李俊峰
深空探测轨道设计、优化与控制;卫星编队飞行动力学与控制;充液航天器晃动动力学;运动稳定性。
个性化签名
- 姓名:李俊峰
- 目前身份:
- 担任导师情况:
- 学位:
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学术头衔:
博士生导师
- 职称:-
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学科领域:
统计力学
- 研究兴趣:深空探测轨道设计、优化与控制;卫星编队飞行动力学与控制;充液航天器晃动动力学;运动稳定性。
李俊峰,Ph.D,教授,博士生导师,1964年出生于黑龙江。现任航天航空学院副院长、清华大学教授提名委员会委员、力学与航空航天学位分委员会副主席、航天航空学院学术委员会委员。主讲课程有理论力学、运动稳定性等,主编和翻译教材6部。指导的研究生已毕业38名,毕业后出国12名、在航天航空单位工作20名。
教育背景
1983.09~1987.07 在北京大学力学系读本科,获理学学士学位;
1989.09~1989.11 在北京大学力学系读研究生;
1989.11~1993.12 受教育部公派在莫斯科大学数学力学系读研究生,获数学物理Ph.D。
工作履历
1987.07~1989.09 在北京大学力学系任助教、党委委员、团委书记;
1993.12~1995.11 在清华大学工程力学系做博士后;
1995.12~1998.06 在清华大学工程力学系任讲师;
1996.07~1999.11 在清华大学工程力学系任副教授;
1998.10~1999.10 在英国Surrey大学参加研制“航天清华1号”卫星,负责姿态控制系统;
1999.12~2004.05 在清华大学工程力学系任教授,2000年起任博士生导师;2003起任副系主任;
2004.05~至今 在清华大学航天航空学院任教授、系主任,2011年起任副院长。
学术兼职
现任中国空间科学学会常务理事、空间机械委员会副主任,中国宇航学会空间控制委员会副主任,中国力学学会动力学与控制委员会副主任;《宇航学报》常务编委,《力学学报》编委、《Theoretical & Applied Mechanics Letters》编委、 《中国科学:物理学 力学 天文学》(中英文版)编委、《空间科学学报》编委、《空间控制技术与应用》编委、《动力学与控制学报》编委、《力学与实践》编委。
曾任国家自然科学基金委数理学部力学学科评审组成员、《Acta Mechanica Sinica》编委和《工程力学》编委。
研究领域
·深空探测轨道设计、优化与控制
·卫星编队飞行动力学与控制
·充液航天器晃动动力学
·运动稳定性
研究概况
自1996年起,主持国家自然科学基金重点项目、面上项目、863课题、总装预研项目、教育部跨世纪优秀人才基金、教育部优秀青年教师奖励基金、博士点基金、航天创新基金、航天器部门委托项目等,共计30多项。
学术成果
在国内外学术刊物发表论文120多篇,其中被SCI检索60余篇,被EI检索50余篇。
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主页访问
1170
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关注数
0
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成果阅读
226
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成果数
5
【期刊论文】On the stability of dissipative mechanical systems with circulatory forces
李俊峰, Junfeng Li
Z. angew. Math. Phys. 48(1997)161-164,-0001,():
-1年11月30日
The paper investigates the stability of a nonlinear dissipative mechanical system subjected to potential forces, gyroscopic forces, Rayleigh damping and circulatory forces, using direct Liapunov method. Assuming the gyroscopic matrix depends on a parameter, two asymptotically stable theorems are obtained, and the lower bounds of the parameter are evaluated.
Dissipative mechanical system,, circulatory forces,, stability of motion,, Liapunov direct method,, system with gyroscopic terms.,
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38浏览
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【期刊论文】New theorems on stability of mechanical systems with circulatory forces
李俊峰, Junfeng Li, Xiaotian Li, Zhaolin Wang
Z. angew. Math. Phys. 50(1999)839-843,-0001,():
-1年11月30日
The paper investigates the stability of mechanical systems subjected to potential forces, gyroscopic forces, circulatory forces and Rayleigh damping, by means of the Rayleigh quotients. Two stability theorems are obtained. Stability criterions are described by the gyroscopic, circulatory and Rayleigh damping matrices.
Stability of motion,, circulatory forces,, gyroscopic forces.,
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46浏览
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【期刊论文】Stability of nonlinear vibrations of a deploying flexible beam from a spacecraft
李俊峰, Li Junfeng and Wang Zhaolin
Z. angew. Math. Phys. 50(1999)999-1005,-0001,():
-1年11月30日
In this paper, stability of a complex spacecraft is studied by the use of two new models. The rst, is a rigid-flexible model, which consists of a rigid body and a deploying flexible beam; while the second, includes a liquid lled rigid body with a deploying flexible beam. In particular, the deploying beam in both models is assumed to have a nite deflection pro le. It has been proved that nonlinear transverse vibrations of a beam are stable when undergoing uniform extension or retrieval
Spacecraft,, deploying flexible beam,, rigid-flexible coupled system,, partial stability.,
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49浏览
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【期刊论文】STABILITY OF NON-CONSERVATIVE LINEAR GYROSCOPIC SYSTEMS*
李俊峰, Li Junfeng, Wang Zhaolin
Applied Mathematics and Mechanics Published by SU, (English Edition, Vol. 17, No. 12, Dec. 1996) Shanghai, China,-0001,():
-1年11月30日
The paper investigates the stability of linear non-conservative mechanical systems subjected to potential, gyroscopic. circulatory forces and Rayleigh damping. Three stability theorems are proved by means qf the Rayleigh quotients. The stability criterions given by tile theorems are convenient and useful because they are independent of the Rayleigh quotients.
stability,, linear systemsc,, irculatory force,, gyroscopic force
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【期刊论文】Dynamical behaviors and relative trajectories of the spacecraft formation flying
李俊峰, H. Baoyin a, ∗, Li Junfeng b, Gao Yunfeng b
Aerospace Science and Technology 6(2002)295-301,-0001,():
-1年11月30日
To describe the relative motion of spacecraft formation flying, this paper presents a method based on relative orbital elements, which is suitable to elliptical orbit with arbitrary eccentricity. The long time formation flying conditions are theoretically derived taken into account the relationship between relative motion and relative orbital elements. These conditions include that both the orbital periods of all participating spacecrafts should be the same and other relative orbital elements should be small enough. The expected relative distance of the spacecrafts would determine the magnitudes of such relative orbital elements. Theoretical analysis and numerical simulation results show that the spacecrafts with sufficient small relative orbital elements can keep long time formation flying without any active control when the orbital perturbations are not considered. The results also show that Hill’s equation is only suitable for describing a short time formation flying.
Spacecraft formation flying, Orbital elements, Relative motion, Hill', s equation
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50浏览
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