CEASIOM

Conceptual Aircraft Design

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Elements of Computational Flight Dynamics for Complete Aircraft

 

This Master degree thesis describes Elements of Computational Flight Dynamics for Complete Aircraft.





Created
Size
2014-11-20 15:49:47
14.32 MB
Design and Analysis of the Control and Stability of a Blended Wing Body Aircraft

 

This Master Thesis describes the use of the CPACS-CEASIOM version for the analysis  of the control and stability of a blended wing body aircraft





Created
Size
2014-09-16 11:55:39
24.24 MB
Development of the CEASIOM Aircraft Design Environment for Novel Aircraft Configurations

 

This Master Thesis describes the development of CEASIOM towards the CPACS format, and the application of the newly developed CEASIOM environment for a Strut Braced Wing Aircraft



Created
Size
2014-09-16 11:52:14
6.23 MB
Design and Analysis of the Control and Stability of a Blended Wing Body Aircraft

 

Future aircraft generations are required to provide higher performance and capacities with minimum cost and environmental impact. This calls for the design of revolutionary unconventional configurations, such as the Blended Wing Body (BWB), a new tailless aircraft which integrates the wing and the fuselage into a single lifting surface. It has been proven in previous works that this concept has an efficient economical performance and is a promising candidate for solving the current air traffic problems, despite its challenging control and stability features. KTH and DLR are investigating new ways to improve the aircraft conceptual design process in a multidisciplinary environment. The CEASIOM1 software for aircraft design is enhanced by implementing CPACS2, as an unified and more versatile software framework. After researching the latest developments in the BWB concept, a BWB aircraft baseline is designed and its aerodynamic behaviour and performance analyzed with a special emphasis on its stability and control features. The allocation and sizing of the control surfaces is then iterated over to find the optimum winglet size for minimum drag and radar detectability conditions. All in all, the satisfactory performance of the BWB concept and the usefulness of new design softwares were confirmed.

1 Computerised Environment for Aircraft Synthesis and Integrated Optimisation Methods
2 Common Parametric Aircraft Configuration Scheme

Some features of the software used during this study will be available in a next release of the CEASIOM package ...





Created
Size
2014-06-24 14:55:40
24.56 MB
Tomasz Grabowski, Flight Dynamic Analysis of an Aircraft within the Conceptual Stage of the Aircraft Design

 

The paper presents the SDSA (Simulation and Dynamic Stability Analyser) module inside the CEASIOM software. The paper was presented at the RRDAE Symposium, October 16-17, 2008, Brno University of Technology, Brno, Czech Republic




Created
Size
2013-11-25 12:57:55
2.22 MB
Aerodynamic analysis of a sustainable-energy sailplane using CEASIOM

 

This master thesis explains in detailed the process followed to make an aerodynamic analysis of the Warsaw University of Technology sailplane, The PW-5 Smyk, using a computerized environment developed as part of the SimSac project: CEASIOM. Throughout the document it is possible to find a step-by-step description on how the geometry should be defined in the CEASIOM’s stand alone module for Vortex Lattice Method solutions, Tornado. Besides, it provides a full description of the grid generation and the criteria used to determine if a mesh could be adequate for the specific purpose. At this point a mesh validation is  carried by comparing aerodynamic predictions with experimental measurements taken during the sailplane’s flight. Moreover, once the domain discretization and  calculation parameters have proven to be effective, a series of flight states are defined in Tornado with the aim of evaluate the airplane aerodynamics during different operating conditions. In fact, those computations were made following a special organization, which is required by SDSA in order to produce graphics as a solution found by the VLM code. At the end of the document the reader will find the presentation of the main plots achieved with CEASIOM and a short discussion on the implications that each of them has on the aircraft’s aerodynamics.




Created
Size
2013-04-08 10:53:52
2.35 MB
Towards a Unifi ed Framework using CPACS for Geometry Management in Aircraft Design

 

A. Rizzi, M. Zhang, B. Nagel, D. Boehnke and P. Saquet, "Towards a Uni fied Framework using CPACS for Geometry Management in Aircraft Design", 50th AIAA Aerospace Sciences Meeting, 9–12 January 2012



Created
Size
2011-12-21 17:03:27
4.9 MB
Application and Development of the CEASIOM-SUMO-EDGE Suite for Rapid AeroData Assessment of Aircraft Flying Qualities

 

MENGMENG ZHANG: "Application and Development of the CEASIOM-SUMO-EDGE Suite for Rapid AeroData Assessment of Aircraft Flying Qualities", Licentiate Thesis, Stockholm, Sweden 2011



Created
Size
2011-08-31 17:02:31
8.46 MB
Coupling Parametric Aircraft Lofting to CFD & CSM Grid Generation for Conceptual Design

 

A. Rizzi, J. Oppelstrup, M. Zhang and M. Tomac: "Coupling Parametric Aircraft Lofting to CFD & CSM Grid Generation for Conceptual Design", 49th AIAA Aerospace Sciences Meeting



Created
Size
2011-02-17 12:28:03
7.77 MB
Multi-Disciplinary Conceptual Aircraft Design using CEASIOM

 

Also available here:

http://www.fzt.haw-hamburg.de/pers/Scholz/ArbeitenAbgegeben.html#Computerprogramme





Created
Size
2011-03-31 14:01:28
7.39 MB