Detection and orbit determination of a satellite executing low thrust maneuvers

Kelecy, Tom; Jah, Moriba

doi:10.1016/j.actaastro.2009.08.029

Cited by 51 publications

(22 citation statements)

References 1 publication

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“…To overcome these challenges, several approaches have been developed to detect orbital maneuvers of spacecraft. Kelecy and Jah [3] used an orbit determination technique based on batch least squares and the extended Kalman filter (EKF) to detect a single finite maneuver, in which they checked the inconsistency between filtered and smoother state estimates. Holzinger et al [4] developed an optimal control performance metric based on the consistency check of measurement residuals to detect and characterize orbital maneuvers.…”

Section: Introductionmentioning

confidence: 99%

Maneuvering Spacecraft Tracking via State-Dependent Adaptive Estimation

Lee

Hwang

2016

Journal of Guidance, Control, and Dynamics

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In this study, an adaptive estimation algorithm is developed to estimate the state of a spacecraft that performs impulsive maneuvers. The accurate tracking of a maneuvering spacecraft with impulsive burns is a challenging problem since the magnitude and the time of occurrence of impulsive maneuvers are usually unknown a priori. To deal with this problem, an adaptive state estimation algorithm is developed in this study using a bank of extended Kalman filters along with interacting multiple models that account for spacecraft motion with and without impulsive maneuvers. Motivated by the fact that impulsive maneuvers usually occur when certain conditions on the spacecraft state are satisfied, the multiple extended Kalman filters are systematically blended using a state-dependent transition probability. Since the information about the conditions based on which impulsive maneuvers occur is explicitly used in the state-dependent transition probability, the proposed algorithm can predict the impulsive maneuvers more accurately and thus produce more accurate state estimates. The proposed algorithm is demonstrated with two illustrative examples: 1) tracking of a geostationary satellite performing station-keeping maneuvers and 2) tracking of a spacecraft performing orbital transfers. Nomenclature B, G = disturbance and control matrix, respectively inc d = maximum allowed inclination error for geostationary satellite k = discrete-time index m i = mode probability for ith mode m ijj = mixing probability from ith mode to jth mode P = state covariance matrix Q, R = covariance matrix of w and v, respectively q = discrete mode index u = control input vector w, v = process and measurement noise, respectively x, y = state and measurement vector, respectivelŷ x = state estimatê x i , P i = ith mode-conditioned state estimate and covariance matrix, respectively y d = maximum allowed along-track error for geostationary satellite ΔT = sampling time πx = state-dependent jump probability π ij x = state-dependent mode transition probability from ith mode to jth mode

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Section: Introductionmentioning

confidence: 99%

Maneuvering Spacecraft Tracking via State-Dependent Adaptive Estimation

Lee

Hwang

2016

Journal of Guidance, Control, and Dynamics

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“…6 Others have used different maneuver detection and reconstruction methods for varying scenarios. Kelecy examined TLEs to determine maneuvers 7 and also detect continuous low thrust maneuvers 8 with the goal of reducing UCTs. Holzinger evaluated maneuver methods to reduce UCTs through maneuver characterization with uncertain boundary conditions.…”

Section: Introductionmentioning

confidence: 99%

Parameter Requirements for Non-Cooperative Satellite Maneuver Reconstruction Using Adaptive Filters

Goff¹,

Black²,

Beck³

2014

AIAA/AAS Astrodynamics Specialist Conference

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investigates short-term tactical satellite missions that require frequent maneuvers. Pairing research in designing and conducting avoidance maneuvers with research in detecting and tracking maneuvering satellites sets the stage for developing and improving both areas. Strategies in stochastic filtering, smoothing, Multiple Model Adaptive Estimation, and maneuver reconstruction are developed to track a high priority satellite. The article develops a wide range of simulations that modify the maneuver type, tracking antenna performance, antenna coverage, reconstruction method, filtering approach, and number of post-maneuver passes collected. The results determine the levels of error covariance necessary to perform successful maneuver reconstructions. Additionally, the results provide maneuver reconstruction confidence percentages based on the estimated covariance and number of post-maneuver passes.

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“…A new dynamic orbit determination method for GEO satellites after orbit maneuvering, proposed by Li et al could not ensure the continuity of orbit before and after maneuvers [17]. Kelecy and Jah determined the low earth orbit (LEO) satellite orbit for low thrust maneuvers, but post-maneuver data are required for maneuver reconstruction and the method is not suitable for GEO/IGSO [18]. Li et al used two-way satellite-station observations to determine GEO satellite orbits by adding empiric force and maneuver force modeling, which needed the information of maneuver thrust.…”

Section: Introductionmentioning

confidence: 99%

Precise Orbit Determination for BeiDou GEO/IGSO Satellites during Orbit Maneuvering with Pseudo-Stochastic Pulses

et al. 2019

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In order to provide better service for the Asia-Pacific region, the BeiDou navigation satellite system (BDS) is designed as a constellation containing medium earth orbit (MEO), geostationary earth orbit (GEO), and inclined geosynchronous orbit (IGSO). However, the multi-orbit configuration brings great challenges for orbit determination. When orbit maneuvering, the orbital elements of the maneuvered satellites from broadcast ephemeris are unusable for several hours, which makes it difficult to estimate the initial orbit in the process of precise orbit determination. In addition, the maneuvered force information is unknown, which brings systematic orbit integral errors. In order to avoid these errors, observation data are removed from the iterative adjustment. For the above reasons, the precise orbit products of maneuvered satellites are missing from IGS (international GNSS (Global Navigation Satellite System) service) and iGMAS (international GNSS monitoring and assessment system). This study proposes a method to determine the precise orbits of maneuvered satellites for BeiDou GEO and IGSO. The initial orbits of maneuvered satellites could be backward forecasted according to the precise orbit products. The systematic errors caused by unmodeled maneuvered force are absorbed by estimated pseudo-stochastic pulses. The proposed method for determining the precise orbits of maneuvered satellites is validated by analyzing data of stations from the Multi-GNSS Experiment (MGEX). The results show that the precise orbits of maneuvered satellites can be estimated correctly when orbit maneuvering, which could supplement the precise products from the analysis centers of IGS and iGMAS. It can significantly improve the integrality and continuity of the precise products and subsequently provide better precise products for users.

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Detection and orbit determination of a satellite executing low thrust maneuvers

Cited by 51 publications

References 1 publication

Maneuvering Spacecraft Tracking via State-Dependent Adaptive Estimation

Maneuvering Spacecraft Tracking via State-Dependent Adaptive Estimation

Parameter Requirements for Non-Cooperative Satellite Maneuver Reconstruction Using Adaptive Filters

Precise Orbit Determination for BeiDou GEO/IGSO Satellites during Orbit Maneuvering with Pseudo-Stochastic Pulses

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