直升机的非线性模型及配平

Nonlinear numerical model and trimming of helicopter

论述和实现了定常平飞时,单旋翼涵道尾桨直升机的非线性全量飞行动力学数值模型,建立模型时,考虑了直升机各部件特别是旋翼的动力学模型,考虑了诱导速度分布的非均匀性,以一具有水平铰外伸量及约束弹簧的铰接式旋翼等效算例直升机的真实旋翼。研究了直升机在平飞时的配平,提出了一种求解直升机平飞初值问题的数值方法-最速下降法。以某直升机为算例,建模并配平,结果表明,该模型符合直升机运动规律。

In this dissertation, a nonlinear numerical model of flight dynamies is discussed and developed for a single rotorcraft with dueted tail rotor in horizontal flight. To establish the model , all parts of the helicopter especially the rotor is considered, and the non - uniformity distribution of the induced velocity is also considered. In this paper, the real rotor of the case helicopter is substituted by using an articulated rotor of horizontal hinge overhang and constraint spring. The helicopter trimming is also discussed in horizontal flight and the initial value is solved by the numerical value method - Fast Descend Method. In this paper, the ease helicopter is modeled and trimmed, and the result shows that the model is conformed to the movement of the helicopter.