Influence of two typical kinds of low-level wind shear on ballistic performance of rockets
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摘要:
针对低空风切变风场特点,基于流体力学基本原理,建立微下击暴流和低空急流2种典型低空风切变的工程化模型,以外弹道理论为基础,将风场模型与火箭弹6自由度刚体弹道模型相结合。以某型尾翼火箭弹为例,研究分析了火箭弹在主动段分别受到2种低空风切变影响下的弹道特性变化。仿真结果表明,微下击暴流和低空急流对火箭弹的飞行时间、射程、侧偏、落速及攻角特性均有影响;相比于微下击暴流,低空急流对弹箭弹道特性的影响更为显著;提高风切变风场的强度和尺度,均会增大对火箭弹弹道特性的影响程度,且风场强度是决定风切变对火箭弹弹道特性影响的主要因素。
Abstract:According to the wind field features of low-level wind shear, the engineering models of microburst and low-level jet are established based on the principle of fluid mechanics. The wind field models are combined with the six-degree-of-freedom ballistics model of rockets based on exterior ballistics theory. As an example, a kind of empennage-rocket was studied on its ballistic performance of prior trajectory influenced by these two kinds of wind shear. The simulation results show that both of these two kinds of wind shear have impact on the flight time, range, side-slip, falling velocity and attack angle of the rocket. Compared to the microburst, the low-level jet has a higher effect on the ballistic performance of rocket. Improving the strength and scale of these two kinds of wind shear makes a greater impact on the ballistic performance of rocket, and meanwhile, the strength of wind field is the determining factor for wind shear to affect the ballistic performance of rocket.
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Key words:
- rockets /
- low-level wind shear /
- microburst /
- low-level jet /
- ballistic performance
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表 1 微下击暴流模型参数
Table 1. Model parameters of microburst
参数 数值 涡环中心坐标/m (800, 0, 600) 涡环半径/m 1 000 涡核半径/m 400 中心垂直诱导风速/(m·s-1) -10 表 2 低空急流模型参数
Table 2. Model parameters of low-level jet
参数 数值 地面粗糙度/m 2 基准高度/m 3.5 基准高度风速/(m·s-1) 4 基准高度风向/(°) 0 急流层最大风速/(m·s-1) 10 最大风速处高度/m 180 最大风速处风向/(°) 30 急流层顶高度/m 500 急流层顶风向/(°) 60 风速分布形状参数 0.8 风向分布形状参数 0.3 表 3 火箭弹弹体参数
Table 3. Body parameters of rocket
参数 数值 弹径/m 0.122 弹长/m 2.9 发动机比冲/s 250 发动机工作时间/s 3.0 火箭弹起始质量/kg 70.0 初始赤道转动惯量/(kg·m-2) 40.05 初始极转动惯量/(kg·m-2) 0.147 火箭弹初始质心位置/m 1.533 火药质量燃烧速率/(kg·s-1) 8 表 4 火箭弹发射条件
Table 4. Launching conditions of rocket
参数 数值 初速/(m·s-1) 40 射角/(°) 50 射向/(°) 0 表 5 不同涡环半径下弹道仿真结果
Table 5. Ballistic simulation results with different radii of vortex ring
涡环半径/m 飞行时间/s 射程/m 侧偏/m 落速/(m·s-1) 800 101.0 33 793 -8.6 360 900 100.5 33 708 -8.4 358 1 000 100.2 33 672 -8.2 356 1 100 99.8 33 662 -8.2 355 表 6 不同中心垂直诱导风速下弹道仿真结果
Table 6. Ballistic simulation results with differentcentral vertical induction wind velocities
中心垂直诱导风速/
(m·s-1)飞行
时间/s射程/
m侧偏/
m落速/
(m·s-1)5 103.0 34 102 -8.6 360 10 100.2 33 672 -8.2 356 15 97.4 33 203 -8.1 354 20 94.5 32 724 -8.0 350 表 7 不同急流层最大风速下弹道仿真结果
Table 7. Ballistic simulation results with different maximum wind velocities of low-level jet
最大风速/
(m·s-1)飞行
时间/s射程/
m侧偏/
m落速/
(m·s-1)6 92.8 32 277 -2 612.1 348 10 90.9 31 914 -2 849.9 346 14 89.0 31 535 -3 078.2 344 18 87.2 31 144 -3 293.2 341 表 8 不同急流层顶高度下弹道仿真结果
Table 8. Ballistic simulation results with different height of low-level jet
层顶
高度/m飞行
时间/s射程/
m侧偏/
m落速/
(m·s-1)400 91.7 32 052 -3 005.2 348 500 90.9 31 914 -2 849.9 346 600 90.2 31 807 -2 703.5 345 700 89.7 31 721 -2 572.9 344 -
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