Morphing wings are of great interest in the aerospace community. Control surfaces with continuously variable geometry can increase the efficiency of aircraft aerodynamics. This research focuses on demonstrating a morphing flap on a small span-wise section of the trailing edge in a wing for a small unmanned air vehicle (UAV). The flaps used flexible matrix composite (FMC) actuators embedded in a flexible structure, rather than hinged control surfaces with conventional actuators. This created a local aerodynamic control force whose effect can be measured using the UAV’s on-board flight control system. After multiple design iterations, in which the FMC actuator material and structure were varied, the final design incorporates a carbon fiber frame with an actuator system embedded in a foam matrix. The FMC control surfaces were successfully demonstrated in flight tests on the eSPAARO unmanned aerial vehicle.

Micro technology supported aerosol processes provide a basis for integrated control of complex processes and therefore a promising research subject. A key aspect in aerosol technology is to control particle deposition, either to avoid clogging or to achieve a well defined coating of surfaces. As a first step we conducted an experimental and theoretical study of the particle deposition in a simple static T-shaped micro mixer. For the experiments monodisperse sodium chloride particles in the particle size range between 10 nm and 700 nm were used. The aerosol was introduced into one branch of the micro reactor and mixed with a particle-free air stream. The predominant particle deposition effect within the mixer is due to impaction, which is induced by the high curvature of stream lines at the inlet and in the mixing zone. Additional CFD calculations confirm the experimental results and show ways of optimizing the inlet geometry of the mixer, which should result in a significant reduction in impaction losses.