无人机飞控系统半实物仿真测试平台的设计与实现

陆文骏

doi:10.12152/j.issn.1672-2868.2019.03.013

巢湖学院学报 >

2019 , Vol. 21 >Issue 3: 93 - 101

DOI: https://doi.org/10.12152/j.issn.1672-2868.2019.03.013

工程与技术

无人机飞控系统半实物仿真测试平台的设计与实现

陆文骏

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安徽三联学院电子电气工程学院，安徽合肥 230601

陆文骏（1979-），男，上海人，安徽三联学院电子电气工程学院讲师，主要从事电子信息工程技术研究。

收稿日期: 2019-04-10

网络出版日期: 2019-05-25

基金资助

基金项目：安徽三联学院校级科研项目（项目编号：KJZD2018003、KJZD2019002、KJYB2019003）

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Design and Implementation of Hardware-in-the-loop Simulation Test Platform for UAV Flight Control System

LU Wen-jun

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Department of Electronic and Electrical Engineering, Anhui Sanlian University, Hefei Anhui 230601

Received date: 2019-04-10

Online published: 2019-05-25

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摘要

飞行控制系统是无人机系统的综合指挥中心和核心部件，针对飞控系统参数现场测试精度差、效率低的难题，结合飞行姿态角传感器要垂直陀螺的外形结构，采用了半实物仿真技术和一体化自动测试方法，设计了以低成本、高精度的小型化无人机姿态校准台和舵偏角测试仪为主要部件的无人机飞控系统半实物仿真测试平台，采用主控设备代替无人机的地面主控站直接给飞机发遥控指令，通过改变飞机姿态，测量控制信号、反馈信号的电压、舵偏角大小，实现了对飞行控制系统参数的综合性能测试。通过不确定度的分析和对平台的性能指标测试表明：能够满足对角度位置、系统电压参数和舵偏角参数的测试要求。

关键词： 无人机; 飞行控制系统; 飞行姿态校准台; 舵偏角测试仪

本文引用格式

陆文骏 . 无人机飞控系统半实物仿真测试平台的设计与实现[J]. 巢湖学院学报, 2019 , 21(3) : 93 -101 . DOI: 10.12152/j.issn.1672-2868.2019.03.013

Abstract

Flight control system is the integrated command center and core component of UAV system. Aiming at the problem of poor accuracy and low efficiency in field measurement of parameters of flight control system, combined with the configuration of flight attitude angle sensor-vertical gyroscope, hardware-in-the-loop simulation technology and integrated automatic test method are adopted. The hardware-in-the-loop simulation test platform of UAV flight control system is composed of a miniaturized UAV attitude calibration platform with low cost and high precision and test device of controlpiston deflexion angle is designed. The main controller is used instead of the main ground control station of UAV to send remote control instructions directly to the aircraft. By changing the attitude of the aircraft, the voltage of control signal, feedback signal and rudder angle are measured, and the comprehensive performance test of flight control system parameters is realized. The performance test of the platform shows that it can meet the test requirements of angle position, system voltage and controlpiston deflexion angle.

Key words： UAV; flight control system; calibration station of flight attitude; test device of controlpiston deflexion angle

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