Abstract
Through the combination of passive and active load alleviation techniques, this paper presents the design, optimization, manufacturing, and update of a flexible composite wind tunnel model. In a first step, starting from the specification of an adequate wing and trailing edge flap geometry, passive, static aeroelastic stiffness optimizations for various objective functions have been performed. The second optimization step comprised a discretization of the continuous stiffness distributions, resulting in manufacturable stacking sequences. In order to determine which of the objective functions investigated in the passive structural optimization most efficiently complemented the projected active control schemes, the condensed modal finite element models were integrated in an aeroelastic model, involving a dedicated gust load alleviation controller. The most promising design was selected for manufacturing. The finite element representation could be updated to conform to the measured eigenfrequencies, based on the dynamic identification of the model. Eventually, a wind tunnel test campaign was conducted in November 2018 and results have been examined in separate reports.
Highlights
The work presented in this paper has been hosted in the DLR (German Aerospace Center) KonTeKst project [1], which focused on the development and analysis of configurations and technologies for emission and noise reduced short range aircraft
Part of the project focused on the development and testing of an actively controlled flexible composite wing that aimed at a validation of active load alleviation techniques
More recent aeroelastic tailoring works which included the manufacturing aspects and constraints were given by Stodieck et al [7,8,9] and Stanford et al [10,11], the latter one presenting an overview of the state-of-the-art
Summary
The work presented in this paper has been hosted in the DLR (German Aerospace Center) KonTeKst project [1], which focused on the development and analysis of configurations and technologies for emission and noise reduced short range aircraft. Gust load alleviation by active means are implemented in many been investigated extensively in the past, for aircraftAeroservoelastic as summarized,applications, for example, in in general,. C-5A aircraft, several control algorithms which command coordinated aileron deflections based on active control to alleviate structural loads during gust encounter is the Lockheed C-5A [19]. Active gust load alleviation has become an integral part acceleration measurements have been evaluated to greatly reduce the wing bending moment during that has allowed for cost savings in terms of fuel and maintenance. This, can begust challenging, especially, because a large number forofa measurements better gust loadoralleviation capability To tackle this problem, control surfaces are available for gust load promising alleviation,control which approaches is generallyas presented in [27]. Through the combination of loads, blending inputs objective isolating and damping aeroelastic modes which dominate the structural and outputs with the objective of isolating and damping aeroelastic modes which dominate thethe blending-based control approaches have been applied, for example, in [29,30,31], where structural loads, approach from [32]is used. blending-based control approaches have been applied, for example, in [29,30,31], where the approach from [32] is used
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