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V. Krishnamurthy, R. Luckner
In preliminary aircraft design, primary and secondary control surfaces are sized by estimating their impact on performance, stability and controllability using heuristic, semi-empirical handbook methods (HBM). Those methods deliver results of low precision. More accurate results are achieved later during the detailed aircraft design process. At that stage, it becomes increasingly difficult and expensive to make significant design changes to control surfaces. Therefore improved evaluation methods for preliminary aircraft design become important. Such methods require a flight mechanical model, i.e. a nonlinear aircraft simulation model with flight control laws, to assess the influence of the control surfaces on handling qualities and performance in the preliminary aircraft design with much higher precision than with currently used methods. For the assessment, a set of criteria is defined. The criteria cover stability and controllability of longitudinal and lateral motion, the flight performance in all low speed flight phases and the determination of reference speeds. The criteria values are computed by various numerical methods including flight simulations that mimic certification flight tests defined in FAR-AC 25-7. This paper describes the method and its application to a typical midrange aircraft, for which two alternative high-lift systems are investigated. The software tool Multiobjective Evaluation of Preliminary Aircraft Designs (MITRA) is described. It allows controlling the aircraft simulation in an automated process and applying the evaluation of the criteria to it. Results from a take-off evaluation are presented to discuss the advantages of the proposed method.
Deutscher Luft- und Raumfahrtkongress 2014, Augsburg
Verlag, Ort:
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2015
Conference Paper
21,0 x 29,7 cm, 9 Seiten
Stichworte zum Inhalt:
Flugsimulation, Neuartige Steuerflächen
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