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为了提高火箭的入轨精度和轨道适应能力,我国在新一代运载火箭末级中采用了迭代制导技术,俯仰、偏航程序角根据火箭运动状态和目标轨道参数实时变化,目前工程设计中仍按照固定程序角方式开展稳定性分析。本文推导出迭代制导程序角与火箭速度、位置之间的线性关系式,在国内首次提出了迭代制导情况下的稳定性分析方法,并以新一代运载火箭为例进行了实例计算,结果表明此分析方法正确、可行,具有一定的参考价值。
In order to improve the rocket’s orbital accuracy and orbit adaptability, an iterative guidance technique is adopted in the final stage of a new generation of launch vehicle. The pitch and yaw program angles change in real time according to the rocket motion state and the target orbital parameters. At present, Fixed angle program to carry out stability analysis. This paper deduces the linear relationship between iterative guidance program angle and rocket velocity and position, and presents the stability analysis method under the condition of iterative guidance for the first time in China, and takes a new generation of launch vehicle as an example to conduct an example calculation. Analysis method is correct and feasible, with a certain reference value.