ABSTRACT
Abstract. This paper presents an adaptive spoiler structure developed by Daimler-Benz Research and Technology within the “Adaptive Wing“ guidance concept, for which Daimler-Benz Aerospace Airbus is responsible. A significant contribution to the variable-geometry wing is a local change in the contour o f the upper wing surface (shock control bump) in order to minimize wave drag due to sonic shock at flight conditions deviating from design point (off-design). Since the intensity o f the sonic shock depends on the flight conditions, the bump has to be adjusted in height. Hence this technology demands an adaptive structure enabling the required contour changes. The integration o f an adaptive system in the wing is difficult because the sonic shock o f a transonic wing designed for shock control occurs within the spoiler region. In case o f the Airbus A340 geometry the optimum crest o f the shock control bump would be significantly higher than the local thickness o f the rear spoiler structure. An example o f a possible design approach to the adaptive structure is presented. This design approach suggests that the shock control bump be achieved by deforming an integral spoiler structure with variable-geometry webs. 1
1 Introduction
Over the past years the Daimler-Benz Research and Technology department has initiated work to explore the benefits o f adaptive structure technologies for use in a broad range o f modem transportation systems in the aerospace, automotive and railway industries.
