风洞虚拟飞行试验中的飞行控制系统快速原型设计与部署技术

Rapid prototyping and implementation of flight control system for wind tunnel virtual flight test

利用风洞虚拟飞行技术可在风洞中开展飞行器的飞行控制验证与评估研究。飞行控制子系统是虚拟飞行试验技术的核心,采用控制系统快速原型技术,可实现嵌入式实时飞行控制代码自动生成和快速部署,从而大幅降低飞行控制系统集成难度,有效提高风洞虚拟飞行试验效率。本文概述了Φ3.2m风洞虚拟飞行试验系统组成和现状,详细介绍了基于该系统的飞行控制系统快速原型开发平台和部署方法,通过某飞机缩比模型全数字仿真、半实物仿真和风洞虚拟飞行试验,验证了该技术具有良好的通用性和开放性等特点,可以满足不同型号飞行器风洞虚拟飞行试验飞行控制系统集成需求。

Wind tunnel virtualflig h t technique （V F T ） can be used to ve rify and evaluate the flight control system of an a irc raf t. The f l ig h t control subsystem, core of V F T , employs rapid control system prototyping to achieve auto generation and rapid implementation of embedded real-time flight control codes, reduce the d if f ic u lty of f l ig h t control system integ ra t ion,and enhance wind tunnel vir tual f l ight test efficiency. This paper summarizes the systeof arts of 4^3. 2m wind tunnel v ir tu a l f l ig h t system, introduces the rapid prototyping development platform and implementation methods of the f l ig h t control system based on that system.Commonality and openness of the system was verified through fu l l digital sim u lat io n, semi-physical simulation and wind tunnel v ir tu a l f l ig h t tests on a scale aircraft model. This techniquecan fulfill the requirements of control system integration fo r various aircraft wind tunnel virtua lflight tests.