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SCIENCE CHINA Information Sciences, Volume 61, Issue 4: 040305(2018) https://doi.org/10.1007/s11432-017-9202-1

Design of communication relay mission for supporting lunar-farside soft landing

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  • ReceivedJun 8, 2017
  • AcceptedJul 3, 2017
  • PublishedDec 12, 2017

Abstract

Chang'E-IV will be the first soft-landing and rover mission on the lunar farside. The relay satellite, which is located near the Earth-Moon L2 point for relay communication, is the key to the landing mission. Based on an analysis of the characteristics of the task and the technical difficulties associated with the relay satellite system, the overall design scheme of the relay communication mission is proposed in terms of trajectory design and communication system design among other aspects. First, according to the complex dynamic environment, a mission orbit that serves as an uninterrupted communication link is presented. A short-duration and low-energy transfer trajectory with lunar flyby is discussed. Orbital correction and a low-cost control strategy for orbit maintenance in the Earth-Moon L2 point region are provided. Second, considering the existing technical constraints, the requirement of relay communication in different stages and the design schemes of frequency division and redundant relay communication system are introduced. Finally, based on the trajectory design index and the performance of the communication system, the overall design scheme of the relay communication mission is proposed. This mission will provide the technical support and reference required for the Chang'E-IV mission.


Acknowledgment

This work was supported by National Science and Technology Major Project of the Ministry of Science and Technology of China (Lunar Exploration Program), National Natural Science Foundation of China (Grant No. 11572038), and Chang Jiang Scholars Program.


References

[1] Farquhar R W, Dunham D W, Guo Y. Utilization of libration points for human exploration in the Sun-Earth-Moon system and beyond. Acta Astronaut, 2004, 55: 687-700 CrossRef ADS Google Scholar

[2] Dunham D W, Farquhar R W, Eysmont N, et al. Interplanetary human exploration enabled by lunar swingbys and libration-point orbits. In: Proceedings of AIAA/AAS Astrodynamics Specialist Conference, San Diego, 2014. Google Scholar

[3] Burns J O, Kring D A, Hopkins J B, et al. A lunar L2 far side exploration and science mission concept with the orion multi-purpose crew vehicle and a teleported lander/rover. Adv Space Res, 2012, 52: 306--320. Google Scholar

[4] Mimoun D, Wieczorek M A, Alkalai L. Farside explorer: unique science from a mission to the farside of the moon. Exp Astron, 2012, 33: 529-585 CrossRef ADS Google Scholar

[5] Farquhar R W. Lunar Communications with Libration-Point Satellites. J Spacecraft Rockets, 1967, 4: 1383-1384 CrossRef ADS Google Scholar

[6] Farquhar R W. The Control and Use of Libration-Point Satellites. NASA Technical Report NASA TR R-346, 1970. Google Scholar

[7] Farquhar R W. The Utilization of Halo Orbits in Advanced Lunar Operations. NASA Technical Note NASA TN D-6365, 1971. Google Scholar

[8] Tang Y, Wu W, Qiao D. Effect of orbital shadow at an Earth-Moon Lagrange point on relay communication mission. Sci China Inf Sci, 2017, 60: 112301 CrossRef Google Scholar

[9] Farquhar R W, Kamel A A. Quasi-Periodic Orbits about the Translunar Libration Point. Celestial Mech, 1973, 7: 458-473 CrossRef ADS Google Scholar

[10] Richardson D L. Analytic construction of periodic orbits about the collinear points. Celestial Mech, 1980, 22: 241-253 CrossRef ADS Google Scholar

[11] Dutt P, Sharma R K. Analysis of periodic and quasi-periodic orbits in the Earth-Moon system. J Guid Control Dyn. 1971, 33: 1010--1017. Google Scholar

[12] Howell K C. Families of orbits in the vicinity of the collinear libration points. In: Proceedings of AIAA/AAS Astrodynamics Specialist Conference and Exhibit, Boston, 1998. Google Scholar

[13] Gómez G, Mondelo J M. The dynamics around the collinear equilibrium points of the RTBP. Physica D-NOnlinear Phenomena, 2001, 157: 283-321 CrossRef ADS Google Scholar

[14] Grebow D J. Generating periodic orbits in the circular restricted three body problem with applications to lunar south pole coverage. Dissertation for Ph.D. Degree. West Lafayette: Purdue University, 2006. Google Scholar

[15] Parker J S, Born G H. Direct lunar halo orbit transfers. J Astronaut Sci, 2008, 56: 441-476 CrossRef ADS Google Scholar

