Design of Morphing Leading and Trailing Edge Surfaces for Camber and Twist Control

Design of Morphing Leading and Trailing Edge Surfaces for Camber and Twist Control

Spirlet, G.B.

De Breuker, R. (mentor)

Aerospace Engineering

Flight Propulsion and Performance

Design Integration and Operations of Aircraft and Rotorcraft

2015-06-23

The application of morphing structures in conventional aircraft is a method to improve aircraft performance by both reducing the total fuel consumption for a given mission profile, or by allowing one type of aircraft to perform a wider range of missions. The current generation of aircraft does not widely use morphing technology to optimize flight performance, instead specialized types are developed specifically for one target mission. This report shows the process of integrating a span, twist and camber morphing system into an unmanned testbed as part of the CHANGE project. First several configuration concepts are proposed and evaluated which allow the twist/camber system to be developed independently from the span extension system. This results in a wing design where the leading and trailing edges contain the morphing mechanism, while the central wing box provides space for the span extension mechanism. The application of morphing surfaces is also limited to the inboard wing sections, as the internal volume of the tips is dedicated entirely to housing the extending wing sections. Several options for the morphing mechanisms are discussed and traded off, though eventually a novel system is developed based on open section torsion for twist control and sheet bending for camber control. The magnitude of the deformation required to meet pre-determined target shapes is calculated via numerical simulation, as are the forces which are imparted on the structure and the actuators by elastic loads. Aerodynamic loads are also calculated. Finally, a detail design is proposed for both the leading and trailing edge mechanisms which satisfies the required camber and twist ranges while taking into consideration the maintainability of the structure and availability of parts. The design consists of a GFRP skin of which the top surface acts as a compliant hinge. The lower surface of the skin is supported and constrained by an internal mechanism, while actuation is provided by electric servos. The symmetry of the final design allows for left to right interchangeability of the entire control surface.

morphing
morhping
uav
unmanned
aircraft
twist
camber
flap
aileron
adaptive
high lift device
variable

http://resolver.tudelft.nl/uuid:241ef267-13e7-4e6f-902e-202d0b15b58f

Student theses

master thesis

(c) 2015 Spirlet, G.B.