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为研究飞行器单独栅格舵全尺寸模型气动特性,考核、验证舵控系统操纵性能,在FL-24风洞(1.2m×1.2m)开展了专项试验技术研究。首次在国内高速风洞建立了全尺寸栅格舵高速风洞试验平台,主要内容包括:风洞大载荷侧壁支撑装置设计、高速风洞模型保护装置设计、高灵敏度气动测试天平研制、模型风载条件下变形测试系统设计以及动态气动力测量与数据处理方法等。该项试验技术实现了模型气动与舵控系统以及气动与结构一体化试验验证,为栅格舵尾翼布局飞行器相关专业设计及飞行试验提供了重要试验数据。
In order to study the aerodynamic characteristics of a full-scale model of a single rudder on an aircraft, the steering performance of the rudder control system was evaluated and verified. Special experimental techniques were studied in the FL-24 wind tunnel (1.2m × 1.2m). For the first time, a full-scale grid rudder high-speed wind tunnel test platform was set up in China’s high-speed wind tunnel. The main contents include: design of wind tunnel large-load sidewall support device, design of high-speed wind tunnel model protection device, development of high sensitivity pneumatic test balance, Deformation under load test system design and dynamic aerodynamic measurements and data processing methods. The test technology has realized the model aerodynamic and rudder control system and the aerodynamic and structural integrated test verification, and provided important test data for the professional design and flight test of the rudder tail wing layout aircraft.