[16] Rowells M. Development of a long-term Earth-Moon trans-lunar libration point orbit. In: Proceedings of AIAA Space Conference and Exposition, Pasadena, 2012. Google Scholar

[17] Geraldo M O, Prado A F, Sanchez D M, et al. Traveling between the Earth-Moon lagrangian points and the earth. In: Proceedings of SpaceOps Conference, Daejeon, 2015. Google Scholar

[18] Gordon D P. Transfers to Earth-Moon L2 halo orbits using lunar proximity and invariant manifolds. Dissertation for Ph.D. Degree. West Lafayette: Purdue University, 2008. Google Scholar

[19] Mingtao L, Jianhua Z. Impulsive lunar Halo transfers using the stable manifolds and lunar flybys. Acta Astronaut, 2010, 66: 1481-1492 CrossRef ADS Google Scholar

[20] Wu W R, Cui P Y, Qiao D. Design and performance of exploring trajectory to Sun-Earth L2 point for Chang'E-2 mission. Chin Sci Bull (Chin Ver), 2012, 57: 1987-1991 CrossRef Google Scholar

[21] Parker J S. Families of low-energy lunar halo transfers. In: Proceedings of AAS/AIAA Spaceflight Dynamics Conference, Tampa, 2006. Google Scholar

[22] Koon W S, Lo M W, Marsden J E. Low energy transfer to the moon. Celestial Mech Dynamical Astron, 2001, 81: 63-73 CrossRef Google Scholar

[23] Lo M W, Ross S D. The lunar L1 gateway: portal to the stars and beyond. In: Proceedings of AIAA Space Conference and Exposition, Albuquerque, 2001. Google Scholar

[24] Alessi E M, Gomez G, Masdemont J J. LEO-Lissajous transfers in the Earth-Moon system. In: Proceedings of the 59th International Astronautical Federation Congress, Glasgow, 2008. Google Scholar

[25] Howell K C, Lo M W, Barden B T. Application of dynamical systems theory to trajectory design for a libration point mission. In: Proceedings of AIAA Astrodynamics Conference, San Diego, 1996. 161--178. Google Scholar

[26] Pergola P, Ruggiero A, Casaregola C, et al. Chemical and electric transfers to Earth-Moon halo orbits. In: Proceedings of the 47th AIAA/ASME/SAE/ ASEE Joint Propulsion Conference, San Diego, 2013. 116--128. Google Scholar

[27] Howell K C, Pernicka H J. Station-keeping method for libration point trajectories. J Guid Control Dyn, 1990, 16: 713--723. Google Scholar

[28] Pavlak T, Howell K. Strategy for long-term libration point orbit station keeping in the Earth-Moon system. In: Proceedings of AAS/AIAA Astrodynamics Specialist Conference, Girdwood, 2011. Google Scholar

[29] Pavlak T, Howell K C. Strategy for optimal, long-term stationkeeping of libration point orbits in the Earth-Moon system. In: Proceedings of AIAA/AAS Astrodynamics Specialist Conference, Minneapolis, 2013. 199--208. Google Scholar

[30] Folta D, Woodard M, Cosgrove D. Stationkeeping of the first Earth-Moon libration orbiters: the ARTEMIS mission. In: Proceedings of AAS/AIAA Astrodynamics Specialist Conference, Girdwood, 2011. Google Scholar

[31] Simó C, Gómez G, Llibre J. On the optimal station keeping control of halo orbits. Acta Astronaut, 1987, 15: 391-397 CrossRef ADS Google Scholar

[32] Kulkarni J, Campbell M. Asymptotic stabilization of motion about an unstable orbit: application to spacecraft flight in halo orbit. In: Proceedings of American Control Conference, Boston, 2004. 1025--1030. Google Scholar

[33] Xin M, Dancer M, Balakrishnan S, et al. Station keeping of an ${\rm~~L}_2$ libration point satellite with $\theta$-D technique. In: Proceeding of the 2004 American Control Conference, Boston, 2004. Google Scholar

[34] Colombo G. The stabilization of an artificial satellite at the inferior conjunction point of the Earth-Moon system. J Astron Sci, 1961, 6: 213--222. Google Scholar

[35] Zhou H, Li H T, Dong G L. Relative position determination between Chang'E-3 lander and rover using in-beam phase referencing. Sci China Inf Sci, 2015, 58: 092201. Google Scholar

