Trajectory Estimation of the Hayabusa Spacecraft During Atmospheric Disintegration
Trajectory Estimation of the Hayabusa Spacecraft During Atmospheric Disintegration
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DOI：
10.2514/1.a32338
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发表时间：
2012-01
影响因子：
1.6
通讯作者：
Michael A. Shoemaker;J. V. D. Ha;S. Abe;K. Fujita
中科院分区：
文献类型：
--
作者：
Michael A. Shoemaker;J. V. D. Ha;S. Abe;K. Fujita
在2010年6月小行星样本返回任务结束时，Hayabusa航天器被故意以超轨道速度在大气层中摧毁。这项研究使用单站地面再入视频观测来分析航天器的解体情况，并估计80个单独的航天器碎片的轨迹。采用批量初始化的扩展卡尔曼滤波方法估计破片的位置、速度和气动弹道系数。对分手进行了描述，并与飞行前的预测进行了比较。在重返大气层的早期可以看到一个高面积质量比的天体，这与预测的太阳能电池板分离非常吻合。几乎所有碎片在其观察到的轨迹中都具有递减的自由流动压。阻力弹道系数高的碎片更有可能在再入早期被观测到。假定为简单的铝球，弹道系数的估算结果表明，破片的半径和半径都是由弹道系数决定的。
The Hayabusa spacecraft was intentionally destroyed in the atmosphere at superorbital velocity at the conclusion of its asteroid sample return mission in June 2010. This study uses single-station ground-based video observations of the reentry to analyze the breakup of the spacecraft and estimate the trajectory of 80 individual spacecraft fragments. An extended Kalman filter with batch initialization is used to estimate the position, velocity, and aerodynamic ballistic coefficients of the fragments. The breakup is characterized and compared with preflight predictions. A high area-to-mass object is seen early during the reentry, which matches closely with the predicted solar panel separation. Nearly all fragments have decreasing freestream dynamic pressure during their observed trajectories. Fragments with high drag ballistic coefficients are more likely to be observed early in the reentry. Assuming simple aluminum spheres, the estimated ballistic coefficients show that the fragments would have radius and m...