摘要
针对高超声速飞行器建立了三自由度动力学模型,研究了高超声速飞行器纵向非对称分离动力学的问题,对高超声速非对称分离流场进行了分析,界定了尾流区边界,分析了气动系数的特点,设定了高超声速飞行器分离时的受力情况,建立了质心运动方程和纵向动力学方程,并进行了验证飞行器和运载火箭分离弹道的仿真计算,得出了符合要求的结果。另外对高超声速飞行器的纵向分离可能遇到的问题进行了分析,为以后高超声速飞行器的分离设计提供了依据。
This paper provides an simulation analysis of stage separation of hypersonic vehicle, three-degrees-of-freedom dynamics equation of hypersonic vechicle designed; hypersonic vechilcle longitudinal separation dynamics and non-axisymmetrical separation flow field analysed; the boundary of tail -flow fixed; the characters of aerodynamic coefficient discussed ; the force confirmed. It＇s constructed of motion equation of center of mass and longitudinal dynamic equation, the simulation of the trajectory of the hypersonic vechicle and the launch vechiale show that there is a good separation event, some possible questions are analysed, which will benefit designing separation of hypersonic vechicle.
出处
《长春理工大学学报（自然科学版）》
2006年第1期118-121,共4页
Journal of Changchun University of Science and Technology(Natural Science Edition)
关键词
高超声速飞行器
三自由度动力学模型
非对称分离
分离动力学
hypersonic vechicle
three-degrees-of-freedom dynamics model
non-axisymmetrical separation
separation dynamics
