High aspect ratio aircraft have a significantly reduced induced drag, but have only limited installation space for control surfaces near the wingtip. This paper describes a multidisciplinary design methodology for a morphing aileron that is based on pressure-actuated cellular structures (PACS). The focus of this work is on the transient dynamic system behavior of the multi-functional aileron. Decisive design aspects are the actuation speed, the resistance against external loads, and constraints preparing for a future wind tunnel test. The structural stiffness under varying aerodynamic loads is examined while using a reduced-order truss model and a high-fidelity finite element analysis. The simulations of the internal flow investigate the transient pressurization process that limits the dynamic actuator response. The authors present a reduced-order model based on the Pseudo Bond Graph methodology enabling time-efficient flow simulation and compare the results to computational fluid dynamic simulations. The findings of this work demonstrate high structural resistance against external forces and the feasibility of high actuation speeds over the entire operating envelope. Future research will incorporate the fluid–structure interaction and the assessment of load alleviation capability.
By using CFD modelling on jet engine test cells, it is possible to get a detailed understanding of the internal flow conditions and aerodynamic interactions between the test facility and an installed jet engine. This knowledge is essential to predict the integration of new engine types into existing enclosed jet engine test beds as well as to support test cell trend monitoring. The present paper provides a summary of the CFD modelling of a real jet engine test bed at MTU Maintenance. A full scale 3D CFD model is generated, which combines all test bed components, such as inlet, test cell, augmenter, and exhaust tower. Within the model, all installations were taken into account, which affect the test cell mass flow and/or the local velocity and pressure field around the engine. Exemplary simulations are carried out with a civil turbofan engine of medium thrust range at different operating conditions from flight idle to maximum take-off thrust. A comparison of simulation results and measured pass-off test data suggests a strong correlation and hereby a high fidelity of the presented CFD model. This valid replication of the test bed characteristics opens up various application cases for the model resulting in an improvement of safety and efficiency in jet engine testing.
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