Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

This paper addresses the problem to define a methodology for the analysis of the performances of different aircraft configurations
in the phase of conceptual design. The proposed approach is based on a numerical optimisation procedure where a scalar
objective function, the take-off weight, is minimized. The optimisation algorithm has obviously important consequences both
from the point of view of the computational times and of the obtained results. For this reason a preliminary discussion is made
where various different methodologies are critically compared. Although the best compromise between different approaches is
probably given by an integration between a genetic algorithm approach and a classical gradient method, in this phase only the
latter procedure has been used to pe$orm the simulations. The methodology takes into account the high number of geometrical
parameters and the flight mechanics requirements involved in the problem. A basic example is described, and the use of the proposed
methodology to investigate the effects of different geometrical and technological parameters is discussed.
Author
Aerodynamic Configurations; Aircraft Configurations; Measure and Integration; Optimization
20000061426 NASA Ames Research Center, Moffett Field, CA USA
Aero-Mechanical Design Methodology for Subsonic Civil Transport High-Lift Systems
vanDam, C. P., California Univ., USA; Shaw, S. G., California Univ., USA; VanderKam, J. C., California Univ., USA; Brodeur,
R. R., California Univ., USA; Rudolph, P. K. C., PKCR, Inc., USA; Kinney, D., NASA Ames Research Center, USA; Aerodynamic
Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment; June 2000, pp. 7-1 - 7-12;
In English; See also 20000061419
Contract(s)/Grant(s): NCC2-5188; NCC2-5255; SNL-A0273; A46374D(LAS); A49736D(SLS); Copyright Waived; Avail:
CASI; A03, Hardcopy
In today’s highly competitive and economically driven commercial aviation market, the trend is to make aircraft systems simpler
and to shorten their design cycle which reduces recurring, non-recurring and operating costs. One such system is the high-lift
system. A methodology has been developed which merges aerodynamic data with kinematic analysis of the trailing-edge flap
mechanism with minimum mechanism definition required. This methodology provides quick and accurate aerodynamic performance
prediction for a given flap deployment mechanism early on in the high-lift system preliminary design stage. Sample analysis
results for four different deployment mechanisms are presented as well as descriptions of the aerodynamic and mechanism
data required for evaluation. Extensions to interactive design capabilities are also discussed.
Author
Procedures; Design Analysis; Subsonic Speed; Operating Costs; Kinematics; Commercial Aircraft; Aerodynamic Characteristics
20000061427 Defence Evaluation Research Agency, Farnborough, UK
Conceptual Design and Optimisation of Modern Combat Aircraft
Crawford, C. A., Defence Evaluation Research Agency, UK; Simm, S. E., Defence Evaluation Research Agency, UK; Aerodynamic
Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment; June 2000, pp. 8-1 - 8-11;
In English; See also 20000061419; Copyright Waived; Avail: CASI; A03, Hardcopy
The design of a combat aircraft is an extremely complex task, due to the large range of design variables available. A fundamental
understanding of the effects of changes to these variables, and to changes in design/performance requirements, is necessary
to achieve a balanced design. At the Defence Evaluation and Research Agency (DERA) this is achieved with the help of conceptual
design and optimisation programs, developed and used extensively over the past 20 years or so. These Multi-Variate Optimisation
(MVO) programs are rapid assessment tools, enabling the effects of variations in design variables and performance requirements,
in terms of overall aircraft sizing and geometric shape. to be quickly demonstrated. The programs are used routinely within the
Air Vehicle Performance Group at DERA to conduct trade-off studies. These include assessments of the benefits of new technologies
(e.g. in the fields of structures, aerodynamics or engines) and the impact of setting various levels of performance requirement.
The results provide information and advice to the military customer, aiding balance of investment decisions and helping with initial
concept definition.
Author
Design Analysis; Aircraft Design; Fighter Aircraft
20000061428 Dassault Aviation, Saint-Cloud, France
Multi-Disciplinary Constraints in Aerodynamic Design
Perrier, P., Dassault Aviation, France; Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary
Environment; June 2000, pp. 10-1 - 10-12; In English; See also 20000061419; Copyright Waived; Avail: CASI; A03, Hardcopy
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