噪声与振动控制

噪声与振动控制 ›› 2013, Vol. 33 ›› Issue (5): 53-57.DOI: 10.3969/j.issn.1006-1335.2013.05.012

• 3.运载工具振动与噪声 • 上一篇    下一篇

低雷诺数下微型四旋翼飞行器气动和振动特性分析

齐书浩，刘素娟，张文明，肖心想   

  1. （ 上海交通大学  机械系统与振动国家重点实验室,  上海  200240 ）
  • 收稿日期:2013-01-17 修回日期:2013-02-04 出版日期:2013-10-18 发布日期:2013-10-15
  • 通讯作者: 齐书浩
  • 基金资助:

    国家自然科学基金;上海市青年科技启明星计划

Analysis of Aerodynamic and Vibration Characteristics of a Micro Quad-rotor Helicopter with Low Reynolds Number

  • Received:2013-01-17 Revised:2013-02-04 Online:2013-10-18 Published:2013-10-15
  • Supported by:

    Project supported by the National Natural Science Foundation of China

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摘要：

基于有限元方法研究低雷诺数下微型四旋翼飞行器的气动特性和振动特性。建立微型四旋翼飞行器悬飞时的三维流场物理模型，给出边界条件，采用有限体积法对多个边界条件进行数值计算和分析，研究微型四旋翼飞行器在悬飞过程中的流场分布，揭示微型四旋翼飞行器的气动特性变化规律；此外，将气动载荷加载到结构分析模块，研究机身应力分布情况和流固耦合特性，得到机身最大应力所在位置及其振动特性。

关键词: 振动与波, 四旋翼飞行器, 低雷诺数, 流固耦合, N-S方程, 模态分析, 振动与波, 高速飞行器, 振动噪声控制, 动力响应, 环境预示

Abstract:

Abstract: Aerodynamic characteristics and vibration characteristics of a micro quad-rotor aircraft were studied based on finite element method. A three dimensional physical model of the fluid fields was established. By adding boundary conditions, the fluid fields were analyzed numerically using the finite volume method and the aerodynamic characteristics were obtained. Then the aerodynamic force was loaded to the aircraft structure to get the stress distribution and find out where the maximum stress is. At last, the first six vibration modes and their vibration characteristics were obtained after the modal analysis of the micro quad-rotor aircraft.

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