摘要
在方向不变的惯性坐标系建立和求解弹道式火箭的动力学方程,可以不考虑牵连惯性力和科氏惯性力,把惯性制导建立在更简捷明了的基础上。不同于过去书刊常常在随地球一起转动的坐标系中研究飞行力学的各种问题。阐明了火箭离开地球表面起飞的初始条件,详细分析了被地球引力吸住一起转动的空气或大气作用在惯性空间运动着的火箭上的空气动力的处理方法。推导了用惯性坐标系中火箭的运动参数计算地理位置的公式和动坐标系运动参数的公式。
To research into mertial guidance system we set up dynamical equations ofballistic rocket and solve it in the inertial frame (fixed direction). It need not considercentrifugal and coriolis inertial force. It is necessary that original condition are givencorrectly when the rocket take off earth's surface. We have clarified aerodynamic forceof atmosphere to act on the moving rocket in the inertial space and have given computtingmethod of this force. It is known that atmosphere are dragged by earth's gravitationand rotate with earth. We have inferred computting formula of the geographic latitudeand longitude, and the moving parameter in the rotating earth which employ parameterin the fixed frame.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1989年第4期30-38,共9页
Journal of Astronautics
关键词
制导
飞行力学
坐标
惯性制导
Inertial guidance, Coordinate, Flight mechanics, Kinetic equation.
