| 有限推力椭圆轨道近距离拦截方法 |
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| 引用本文： | 周荻,张刚,孙胜. 有限推力椭圆轨道近距离拦截方法[J]. 宇航学报, 2010, 31(7): 1762-1767. DOI: 10.3873/j.issn.1000-1328.2010.07.010 |
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| 作者姓名： | 周荻 张刚 孙胜 |
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| 作者单位： | （哈尔滨工业大学，哈尔滨 150001） |
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| 基金项目： | 国家自然科学基金，新世纪优秀人才资助计划 |
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| 摘 要： | 针对椭圆轨道近距离飞行器确定时间最小能量拦截问题，研究了有限推力一次机动作
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| 关 键 词： | 椭圆轨道 有限推力 相对运动 速度增益制导 |
| 收稿时间： | 2009-07-03 |
A Thurst-Limited Short-Distance Interception Scheme on Elliptical Orbit |
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| ZHOU Di,ZHANG Gang,SUN Sheng. A Thurst-Limited Short-Distance Interception Scheme on Elliptical Orbit[J]. Journal of Astronautics, 2010, 31(7): 1762-1767. DOI: 10.3873/j.issn.1000-1328.2010.07.010 |
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| Authors: | ZHOU Di ZHANG Gang SUN Sheng |
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| Affiliation: | ZHOU Di,ZHANG Gang,SUN Sheng(Department of Control Science and Engineering,Harbin Institute of Technology,Harbin 150001,China) |
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| Abstract: | For the fixed time,min-fuel interception problem on elliptical orbits,a method for solving the ignition time and thrust direction with a thrust-limited maneuver is proposed. Classical two-point boundary value problem requires that the thruster imposes an impulse on an interceptor at initial time,such that the interceptor can reach a desired position at the terminal time. For the min-fuel demand,a method for calculating the optimal ignition time with the impulse-thrust is analyzed; usually that is not the in... |
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| Keywords: | Elliptical orbits Limited thrust Relative motion Velocity gain guidance |
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