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Multistrand, Fast Reaction, Shape Memory Alloy System for Uninhabited Aerial Vehicle Flight Control

DOI: 10.1155/2012/238314

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This paper details an investigation of shape memory alloy (SMA) filaments which are used to drive a flight control system with precision control in a real flight environment. An antagonistic SMA actuator was developed with an integrated demodulator circuit from a JR NES 911 subscale UAV actuator. Most SMA actuator studies concentrate on modeling the open-loop characteristics of such a system with full actuator performance modeling. This paper is a bit different in that it is very practically oriented and centered on development of a flight-capable system which solves the most tricky, practical problems associated with using SMA filaments for aircraft flight control. By using well-tuned feedback loops, it is shown that intermediate SMA performance prediction is not appropriate for flight control system (FCS) design. Rather, capturing the peak behavior is far more important, along with appropriate feedback loop design. To prove the system, an SMA actuator was designed and installed in the fuselage of a 2?m uninhabited aerial vehicle (UAV) and used to control the rudder through slips and coordinated turns. The actuator was capable of 20 degrees of positive and negative deflection and was capable of 7.5 in-oz (5.29?N cm) of torque at a bandwidth of 2.8?Hz. 1. Introduction 1.1. Background Irreversible aircraft flight control is typically achieved by using some form of conventional hydraulic or electromechanical servoactuators. These types of actuators are often quite large, heavy, and use numerous moving parts. For more than 20 years, adaptive structures technologists have worked to reduce weight, volume, and power consumption of these actuators by employing adaptive materials. The earliest inklings of flight control via adaptive aerostructures were seen in the 1980s with experiments on various kinds of twisting and bending plates [1–3]. These early experiments were followed by a slew of innovations directed towards control of rotorcraft via actively twisting structures, flaps, and pitch activation mechanisms [4]. A host of missile and munition applications first came around in the 1990s employing adaptive aerostructures in pitch-, camber-, and twist-active fins, canards, and wings [5–9]. Helicopter rotors were manipulated in their entirety and flown for the first time in 1997 [10]. These adaptive rotors were morphed into the DoD’s first successful Micro Aerial Vehicles with a program starting in 1994. This early effort eventually lead to internal combustion-engine powered, adaptive structures controlled rotorcraft successfully flying off in a DARPA

References

[1]  E. Crawley, K. Lazarus, and D. Warkentin, “Embedded actuation and processing in intelligent materials,” in Proceedings of the 2nd International Workshop on Composite Materials and Structures for Rotorcraft, Troy, NY, USA, September 1989.
[2]  K. Lazarus and E. Crawley, “Multivariable active lifting surface control using strain actuation: analytical and experimental results,” in Proceedings of the 2nd International Conference on Adaptive Structures, ASME, San Diego, Calif, USA, November 1992.
[3]  K. B. Lazarus, E. F. Crawley, and J. D. Bohlmann, “Static aeroelastic control using strain actuated adaptive structures,” in Proceedings of the 1st Joint U.S./Japan Conference on Adaptive Structures, Maui, Hawaii, USA, October 1990.
[4]  R. L. Spangler and S. R. Hall, “Piezoelectric actuators for helicopter rotor control,” in Proceedings of the 31st Structures, Structural Dynamics and Materials Conference, pp. 1589–1599, Long Beach, Calif, USA, April 1990.
[5]  S. M. Ehlers and T. A. Weisshaar, “Static aeroelastic behavior of an adaptive laminated piezoelectric composite wing,” in Proceedings of the 31st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, pp. 1611–1623, April 1990.
[6]  S. M. Ehlers and T. Weisshaar, “Adaptive wing flexural axis control,” in Proceedings of the 2nd International Conference on Adaptive Structures, ASME, San Diego, Calif, USA, November 1992.
[7]  S. M. Ehlers and T. A. Weisshaar, “Effect of material properties on static aeroelastic control,” in Proceedings of the 33rd Structures, Structural Dynamics and Materials Conference, Dallas, Tex, USA, April 1992.
[8]  G. Winchenbach, “Cone aerodynamics test,” Aeroballistic Research Facility Ballistic Spark Range Technical Report, USAF Wright Laboratory Flight Vehicles Branch, WL/MNAV, 1996.
[9]  G. Knowles, R. Barrett, and M. Valentino, “Self-contained high authority control of miniature flight control systems for area dominance,” in Proceedings of the SPIE 11th International Symposium on Smart Structures and Materials, San Diego, Calif, USA, March 2004.
[10]  G. Lee, “Design and testing of the kolibri vertical take-off and landing micro aerial vehicle,” Final Report, Department of Defense CounterDrug Technology Office, 1997.
[11]  C. Burger, Design of a Roll Control System for a Sailplane Using All-Wing Deflections with Adaptive Materials, Auburn University, Birmingham, Ala, USA, 2001.
[12]  “Dynalloy Mechanical Properties,” December 2004, http://www.dynalloy.com/.
[13]  D. St?ckel, in The Martensitic Transformation in Science and Technology, E. Hornbogen and N. Jost, Eds., p. 223, Informationsgesellschaft, 1989.
[14]  D. Padgett, The Design and Construction of a Shape Memory Alloy Tail Boom Actuator, Auburn University, Birmingham, AL, USA, 2002.

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