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A Cost Effective Design for a Propeller Thrust/Torque Balance

机译:螺旋桨推力/扭矩平衡的经济高效设计

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摘要

Wind tunnel balances are used with aircraft models, propellers, and components to measure applied forces and moments. The design and manufacture of a balance is often for a specific test, test article and conditions. This paper discusses the theory, design, calibration, and testing of a new small propeller balance for use in a low-speed wind tunnel. The new balance is named the ODU15X15.;Theory discussed herein covers how the two measurement components, thrust and torque, affect the balance design. These loads generate strains which are in turn read by strain gages arranged in Wheatstone bridges. The design follows well known practices established at NASA Langley for single-piece balances.;Design considerations include constraints on geometry shape/size, thermal compensation, vibration inputs, balance sensitivity requirements, and safety. Analysis of the balance is performed using solid computer aided design models and iterative finite element analysis. Goals for this design were to create a cost effective balance, made using only conventional machining, made out of a single billet or section of tubing, and to create a balance capable of measuring loads more accurately then those commercially available for the relatively low loads predicted. The ODU15X15 is designed to read 15 lbs thrust and 15 in-lbs torque.;Calibration, including theory, set-up, design, and procedures, follows the principles of Design of Experiments. A LabView code is used to record voltage outputs from Wheatstone bridges with known loads applied to the balance. Fixtures are used to apply the static thrust and torque loads. Calibration of the balance resulted in less than +/-0.1% full-scale error at a ninety five percent confidence level. Confirmation points provided additional assurance of model adequacy.;Wind tunnel trials were performed with a Scorpion SII-4020-420kv motor, and a 3 blade 16 X 8 Master Airscrew propeller at conditions representative of previous testing with NASA GL-10 propeller candidates. While further testing is needed, results indicate that the balance performance was superior to the commercial load cell.
机译:风洞天平与飞机模型,螺旋桨和部件一起使用,以测量施加的力和力矩。天平的设计和制造通常用于特定的测试,测试物品和条件。本文讨论了用于低速风洞的新型小型螺旋桨天平的理论,设计,校准和测试。新的天平称为ODU15X15。本文讨论的理论涵盖了两个测量分量(推力和扭矩)如何影响天平的设计。这些载荷产生的应变又由布置在惠斯通电桥中的应变计读取。该设计遵循NASA Langley建立的单件天平的众所周知的惯例。设计注意事项包括几何形状/尺寸,热补偿,振动输入,天平灵敏度要求和安全性的限制。使用可靠的计算机辅助设计模型和迭代有限元分析来进行平衡分析。此设计的目标是创建一种成本有效的天平,该天平仅由常规加工制成,由单个钢坯或一段管材制成,并创建一种能够比预期的相对低负载的负载更准确地测量负载的天平。 ODU15X15旨在读取15磅推力和15英寸磅扭矩。校准(包括理论,设置,设计和程序)遵循实验设计的原理。 LabView代码用于记录惠斯通电桥的电压输出,并在天平上施加已知负载。夹具用于施加静态推力和扭矩负载。天平的校准在95%的置信度水平下导致满量程误差小于+/- 0.1%。确认点为模型的适当性提供了额外的保证。风洞试验是使用Scorpion SII-4020-420kv电动机和3叶片16 X 8主螺旋桨进行的,条件是先前使用NASA GL-10螺旋桨进行了测试。尽管需要进一步测试,但结果表明,天平性能优于商用称重传感器。

著录项

  • 作者

    Sadowski, Nicholas Barrett.;

  • 作者单位

    Old Dominion University.;

  • 授予单位 Old Dominion University.;
  • 学科 Mechanical engineering.;Aerospace engineering.;Engineering.
  • 学位 M.S.
  • 年度 2018
  • 页码 149 p.
  • 总页数 149
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 古生物学;
  • 关键词

  • 入库时间 2022-08-17 11:52:56

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