Details of the Researcher

PHOTO

Lin Mingpei
Section
Advanced Institute for Materials Research
Job title
Assistant Professor
Degree

  • Ｐｈ．Ｄ．（Beihang University）

  • Ｍ．Ｓ．（Beihang University）

e-Rad No.
90993519

Research History 2

  • 2022/10 - Present
    Tohoku University　Assistant Professor

  • 2021/03 - 2022/09
    Sun Yat-sen University　Postdoctor

Education 2

  • Beihang University　PH.D

    2014/09 - 2020/08

  • Shenzhen University　Bachelor's degree

    2010/09 - 2014/06

Research Interests 6

  • Bifurcation theory

  • Astrodynamics

  • Orbital dynamics

  • Restricted three-body problem

  • Celestial mechanics

  • Dynamical systems theory

Research Areas 3

  • Natural sciences / Mathematical analysis / Bifurcation theory

  • Aerospace, marine, and maritime Engineering / Aerospace engineering / Spacecraft orbit dynamics and control

  • Natural sciences / Astronomy / Celestial mechanics

Papers 20

  1. Analysis of Pitchfork Bifurcations and Symmetry Breaking in the Elliptic Restricted Three-body Problem Peer-reviewed

    Haozhe Shu, Mingpei Lin

    Celestial Mechanics and Dynamical Astronomy　137　(21)　2025/06/26

    DOI： 10.1007/s10569-025-10252-4 　

    ISSN： 0923-2958 1572-9478

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    <jats:title>Abstract</jats:title> <jats:p>A unified framework is proposed to quantitatively characterize pitchfork bifurcations and associated symmetry breaking in the elliptic restricted three-body problem (ERTBP). It is known that planar/vertical Lyapunov orbits and Lissajous orbits near the collinear libration points undergo pitchfork bifurcations with varying orbital energy. These bifurcations induce symmetry breaking, generating bifurcated families including halo/quasi-halo orbits, axial/quasi-axial orbits, and their corresponding invariant manifolds. Traditional semi-analytical methods for constructing halo orbits, based on resonant bifurcation mechanisms, have obstacles in fully exploiting the intrinsic symmetry breaking characteristics in pitchfork bifurcations. In this paper, a unified trigonometric series-based framework is proposed to analyze these bifurcated families from the perspective of coupling-induced bifurcation mechanisms. By introducing a coupling coefficient and various bifurcation equations into the ERTBP, different symmetry breaking is achieved when the coupling coefficient is nonzero. This unified semi-analytical framework captures bifurcations of both periodic/quasi-periodic and transit/non-transit orbits. Furthermore, it reveals that pitchfork bifurcation solutions in the ERTBP fundamentally depend solely on the orbital eccentricity and three amplitude parameters of the system’s degrees of freedom, governing both the elliptic direction and the hyperbolic one.</jats:p>

  2. Semi-analytical computation of bifurcation of orbits near collinear libration point in the restricted three-body problem Peer-reviewed

    Mingpei Lin, Tong Luo, Hayato Chiba

    Physica D: Nonlinear Phenomena　470　134404-134404　2024/12

    Publisher: Elsevier BV

    DOI： 10.1016/j.physd.2024.134404 　

    ISSN： 0167-2789

  3. Bifurcation Mechanism of Quasi-Halo Orbit from Lissajous Orbit Peer-reviewed

    Mingpei Lin, Hayato Chiba

    Journal of Guidance, Control, and Dynamics　1-13　2024/09/19

    Publisher: American Institute of Aeronautics and Astronautics (AIAA)

    DOI： 10.2514/1.g008233 　

    ISSN： 0731-5090

    eISSN： 1533-3884

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    This paper presents a general analytical method to describe the center manifolds of collinear libration points in the restricted three-body problem (RTBP). It is well known that these center manifolds include Lissajous orbits, halo orbits, and quasi-halo orbits. Previous studies have traditionally treated these orbits separately by iteratively constructing high-order series solutions using the Lindstedt–Poincaré method. Instead of relying on resonance between their frequencies, this study identifies that halo and quasi-halo orbits arise due to intricate coupling interactions between in-plane and out-of-plane motions. To characterize this coupling effect, a novel concept, coupling coefficient [Formula: see text], is introduced in the RTBP, incorporating the coupling term [Formula: see text] in the [Formula: see text]-direction dynamics equation, where [Formula: see text] represents a formal power series concerning the amplitudes. Subsequently, a uniform series solution for these orbits is constructed up to a specified order using the Lindstedt–Poincaré method. For any given paired in-plane and out-of-plane amplitudes, the coupling coefficient [Formula: see text] is determined by the bifurcation equation [Formula: see text]. When [Formula: see text], the proposed solution describes Lissajous orbits around libration points. As [Formula: see text] transitions from zero to nonzero values, the solution describes quasi-halo orbits, which bifurcate from Lissajous orbits. Particularly, halo orbits bifurcate from planar Lyapunov orbits if the out-of-plane amplitude is zero. The proposed method provides a unified framework for understanding these intricate orbital behaviors in the RTBP.

