倾转旋翼机是目前国内外研究热点，同时也是中国航空发展的重要方向之一。本文围绕 8 吨级倾转旋翼机设计目标开展总体设计，旋翼系统优化设计，整机性能、动力学分析及控制策略研究等。论文进行了 8 吨级倾转旋翼的总体设计，并建立了整机（除旋翼外）气动模型。针对最小化悬停及巡航两种工况下的功率系数这两项优化目标，文章采用了基于代理模型的优化算法对桨叶的气动外形参数进行了多目标优化。相比于对原模型直接进行多目标遗传优化，本文采用的代理优化算法利用较少的样本点得到了优化结果。较优化前，悬停性能及巡航性能分别提升1% 及 5%。并对其进行了悬停、前飞等多种状态下的性能分析及气动载荷分析。在前述得到的气动外形基础上，论文采用 matlab 及 有限元分析程序搭建了基于桨叶部件整体参数建模及三维有限元分析的桨叶快速设计及分析平台。为得到满足动力学设计条件的结构设计方案，论文利用此平台进行数值实验并构建高精度代理模型，对 8 吨级倾转旋翼机的桨叶结构部件进行了参数优化。相比于传统基于剖面特性的桨叶结构设计流程，本文的方法在提高计算精度的同时，不显著增加计算量，且能直接得到结构部件设计方案。此外，对桨叶开展了刚度、强度方面的校核，分析表明本设计满足基本的设计约束条件。论文基于上述设计方案开展了倾转旋翼机在直升机模式、倾转模式及飞机模式下的飞行性能分析，得到了整机关键性能参数。同时对其飞行稳定性及颤振问题进行研究，验证了飞行器在飞行包线内满足稳定性边界条件。最后，论文构建了倾转旋翼机实时仿真模型，对上述不同工作模式下的控制策略进行了研究，对典型飞行过程进行了飞行仿真，验证了控制策略的有效性。

The Research of tiltrotor aircraft is a hot topic, and also one of the important directions of China’s aviation development. This paper focuses on the general design of an 8-ton tiltrotor aircraft, the aerodynamic and structural optimization of rotor system, analysis of the flight performance and flight dynamics, as well as control strategy research.We carry out the general design of the 8-ton tiltrotor, and build the aerodynamic model of the aircraft (except the rotor). Aiming at minimizing the power coefficient under the two flight conditions of hovering and cruising, the article uses an optimization algorithm based on the surrogate model to optimize the shape parameters of the blade. Compared with the direct multi-objective genetic optimization of the original model, the surrogate optimization algorithm used in this paper uses fewer sample to obtain the optimization results. Compared with the original design, the hovering performance and cruise performance are improved by 1% and 5% respectively, and the performance and aerodynamic load under various conditions are caculated.As the profile has been obtained above, we use matlab and FEM procedure to build a rapid blade structural design and analysis platform, based on the parametric modeling of the blade components and 3D finite element analysis. To obtain a structural design that meets the rotor dynamic design criterion, we use this platform to carry out numerical experiments and build a high-precision surrogate model to optimize the structural components of the aircraft. Compared with the traditional blade structure design based on section characteristics analysis, the method in this paper improves the calculation accuracy without significantly increasing the amount of calculation, and can directly obtain the designscheme of structural components. In addition, the stiffness and strength of the blades are checked, and the analysis showes that this design satisfies the basic design constraints.Based on the above design scheme, we carry out the flight performance analysis of the tiltrotor aircraft in helicopter mode, tilt mode and airplane mode. Meanwhile, the flight stability and flutter are studied, and it is verified that the aircraft satisfies the stability boundary conditions in the flight envelope. Finally, we build a real-time simulation model of the tiltrotor aircraft, and the control strategies in the above-mentioned different flight modes are studied. Then we conduct several flight simulations on typical flight processes to verify the effectiveness of the control strategies.