Mercury sun-synchronous polar orbiter with a solar sail

被引:29
|
作者
Leipold, M
Seboldt, W
Lingner, S
Borg, E
Herrmann, A
Pabsch, A
Wagner, O
Bruckner, J
机构
[1] Ger. Aerosp. Res. Estab. (DLR), Space Systems Analysis Division, Cologne
[2] Ger. Aerosp. Res. Estab. (DLR), Institute for Planetary Exploration, Berlin
[3] Ger. Aerosp. Res. Estab. (DLR), German Remote Sensing Data Center, Neustrelitz
[4] Ger. Aerosp. Res. Estab. (DLR), Institute of Structural Mechanics, Braunschweig
[5] Max-Planck-Institute for Chemistry, Department of Cosmochemistry, Mainz
关键词
D O I
10.1016/S0094-5765(96)00131-2
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
An innovative mission MESSAGE (MErcury Solar Sailing Advanced Geoscience Exploration) is proposed where a solar sail spacecraft of about 240kg total mass delivers a limited but highly valuable science payload to a sun-synchronous Mercury orbit in 3 1/2 years. Corresponding operation near the terminator offers favorable thermal and remote sensing conditions for the considered instruments. Since Mercury is still the poorest explored and least known planet of the inner solar system, there is a high level of scientific interest for further exploration. Science objectives and a potential payload package of about 20 kg for the proposed solar sail mission considering the special orientation and geometry of a sun-synchronous orbit about Mercury will be discussed. Determination of the elemental composition of the Hermian surface with respect to major rock forming elements and volatiles could be carried out by a gamma-ray spectrometer. In the current mission architecture the spacecraft will be launched into an Earth escape trajectory with a relatively low-cost launch option such as TAURUS or ROCKOT with upper stages. The sail is used as a transportation means for the interplanetary transfer, for orbit capture upon Mercury arrival, and subsequent adjustment of a sun-synchronous orbit about the planet near the terminator. Due to Mercury's 3:2 spin-orbit coupling the eccentric polar orbit of 200 km x 6350 km altitude with periapsis above the north pole will allow complete coverage of the planet's surface within two Mercury years. Optimized interplanetary trajectories as well as simulations of the orbit about Mercury will be shown. A conceptual design of the spacecraft including the deployment concept of the square sail of an estimated size of about 86m x 86m and its support structure will be presented. The lightweight booms are proposed to be manufactured of carbon fibre reinforced plastic profiles that can be stored on a central hub prior to deployment. Possible sail film materials, coatings and folding concepts will be discussed. In a more advanced scenario two identical solar sails could be launched in a stacked configuration by a Med-Lite to realize a dual sun-synchronous Mercury orbiter mission. Copyright (C) 1997 Elsevier Science Ltd.
引用
收藏
页码:143 / 151
页数:9
相关论文
共 50 条
  • [31] Descending Sun-Synchronous Orbits with Aerodynamic Inclination Correction
    Llop, Josep Virgili
    Roberts, Peter C. E.
    Palmer, Kyle
    Hobbs, Stephen
    Kingston, Jennifer
    JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 2015, 38 (05) : 831 - 842
  • [32] The optimization of initial inclination for a desired sun-synchronous orbit
    Chao, CC
    Gist, RG
    ASTRODYNAMICS 1995, 1996, 90 : 509 - 520
  • [33] SUN-SYNCHRONOUS ORBIT SLOT ARCHITECTURE: ANALYSIS AND DEVELOPMENT
    Watson, Eric
    Lovell, T. Alan
    Abercromby, Kira
    SPACEFLIGHT MECHANICS 2012, 2012, 143 : 2325 - +
  • [34] Electric power supply system of sun-synchronous satellite
    Belov, DG
    Dranovsky, VJ
    Perekopsky, IT
    PROCEEDINGS OF THE FIFTH EUROPEAN SPACE POWER CONFERENCE (ESPC), VOLS 1 AND 2, 1998, 416 : 191 - 194
  • [35] On the long-period evolution of the sun-synchronous orbits
    Kuznetsov, E. D.
    Jasim, A. T.
    SOLAR SYSTEM RESEARCH, 2016, 50 (03) : 197 - 203
  • [36] On the long-period evolution of the sun-synchronous orbits
    E. D. Kuznetsov
    A. T. Jasim
    Solar System Research, 2016, 50 : 197 - 203
  • [37] Displaced Sun-Synchronous Orbit Control Scheme for Sailcraft
    Xia Xiwang
    Zhang Keke
    Chen Hongyu
    Chen Yingbo
    Zhou Meijiang
    Li Chaoyong
    Mu Zhongcheng
    Liu Shanwu
    PROCEEDINGS OF THE 36TH CHINESE CONTROL CONFERENCE (CCC 2017), 2017, : 5009 - 5014
  • [38] Statistical analysis of one Chinese sun-synchronous satellite anomalies
    TIAN Tian
    ZONG QiuGang
    CHANG Zheng
    WANG YongFu
    YANG XiaoHua
    Science China(Technological Sciences), 2016, 59 (04) : 540 - 546
  • [39] Solar orbiter: Mission to study the sun
    Murray L.
    Engineering and Technology, 2021, 16 (03): : 28 - 31
  • [40] Erratum to: Stability of a Magnetically Actuated Satellite towards the Sun on a Sun-Synchronous Orbit
    D. S. Roldugin
    Cosmic Research, 2023, 61 : 454 - 454