Maintenance of Libration Point Orbit in Elliptic Sun–Mercury Model

The maintenance of the nominal multirevolution elliptic halo orbit, whose special features can benefit mercurial explorations, is first investigated through Monte–Carlo simulations in the elliptic Sun–Mercury model, and then validated in the high-fidelity ephemeris model. The receding horizon control strategy solved by the indirect Radau pseudospectral method demonstrates that the orbit can be maintained robustly with respect to very large initial deviations. Moreover, the result proves that the elliptic Sun–Mercury model is an accurate approximation.

[1]  Xue Ma,et al.  Distant quasi-periodic orbits around Mercury , 2013 .

[2]  Gerard Gómez,et al.  Dynamics and Mission Design Near Libration Points , 2001 .

[3]  Xue Ma,et al.  Artificial frozen orbits around Mercury , 2013 .

[4]  Ryan P. Russell,et al.  Survey of spacecraft trajectory design in strongly perturbed environments , 2012 .

[5]  Hao Peng,et al.  Continuation of periodic orbits in the Sun-Mercury elliptic restricted three-body problem , 2017, Commun. Nonlinear Sci. Numer. Simul..

[6]  Shijie Xu,et al.  Low-energy transfers to a Lunar multi-revolution elliptic halo orbit , 2015 .

[7]  Shijie Xu,et al.  Optimal Low-Thrust Transfers to Lunar L1 Halo Orbit Using Variable Specific Impulse Engine , 2015 .

[8]  H. Rix,et al.  The James Webb Space Telescope , 2006, astro-ph/0606175.

[9]  Robert W. Farquhar,et al.  The flight of ISEE-3/ice: Origins, mission history, and a legacy , 1998 .

[10]  Shengping Gong,et al.  Reflectivity-controlled solar sail formation flying for magnetosphere mission , 2013 .

[11]  M. Leipold,et al.  Mercury orbiter with a solar sail spacecraft , 1995 .

[12]  R. Meire,et al.  The stability of the triangular points in the elliptic restricted problem , 1981 .

[13]  J. M. A. Danby,et al.  Stability of the triangular points in the elliptic restricted problem of three bodies , 1964 .

[14]  J Llibre,et al.  Dynamics and Mission Design Near Libration Points: Volume II: Fundamentals: The Case of Triangular Libration Points , 2001 .

[15]  Xin Jiang,et al.  Nonlinear receding horizon guidance for spacecraft formation reconfiguration on libration point orbits using a symplectic numerical method. , 2016, ISA transactions.

[16]  Shengping Gong,et al.  Solar sail periodic orbits in the elliptic restricted three-body problem , 2015 .

[17]  Robert C. Moore,et al.  The MESSENGER mission to Mercury: spacecraft and mission design , 2001 .

[18]  Bong Wie,et al.  Solar Sail Attitude Control and Dynamics, Part 1 , 2004 .

[19]  J. Betts.  Survey of Numerical Methods for Trajectory Optimization , 1998 .

[20]  Bruce A. Conway,et al.  A Survey of Methods Available for the Numerical Optimization of Continuous Dynamic Systems , 2011, Journal of Optimization Theory and Applications.

[21]  Robert W. Farquhar,et al.  The Utilization of Halo Orbits in Advanced Lunar Operations , 1971 .

[22]  Pini Gurfil,et al.  Semi-Analytical Method for Calculating the Elliptic Restricted Three-Body Problem Monodromy Matrix , 2007 .

[23]  Hanlun Lei,et al.  High-order solutions around triangular libration points in the elliptic restricted three-body problem and applications to low energy transfers , 2014, Commun. Nonlinear Sci. Numer. Simul..

[24]  Ming Xu,et al.  Impulsive Control for Formation Flight About Libration Points , 2012 .

[25]  Hexi Baoyin,et al.  Practical Techniques for Low-Thrust Trajectory Optimization with Homotopic Approach , 2012 .

[26]  Johannes Benkhoff.  BepiColombo , 2022, Encyclopedia of Astrobiology.

[27]  X. Y. Hou,et al.  On motions around the collinear libration points in the elliptic restricted three-body problem , 2011 .

[28]  W. Zhong,et al.  Optimal guidance based on receding horizon control for low-thrust transfer to libration point orbits , 2013 .

[29]  Shijie Xu,et al.  Stability of two groups of multi-revolution elliptic halo orbits in the elliptic restricted three-body problem , 2015 .

[30]  Shijie Xu,et al.  Transfer to a Multi-revolution Elliptic Halo orbit in Earth–Moon Elliptic Restricted Three-Body Problem using stable manifold , 2015 .

[31]  Francesco Topputo,et al.  The role of true anomaly in ballistic capture , 2013 .

[32]  Li Huifeng,et al.  Indirect Radau pseudospectral method for the receding horizon control problem , 2016 .

[33]  Shengping Gong,et al.  Analytical criteria of Hill stability in the elliptic restricted three body problem , 2015 .