| 引用本文: | 姚党鼐,王振国.航天器在轨防碰撞自主规避策略.[J].国防科技大学学报,2012,34(6):100-103,110.[点击复制] |
| YAO Dangnai,WANG Zhenguo.Active collision avoidance maneuver strategy for on-orbit spacecraft[J].Journal of National University of Defense Technology,2012,34(6):100-103,110[点击复制] |
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| 航天器在轨防碰撞自主规避策略 |
| 姚党鼐, 王振国 |
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(国防科技大学 航天与材料工程学院,湖南 长沙 410073)
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| 摘要: |
| 论文提出了航天器与空间目标距离较近时的自主规避策略。分析了航天器与目标的相对运动模型，将相对运动分解为视线瞬时旋转平面内的运动与该平面的转动。对视线瞬时平面内的运动进行了分析，推导了航天器的最佳规避方向。探讨了在三维惯性空间中该方向的确定方法。通过仿真分析，对比了航天器具有不同规避加速度和不同探测距离时，通过机动所得脱靶量的大小，验证了航天器近距离自主规避策略的有效性。 |
| 关键词: 自主规避策略 最佳规避方向 视线瞬时旋转平面 脱靶量 |
| DOI： |
| 投稿日期：2012-06-30 |
| 基金项目:国家部委基金资助项目 |
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| Active collision avoidance maneuver strategy for on-orbit spacecraft |
| YAO Dangnai, WANG Zhenguo |
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(College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha 410073, China)
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| Abstract: |
| The active evasion strategy of spacecraft is discussed when the distance between spacecraft and target is relatively short. Firstly, the relative dynamic model is analyzed. The relative motion can be decomposed into two submotions, viz., the relative motion in the instantaneous rotation of the line of sight (IRPL) and the rotation of this plane. Secondly, the optimum evasion direction of the spacecraft is proposed, through the analysis of the relative motion in IRPL. Thirdly, the determination of this direction in the inertial space is discussed. Finally, the numerical simulation is conducted with different maneuver accelerations and different detective distance of the spacecraft. The effectiveness of the active evasion strategy is demonstrated with the simulation results. |
| Keywords: active evasion strategy optimum evasion direction instantaneous rotation plane of line of sight miss-distance |
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