| 集成于微型飞行器机翼上的流场传感器测量系统研究 | |
| 刘旭东 ; 朱荣 ; 续立军 ; 张福星 ; 刘鹏 ; 周兆英 ; LIU Xudong ; ZHU Rong ; XU Lijun ; ZHANG Fuxing ; LIU Peng ; ZHOU Zhaoying | |
| 2010-07-19 ; 2010-07-19 | |
| 关键词 | 传感器阵列 风洞 风速 迎角 侧滑角 最小二乘法 Sensor array Wind tunnel Air speed Angle of attack Angle of sideslip Least square approach TP274 |
| 其他题名 | Research on Flow Sensor System Integrated with Wing of Micro Air Vehicle |
| 中文摘要 | 阐述了热式流场传感器测量微型飞行器(MAVs)飞行参数的基本原理,介绍了流场传感器阵列在翼表流场测量中的应用。选用薄膜热敏电阻作为流场传感器敏感元件,采用恒温工作方式实现传感系统的测量。通过小型风洞试验,对传感器阵列进行了测试,并运用最小二乘法进行模型辨识。实验结果表明,所采用的流场传感器阵列可实现对风速测量,测量范围为2m/s～12m/s,测量精度为1m/s;对迎角的测量范围为0°～20°,测量精度为1°;对侧滑角的测量范围为-16°～18°,测量精度为1°。基本满足微型飞行器翼表流场的使用需要。; The basic theory of the hot wire/ film anemometer and its application in measuring the flight parameters of MAVs (Micro Air Vehicles) are presented.The thin film resistance is selected as the sensitive element and works in the constant-temperature mode.The model of the sensor is identified by using least square approach,and the data acquired through wind tunnel experiment.The measuring accuracy is estimated to be 1m/s for airflow speed with a range of 2~12 m/s;1 degree for angle of attack with a range of 0~20 degree;and 1 degree for angle of sideslip with a range of-16~18 degree,all of which meet the requirements for applications of the flow field measurements on the wing of MAVs.; 863计划项目资助(2006AA04Z257) |
| 语种 | 中文 ; 中文 |
| 内容类型 | 期刊论文 |
| 源URL | [http://hdl.handle.net/123456789/76330]  |
| 专题 | 清华大学 |
| 推荐引用方式 GB/T 7714 | 刘旭东,朱荣,续立军,等. 集成于微型飞行器机翼上的流场传感器测量系统研究[J],2010, 2010. |
| APA | 刘旭东.,朱荣.,续立军.,张福星.,刘鹏.,...&ZHOU Zhaoying.(2010).集成于微型飞行器机翼上的流场传感器测量系统研究.. |
| MLA | 刘旭东,et al."集成于微型飞行器机翼上的流场传感器测量系统研究".(2010). |
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