This project belongs to the discipline of structural strength of aviation engineering and the professional direction of aeroelasticity. The study of the flutter characteristics of the wing-engine system taking into account the effect of the engine rotor is one of the key issues in the development of the C919 aircraft. This project relies on the C919 aircraft project and takes the wing-engine system composed of a wing-suspended engine and a wing and the entire aircraft as the research objects. It aims to study the system dynamic characteristics and flutter characteristics analysis methods that take into account the engine rotor effect, analyze the influence of the engine rotor effect on the dynamic characteristics and flutter characteristics of the system under the condition of mutual coupling between the wing structure and the engine, and reveal the mechanism of the influence, thereby making it more scientific. Accurately evaluate the impact of the flutter characteristics of the C919 aircraft and establish corresponding airworthiness verification methods and systems. The main technological innovation contents and innovation points of this project include: 1. On the basis of a thorough understanding of the requirements of the CCAR25 airworthiness clause, a wing flutter airworthiness verification technical system for the C919 aircraft that takes into account the gyroscopic effect of the engine rotor was proposed and established for the first time in China. Airworthiness clause CCAR25.629 clearly requires that aeroelasticity The assessment must include rotational modes associated with rotating devices that generate significant dynamic forces. The C919 aircraft adopts a wing-hung large bypass ratio engine configuration. The gyroscopic moment generated by the rotation of the engine rotor system is a significant dynamic force that affects the flutter characteristics of the aircraft. Based on full investigation and understanding of the requirements of airworthiness clauses, this project aims at the C919 aircraft configuration characteristics, a wing flutter analysis method and test verification method that consider the gyroscopic effect of the engine rotor have been proposed for the first time in China, and a corresponding airworthiness verification technical system has been established. It provides technical guarantee for the aeroelastic airworthiness compliance verification of the C919 aircraft. 2. A flutter design and calculation method for the wing-engine rotor gyroscopic effect of the C919 aircraft is established. The mechanism and laws of the influence of the engine rotor gyroscopic effect on the aircraft flutter characteristics are explained. Combined with the aircraft flutter equations and rotor dynamics equations, the wing flutter equation considering the engine rotor gyroscopic effect is systematically deduced and established. The mechanism of the influence of the engine rotor gyroscopic effect on the aircraft flutter characteristics is explained, and the relevant flutter theoretical and method system is improved. Starting from the model application, a finite element flutter analysis method considering the gyroscopic effect of the engine rotor was further established, and the flutter characteristics of the C919 aircraft taking into account the gyroscopic effect of the engine rotor were analyzed and optimized. 3. For the first time in China, the wind tunnel test of the low-speed flutter model of the C919 aircraft that takes into account the gyroscopic effect of the engine rotor has been completed. The design and wind tunnel test verification technology of the wing-engine rotor effect flutter model of the C919 aircraft has been established. By designing a scaled model simulation device for the gyroscopic effect of the engine rotor, the low-speed flutter wind tunnel test of the wing and entire aircraft of the C919 aircraft that takes into account the gyroscopic effect of the engine rotor has been completed for the first time in China. A wind tunnel test verification technology for wing-engine rotor effect flutter models was established, which verified the calculation and analysis methods and conclusions. The results of this project have been applied to the development of the C919 aircraft. The results of this project are used to analyze, optimize and design and verify the flutter characteristics of the C919 aircraft, which shows that the engine rotor gyro effect has no significant adverse effect on the flutter characteristics of the C919 aircraft. In response to the concerns of airworthiness authorities on related issues, this technology effectively explains the impact of the engine rotor effect on the flutter characteristics of the C919 aircraft, ensures the smooth progress of model certification, and saves the human, financial and time costs of model development, approximately 45 million yuan. Based on the engineering application of technology, this project has formed a series of model technical reports. At the same time, during the research process of this project, 5 related papers were published and 7 patents were applied (5 domestic invention patents were applied and 2 utility model patents were obtained), forming 6 company technical specifications.