Two Line Element Accuracy Assessment Based On A Mixture of Gaussian Laws

Legendre, Paul; Deguine, B.; Garmier, Romain; Revelin, Bruno

doi:10.2514/6.2006-6518

Cited by 17 publications

(7 citation statements)

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“…1). This conclusion is consistent with Flohrer et al (2008); Hirose et al 2010; Legendre et al (2006). The correlation parameter errors, with normalized units after 14 days of orbital propagation, for four objects are listed in Table 3 and illustrated in Figures 2-5.…”

Section: Error Analysis Of the Correlation Parameterssupporting

confidence: 89%

Orbital correlation of space objects based on orbital elements

Wang

et al. 2016

Res. Astron. Astrophys.

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Orbital correlation of space objects is one of the most important elements in space object identification. Using the orbital elements, we provide correlation criteria to determine if objects are coplanar, co-orbital or the same. We analyze the prediction error of the correlation parameters for different orbital types and propose an orbital correlation method for space objects. The method is validated using two line elements and multisatellite launching data. The experimental results show that the proposed method is effective, especially for space objects in near-circular orbits.

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Section: Error Analysis Of the Correlation Parameterssupporting

confidence: 89%

Orbital correlation of space objects based on orbital elements

Wang

et al. 2016

Res. Astron. Astrophys.

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“…filtering) and other techniques from statistical orbit determination, treating TLEs as observations. Also, recent work Legendre et al (2008); Muldoon & Elkaim (2008) suggests that there may be simple global transformations of TLE data that can improve TLE/SGP4 accuracy. These systematic corrections might also be further refined on the basis of orbital parameters, resulting in a look-up-table used to correct TLEs as a function of their orbital regimes.…”

Section: Methodological Improvementsmentioning

confidence: 99%

Improved orbit predictions using two-line elements

Levit

Marshall

2011

Advances in Space Research

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The density of orbital space debris constitutes an increasing environmental challenge. There are three ways to alleviate the problem: debris mitigation, debris removal and collision avoidance. This paper addresses collision avoidance, by describing a method that contributes to achieving a requisite increase in orbit prediction accuracy. Batch least-squares differential correction is applied to the publicly available two-line element (TLE) catalog of space objects. Using a high-precision numerical propagator, we fit an orbit to state vectors derived from successive TLEs. We then propagate the fitted orbit further forward in time. These predictions are compared to precision ephemeris data derived from the International Laser Ranging Service (ILRS) for several satellites, including objects in the congested sun-synchronous orbital region. The method leads to a predicted range error that increases at a typical rate of 100 meters per day, approximately a 10-fold improvement over TLE's propagated with their associated analytic propagator (SGP4). Corresponding improvements for debris trajectories could potentially provide initial conjunction analysis sufficiently accurate for an operationally viable collision avoidance system. We discuss additional optimization and the computational requirements for applying all-on-all conjunction analysis to the whole TLE catalog, present and near future. Finally, we outline a scheme for debris-debris collision avoidance that may become practicable given these developments.Comment: Submitted to Advances in Space Research. 13 pages, 4 figure

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“…Collision with orbital debris is a serious threat that can damage the spacecraft. Several collision risk assessment methods have been developed, see for example, and references therein, along with debris collision avoidance strategies, see for example, and references therein. In , for instance, collision avoidance strategies for polyhedral objects as obstacles have been developed on the basis of mixed‐integer linear programming.…”

Section: Collision Avoidance Maneuversmentioning

confidence: 99%

Model Predictive Control approach for guidance of spacecraft rendezvous and proximity maneuvering

Cairano

Park

Kolmanovsky

2012

Intl J Robust & Nonlinear

214

122

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Traditionally rendezvous and proximity maneuvers have been performed using open-loop maneuver planning techniques and ad hoc error corrections. In this paper, a Model Predictive Control (MPC) approach is applied to spacecraft rendezvous and proximity maneuvering problems in the orbital plane. We demonstrate that various constraints arising in these maneuvers can be effectively handled with the MPC approach. These include constraints on thrust magnitude, constraints on spacecraft positioning within Line-of-Sight (LOS) cone while approaching the docking port on a target platform, and constraints on approach velocity to match the velocity of the docking port. The two cases of a non-rotating and a rotating (tumbling) platform are treated separately, and trajectories are evaluated in terms of maneuver time and fuel consumption. For the case when the platform is not rotating and the docking port position is fixed with respect to the chosen frame, an explicit off-line solution of the MPC optimization problem is shown to be possible; this explicit solution has a form of a piecewise affine control law suitable for on-line implementation without an onboard optimizer. In the case of a fast rotating platform, it is, however, shown that the prediction of the platform rotation is necessary to successfully accomplish the maneuvers and to reduce fuel consumption. Finally, the proposed approach is applied to debris avoidance maneuvers with the debris in the spacecraft rendezvous path. The significance of this paper is in demonstrating that Model Predictive Control can be an effective feedback control approach to satisfy various maneuver requirements, reduce fuel consumption, and provide robustness to disturbances. International Journal of Robust and Nonlinear ControlThis work may not be copied or reproduced in whole or in part for any commercial purpose. Permission to copy in whole or in part without payment of fee is granted for nonprofit educational and research purposes provided that all such whole or partial copies include the following: a notice that such copying is by permission of Mitsubishi Electric Research Laboratories, Inc.; an acknowledgment of the authors and individual contributions to the work; and all applicable portions of the copyright notice. Copying, reproduction, or republishing for any other purpose shall require a license with payment of fee to Mitsubishi Electric Research Laboratories, Inc. All rights reserved. SUMMARYTraditionally rendezvous and proximity maneuvers have been performed using open-loop maneuver planning techniques and ad hoc error corrections. In this paper, a Model Predictive Control (MPC) approach is applied to spacecraft rendezvous and proximity maneuvering problems in the orbital plane. We demonstrate that various constraints arising in these maneuvers can be effectively handled with the MPC approach. These include constraints on thrust magnitude, constraints on spacecraft positioning within Line-of-Sight (LOS) cone while approaching the docking port on a target platform, and ...

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Two Line Element Accuracy Assessment Based On A Mixture of Gaussian Laws

Cited by 17 publications

References 0 publications

Orbital correlation of space objects based on orbital elements

Orbital correlation of space objects based on orbital elements

Improved orbit predictions using two-line elements

Model Predictive Control approach for guidance of spacecraft rendezvous and proximity maneuvering

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