| 一种可实现星箭分离前后测轨数据联合定轨的初轨确定方法 |
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| 引用本文： | 茅永兴,马静远,掌静,宋叶志.一种可实现星箭分离前后测轨数据联合定轨的初轨确定方法[J].宇航学报,2014,35(12):1359-1366. |
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| 作者姓名： | 茅永兴 马静远 掌静 宋叶志 |
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| 作者单位： | 1.中国科学院紫金山天文台，南京210008；2.中国卫星海上测控部，江阴214431；3.飞行器海上测量与控制联合实验室，江阴214431;4.中国科学院上海天文台，上海200030 |
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| 摘 要： | 针对弹簧分离方式的卫星发射任务中，在星箭分离瞬间卫星获得弹簧分离力产生的速度增量，使星箭分离前后的两段外测数据不能同时参与定轨的问题，提出了一种可同时求解一个位置矢量和两个速度矢量的定轨新方法——改进的有摄初轨计算的单位矢量法，建立了相应的计算模型，构造了条件方程组的解算方法。仿真计算和任务实测数据验算表明，该方法首次实现了利用星箭分离前后处于两条不同轨道的测轨数据的联合定轨。由于延长了定轨数据弧段，有效地提高了入轨段初轨确定精度。
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| 关 键 词： | 星箭分离 速度增量 联合定轨 |
| 收稿时间： | 2013-09-18 |
An Orbit Determination Method Using Data Before and After Satellite Rocket Separation |
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| MAO Yong xing,MA Jing yuan,ZHANG Jing,SONG Ye zhi.An Orbit Determination Method Using Data Before and After Satellite Rocket Separation[J].Journal of Astronautics,2014,35(12):1359-1366. |
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| Authors: | MAO Yong xing MA Jing yuan ZHANG Jing SONG Ye zhi |
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| Affiliation: | 1. Purple Mountain Observatory, Chinese Academy of Sciences, Nanjing 210008, China;
2. China Satellite Marine Tracking and Control Department, Jiangyin 214431, China;
3. Joint Laboratory of Flight Vehicle Ocean-based Measurement and Control, Jiangyin 214431, China;
4. Shanghai Astronomical Observatory, Chinese Academy of Sciences, Shanghai 200030, China |
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| Abstract: | In a satellite launch task using spring separation mode, the satellite obtains a velocity increment produced from the separating force of spring, data of two segments before and after the epoch of satellite-rocket separation are not in the same orbit, and can’t be used to calculate the orbit together by using traditional method. To solve the problem, a new method, improved method of perturbed initial orbit determination based on Unit Vector Method, is proposed to solve a position vector and two velocity vectors simultaneously in this paper. The results of simulated and measured data show that the method can realize combined orbit determination by using the measured data of two different orbits before and after the satellite-rocket separation. Because the orbit determination data is increased, the accuracy of initial orbit determination in injection phase is also improved. |
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| Keywords: | Satellite-rocket separation Velocity increment Orbit determination |
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