火箭外弹道快速计算与修正方法研究

发布时间：2018-03-13 12:06

本文选题：外弹道　切入点：快速计算　出处：《南京理工大学》2016年硕士论文　论文类型：学位论文

【摘要】：提高多管火箭射击精度是多管火箭研制的重要目标,依据外弹道快速计算进行落点修正是提高多管火箭射击准确度进而提高射击精度的有效途径之一。现在外弹道计算中广泛采用的数值积分方法计算时间长,同时对落点的修正需要多次迭代,难以满足未来战争快速精确打击的需求。本文以某国家973项目为背景,提出了一种火箭外弹道快速计算方法(DTTMM)和基于射角的快速落点修正算法,实现了火箭外弹道快速计算和落点准确修正。本文主要研究内容如下：1)仿真分析了火箭弹加工误差对其气动力参数的影响,获得了火箭弹在确定马赫数和攻角情况下,各气动力参数随尾翼斜置角、弹头尺寸误差的变化规律。同时仿真分析了火箭弹有无加工误差的情况下,气动力参数随马赫数变化的情况,揭示了其随速度变化的规律。2)建立了火箭外弹道快速计算的离散时间传递矩阵法,实现了对122mm火箭弹外弹道的快速计算,计算有效性得到了实际射击结果的验证。与相同条件下传统数值计算方法对比,本文方法提高计算速度25%。3)仿真分析了火箭弹加工误差对射击密集度的影响。结果表明现有加工水平下,火箭弹加工误差对纵向密集度有较小影响,对横向密集度的影响基本可以忽略。4)在不同射角情况下,定量分析了起始扰动、加工误差、风等各个因素对火箭弹射击精度的影响。仿真结果表明起始扰动已经成为影响射击精度的最主要因素,在小射角下,这一情况尤为明显。5)提出了一种基于射角的落点修正算法。通过对单位射角修正量的合理改变,可实现不同射角下的快速准确修正。利用此修正算法,对具体三组不同射角、不同误差情况的落点进行了修正,达到预期效果。
[Abstract]:To improve the firing accuracy of multi-barrel rocket is an important goal in the research and development of multi-tube rocket. It is one of the effective ways to improve the firing accuracy and improve the firing accuracy of multiple rocket fire based on the fast calculation of the outer trajectory. Now the numerical integral method widely used in the calculation of the outer ballistic trajectory has a long time to calculate. At the same time, the correction of the landing point needs many iterations, which is difficult to meet the needs of rapid and accurate attack in future wars. This paper takes 973 projects in a certain country as the background. This paper presents a fast calculation method of rocket exterior trajectory (DTTMMM) and a fast point correction algorithm based on the angle of fire. The fast calculation of rocket outer trajectory and the accurate correction of impact point are realized. The main contents of this paper are as follows: 1) the effect of rocket processing error on aerodynamic parameters is simulated and analyzed, and the rocket under the condition of determining Mach number and angle of attack is obtained. The aerodynamic parameters vary with the angle of the tail wing and the warhead size error. At the same time, the variation of the aerodynamic parameters with Mach number is simulated and analyzed with or without the machining error of the rocket. The discrete time transfer matrix method for fast calculation of rocket outer trajectory is established, and the fast calculation of outer trajectory of 122 mm rocket is realized. The effectiveness of the calculation is verified by the actual firing results, which are compared with the traditional numerical methods under the same conditions. In this paper, the effect of rocket processing error on firing intensity is simulated and analyzed by improving the calculation speed. The results show that the rocket processing error has a small effect on the longitudinal intensity under the existing processing level. The influence on transverse dispersion can be neglected basically. 4) in the case of different firing angles, the initial disturbance and machining error are quantitatively analyzed. The simulation results show that the initial disturbance has become the most important factor affecting the firing accuracy. This case is especially obvious. 5) A drop point correction algorithm based on incident angle is proposed. By reasonable change of unit angle correction quantity, fast and accurate correction can be realized under different incident angles. Using this correction algorithm, three groups of different incident angles can be obtained. The falling point of different error cases was corrected to achieve the expected effect.
【学位授予单位】：南京理工大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V412.1

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