A simplex method for the orbit determination of maneuvering satellites

Jianrong, Chen; Li, Junfeng; Wang, Xijing; Zhu, Jun; Wang, DanNa

doi:10.1007/s11433-017-9102-1

Cited by 4 publications

(2 citation statements)

References 16 publications

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“…However, for a continuous thrust spacecraft, its orbit in space cannot be described by a conic curve, the unknown thrust acceleration increases the dimension of the problem, and the traditional initial orbit determination algorithm [6] is no longer applicable. JianRong Chen et al [7] used the simplex method to solve the orbit determination problem of a continuous small-thrust maneuvering satellite based on the start and end times of electric propulsion control. However, it uses GPS data and cannot solve the problem for non-cooperative targets.…”

Section: Introductionmentioning

confidence: 99%

Initial Identification of Thrust and Orbit Elements for Continuous Thrust Spacecraft in Circular Orbit

Zhao,

Tao,

2023

Aerospace

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Continuous thrust spacecraft in circular orbits have had a great influence on the identification and cataloging of space targets. Gaussian-type orbital element variational equations are simplified and approximated. Ground-based radar observation datasets are transformed into orbit elements datasets. The initial thrust and orbit elements are obtained by optimally solving the spatial parameter error sum of squares minimization problem with the Levenberg–Marquardt method. The simulation analysis is carried out under the high-precision orbit model, and the solution error of tangential acceleration is around 5 × 10−7 m/s2, and that of normal acceleration is around 3 × 10−6 m/s2; the accuracy of the semi-major axis is 350 m, and the accuracy of inclination is 0.095°. The method is applicable to the preliminary identification of thrust and orbit elements for circular orbit continuous thrust spacecraft and can provide reliable initial values for the subsequent precision orbit determination of such spacecraft.

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Section: Introductionmentioning

confidence: 99%

Initial Identification of Thrust and Orbit Elements for Continuous Thrust Spacecraft in Circular Orbit

Zhao,

Tao,

2023

Aerospace

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“…Uncertainty propagation plays a key role in many application fields of astrodynamics, such as vehicle navigation, orbit determination, target tracking, space situational awareness, as well as collision assessment [1][2][3][4][5][6]. Moreover, when a complete and accurate statistical description of the propagated statistics is of interest, uncertainty propagation poses the significant challenge of solving partial differential equations to map the probability density functions (PDF) [7][8][9], or carrying out particle-type, computationally demanding studies such as Monte Carlo simulations [3,[10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Nonlinear orbital uncertainty propagation with differential algebra and Gaussian mixture model

Sun

Luo

Lizia

et al. 2018

Sci. China Phys. Mech. Astron.

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Nonlinear uncertainty propagation is of critical importance in many application fields of astrodynamics. In this paper, a framework combining the differential algebra technique and the Gaussian mixture model method is presented to accurately propagate the state uncertainty of a nonlinear system. A high-order Taylor expansion of the final state with respect to the initial deviations is firstly computed with the differential algebra technique. Then the initial uncertainty is split to a Gaussian mixture model. With the high-order state transition polynomial, each Gaussian mixture element is propagated to the final time, forming the final Gaussian mixture model. Through this framework, the final Gaussian mixture model can include the effects of high-order terms during propagation and capture the non-Gaussianity of the uncertainty, which enables a precise propagation of probability density. Moreover, the manual derivation and integration of the high-order variational equations is avoided, which makes the method versatile. The method can handle both the application of nonlinear analytical maps on any domain of interest and the propagation of initial uncertainties through the numerical integration of ordinary differential equation. The performance of the resulting tool is assessed on some typical orbital dynamic models, including the analytical Keplerian motion, the numerical J 2 perturbed motion, and a nonlinear relative motion.

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The analysis and detection of orbit maneuvers for the BeiDou satellites based on orbital elements

et al. 2021

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A simplex method for the orbit determination of maneuvering satellites

Cited by 4 publications

References 16 publications

Initial Identification of Thrust and Orbit Elements for Continuous Thrust Spacecraft in Circular Orbit

Initial Identification of Thrust and Orbit Elements for Continuous Thrust Spacecraft in Circular Orbit

Nonlinear orbital uncertainty propagation with differential algebra and Gaussian mixture model

The analysis and detection of orbit maneuvers for the BeiDou satellites based on orbital elements

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