| 引用本文: | 朱龙根.改进的Barrar型中间轨道——远程弹道飞行器自由飞行段的解析解.[J].国防科技大学学报,1985,(2):61-76.[点击复制] |
| Zhu Longgen.An Improved Barrar-Type Intermediate Orbit—Analytic Solutions for Free Flight Trajectory of Long-range Ballistic Vehicle[J].Journal of National University of Defense Technology,1985,(2):61-76[点击复制] |
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| 改进的Barrar型中间轨道——远程弹道飞行器自由飞行段的解析解 |
| 朱龙根 |
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| 摘要: |
| 本文提出了一种改进了的Barrar型中间轨道，得到了远程弹道飞行器自由飞行段的解析解。利用不同的C值，经过不同的组合，可以求得 Kepler 椭圆轨道解，以及考虑J2或J3 项摄动的不同解。此方法宜于推广使用。几十条模拟弹道的计算结果表明：此方法的计算量较小；考虑 J2项摄动的方法误差(射程和横程)约为10m，考虑J3项摄动时约为10mm。 |
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| 投稿日期：1984-11-20 |
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| An Improved Barrar-Type Intermediate Orbit—Analytic Solutions for Free Flight Trajectory of Long-range Ballistic Vehicle |
| Zhu Longgen |
| Abstract: |
| An improved Barrar-type intermediate orbit is proposed in this paper and an analytic solution is reached. When the special C values are applied by means of different combinations，we can obtain the analytic solution due to the J2 or J3 oblateness perturbation for the long-range ballistic vehicle，as well as the solution of Kepler's ellipse. This method is worth to popularize，it's application to dozens of simulative trajectories have shown that this method not only helps to simplify the whole process of calculations but also results in smaller truncation error. the range error and lateral error for the J2 perturbation are approximately 10m while those for the J3 are about 10mm. |
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