基于分离点信息的火箭残骸落点计算模型

Model for Computing Rocket Wreckage Landing Point Based on information of Separation Point

摘要:

为预测某火箭残骸落点,需建立一套精确度高、快速高效、经济性好的落点计算模型；对残骸弹道特性进行分析后,基于火箭与残骸分离时的位置和速度信息,通过分段拟合的方式建立空气阻力系数与H、V的直接关系,较好的体现残骸在大气中的气动参数；运用动力学原理建立系列方程组,积分得到残骸运动轨迹数据；计算对比了绝对误差和相对误差并与其他类似模型进行了对照,证明该落点计算模型在精度、效率和经济性上处于较为均衡的位置,能够起到辅助发射指挥人员决策的效果。

Abstract:

In order to predict the landing point of the debris of a space vehicle when it is launched at sea, it’s necessary to build a set of impact point calculation model with high accuracy and high efficiency. After analyzing the trajectory characteristics of the wreckage, the direct relationship between the air drag coefficient and the height and velocity is found by means of subsection fitting, which better reflects the movement of the wreckage in the atmosphere based on the position and velocity when the vehicle and the wreckage are separated. A series of equations are established by using the principle of dynamics, and the trajectory of the wreckage is obtained by integration. The absolute error and relative error are calculated and compared with other similar models. It’s proved that this model for landing point is in a balanced position to accuracy, efficiency and economy, and has practical value in a space vehicle launch mission.