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Development of an adaptive flap/flaperon flight control system with shape memory alloy actuation.

机译:带有形状记忆合金致动的自适应襟翼/襟翼飞行控制系统的开发。

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摘要

This thesis discusses the design, manufacturing and testing of a new kind of adaptive airfoil using Shape Memory Alloy (SMA) actuation. An antagonistic arrangement of SMA wires was used in a Post-Buckled Precompressed (PBP) kind of actuator that was employed in an adaptive flap system. The thesis opens with a short survey on the history of the PBP mechanism and a literature research on different flap systems actuated by adaptive materials. The conceptual design of the SMAPBP actuator and its evolution to the actuator employed in an adaptive aerostructure is discussed in the first chapters. Experiments showed that the SMAPBP actuator could obtain tip rotations up to 65°, which nearly quadrupled the levels achieved by piezoelectric PBP actuators. In the following, former developed theory for piezoelectric PBP actuators was modified to account for the trapezoidal shape of the SMAPBP actuator. The developed theory was then compared to experimental results. A FEM model was also developed and evaluated to prove the PBP concept for this actuator numerically. In the second section of the thesis the author gives a detailed explanation of the design concept and the manufacturing of the airfoil. A NACA0012 airfoil with a chord length of 150mm and a width of 100mm was used to prove the concept of the adaptive flap system. The thesis continues with a description of the test setup, the CFD model assumptions and the results of wind tunnel tests. The developed adaptive airfoil proved its capabilities during the numerical and experimental tests and showed that the employment and actuation of the SMAPBP actuator could more than doubled the lift coefficient of the airfoil. The architecture and employment of a closed loop position feedback system to overcome the nonlinear behavior of the SMA material and the PBP mechanism is also discussed. The thesis closes with an overview over the adaptive airfoil with SMAPBP actuator and gives recommendations for future work in this field.
机译:本文讨论了一种使用形状记忆合金(SMA)致动的新型自适应翼型的设计,制造和测试。 SMA线的对立布置用于后扣式预压缩(PBP)类型的执行器,该执行器用于自适应襟翼系统。本文首先简要回顾了PBP机理的历史,并就适应性材料驱动的不同襟翼系统进行了文献研究。第一章讨论了SMAPBP执行器的概念设计及其向自适应航空结构中使用的执行器的演变。实验表明,SMAPBP执行器可以获得高达65°的刀尖旋转,几乎是压电PBP执行器的三倍。在下文中,对压电PBP致动器的以前开发的理论进行了修改,以解决SMAPBP致动器的梯形形状。然后将发达的理论与实验结果进行比较。还开发并评估了FEM模型,以数字方式证明该执行器的PBP概念。在论文的第二部分,作者对机翼的设计概念和制造进行了详细说明。弦长为150mm且宽度为100mm的NACA0012机翼用于证明自适应襟翼系统的概念。本文继续介绍了测试设置,CFD模型假设以及风洞测试的结果。研制的自适应翼型在数值和实验测试中证明了其功能,并表明SMAPBP执行器的使用和启动可以使翼型的升力系数增加一倍以上。还讨论了用于克服SMA材料的非线性行为和PBP机制的闭环位置反馈系统的体系结构和应用。最后,本文概述了带有SMAPBP执行器的自适应机翼,并为该领域的未来工作提出了建议。

著录项

  • 作者

    Sinn, Thomas.;

  • 作者单位

    University of Kansas.;

  • 授予单位 University of Kansas.;
  • 学科 Engineering Aerospace.
  • 学位 M.S.
  • 年度 2010
  • 页码 144 p.
  • 总页数 144
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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