射入段仿真数模与散布分析  

SIMULATION MATHEMATICAL MODEL OF EJECTION TRAJECTORY AND SPREAD ANALYSIS

作　　者：陆毓峰[1] 施志佳 

机构地区：[1]西北工业大学航天工程学院,西安710072

出　　处：《宇航学报》1993年第2期14-22,共9页Journal of Astronautics

摘　　要：本文导出了考虑飞行器质心偏移(质量偏心、质心相对壳体有速度和加速度)、推力线偏斜和水平风等因素的射入段弹道数学仿真模型,并以算例计算分析了上述因素的极限误差对散布的影响。结果表明,与实测飞行试验数据相当吻合,证明该数模是有效的。Numerical simulation is a tool used in the design of a new missile system and in the modification or evaluation of existing systems. Missile simulation allows the engineer to actually try out his design without the expense of building and flying an actual missile. Through simulation with a substantial savings in time and expense a great deal can be learned. A central part of missile simulation is the missile dynamics equations which govern how the missile will react to given forces or moments. These simulations are usually put together with emphasis on a particular aspect of the design such as guidance, controlability, component evaluation etc. These equations can be implemented in a variety of ways and are often the source of confusion due to the differences and simplifications made. This paper deals with this issue by developing several common forms of missile dynamics equations that takes account of influence of various disturbances such as eccentricities of resultant thrust and mass centre, the horizontal constant wind... etc. The equations presented in the paper are suitable for studying ejection trajectory of other vehicle. In the paper spread problem due to above factors is discussed also.

关 键 词：随机扰动 推力偏心 射入段弹道 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]