[36] Wu W R, Luo H, Chen M, et al. Design and experiment of deep space telemetry and data transmission system in libration points 2 exploring. Syst Eng Electron, 2012, 34: 2559--2563. Google Scholar

[37] Wu W R, Huang L, Jie D G, et al. Design and experiment of X-band TT$\&$C system for the project of CE-2. Sci Sin Inform, 2011, 41: 1171--1183. Google Scholar

[38] Wu W R, Dong G L, Li H T, et al. Engineering and Technology of Deep Space measurement and Control Communication System (in Chinese). Beijing: Science Press, 2013. Google Scholar

[39] Gao L, Zhang S, Liu Z. An overview of multi-antenna technologies for space-ground integrated networks. Sci China Inf Sci, 2016, 59: 121301 CrossRef Google Scholar

  • Figure 1

    (Color online) Geometric relationships of the Earth-Moon system, and distributions of libration points.

  • Figure 2

    (Color online) Measurement and control of relay satellite and relay communication link.

  • Figure 3

    (Color online) Relay satellite located in Earth-Moon L2 halo orbit, and communications for lunar farside.

  • Figure 4

    (Color online) Orbital types near the libration point.

  • Figure 5

    Halo orbit in the region of Earth-Moon L2.

  • Figure 6

    (Color online) Direct transfer trajectory (LU: Earth-Moon distance).

  • Figure 7

    (Color online) Transfer trajectory with lunar flyby.

  • Figure 8

    (Color online) Flight trajectory of low-energy transfer via Sun-Earth L2 point (AU: Sun-Earth distance).

  • Figure 9

    (Color online) Flight trajectory of low-energy transfer via Earth-Moon L1 point.

  • Figure 10

    (Color online) Flight trajectory of low-energy transfer in three-body system.

  • Figure 11

    (Color online) Flight sequence of lunar flyby transfer.

  • Figure 12

    Flight trajectory of relay satellite for three years on Earth-Moon halo orbit.

  • Figure 13

    (Color online) Expanded state of high-gain mesh parabolic antenna.

  • Figure 14

    (Color online) Configuration of relay satellite for launch state.

  • Figure 15

    (Color online) Configuration of relay satellite in orbit state.

  • Figure 16

    (Color online) Schematic flight diagram of relay satellite.

  • Table 1   Comparison and analysis of halo and Lissajous orbits
    Index Halo orbit Lissajous orbit
    Earth communication No Moon occlusion, Short-time disruption due to
    coverage condition always visible to the Earth lunar shadow
    Shadow condition Shadows caused by both Shadows caused by both
    the Earth and the Moon the Earth and the Moon
    Cost of orbit insertion Relatively high Relatively low
    Velocity increment of orbit maintenance Relatively small Relatively large
    Frequency of orbit maintenance Equivalent frequency Equivalent frequency
    Antenna beam angle Relatively small Comparatively large
    for Earth communication
    Angle variation range of Sun Relatively small Comparatively large
    relative to satellite $Y$-axis (shown in Figure 15)
  • Table 2   Comparisons of three types of transfer trajectories
    Velocity of perigee The time of flight Velocity increment Application
    when launching to the L2 point
    Direct transfer Short transfer time, About 900–1000 m/s Few application
    about 6–7 days
    Lunar flyby transfer About 10.9 km/s Relative short transfer time, About 200–300 m/s CE-5T in-orbit
    about 3–4 weeks verification
    Low-energy transfer Long transfer time, About 0–200 m/s Widely applied to
    from 1 month to 3 years exploration mission
  • Table 3   Deflection of trajectory in rotating frame
    Parameters Mean Standard deviation Maximum
    Position error in $X$ direction (km) $-$2387.330 9161.371 34610.423
    Position error in $Z$ direction (km) 1054.920 3725.730 12450.725
    Velocity error in $X$ direction (m/s) $-$23.539 78.788 335.301
    Velocity error in $Y$ direction (m/s) 4.984 23.778 88.371
    Velocity error in $Z$ direction (m/s) 4.714 18.489 58.695
    Cross-time error (min) 104.347 260.616 962.599
  • Table 4   Halo orbit maintenance for different amplitudes and frequencies
    Amplitude of halo orbit 9000 km 12000 km 15000 km
    maintenance frequency Half cycle One cycle Half cycle One cycle Half cycle One cycle
    Mean (m/s) 82.889 205.447 85.493 213.157 87.529 225.497
    Standard deviation (m/s) 8.653 29.145 8.513 35.692 8.004 37.244
    Maximum (m/s) 102.202 240.996 109.582 276.406 105.196 279.644

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