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论文:2012,Vol:30,Issue(2):181-186 |
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引用本文： |
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朱战霞, 金伟, 韩沛. 一种基于引力场线性化的制导方法[J]. 西北工业大学 |
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Zhu Zhanxia, Jin Wei, Han Pei. A New Guidance Method Using Linearized Gravitational Field[J]. Northwestern polytechnical university |
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| 一种基于引力场线性化的制导方法 |
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| 朱战霞, 金伟, 韩沛 |
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| 西北工业大学 航天学院,陕西 西安 710072 |
| 摘要: |
| 文章针对航天器连续推力轨道机动过程中各种摄动误差的修正问题, 提出了最优补偿系数的引力场线性化闭环制导方法。按照力的性质可将摄动力分为保守摄动力和非保守摄动力。通过对保守摄动力进行简化, 给出了力的线性表达式, 在此基础上基于引力场线性化方法, 将惯性系下航天器受摄运动方程转化为线性形式, 推导出了以摄动引起的位置偏差为反馈量的闭环制导加速度的表达式。之后考虑非保守摄动力(也即大气阻力), 通过引入补偿系数, 并利用遗传算法对补偿系数进行优化, 得到修正的闭环制导加速度表达式。文中所提的制导方法可用于各种空间轨道机动过程中摄动误差的修正, 以交会为例进行了仿真, 结果表明修正后的轨道能够很好地跟踪理想轨道, 且交会精度高。 |
| 关键词:
制导律
引力场线性化
轨道机动
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| A New Guidance Method Using Linearized Gravitational Field |
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| Zhu Zhanxia, Jin Wei, Han Pei |
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| College of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China |
| Abstract: |
| Aiming at correcting various types of perturbation errors induced during the orbital maneuver of a contin-uous thrust spacecraft, we propose a closed-loop guidance method for linearizing its gravitational field with optimalcompensation coefficients. Generally, there are two kinds of perturbation: conservative perturbation and non-con-servative perturbation. Sections 1 and 2 of the full paper explain our method mentioned in the title, which we be-lieve is new. Their core consists of: (1) we simplify the conservative perturbation and give its linear expressions;then we linearize the equations of motion of the perturbed spacecraft in its inertial frame and deduce the expressionsof closed-loop guidance acceleration, which is the feedback of position errors due to perturbation; (2) we take thenon-conservative perturbation, namely atmospheric drag, into consideration and use the genetic algorithm to opti-mize the compensation coefficient k, thus obtaining the modified closed-loop guidance acceleration expressions.Section 3 gives a numerical example of rendezvous; the simulation results, presented in Figs 2 through 8, and theiranalysis show preliminarily that the orbit of the tracking spacecraft, which is modified with our new method, canwell track the ideal orbit of the target spacecraft with good rendezvous accuracy. Our new guidance method can beused for modifying the perturbation errors during various types of orbital maneuver. |
| Key words:
closed loop control systems
drag
equations of motion
errors
feedback
genetic algorithms
gravita-tional effects
linearization
optimization
orbits
parameterization
spacecraft
target tracking;guid-ance law
linearized gravitational field
rendezvous
simulation
analysis
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| 收稿日期: 2011-06-12
修回日期:
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| DOI: |
| 基金项目: 国家自然科学基金(10802064)资助 |
| 通讯作者:
Email： |
| 作者简介: 朱战霞(1973-),女,西北工业大学教授、博士生导师,主要从事飞行器动力学与控制研究。
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| 作者相关文章 |
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| 朱战霞 在本刊中的所有文章 |
| 金伟 在本刊中的所有文章 |
| 韩沛 在本刊中的所有文章 |
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参考文献: |
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[1] Pini Gurfil. Nonlinear Feedback Control of Low-Thrust Orbital Transfer in a Central Gravitational Field. Acta Astronautica, 2007, 60: 631-648
[2] Francesco Topputo, Ashraf H, et al. Analytical Solution of Optimal Feedback Control for Radially Accelerated Orbits. Journal ofGuidance, Control, and Dynamics, 2008, 31(5):1352-1359
[3] 陈伟跃, 荆武兴等. 小推力速度闭环交会制导律设计. 宇航学报, 2009, 30(3):1030-1039Chen Weiyue, Jing Wuxing, et al. Fast Closed-Loop Guidance Law with Finite Thrust Amplitude Jets for Rendezvous. Journalof Astronautics, 2009, 30(3):1030-1039 (in Chinese)
[4] 尚海滨. 近地小推力转移轨道的加权组合制导策略. 航空学报, 2007, 28(6):1419-1428Shang Haibi. Guidance Scheme for Near-Earth Low-Thrust Orbit Transfers Using Blended Locally Optimal Laws. Acta Aeronau-tica et Astronautica Sinica, 2007, 28(6):1419-1428 (in Chinese) |
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