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dc.contributor.advisor Inman, Daniel J. en_US
dc.contributor.advisor Robertshaw, Harry H. en_US
dc.contributor.advisor Mason, William H. en_US
dc.contributor.author Johnston, Christopher Owen en_US
dc.date.accessioned 2011-08-06T14:42:32Z
dc.date.available 2011-08-06T14:42:32Z
dc.date.issued 2003-11-14 en_US
dc.identifier.other etd-11232003-133555 en_US
dc.identifier.uri http://hdl.handle.net/10919/9625
dc.description.abstract The research presented in this thesis examines the use of an estimated "actuator work" value as a performance parameter for the comparison of various aerodynamic control device configurations. This estimated "actuator work," or practical work as it will be referred to as in this thesis, is based on the aerodynamic and structural resistance to a control surface deflection. It is meant to represent the actuator energy cost required to deflect a general configuration of conventional or unconventional control surface. Thin airfoil theory is used to predict the aerodynamic load distribution required for this work calculation. The details of applying thin airfoil theory to many different types of control surface arrangements are presented. Convenient equations for the aerodynamic load distributions and aerodynamic coefficients are obtained. Using the developed practical work equations, and considering only the aerodynamic load component, the practical work required for a given change in lift is compared between different control surface arrangements. For single control surface cases, it is found that a quadratic (morphing) trailing edge flap requires less practical work than a linear flap of the same size. As the angle of attack at which the change in lift occurs increases, the benefit of the quadratic flap becomes greater. For multiple control surface cases, it is necessary to determine the set of control deflections that require the minimum practical work for a given change in lift. For small values of the initial angle of attack, it is found that a two-segment quadratic trailing edge flap (MTE) requires more work than a two-segment linear flap (TETAB). But, above a small value of angle of attack, the MTE case becomes superior to the TETAB case. Similar results are found when a 1-DOF static aeroelastic model is included in the calculation. The minimum work control deflections for the aeroelastic cases are shown to be strongly dependent on the dynamic pressure. en_US
dc.format.medium ETD en_US
dc.publisher Virginia Tech en_US
dc.relation.haspart Johnston_Thesis.pdf en_US
dc.rights The authors of the theses and dissertations are the copyright owners. Virginia Tech's Digital Library and Archives has their permission to store and provide access to these works. en_US
dc.source.uri http://scholar.lib.vt.edu/theses/available/etd-11232003-133555 en_US
dc.subject thin airfoil theory en_US
dc.subject morphing aircraft en_US
dc.subject aerodynamics en_US
dc.title Actuator-Work Concepts Applied to Morphing and Conventional Aerodynamic Control Devices en_US
dc.type Thesis en_US
dc.contributor.department Aerospace and Ocean Engineering en_US
dc.description.degree MS en_US

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