Internal systems design for smart fixed wing technologies using knowledge based engineering

Abstract

The growing awareness of our environment demands the aviation industry to produce eco-friendly and more efficient aircrafts. To support this the Clean Sky Joint Technology Initiative (JTI) is developing and improving breakthrough technologies, that will be demonstrated on a flying prototype. The Clean Sky JTI is split up into six technology domains; one of these is the Smart Fixed Wing Aircraft (SFWA). This domain aims to develop and test a new wing design that makes use of passive and active flow and load control technologies. Department of Systems Engineering and Aircraft Design (SEAD) at Delft University of Technology has been asked to develop a simulation framework to support the internal systems design on the Smart Fixed Wing Aircraft. During this thesis work a parametric model and framework has been created for two flow control technologies and their pneumatic supply system. The model is based on Knowledge Based Engineering (KBE) techniques, which aim to increase the productivity of engineers and allow more detailed and fair concepts trade-offs. The two selected ‘smart technologies’ are Hybrid Laminar Flow Control (HLFC) and Fluidic Actuated Flow Control (FAFC). The first extends laminar flow using a combination of Natural Laminar Flow and Boundary Layer Suction. The second delays separation, stalling and buffeting by reenergising the boundary layer using pulsating or synthetic jets. The parametric model creates a 3D representation of various internal system concepts, which is used to evaluate the Internal Aerodynamics, External Aerodynamics (HLFC only), weight and cost. The internal aerodynamic analysis uses handbook relations and has been incorporated into the KBE environment. It has been validated for conceptual design with limited success. External aerodynamics is performed with a link to Xfoil-suc. The cost and weight are currently based on component and (sheet-)material price and weight. The product model created in this thesis work can evaluate multiple concepts of the internal system for both ‘smart technologies’ and thereby allow a more detailed and fair trade-off. Due to the lack of available input specifications, e.g. aircraft-type and external aerodynamic data, a trade-off between the concepts could unfortunately not yet be made.