Airplane airfoil structure load identification method based on multi-source data fusion

• Main Authors: LU SONGSONG, BAO RUI, SHI YINGJIE, LIU BINCHAO
• Format: Patent
• Language: Chinese; English
• Published: 04.06.2024
• Subjects: CALCULATING; COMPUTER SYSTEMS BASED ON SPECIFIC COMPUTATIONAL MODELS; COMPUTING; COUNTING; ELECTRIC DIGITAL DATA PROCESSING; PHYSICS

The invention relates to the technical field of aircraft flight load identification, and provides a multi-source data fusion aircraft airfoil surface structure load identification method, which comprises the following steps of: establishing a multi-source data set which comprises a wing typical working condition data set, a finite element data set, a calibration working condition data set and a calibration test data set; a plurality of multi-level fusion neural networks are constructed, the multi-level fusion neural networks comprise a first network and a second network, and the first network is obtained through training based on the finite element data set; training based on the calibration experiment data set and the predicted value of the first network to obtain a second network; optimizing the plurality of multi-level fusion neural networks to obtain an aircraft airfoil structure load identification prediction model; applying the aircraft airfoil structure load identification model to load identification;