提高变体飞机风洞测力试验精度的方法研究  

Study on improving precision of morphing aircraft wind tunnel force test

作　　者：蒋增龑[1] 刘铁中[1] 何宏伟[1] 

机构地区：[1]中国航空工业空气动力研究院,哈尔滨150001

出　　处：《实验流体力学》2016年第1期102-106,共5页Journal of Experiments in Fluid Mechanics

摘　　要：变体飞机风洞试验主要测量机翼等变形过程对流场的扰动引起的动态气动力、力矩和力矩操纵效率变化。相对于常规测力试验,由于模型的变体运动导致试验数据精度差。本文对纯机械驱动的变体飞机模型的风洞试验精度的主要影响因素进行了分析,从试验方案、数据采集触发方式和数据处理方法等进行了改进。验证试验表明,试验精度大幅提高,升力系数重复性最大误差约为0.00538,阻力系数重复性最大误差约为0.00098,俯仰力矩系数重复性最大误差约为0.00113,动态试验精度达到常规试验水平。Morphing aircraft wind tunnel test is the main experimental technique for studies on aerodynamics and moments of force characteristics during wing morphing. Because of model morphing movement, the force test precision is lower than that of routine wind tunnel test. This paper analyzes the dominating impact factor of purely mechanical morphing aircraft wind tunnel force test and offers improving experiment program and data acquisition and processing methods. The verification test result shows that the modified test methods greatly improve the test precision. The max lift coefficient repeatability error is 0. 00538, the max drag coefficient repeatability error is 0. 00098, the max pitch moment coefficient repeatability error is 0. 00113, the dynamic test precision is the same as that of routine wind tunnel test.

关 键 词：变体飞机 风洞试验 数据处理 动态测力 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]