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Development of a proof–of–concept aircraft smart control system

Published online by Cambridge University Press:  03 February 2016

P. Hutapea ,
K. Jacobs ,
M. Harper ,
E. Meyer  and
B. Roth
P. Hutapea
Affiliation:
hutapea@temple.edu
K. Jacobs
Affiliation:
Department of Mechanical Engineering, Temple University, Philadelphia, Pennsylvania, USA
M. Harper
Affiliation:
Department of Mechanical Engineering, Temple University, Philadelphia, Pennsylvania, USA
E. Meyer
Affiliation:
Department of Mechanical Engineering, Temple University, Philadelphia, Pennsylvania, USA
B. Roth
Affiliation:
Department of Mechanical Engineering, Temple University, Philadelphia, Pennsylvania, USA
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Abstract

Hutapea et al showed that an actuation system based on shape memory alloy coils could be employed for a wing flap of an aircraft. A continued research and development of these previously demonstrated smart flight control mechanisms was performed with the goal to develop a proof-of-concept shape memory alloy (SMA) actuation system, which utilises SMA springs to control the six degrees of freedom of an aircraft. For this actuation system, the springs are heated via an electric current, causing the spring to contract as the metal’s phase changes from martensite to austenite. The contraction allows the springs to function as linear actuators for the aircraft’s control surfaces, specifically the flaps and ailerons on the wings and horizontal stabilisers and a rudder on the tail. As a significant advancement to the overall actuation system, an air burst-cooling system increases the cooling rate of the coils by means of forced convection. Computer-based finite element model analysis and experimental testing were used to define and optimise SMA spring specifications for each individual control surface design. A onesixth scale proof-of-concept model of a Piper PA-28 Cherokee 160 aircraft was constructed to demonstrate and to verify the final actuation system design.

Type
Technical Note
Information
The Aeronautical Journal , Volume 113 , Issue 1147 , September 2009 , pp. 587 - 590
Copyright
Copyright © Royal Aeronautical Society 2009 

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