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Atmospheric Reentry Dispersion Correction Ascent Phase Guidance for a Generic Reentry Vehicle

机译：通用再入飞行器的大气再入弥散校正上升阶段指导

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摘要

Launch vehicle explicit guidance mechanism depends on the estimation of the desired burnout conditions and driving the vehicle to achieve these conditions. The accuracy of the vehicle at the target point depends on how tightly these conditions are achieved and what is the strategy used to define the trajectory. It has been observed in the literature that most of the guidance mechanisms during reentry use vacuum guidance equations that is during reentry the atmospheric effects are not considered. In order to achieve minimum miss distance at the target point the atmospheric effects are to be considered during the guided phase and appropriate corrections should be executed, otherwise depending on the reentry flight path angle and ballistic coefficient the errors can be as high as tens of nautical miles. In this paper, the authors develop a novel approach to these vacuum guided launch vehicle problems. The paper elaborates how to calculate a prior the reentry dispersion during the ascent phase guidance and provide guidance corrections such that the terminal conditions are achieved with higher accuracy.
机译：运载火箭的显式制导机制取决于期望的燃尽条件的估计以及驱动飞行器以实现这些条件。车辆在目标点的精度取决于这些条件的实现程度以及用于定义轨迹的策略是什么。在文献中已经观察到，折返过程中的大多数引导机制都使用真空引导方程，因为折返过程中没有考虑大气效应。为了在目标点上获得最小的失误距离，在制导阶段应考虑大气影响并应进行适当的校正，否则根据再入飞行路径的角度和弹道系数，误差可能高达数十海里。英里。在本文中，作者开发了解决这些真空制导运载火箭问题的新方法。本文阐述了如何在上升阶段引导期间计算先前的折返弥散，并提供引导校正，以便以更高的精度获得最终条件。

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