• Title/Summary/Keyword: Relative Orbit Propagator

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A Study on Multiple Spacecraft Formation-keeping Control (다위성체의 편대비행 형상유지 제어에 관한 연구)

  • No, Tae-Soo;Lee, Jae-Gyu;Jung, Ok-Chul
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.10
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    • pp.51-59
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    • 2005
  • In this paper, results of a multiple spacecraft formation-keeping control using the orbital relative motion and optimization technique are presented. To analyze and predict the relative motion between the formation-flying satellites, a closed-form orbit propagator obtained using the method of ephemeris compression is used. This closed-form orbit propagator is combined with optimization technique to plan a series of impulsive maneuvers, which maintain the formation configuration within the specified limit. As an example, this method is applied to the problem of maintaining the projected circular formation geometry and results from nonlinear simulation are presented.

Station Collocation of Geostationary Spacecraft Via Direct Control of Relative Position (상대위치 직접 제어를 통한 정지궤도 위성의 Collocation에 관한 연구)

  • Lee, Jae-Gyu;No, Tae-Su
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.34 no.5
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    • pp.56-64
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    • 2006
  • Station collocation of closely placed multiple GEO spacecraft is required to avoid the problem of collision risk, attitude sensor interference and/or occultation. This paper presents the method of obtaining the orbit correction scheme for collocating two GEO spacecraft within a small station-keeping box. The relative motion of each spacecraft with respect to the virtual geostationary satellite is precisely expressed in terms of power and trigonometry functions. This closed-form orbit propagator is used to define the constraint conditions which meet the requirements for the station collocation. Finally, the technique of constrained optimization is used to find the orbit maneuver sequence. Nonlinear simulations are performed and their results are compared with those of the classical method.

A Numerical Approach for Station Keeping of Geostationary Satellite Using Hybrid Propagator and Optimization Technique

  • Jung, Ok-Chul;No, Tae-Soo;Kim, Hae-Dong;Kim, Eun-Kyou
    • International Journal of Aeronautical and Space Sciences
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    • v.8 no.1
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    • pp.122-128
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    • 2007
  • In this paper, a method of station keeping strategy using relative orbital motion and numerical optimization technique is presented for geostationary satellite. Relative position vector with respect to an ideal geostationary orbit is generated using high precision orbit propagation, and compressed in terms of polynomial and trigonometric function. Then, this relative orbit model is combined with optimization scheme to propose a very efficient and flexible method of station keeping planning. Proper selection of objective and constraint functions for optimization can yield a variety of station keeping methods improved over the classical ones. Nonlinear simulation results have been shown to support such concept.