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首页> 外文期刊>The Aeronautical Journal >Dispersion reduction of artillery rockets guided by flight path steering method
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Dispersion reduction of artillery rockets guided by flight path steering method

机译：飞行路径转向法制导火炮火箭的色散降低

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摘要

Artillery rockets are sensitive to disturbances (total impulse variation, wind, thrust misalignment, etc.). As the range of ground-to-ground rockets increases, the accuracy of free flight rockets decreases. Requirements for the increase of the range and minimisation of the impact point dispersions can be solved by adding guidance and control systems to rockets. Based on the differences between the measured flight parameters and the calculated parameters for the nominal trajectory, the flight path angle correction algorithm is obtained by adding the correction to the nominal value. The flight path steering guidance system with lateral acceleration autopilot in the inner loop, is used for the guidance of hypothetical artillery rockets. The guidance algorithm given in this paper eliminates the time correction due to rocket velocity variations. Efficiency of the proposed algorithm is illustrated by numerical simulation. There is no practical influence of the external disturbances on impact point dispersion. It is also shown that the measurement errors of the inertial measurement unit are the dominant factor affecting impact point dispersion of artillery rockets modified by adding a guidance system based on the flight path steering method.
机译：火炮火箭对干扰（总脉冲变化，风，推力未对准等）敏感。随着地对地火箭射程的增加，自由飞行火箭的准确性下降。可以通过向火箭增加制导和控制系统来解决增加射程和最小化冲击点散布的要求。根据测得的飞行参数与计算出的标称轨迹参数之间的差异，通过将校正值添加到标称值来获得飞行路径角度校正算法。内环带有横向加速度自动驾驶仪的飞行路径转向制导系统，用于制导假设的火炮火箭。本文给出的制导算法消除了由于火箭速度变化引起的时间校正。数值仿真表明了该算法的有效性。外部干扰对冲击点分散没有实际影响。研究还表明，惯性测量单元的测量误差是影响火炮火箭冲击点分散的主要因素，该因素是通过添加基于飞行路径转向方法的制导系统而修改的。

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