低速风洞模型自由飞试验飞行控制系统相似准则及模拟方法研究

Similarity criteria and simulation method for flight control system of free-flight test in low speed wind tunnel

低速风洞模型自由飞试验技术具有试验成本低、风险低、试验条件可控、试验数据精度高等优点,是支撑新型飞行器研制和新技术验证的重要试验技术。飞行控制系统作为风洞模型自由飞试验平台的核心系统,与原型机的系统相似是保证试验结果反映原型机稳定与控制特性的关键。从试验相似准则出发,针对飞行控制系统的相似要求进行分析和仿真,研究了其需要满足的相似关系及其模拟方法,分析了飞行控制律相似性转换的方法、系统采样频率的确定以及飞控系统部件动态特性对飞机响应的影响等问题,最后开展了试验验证,验证了飞行控制系统实现以及试验结果应用于原型机飞行稳定与控制响应特性预测的可行性,为低速风洞模型自由飞试验技术的发展与完善提供依据,为其工程化应用奠定基础。

With the advantages of low cost, reducing r is k , configurable test condit ions, andaccurate test data,low speed wind tunnel free- f light test technique has become an important method to support the development of aircraft w ith radical configuration and new technology. As the core-system of the wind tunnel free- f light test p la t fo rm ,the f l ig h t control system shouldsatisfy simi larity criteria to ensure that the test results represent the s ta b i l ity and control characteristics of prototype a irc ra f t. Based on the s im i la r ity c r ite r ia , the s im i la r ity requirements and simulation methods of the f l ig ht control system were analyzed. We discussed the problems of similarity conversion of the f l ig h t control la w,the determination of the system sampling frequency, and the impact of performance of onboard sensors and actuators on aircraft response. A wind tunnel free- f light test has been conducted to ve rify the feasibility of the system implementation and the accuracy of the test results in predicting s ta b i l ity and control characteristics of the prototype a irc ra f t. The research established a foundation fo r theimprovement of the test technique and the promotion of its industrial application.