论文部分内容阅读
对具有典型乘波体结构的吸气式高超声速飞行器的纵向进行了稳定性相关分析。利用空气动力学相关理论分别得到了飞行器的气动力和推力数据,并进一步计算出弹性模型中的模态和广义力;通过变量代换将纵向刚体-弹性动力学模型转换成非线性动力学系统的标准形式,采用扩展分支分析方法得到了系统的平衡曲线,分析发现系统此时由于重心位于压心之前所有的平衡状态都是静不稳定的。同时,当飞行器处于高空巡航平衡状态时,根据建立的弹性模型发现,由二维机身弹性引起的迎角变化最大不超过0.120 8°,影响很小。
The longitudinal correlation of the aspirated hypersonic vehicle with a typical multipath structure was analyzed. The aerodynamic and thrust data of the aircraft are obtained by using the aerodynamic theory respectively and the modal and generalized forces in the elastic model are further calculated. The longitudinal rigid body-elastic dynamic model is transformed into a nonlinear dynamic system by variable substitution The equilibrium form of the system is obtained by using the extended branch analysis method. It is found that all the equilibrium states of the system are unstable at this moment because the center of gravity is located at the center of pressure. At the same time, when the aircraft is in cruise equilibrium at high altitude, it is found that the change of angle of attack caused by the elasticity of two-dimensional fuselage does not exceed 0.120 8 ° at the maximum with little effect on the established elastic model.