Collaborative Aircraft Design Methodology using ADAS Linked to CEASIOM

Zhang, Mengmeng; Rizzi, Arthur; Nicolosi, Fabrizio; Marco, Agostino De

doi:10.2514/6.2014-2012

Cited by 16 publications

(7 citation statements)

References 19 publications

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“…Zhang et al (2014) showed a thrust effect on lift and pitching moment through CFD Eulerian simulation on a new commuter aircraft, highlighting the lift and longitudinal stability increment.…”

Section: Introductionmentioning

confidence: 92%

Commuter aircraft aerodynamic characteristics through wind tunnel tests

Nicolosi

Corcione

Vecchia

2016

Aircraft Eng & Aerospace Tech

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Purpose-This paper aims to deal with the experimental estimation of both longitudinal-and lateral-directional aerodynamic characteristics of a new twin-engine, 11-seat commuter aircraft. Design/methodology/approach-Wind tunnel tests have been conducted on a 1:8.75 scaled model. A modular model (fuselage, wing, nacelle, winglet and tail planes) has been built to analyze both complete aircraft aerodynamic characteristics and mutual effects among components. The model has been also equipped with trailing edge flaps, elevator and rudder control surfaces. Findings-Longitudinal tests have shown the goodness of the aircraft design in terms of aircraft stability, control and trim capabilities at typical clean, take-off and landing conditions. The effects of fuselage, nacelles and winglets on lift, pitching moment and drag coefficients have been investigated. Lateral-directional stability and control characteristics of the complete aircraft and several aircraft component combinations have been tested to estimate the aircraft components' interactions. Research limitations/implications-The experimental tests have been performed at a Reynolds number of about 0.6e6, whereas the free-flight Reynolds number range should be between 4.5e6 and 9.5e6. Thus, all the measured data suffer from the Reynolds number scaling effect. Practical implications-The study provides useful aerodynamic database for P2012 Traveller commuter aircraft. Originality/value-The paper deals with the experimental investigation of a new general aviation 11-seat commuter aircraft being brought to market by Tecnam Aircraft Industries and it brings some material on applied industrial design in the open literature

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Section: Introductionmentioning

confidence: 92%

Commuter aircraft aerodynamic characteristics through wind tunnel tests

Nicolosi

Corcione

Vecchia

2016

Aircraft Eng & Aerospace Tech

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“…Extensive use of this environment has been made and a broad list of publications are available demonstrating the capability of the environment. [28][29][30][31][32][33][34][35] Desktop Aeronautics developed the program for aircraft synthesis studies (PASS). 36 It is suited for conventional subsonic layouts, but is also capable of analyzing supersonic business jets or oblique wings.…”

Section: Introductionmentioning

confidence: 99%

The GENUS aircraft conceptual design environment

Smith

Sziroczák

Abbe

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The design of aircraft has evolved over time from the classical design approach to the more modern computer based design method utilising multivariate design optimisation. In recent years aircraft concepts and configurations have become more diverse and complex thus pushing many synthesis packages beyond their capability. Furthermore, many examples of aircraft design software focus on the analysis of one particular concept thus requiring separate packages for each concept. This can lead to complications in comparing concepts and configurations as differences in performance may originate from different prediction toolsets being used. This paper presents the GENUS Aircraft Design Framework developed by Cranfield University's Aircraft Design Group to address these issues. The paper reviews available aircraft design methodologies and describes the challenges faced in their development and application. Following this, the GENUS aircraft design environment is introduced, along with the theoretical background and practical reasoning behind the program architecture. Particular attention is given to the programming, choice of methodology and optimization techniques involved. Subsequently, some applications of the developed methodology, implemented in the framework are presented to illustrate the diversity of the approach. Three special classes of aircraft design concept are presented briefly.

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“…A remarkable example is the ADAS software developed at University of Naples (Nicolosi and Paduano, 2011) mainly for teaching purposes. Another interesting example of software developed in academia is given by the CEASIOM framework which has been also used in combination with the ADAS software (Zhang et al, 2014).…”

Section: Introductionmentioning

confidence: 99%

Java framework for parametric aircraft design – ground performance

Trifari

Ruocco

Cusati

et al. 2017

AEAT

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Purpose This paper aims to introduce the take-off and landing performance analysis modules of the software library named Java toolchain of Programs for Aircraft Design (JPAD), dedicated to the aircraft preliminary design. An overview of JPAD is also presented. Design/methodology/approach The calculation of the take-off and landing distances has been implemented using a simulation-based approach. This expects to solve an appropriate set of ordinary differential equations, which describes the aircraft equations of motion during all the take-off and landing phases. Tests upon two aircraft models (ATR72 and B747-100B) have been performed to compare the obtained output with the performance data retrieved from the related flight manuals. Findings The tool developed has proven to be very reliable and versatile, as it performs the calculation of the required performance with almost no computational effort and with a good accuracy, providing a less than the 5 per cent difference with respect to the statistical trend and a difference from the flight manual or public brochure data around 10 per cent. Originality/value The use of a simulation-based approach to have a more accurate estimation of the ground performance with respect to classic semi-empirical equations. Although performing the simulation of the aircraft motion, the approach shown is very time-saving and can be easily implemented in an optimization cycle.

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Collaborative Aircraft Design Methodology using ADAS Linked to CEASIOM

Cited by 16 publications

References 19 publications

Commuter aircraft aerodynamic characteristics through wind tunnel tests

Commuter aircraft aerodynamic characteristics through wind tunnel tests

The GENUS aircraft conceptual design environment

Java framework for parametric aircraft design – ground performance

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