  4. Minimum-Time Control for the Test Mass Release Phase of Drag-Free Spacecraft Peer-reviewed

    Mingpei Lin, Jinxiu Zhang, Yanchao He

    Space: Science &amp; Technology　4　2024/01

    Publisher: American Association for the Advancement of Science (AAAS)

    DOI： 10.34133/space.0151 　

    eISSN： 2692-7659

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    The capture control of test mass by means of the electrostatic suspensions is crucial for drag-free spacecraft. The test mass must be released to the cage center of the inertial sensor accurately and quickly. This paper proposes a minimum-time capture control method for the test mass release phase of drag-free spacecraft. An analytical solution of optimal control is derived based on Pontryagin’s minimum principle and the linearized dynamics model of the test mass during the release phase. The parameters of the analytical solution are initially guessed with an approximate linear solution of the test mass dynamics model and are slightly modified by using differential correction. Compared with the exact numerical solution by the hp -adaptive pseudospectral method, the analytical solution is proved to be minimum-time. Numerical simulation shows that the proposed control method quickly captures the test mass to the cage center of the inertial sensor. The capture time to stabilization is only half that of the traditional controller.

  5. Test mass 6-DOF control allocation based on the null space for space gravitational wave mission Peer-reviewed

    Jinxiu Zhang, Juzheng Zhang, Yu Zhang, Wenjian Tao, Zhenkun Lu, Mingpei Lin

    Aerospace Science and Technology　140　2023/09

    DOI： 10.1016/j.ast.2023.108485 　

    ISSN： 1270-9638

    eISSN： 1626-3219

  6. High-order analytical solutions of bounded relative motions for Coulomb formation flying Peer-reviewed

    Mingpei Lin, Jinxiu Zhang, Ming Xu, Xiao Pan

    Nonlinear Dynamics　111　(14)　12931-12946　2023/07

    DOI： 10.1007/s11071-023-08518-3 　

    ISSN： 0924-090X

    eISSN： 1573-269X

  7. Robust optimal sliding mode control for the deployment of Coulomb spacecraft formation flying Peer-reviewed

    Peerawat Artitthang, Ming Xu, Mingpei Lin, Yanchao He

    Advances in Space Research　71　(1)　439-455　2022

    DOI： 10.1016/j.asr.2022.08.085 　

    ISSN： 1879-1948 0273-1177

    eISSN： 1879-1948

  8. Application of Lagrangian coherent structures to Coulomb formation on elliptic orbit Peer-reviewed

    Mingpei Lin, Yaru Zheng, Ming Xu

    Nonlinear Dynamics　102　(4)　2649-2668　2020/10

    DOI： 10.1007/s11071-020-05968-x 　

    ISSN： 1573-269X 0924-090X

    eISSN： 1573-269X

  9. Coulomb spacecraft formation flying: Equilibrium points, periodic orbits, and center manifolds Peer-reviewed

    Mingpei Lin, Xiaoyu Fu, Ming Xu, Han Yan

    Physica D: Nonlinear Phenomena　404　2020

    DOI： 10.1016/j.physd.2020.132357 　

    ISSN： 0167-2789

    eISSN： 1872-8022

  10. Lagrangian coherent structures in the planar parabolic/hyperbolic restricted three-body problem Peer-reviewed

    Qingyu Qu, Mingpei Lin, Ming Xu

    Monthly Notices of the Royal Astronomical Society　493　(2)　1574-1586　2020

    DOI： 10.1093/mnras/staa199 　

    ISSN： 1365-2966 0035-8711

    eISSN： 1365-2966

  11. Entire flight trajectory design for temporary reconnaissance mission Peer-reviewed

    Mingpei Lin, Ming Xu

    Transactions of the Japan Society for Aeronautical and Space Sciences　60　(3)　137-151　2017/05

