一种基于螺旋桨部件特性的螺旋桨建模方法

通过缩比法,利用螺旋桨通用部件特性获得期望研究的螺旋桨部件特性,提出了飞行速度不为零条件下的螺旋桨数学模型建模算法,同时,借鉴缩比后螺旋桨部件特性、螺旋桨定桨叶角工作性能曲线以及螺旋桨空气动力学原理,分析了静拉力状态下的螺旋桨功率系数、拉力系数、桨叶角、螺旋桨静态推力进距比阈值以及螺旋桨几何设计参数的相互作用关系,提出了静拉力状态下的螺旋桨数学模型建模算法。所述算法与Gas Turbine Simulation Program (GSP)软件仿真数据进行了数字仿真对比验证。结果表明:所提出的螺旋桨建模算法具有有效性,在前进状态下,螺旋桨拉力相对误差最大不超过6.6059×10-6，需求功率相对误差最大不超过5.5098×10-6，效率相对误差最大不超过6.6955×10-6。 

A modeling method of propeller based on the propeller component characteristic

The studied propeller components characteristic was obtained by use of the general components characteristic of the propeller by scaling method.Under the condition of the none-zone flight speed,the algorithm on the propeller mathematical model was presented.At the same time,by use of the scaled characteristics of propeller,the working performance curve of the fixed blade angle and the aerodynamic principle of propeller,the interaction relationships of propeller power coefficient,force coefficient,blade angle,static thrust advance ratio threshold and the designed geometric parameters of propeller were analyzed,and the algorithm on the propeller mathematical model under the state of the static force was proposed.The simulation data of the above algorithms by digital simulation was verified with the comparison of the simulation data of Gas Turbine Simulation Program (GSP) software.The results show that the proposed algorithm on the propeller model was valid.When the propeller was in the advanced state,the maximum relative error of propeller force was no more than 6.605 9 × 10-6,the maximum relative error of propeller power demanded did not exceed 5.5098× 10-6,the maximum relative error of propeller efficiency was not more than 6.695 5 × 10-6.