The objective of the project is is to develop scale models for the Synthetic Jet Actuator (SJA), that shall be used to enable the design of next generation SJA’s, compared to state of the art. The development of this scale model is intented for improvement of performance predictions, and modelling accuracy of SJA actuators, for future applications. A demonstration rationale is therefore targeted, in order to enable accurate theoretical performance estimations, for given actuator configurations, calculated from geometrical input parameters, and transducer elements parameters. In order to achieve such an objective, the project activities will focus first on analyses and tests of existing SJA’s designs, provided by the topic manager, in order to derive accurate numerical models, and achieve lessons learings, before designing, manufacturing, and testing of a third scale model.

The project FloCoS will focus on an integrated flow control actuator driving system taking into account the specific requirements of piezoelectrically driven Synthetic Jet Actuators. The system will be divided into two different main parts: The amplifier unit on the one hand and the control part on the other hand. For making measurement values available which will be used for closed-loop control of the actuator, a dedicated measurement circuit will be developed and optimized for this specific application. A highly integrated and miniaturized electronic module for fluidic AFC actuators will be the output of this project. FloCoS will not only provide smart power amplifier solutions, but also efficient solutions. State-of-the-art power recovery technologies will be used to minimize the needed power for driving the piezoelectric elements. For the addressed application scenarios, e.g. the test of actuators in large scale wind tunnel test studies, there are special requirements for remote access and control for the system. For the test of the actuators as well as the aerodynamic concepts, the actuators have to be driven in WT/T environment, where control computers and power supply connectors may be far away from the point of action. FloCoS will provide remote access to all system parameters with an advanced monitoring and logging functionality. The requested number of actuators suggests that there is a short term plan to test the actuators at a specific region in the wing, e.g. pylon-wing junction or outer wing. The integration aspects for these regions will demand special concepts for miniaturized solutions. The system itself will be encapsulated to comply with all harsh environmental requirements which are applied to the system in relevant environmental conditions. The conformity of the system with the electromagnetic compatibility requirements will be demonstrated by testing.

Design and development of a long The objective of the AUDACITY project is to make the demonstration of a compact powerful and reliable piezoelectric actuator for future locking applications in landing gear systems. Audacity is required to get rid of the well-established hydraulic actuators in order to comply with System ITD Strategic Objectives in terms of environmental impact and More Electric Aircraft (MAE). One American and one Japanese company have shown the relevance of the piezoelectric technology to be used in landing gear systems. Their demonstration are today without equivalent in Europe. Whereas the principle of long stroke piezoelectric actuator is not new, technical challenges occur. The consortium of AUDACITY has come to the conclusion that every technical limitations one by one during the 20 past years. The technical objective is then to integrate all these individual progresses within a prototype for TRL4 demonstration AUDACITY aims at impacting the competitiveness of Europe and Associated countries with the direct creation of 20 jobs and 45 Millions of cumulative sales before 2030.