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以卫星/激光半主动复合制导迫弹弹道建模为背景,提供制导弹药修正能力分析的一般思路和方法,分析了制导迫弹的制导原理,建立了舵偏角转换关系。在建立弹道模型的基础上,重点分析了制导段最大修正能力,激光导引头最大有效距离的精度需求及影响修正能力的主要因素。仿真研究结果表明,制导迫弹的修正能力均大于全弹道及激光制导段的落点散布范围,能够满足修正需求。同时,舵偏角、起控时间等均对修正能力产生影响。
Based on the background of satellite / laser semi-active composite guidance-oriented projectile trajectory modeling, the general idea and method of guided munition correction capability analysis are provided. The guidance principle of guided projectile is analyzed and the relationship between rudder deflection angle is established. Based on the establishment of the ballistic model, the main correction factors of the guidance section, the accuracy requirements of the maximum effective distance of the laser seeker and the main factors affecting the correction ability are analyzed emphatically. The simulation results show that the corrective capability of the guidance projectile is larger than that of the full ballistic and laser guided segment, which can meet the need of correction. At the same time, the steering angle, starting time and so on have an impact on the ability to amend.