旋翼涡流理论的诱导速度场在无铰旋翼直升机操稳研究中的应用

 本文给出了无铰旋翼直升机稳定性与操纵性计算方法。考虑并研究了旋翼诱导速度的一阶谐波分布和桨叶的一、二阶挥舞弯曲模态的影响。特别是详细地描述了王适存广义涡流理论导出的诱导速度场在无铰旋翼直升机操稳研究中的应用。采用了μ_x,μ_y,μ_z推导方法和数值求导法。最后以Bo-105直升机为算例,计算结果与有关试飞数据符合较好。

APPLICATION OF ROTOR INDUCED VELOCITY FIELD OF THE VORTEX THEORY TO THE STUDY OF STABILITY AND CONTROLLABILITY OF HELICOPTER WITH HINGELESS ROTOR

With the aim of developing a new rotor system, a method is presented for calculation of stability and controllability of helicopter with hingeless rotor. The effects of nonuniformity of rotor induced velocity distribution and blade flapping elasticity are taken into account and investigated in detail.It is the first time that the first harmonic term of rotor induced velocity distribution derived from the generalized vortex theory of rotor is employed and a close form of equation for the induced velocity and circulation is established. Finally, analytic formulae suitable to engineering application are given, which consider the effects of motion parameter, control parameter, blade flapping elasticity and so on. Also, the effect of the second flapping mode on stability and controllability of helicopter with hingeless rotor is discussed in an all-round way. The calculations show that only the first flapping bending mode should be taken into account in stability and controllability calculation of helicopter with hinge-less rotor in the range of μ<0.3.Finally, a typical helicopter Bo-105 is taken as a numerical example, and it is found that the results are in good agreement with its flight-teet data.