    DOI： 10.2322/tjsass.60.137 　

    ISSN： 0549-3811

  12. GPU-accelerated computing for Lagrangian coherent structures of multi-body gravitational regimes Peer-reviewed

    Mingpei Lin, Ming Xu, Xiaoyu Fu

    Astrophysics and Space Science　362　(4)　2017/04

    DOI： 10.1007/s10509-017-3050-y 　

    ISSN： 1572-946X 0004-640X

    eISSN： 1572-946X

  13. A parallel algorithm for the initial screening of space debris collisions prediction using the SGP4/SDP4 models and GPU acceleration Peer-reviewed

    Mingpei Lin, Ming Xu, Xiaoyu Fu

    Advances in Space Research　59　(9)　2398-2406　2017/03

    DOI： 10.1016/j.asr.2017.02.023 　

    ISSN： 1879-1948 0273-1177

    eISSN： 1879-1948

  14. Adaptive Wind Direction Strategy for Neuro-network-based Active Disturbance Rejection Control of Tandem Twin-rotor Aerial-aquatic Vehicle

    Maosen Shao, Sihuan Wu, LiDong Wang, Sifan Wu, Hui Wang, Zhilin He, Mingpei Lin, Jinxiu Zhang

    Aerospace Science and Technology　2025/02/23

    DOI： 10.1016/j.ast.2025.110089 　

    ISSN： 1270-9638

  15. Gravity assist space pruning and global optimization of spacecraft trajectories for solar system boundary exploration Peer-reviewed

    Yuqi Song, Weiren Wu, Hang Hu, Mingpei Lin, Hui Wang, Jinxiu Zhang

    COMPLEX & INTELLIGENT SYSTEMS　2023/07

    DOI： 10.1007/s40747-023-01123-2 　

    ISSN： 2199-4536

    eISSN： 2198-6053

  16. Mode Switching Control for Drag-Free Satellite Based on Region of Attraction Peer-reviewed

    Xiaobin Lian, Jinxiu Zhang, Xiaozheng Song, Zhenqiang Hong, Shengpeng Zhou, Mingpei Lin

    SPACE: SCIENCE & TECHNOLOGY　3　2023/05

    DOI： 10.34133/space.0020 　

    eISSN： 2692-7659

  17. Robust Control Allocation for Space Inertial Sensor under Test Mass Release Phase with Overcritical Conditions Peer-reviewed

    Juzheng Zhang, Yu Zhang, Wenjian Tao, Zhenkun Lu, Mingpei Lin

    SENSORS　23　(6)　2023/03

    DOI： 10.3390/s23062881 　

    eISSN： 1424-8220

  18. Ascent trajectory design of small-lift launch vehicle using hierarchical optimization Peer-reviewed

    Zheng, Y., Fu, X., Xu, M., Li, Q., Lin, M.

    Aerospace Science and Technology　107　2020/12

    DOI： 10.1016/j.ast.2020.106285 　

    ISSN： 1270-9638

    eISSN： 1626-3219

  19. Charged-Spacecraft Formation: Concept, Deployment and Coulomb-Force Control Peer-reviewed

    Mingpei Lin, Ming Xu

    IEEE Access　8　59670-59677　2020/05

    DOI： 10.1109/ACCESS.2020.2983307 　

    ISSN： 2169-3536

  20. The bifurcation of periodic orbits and equilibrium points in the linked restricted three-body problem with parameter ω Peer-reviewed

    Yuying Liang, Jinjun Shan, Ming Xu, Mingpei Lin

    Chaos　29　(10)　2019/10

    DOI： 10.1063/1.5096966 　

    ISSN： 1054-1500

    eISSN： 1089-7682

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Presentations 3

  1. Application of Coupling-Induced Bifurcation Mechanism to Analyzing Local Bifurcation in Dynamical Systems Invited

    Mingpei Lin

    AIMR Math Group Seminar, Tohoku University, Sendai, Japan　2024/07/26

  2. Charged-spacecraft formation: Manifolds, deployment and reconfiguration Invited

    Mingpei Lin

    The 70th International Astronautical Congress, Washington D.C., United States, IAC 2019.　2019/10/22

  3. The Lagrangian coherent structures of elliptic formation flying Invited

    Mingpei Lin

    The 18th Academic Annual Conference on Space and Motion Control　2018/08/17