摘要：基于JSBSim建立了飞机的气动模型、起落架模型及全机飞行力学模型,对不同重心位置、不同重量模型进行配平分析,给出了民用飞机设计重心包线的计算方法。以B737飞机为例对不同飞行状态进行了配平计算,证明了该方法的合理性。最后,以该机为算例进行了设计重心包线的计算。结果表明,所计算的重心包线与实际情况较吻合。

摘要：研究双拉力螺旋桨复合式高速直升机的气动特性可以为高速直升机的设计及气动优化提供参考。基于动量源方法构建针对双拉力螺旋桨复合式高速直升机旋翼/螺旋桨/机身干扰特性数值计算及分析方法;对孤立旋翼、旋翼/机身干扰进行算例验证;应用所构建的方法对双拉力螺旋桨高速复合式直升机悬停及前飞状态的干扰流场进行数值模拟,分析机身对悬停流场影响及不同前飞速度旋翼/螺旋桨/机身干扰特性。结果表明:悬停时机身对气流的阻塞作用降低了旋翼的升力,螺旋桨对旋翼下洗气流的加速作用使旋翼升力提高;低速前飞时旋翼/螺旋桨/机身干扰较大,主要体现在旋翼下洗流造成螺旋桨滑流偏折以及机翼上表面压力分布增大,高速前飞时这种干扰较小。

摘要：Shaftless ducted rotor(SDR)is a new type of ducted rotor system designed with ducted-rotor-motor integration,which is quite different from traditional ducted rotor(DR)in aerodynamic *** sliding mesh based on unstructured grid is used to simulate the aerodynamic characteristics of SDR and ***,the effects of five key parameters,namely,the rotor disk height,the number of blades,the spread angle of the duct,the central hole radius and the ducted lip radius on the aerodynamic characteristics of the SDR are *** is found that the same-sized SDR produces a larger total lift than the DR in hovering,but the lift proportion of its duct is *** the forward flight,a large low-speed region is generated behind the SDR duct,and the reflux vortex in blade root above the advancing blade has the trend for inward *** rotor disk height has similar effects on SDR and *** the number of blades can effectively increase the total lift of SDR,which also increases the lift proportion of *** the spread angle of the duct will lead to the rotor lift coefficient decrease,reducing the central hole radius can increase the total lift,but the component lift coefficient *** increasing the ducted lip radius can increase the total lift,which begins to decrease after reaching a certain value.