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论文:2012,Vol:30,Issue(1):38-43 |
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引用本文： |
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高怀, 朱战霞. 常值径向推力加速度下航天器轨道运动特性研究[J]. 西北工业大学 |
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Gao Huai, Zhu Zhanxia. Exploring Orbit Motion Characteristics of Spacecraft under Constant Radial Thrust Acceleration[J]. Northwestern polytechnical university |
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| 常值径向推力加速度下航天器轨道运动特性研究 |
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| 高怀, 朱战霞 |
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| 西北工业大学 航天学院,陕西 西安 710072 |
| 摘要: |
| 文章研究了航天器在常值连续径向推力加速度作用下的运动特性。首先,基于非开普勒轨道理论,在惯性坐标系中建立了连续推力作用下航天器的动力学模型,经过推导和分析得了出在常值径向推力加速度下轨道动量矩仍保持常值,但其能量发生变化的结论。同时针对初始轨道是椭圆轨道的一般情况,分析了航天器在连续常值径向推力作用下环绕地球运动的条件,推导给出了求解逃逸点临界加速度的方程组。最后,对椭圆初始轨道和圆初始轨道的情况分别进行了分析和求解,并以仿真曲线的形式给出了不同常值加速度下轨道变化特性以及逃逸点临界加速度随轨道参数变化的特性,为机动轨道设计提供了理论参考。 |
| 关键词:
非开普勒轨道
连续推力
常值径向推力加速度
椭圆轨道
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| Exploring Orbit Motion Characteristics of Spacecraft under Constant Radial Thrust Acceleration |
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| Gao Huai, Zhu Zhanxia |
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| College of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China |
| Abstract: |
| Aim.The introduction of the full paper discusses relevant matters and then proposes the exploration men-tioned in the title,which is explained in sections 1 through 3.Their core consists of: "Firstly,based on non-Kep-lerian orbit theory,we establish the dynamics model of the spacecraft under constant radial thrust in inertial frame.Under the constant radial acceleration,the moment of momentum of the orbit is constant,while the energy of thespacecraft is changed.Then,the conditions for spacecraft orbiting earth under constant radial thrust are analyzed inthe general form of elliptical initial orbits,and the equations for solving critical acceleration are derived."Finally,section 4 studies respectively the two cases of elliptical and circular initial orbits.Simulation curves are presented inFigs.1, 2 and 3 and we analyze these curves with the help of Figs.4, 5 and 6.These simulation curves and their a-nalysis are,in our opinion,useful for the design of maneuver orbits. |
| Key words:
analysis
design
dynamics
equations of motion
iterative methods
models
motion estimation
nu-merical methods
orbits
simulation
spacecraft
constant radial thrust acceleration
continuousthrust
non-Keplerian orbit
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| 收稿日期: 2011-04-18
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: 高怀(1985-),西北工业大学硕士研究生,主要从事航天飞行动力学与控制研究。
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| 作者相关文章 |
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| 高怀 在本刊中的所有文章 |
| 朱战霞 在本刊中的所有文章 |
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参考文献: |
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[1] Tsien H S. Take-Off from Satellite Orbit. Journal of the American Rocket Society, 1953，(7～8): 233～236
[2] Frederick W Boltz. Orbital Motion under Continuous Radial Thrust. J Guidance Engineering Notes, 1991, 667～670
[3] Frederick W Boltz. Orbital Motion under Continuous Tangential Thrust. J Guidance Engineering Notes, 1991, 1503～1507
[4] John E Prussing. Constant Radial Thrust Acceleration Redux. Journal of Guidance，Control，and Dynamics, 1998, 21(3)
[5] 周姜滨. 空间飞行器连续推力机动轨道研究: [博士学位论文]. 西安: 西北工业大学, 2008Zhou Jiangbin. Maneuvering Orbits of Spacecrafts under Continuous Thrust. Ph. D. Thesis. Xi'an: Northwestern Polytechnical U-niversity, 2008 (in Chinese)
[6] Giovanni Mengali. Escape from Elliptic Orbit Using Constant Radial Thrust. Journal of Guidance，Control，and Dynamics，2009, 32(3): 1018～1022 |
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相关文献: |
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1．高怀, 朱战霞, 刘剑.基于遗传算法的连续推力最短时间转移轨道设计[J]. 西北工业大学, 2012,30(2): 187-191 |
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