Laminarization of airfoils offers substantial potential for improving aerodynamic performance and represents a key area of research in the optimization of modern commercial aircraft. However, a persistent challenge is contamination of the wing’s leading edge, which induces turbulence wedges preventing maintained laminar flow. The raised bull-nose Krueger Flap provides a viable solution to this by shielding the leading edge and thus protecting the wing from contamination. It has been identified, that the Krueger Flap is subjected to aerodynamic suction forces in certain flight conditions, which cause inadvertent movement of the flap, due to the compliance of the kinematics. A potential solution to this issue is pretensioning the kinematics, to counteract the aerodynamic forces. For the purpose of developing a first design of the pretension control architecture, a simulative assessment of a suitable control architecture is presented. This is done using a co-simulation framework, consisting of an FMI coupling between MATLAB Simulink and MSC Adams. The sub-model part in Simulink/Simscape presents the actuation system, serving as simulation master. It contains customized modelling elements in Simscape representing the physical behaviour. Two multibody systems implemented in Adams function as simulation slaves and are included as separate FMUs. The first FMU captures a fully flexible representation of the kinematics and Krueger Flap. The second contains a geared rotary actuator equipped with flexible spur gears and contact simulation between the intermeshing teeth, allowing compliance and backlash effects to be represented. This method of analysing the actuation system of slats at the wing’s leading edge has already been used and was adapted in the present work. The aim of the virtual testing environment is to compare different control strategies and evaluate a final control architecture. Furthermore, selected failure conditions are simulated, for evaluation of the control architecture in a degraded system state.