| 1. | Based on the mathematical model developed by the paper , the trim calculations are carried out in the conditions that the example aircraft converts from helicopter to airplane mode in level flight with zero longitudinal acceleration and angular rate
本文依据所建立的样例机纵向动力学模型,假定飞机在给定高度平飞,纵向加速度和角加速度均为零,完成过渡模式下的动力学配平。 |
