应用该方法建立了直升机旋翼自转着陆过程的仿真模型，给出了全量模型和模型调整过程。
The simulation model for landing process of a helicopter with rotator self-rotating is built with the proposed method. The whole model and model tuning method are also given.
直升机旋翼系统动部件飞行载荷测量是全机飞行载荷测量的关键，也是直升机寿命可靠性工作的基础。
Helicopter flight load test of rotor system dynamic components is the key part of flight load test of the whole aircraft, and is also the basis of helicopter life reliability calculations.
深入探讨了单旋翼涵道风扇式无人直升机的动力学原理，结合其全量方程和线性化增量方程，推导出了其钟摆模态的数学表示。
Then the equation of helicopter pendulum is derived from the nonlinear differential equation and linear differential equation, with the principle of helicopter aerodynamics.
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