基于模糊逻辑的飞机结构应力预测技术

Research of Aircraft Structural Stress Prediction Based on Fuzzy Logic

利用模糊逻辑建模参数不受限制,不要求对多变量参数进行非线性近似假设的优点,通过分析飞行试验数据,选取了适合的建模参数并利用模糊逻辑原理建立了飞机对称机动时机翼根部结构应力预测模型。通过与飞行试验结果进行对比,预测结果与实测结果一致性较好,能反映出对称机动时飞机机翼根部结构的应力水平变化趋势。在进行风险科目试飞时可以有效预测飞机在极限过载飞行时的结构应力水平,为降低试飞风险,采取必要的处置措施提供支持。

Fuzzy logic modeling parameters is not restricted, does not require the parameters of nonlinear multivariable approximate assumption, the advantages of through the analysis of flight test data, the selection of the suitable modeling parameters and established the plane symmetric motor using fuzzy logic principles when wing root structure stress prediction model. By comparing with the flight test results, the predicted results with the measured results are in good consistency and reflects the aircraft wing root structure of the stress level of motor with trends. When making risk subject test can effectively predict the structure of the stress level when the plane fly in the overload limit, the test to reduce the risk and take necessary measure to provide support.