高超声速飞行器非线性动态特性分析  

Nonlinear dynamics analysis of the hypersonic vehicle

作　　者：徐敏[1] 白斌[1] 祝小平[2] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]西北工业大学无人机研究所,陕西西安710072

出　　处：《飞行力学》2014年第5期408-412,417,共6页Flight Dynamics

摘　　要：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。In this paper, the longitudinal characteristics of the hypersonic vehicle with a typical ride wave structure are discussed. Through the aerodynamic theories, the data of the aerodynamic and thrust are calculated respectively. Then the mode shapes and generalized force can be worked out. Then the rigidflexible model is transformed into the standard form of the nonlinear dynamic system. Based on the extended bifurcation method, the system balance curves are got. Because the gravity center is in front of the pressure center, all the trim points are instable. At the same time, the maximum change of AOA caused by the structural flexibility of the fuselage is 0. 120 8° which is very small in cruising flight.

关 键 词：高超声速 扩展分支分析方法 建模 气动计算 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程] V215.3