DESIGN AND ANALYSIS OF RIGID-BODY SHAPE-CHANGE MECHANISM FOR AIRCRAFT WINGS
DOI:
https://doi.org/10.11113/jt.v77.6600Keywords:
Kinematic Synthesis, shape-changing mechanism, geometric constraint programming, aerodynamic performance, coefficient of pressureAbstract
Airframe noise reduction becomes a main interest among researchers who study the performance of aircrafts. The airframe noise can occur between the high-lift systems and main body of the airfoil. The proposed shape-changing airfoil is one of many ideas to reduce airframe noise by eliminating the gap between the main body and high-lift systems. This paper presents a new design of 30P30N airfoil, which converts the three-element airfoil (slat, main body and flap) into two-element airfoil (combination of slat and main body as an element and flap) by installing a shape-changing slat into the systems. This work applies a chain of rigid bodies connected by revolute and prismatic joints that are capable of approximating a shape change defined by a set of morphed slat design profiles. To achieve a single degree of freedom (DOF), a building-block approach is employed to mechanize the fixed-end shape-changing chain with the helped of Geometric Constraint Programming technique as an effective method to develop the mechanism. The conventional and shape-change 30P30N airfoils are compared to study the performances of airfoils with the velocity and angle of attack are constant.References
Hayes, J. A., W. C., 1997, Soderman. P. T., and Bent, P.H., Airframe Noise Characteristics of a 4.7% Scale DC-10 Mode. AIAA Paper. 97-1594.
Konig, D., Koh, S. R., Schroder, W., and Meinke, M., 2009, Slat Noise Identification. AIAA Paper. 2009-3100.
Khorrami, M.R. 2003, Understanding Slat Noise Sources, Colloquium EUROMECH 449, Chamonix, France.
Gaunaa, 2010, Unsteady Two-Dimensional Potential-Flow Model for Thin Variable Geometry Airfoils. Wind Energy. 12: 167-192.
Morrison, J.H., 1998. Numerical Study of Turbulent Model Predictions for the MD 30P/30N and the NHLP-2D Three-Element Highlift Configurations, NASA CR-1998-208967.
Weisshar, T.A. 2006. Morphing Aircraft Technology - New Shapes for Aircraft Design, In Proceedings of the Multifunctional Structures Integration of Sensors and Antennas Meeting. 1.
Abdulrahim, M., Garcia, H., and Lind, R. 2005. Flight Characteristics of Shaping the Membrane Wing of a Micro Air Vehicle. Journal of Aircraft. 42: 131-137.
Kota, S. and Hetrick, J. A. 2008, Adaptive Compliant Wing and Rotor System, U.S. Patent US7. 384, 016B2.
Shamsudin, S. A. 2013. Kinematic Synthesis Of Planar, Shape-Changing Rigid Body Mechanisms for Design Profiles with Significant Differences in Arc Length. University of Dayton, Ohio, United States.
Rumsey, C. L., and Ying, S. X., 2002. Prediction of High Lift: Review of Present CFD Capability. Progress in Aerospace Sciences. 38: 145-180.
Fang, L., 2011. Suppression Of Stall On High-Chamber Flap Using Upper-Surface Flow. Cranfield University, Bedfordshire, United Kingdom, January.
Zhao, K., Schmiedeler, J. P., and Murray, A. P., 2012. Design of Planar, Shape-Changing Rigid-Body Mechanisms for Morphing Aircraft Wings. ASME Journal of Mechanisms and Robotics. 4(4): 041007. 

Kinzel, G. L., and Chang, C., 1984. The Analysis of Planar Linkages Using a Modular Approach, Mech. Mach. Theory. 19(1):165–172. 

Myszka, D. H., Murray, A. P., and Schmiedeler, J. P., 2009. Singularity Analysis of an Extensible Kinematic Architecture: Assur Class N, Order N-1. ASME J. Mech. Rob. 1(1): 011009. 

Neville, A. B., and Sanderson, A. C., 1996. Tetrobot family tree: modular synthesis of kinematic structures for parallel robotics, In Proc. IEEE/RSJ IROS. Osaka, Japan. 

Krishnan, G., Kim, C., and Kota, S., 2011. An Intrinsic Geometric Framework for the Building Block Synthesis of Single Point Compliant Mechanisms. ASME J. Mech. Rob. 3(1): 011001.
Kinzel, E. C., Schmiedeler, J. P., and Pennock, G. R., 2006. Kinematic Synthesis for Finitely Separated Positions Using Geometric Constraint Programming. ASME J. Mech. Des. 128(5): 1070–1079.
Kintscher, M., Wiedemann, M., Monner, H. P., Heintze, O., and Kuhn, T., 2011. Design of a smart leading edge device for low speed wind tunnel tests in the European project SADE. International Journal of Structural. 4(4): 383-405.
Pott-Pollenske, M., Wild, J., Herr, M., Delfs, J., 2014. Slat Noise Reduction by Means of Adaptive Leading Edge Devices, Aircraft Noise Reduction by Flow Control and Active/Adaptive Techniques, Vilnius, Lithuania, Sept. 25-26
Downloads
Published
Issue
Section
License
Copyright of articles that appear in Jurnal Teknologi belongs exclusively to Penerbit Universiti Teknologi Malaysia (Penerbit UTM Press). This copyright covers the rights to reproduce the article, including reprints, electronic reproductions, or any other reproductions of similar nature.
