CAJ | 학술논문

通过多体动力学方法建立了倾转旋翼机动力学分析模型.结合动力入流,研究了直升机模式下倾转旋翼机非线性非定常气弹耦合动力学特性.集成了非定常动态入流方程与倾转过渡状态的多体动力学方程,建立了倾转旋翼机时域非定常气弹耦合分析模型.以半展长弹性机翼全铰接式倾转旋翼机模型为例,在直升机模式下分析了桨叶摆振刚度及飞行速度对倾转旋翼机气弹稳定性的影响.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.
통과다체동역학방법건립료경전선익궤동역학분석모형.결합동력입류,연구료직승궤모식하경전선익궤비선성비정상기탄우합동역학특성.집성료비정상동태입류방정여경전과도상태적다체동역학방정,건립료경전선익궤시역비정상기탄우합분석모형.이반전장탄성궤익전교접식경전선익궤모형위례,재직승궤모식하분석료장협파진강도급비행속도대경전선익궤기탄은정성적영향.수치계산표명:건립적다체동역학모형능구쾌속분석직승궤모식하경전선익궤복잡적선익/궤익기탄우합동역학특성.
The multi-body analysis of the aeroelastic stability of the tiltrotor aircraft is presented. Multi-body dynamic differential equations are combined with the equations of the unsteady dynamic inflow model to establish the complete unsteadily aeroelastic coupling analytical model of the tiltrotor. The stability of the tiltrotor in the helicopter mode is analyzed aiming at a semi-span soft-inplane tiltrotor model with an elastic wing. Parametric effects of the lag stiffness of blades and the flight speed are analyzed. Numerical simulations demonstrate that the multi-body analytical model can analyze the aeroelastic stability of the tiltrotor aircraft in the helicopter mode.