| 1. | Mathematical model and formulations of a new tilt - rotor aircraft for aeroelastic stability analysis
新型倾转旋翼机气动弹性稳定性分析模型 |
| 2. | The multi - body analysis of the aeroelastic stability of the tiltrotor aircraft is presented
摘要通过多体动力学方法建立了倾转旋翼机动力学分析模型。 |
| 3. | Model experiment and damping identification for aeroelastic stability of helicopter rotor with elastomeric lag damper
带粘弹减摆器旋翼系统气弹稳定性试验与阻尼识别 |
| 4. | Numerical simulations demonstrate that the multi body analytical model can analyze the aeroelastic stability of the tiltrotor aircraft in the helicopter mode
数值计算表明：建立的多体动力学模型能够快速分析直升机模式下倾转旋翼机复杂的旋翼机翼气弹耦合动力学特性。 |
| 5. | By numerical simulation , the servo system in this paper greatly reduces the aeroelastic stability . the structural flitter added to the system can reduce the coupling effect of servo system and structure mode and increase the flutter velocity
通过数值模拟发现，伺服系统会降低原有气动弹性系统的稳定性，结构陷波器的引入可以减弱伺服系统和结构模态的耦合。 |
