristics are derived. The obtained results contribute to a better understanding of more appropriate aircraft design attributes for advanced system architectures.

Bayesian Belief Network for Robust Engine Design and Architecture Selection

2014 ◽  
Author(s):  
Brian K. Kestner ◽  
Christopher A. Perullo ◽  
Jonathan S. Sands ◽  
Dimitri N. Mavris
Keyword(s):  
Design Process ◽  
New Technologies ◽  
Bayesian Belief Network ◽  
Propulsion System ◽  
System Architectures ◽  
Belief Network ◽  
The Core ◽  
Future Performance ◽  
Performance Requirements ◽  
Engine Design

Designing propulsion system architectures to meet next generation requirements requires many tradeoffs be made. These trades are often between performance, risk, and cost. For example, the core of an engine is the most expensive and highest risk area of a propulsion system design. However, a new core design provides the greatest flexibility in meeting future performance requirements. The decision to upgrade or redesign the core must be justified by comparison with other lower risk options. Furthermore, for turboshaft applications, the choice of compressor, whether axial or centrifugal, is a major decision and trade with the choice being heavily driven by both current and projected weight and performance requirements. This problem is confounded by uncertainty in potential benefits of technologies or future performance of components. To address these issues this research proposes the use of a Bayesian belief network (BBN) to extend the more traditional robust engine design process. This is done by leveraging forward and backward inference to identify engine upgrade paths that are robust to uncertainty in requirements performance. Prior beliefs on the different scenarios and technology uncertainty can be used to quantify risk. Forward inference can be used to compare different scenarios. The problem will be demonstrated using a two-spool turboshaft architecture modeled using the Numerical Propulsion System Simulation (NPSS) program. Upgrade options will include off the shelf, derivative engine (fixed core) with no technologies, derivative engine with new technologies, a new engine with no technologies, and a new engine with new technologies. The robust design process with a BBN will be used to identify which engine cycle and upgrade scenario is needed to meet performance requirements while minimizing cost and risk. To demonstrate how the choice of upgrade and cycle change with changes in requirements, studies are performed at different horsepower, ESFC, and power density requirements.

Sign in / Sign up

Export Citation Format

Share Document