A study was conducted to investigate the applicability of active-aeroelastic-wing technology to a joined-wing sensorcraft configuration for the purpose of minimization of embedded antenna deformations. The study was performed using a half-span aeroelastic model of a joined-wing sensorcraft design with six control surfaces. These control surfaces were used concurrently to minimize the elastic deformations at structural nodes corresponding to the antenna tip, while trimming the aircraft to a required 1-g level flight, simultaneously satisfying constraints on the allowable hinge moments and maximum control surface deflections. Comparison of antenna displacements for the optimized and baseline cases (using one control surface at a time) demonstrates that the active-aeroelastic-wing concept can be used to significantly reduce the antenna displacements, potentially improving the performance of the embedded antenna system. Aeroelastic displacements from the trim-optimized system are an order-of-magnitude smaller than those of the baseline. These results demonstrate the feasibility of active-aeroelastic-wing technology for the improvement of embedded antenna performance caused by structural deformations.
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Reich et al. (2004) studied this question.
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