Small-amplitude periodic orbit around sun-earth L1/L2 Controlled by solar radiation pressure

被引：0
|
作者：
机构：
[1] Tanaka, Keita
[2] Kawaguchi, Jun'ichiro
来源：
Tanaka, Keita (k-tanaka@jh.jp.nec.com) | 1600年 / Japan Society for Aeronautical and Space Sciences卷 / 59期
关键词：
The L1 and L2 points of the Sun-Earth system attract much attention for various space uses; such as observation and communication. Deploying the spacecraft just on L1/L2 is; however; not convenient; because L1 always overlaps with the Sun as seen from the Earth and L2 is hidden behind the shadow of the Earth. Adopting a small-amplitude periodic orbit around the L1/L2 points is one option to solve this problem. The orbit can be achieved by low continuous maneuvering. The required magnitude of acceleration is at a level that can be managed by solar radiation pressure. Utilizing solar radiation pressure has the possibility of saving maneuvering to keep the spacecraft near a L1/L2 orbit. Acceleration due to solar radiation pressure depends on the surface area of the spacecraft and thus the spacecraft should be equipped with a large flat surface. A spacecraft equipped with a solar sail is appropriate. This paper presents two station-keeping examples of solar sails in the vicinity of SE L1/L2 using acceleration resulting from solar radiation pressure. The orbit control laws are built into the linear system about the equilibrium; and we confirm that they are applicable in the non-linear system through numerical calculation. © 2016 The Japan Society for Aeronautical and Space Sciences;
D O I：
暂无
中图分类号：
学科分类号：
摘要：
Journal article (JA)
引用
收藏
相关论文
共 50 条
  • [1] Small-amplitude Periodic Orbit around Sun-Earth L1/L2 Controlled by Solar Radiation Pressure
    Tanaka, Keita
    Kawaguchi, Jun'ichiro
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2016, 59 (01) : 33 - 42
  • [2] Formation flight near L1 and L2 in the sun-earth/moon ephemeris system including solar radiation pressure
    Marchand, BG
    Howell, KC
    ASTRODYNAMICS 2003, PTS 1-3, 2003, 116 : 1463 - 1498
  • [3] Formation Control at the Sun-Earth L2 Libration Point Using Solar Radiation Pressure
    Shahid, Kamran
    Kumar, K. D.
    JOURNAL OF SPACECRAFT AND ROCKETS, 2010, 47 (04) : 614 - 626
  • [4] Sun-Earth L1 and L2 to Moon Transfers Exploiting Natural Dynamics
    van der Weg, Willem J.
    Vasile, Massimiliano
    ASTRODYNAMICS NETWORK ASTRONET-II: THE FINAL CONFERENCE, 2016, 44 : 273 - 292
  • [5] A multi-step method to calculate long-term quasi-periodic orbits around the Sun-Earth L1/L2
    Tan, Minghu
    Ma, Bingbing
    Li, Haoyu
    ASTROPHYSICS AND SPACE SCIENCE, 2022, 367 (10)
  • [6] Low thrust transfer to sun-earth L1 and L2 points with a constraint on the thrust direction
    Sukhanov, AA
    Eismont, NA
    PROCEEDINGS OF THE CONFERENCE ON LIBRATION POINT ORBITS AND APPLICATIONS, 2003, : 439 - 454
  • [7] Transfer trajectory design between L2 in Sun-Earth system and L1 in Sun-Mars system
    Lü, Jing
    Zhang, Mingming
    Zhang, Yongwei
    Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics, 2013, 39 (08): : 1031 - 1036
  • [8] FORMATION MANEUVERING IN THE VICINITY OF THE SUN-EARTH/MOON L2 LIBRATION POINT USING SOLAR RADIATION PRESSURE
    Shahid, Kamran
    Kumar, Krishna Dev
    APPLICATIONS OF SPACE TECHNOLOGY FOR HUMANITY, 2010, 138 : 177 - +
  • [9] Nonlinear Station-Keeping Control in the Vicinity of the Sun-Earth L2 Point Using Solar Radiation Pressure
    Shahid, Kamran
    Kumar, Krishna Dev
    JOURNAL OF AEROSPACE ENGINEERING, 2016, 29 (03)
  • [10] Transfer scheme of CHANG'E-2 from the Sun-Earth L2 point to the L1 point
    Liu, Lei
    Li, Xie
    Cao, Jian-Feng
    Tang, Ge-Shi
    Hu, Song-Jie
    Liu, L. (15810340789@139.com), 1600, Chinese Institute of Electronics (36): : 1386 - 1391
12345