Integrated Design Tools for RF Antennas for Helicon Plasma Thrusters

2014 ◽  
Author(s):  
Fabio Trezzolani ◽  
Antonio Selmo ◽  
Davide Melazzi ◽  
Vito Lancellotti ◽  
Marco Manente ◽  
...  
Keyword(s):  
Integrated Design ◽  
Design Tools ◽  
Helicon Plasma ◽  
Rf Antennas ◽  
Plasma Thrusters

scholarly journals AN INTEGRATED DESIGN METHODOLOGY

2011 ◽  
Author(s):  
T. Freiheit ◽  
S. S. Park ◽  
V Giuliani
Keyword(s):  
Design Methodology ◽  
Integrated Design ◽  
Cost Effective ◽  
Global Markets ◽  
Design Tools ◽  
Regulatory Requirements ◽  
Life Cycle Design ◽  
Design Requirements ◽  
Stakeholder Needs ◽  
Integrated Design Methodology

Global markets demand quick product develop-ment that is simultaneously cost-effective and meets stakeholder needs. Many tools and design methodolo-gies have been developed that address individual as-pects of the design problem, such as Axiomatic De-sign, Design for Manufacture, Life Cycle Design, etc. However, competitive viability can be put at risk when a product fails to achieve all customer, business, manufacturing, and regulatory requirements. To de-liver all design requirements, an efficient integrated design methodology is required. This paper proposes a design approach which integrates previously devel-oped design tools to economically achieve essential design objectives, within a framework that facilitates a rapid design process.

Non-Linear Aeromechanical Behaviour of Axial Core Compressor Stator Vanes

2007 ◽  
Author(s):  
Caetano Peng
Keyword(s):  
Integrated Design ◽  
Engine Performance ◽  
Forced Response ◽  
Design Tools ◽  
Virtual Testing ◽  
Aero Engine ◽  
Stator Vane ◽  
Recent Developments ◽  
Aero Engines ◽  
Engine Components

This paper highlights some engine non-linearities that can affect both performance and robustness of aero engines. It pays particular attention to non-linearities generated at the stator vane contact end joints. These non-linearities resulting from friction contact joints affect the vane modeshapes, damping and forced response. This work proposes upper and lower bound solutions based on vane end restraints non-linearities to predict conservative forced response of stator vanes. Some non-linearities such as those caused by mistuning can be beneficial to the component and system. There are also non-linearities that can be detrimental to engine performance, robustness and reliability. Moreover, it proposes and discusses the concept of temporal HCF or CCF lifing method. Recent developments in FE, CFD, mistuning, forced response and probabilistic codes can help to create more integrated design tools that incorporate time-dependent non-linearities in the lifing of aero engine components. Computations performed here demonstrated some level of component virtual testing. These analyses are important component virtual testing that will be gradually extended to whole aero engine virtual testing.

scholarly journals High-Density Helicon Plasma Thrusters Using Electrodeless Acceleration Schemes

2016 ◽  
Vol 14 (ists30) ◽  
pp. Pb_117-Pb_121 ◽  
Author(s):  
Daisuke KUWAHARA ◽  
Shunjiro SHINOHARA ◽  
Takamichi ISHII ◽  
Shuhei OTSUKA ◽  
Toshiki NAKAGAWA ◽  
...  
Keyword(s):  
High Density ◽  
Helicon Plasma ◽  
Plasma Thrusters

scholarly journals Global Modeling of N2O Discharges: Helicon Plasma Thruster Application

2013 ◽  
Vol 2013 ◽  
pp. 1-9 ◽  
Author(s):  
Konstantinos Katsonis ◽  
Chloe Berenguer
Keyword(s):  
Electron Temperature ◽  
Electric Propulsion ◽  
Global Modeling ◽  
Helicon Plasma ◽  
Plasma Thruster ◽  
Plasma Thrusters ◽  
Averaged Model

A global (volume averaged) model pertaining to N2O discharges is used to design and to study electric propulsion applications, especially helicon plasma thrusters fed with pure N2O and also with N2/O2mixtures including air. Results obtained for N2O feeding are discussed and compared to those pertaining to an air-like N2/O2mixture feeding. An interesting similarity is observed. Comparison of the N2O model results versus those of Ar shows lower ionization percentage with higher electron temperature for N2O propellant.

Integrated Design Toolbox for Tripod-Based Parallel Kinematic Machines

2006 ◽  
Vol 129 (8) ◽  
pp. 799-807 ◽  
Author(s):  
Z. M. Bi ◽  
S. Y. T. Lang ◽  
D. Zhang ◽  
P. E. Orban ◽  
M. Verner
Keyword(s):  
Computer Aided Design ◽  
Integrated Design ◽  
Design System ◽  
Forward Kinematics ◽  
Design Tools ◽  
Parallel Kinematic Machines ◽  
Actual Application ◽  
On Line ◽  
Parallel Kinematic ◽  
Aided Design

This paper presents a concept and implementation of a toolbox for design and application of tripod-based parallel kinematic machines (PKMs). The toolbox is a suite of design tools to support users from conceptual design to actual application of tripod-based PKMs. These design tools have been individually developed in different languages and development environments, and are integrated seamlessly using a JAVA-based platform. Users can access all the design tools through a friendly graphical user interface (GUI). It is the first computer-aided design system specially developed for tripod-based PKMs. The toolbox includes some innovative methodologies, such as a forward kinematics solver, the concept of joint workspace, on-line monitoring based on forward kinematics, and the concept of motion purity. The paper gives an overview on the toolbox architecture and some key technologies.

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