|本期目录/Table of Contents|

[1]卿绿军,晁文雄,周创辉,等.无人机燃油系统增压泵性能测试系统设计[J].工业仪表与自动化装置,2025,(05):31-35.[doi:10.19950/j.cnki.CN61-1121/TH.2025.05.006]
　QING Lvjun,CAO Wenxiong,ZHOU Chuanghui,et al.Performance measurement system for centrifugal pump in UAV fuel system[J].Industrial Instrumentation & Automation,2025,(05):31-35.[doi:10.19950/j.cnki.CN61-1121/TH.2025.05.006]
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无人机燃油系统增压泵性能测试系统设计(PDF)

《工业仪表与自动化装置》[ISSN:1000-0682/CN:61-1121/TH]

卷:
期数:
2025年05期
页码:
31-35
栏目:
出版日期:
2025-10-15

文章信息/Info

Title:
Performance measurement system for centrifugal pump in UAV fuel system
文章编号:
1000-0682（2025）05-0031-05
作者:
卿绿军1; 晁文雄1; 周创辉1; 许 睿2
1.西安航空学院 液压技术研究院, 陕西 西安 710077;2. 西安航空学院 机械工程学院, 陕西 西安 710077
Author(s):
QING Lvjun1; CAO Wenxiong1; ZHOU Chuanghui1; XU Rui2
1. School of Automation, Nanjing University of Science and Technology,Jiangsu Nanjing 210094,China;2. Suzhou Konig Electronic Technology Co., Ltd.,Jiangsu Changshu 215562,China
关键词:
无人机; 燃油增压泵; LabVIEW; 性能测试
Keywords:
UAV;  fuel centrifugal pump;  LabVIEW;  measurement
分类号:
TH137
DOI:
10.19950/j.cnki.CN61-1121/TH.2025.05.006
文献标志码:
A
摘要:
针对无人机用高性能增压泵的研制需求，开发了一套无人机燃油系统增压泵性能测试系统。通过分析试验台组成及其工作原理，确定了测试系统的总体方案；以USB-4711多功能数据采集卡为核心，搭建了测试系统的硬件系统；采用LabVIEW软件，开发了基于PID算法的测试系统上位软件；以DCW2-1828离心泵为被测试验件，对所搭建测试系统的功能进行了验证，其结果表明：该测试系统信号采集、信号处理、信号输出、数据显示等功能均能正常工作，其压力控制误差小于2%，验证了测试系统的有效性，为高性能增压泵研制提供实验基础。
Abstract:
To meet the development requirements of high-performance centrifugal pump for UAV fuel system, a performance measurement system for centrifugal pumps is designed. The working principle of the centrifugal pump performance measurement system is first analyzed, leading to the determination of the overall system design. The hardware system is then constructed using the USB-4711 multifunctional data acquisition card as the core component. The performance measurement system for the centrifugal pump is subsequently developed using LabVIEW software, enabling the collection of performance parameters, adjustment of operating conditions, data processing, and the display and storage of data during the testing process. Finally, through the experimental test on the centrifugal pump performance, it is shown the system can meet the performance measurement requirements for centrifugal pumps in UAV fuel systems, and the feasibility of the system is verified. The results show that the signal acquisition, signal processing, signal output, data display and other functions of the testing system can work normally, and the pressure control error is less than 2%, which verifies the effectiveness of the testing system and provides experimental foundation for the development of high-performance centrifugal pump.

参考文献/References:

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备注/Memo

备注/Memo:
收稿日期：2025-05-06基金项目：陕西省自然科学基础研究计划项目2023-JC-YB-407、校级科研基金项目2022KY0206和2024KY0222。第一作者：卿绿军（1987—），男，汉族，四川绵阳，博士，讲师。研究方向为航空机电液测控系统研究。
更新日期/Last Update: 1900-01-01