An adaptive optics aided differential optical positioning for passive orbit determination of the space debris at the geostationary orbit

2017 ◽  
Vol 139 ◽  
pp. 367-376 ◽  
Author(s):  
Piotr Piatrou ◽  
Francois Rigaut
Keyword(s):  
Adaptive Optics ◽  
Orbit Determination ◽  
Space Debris ◽  
Geostationary Orbit ◽  
Optical Positioning

Enabling orbit determination of space debris using narrowband radar

2015 ◽  
Vol 51 (2) ◽  
pp. 1231-1240 ◽  
Author(s):  
Mauro Grassi ◽  
Ediz Cetin ◽  
Andrew G. Dempster
Keyword(s):  
Orbit Determination ◽  
Space Debris

scholarly journals Modeling and Analysis of an Echo Laser Pulse Waveform for the Orientation Determination of Space Debris

2020 ◽  
Vol 12 (10) ◽  
pp. 1659
Author(s):  
Hyung-Chul Lim ◽  
Zhong-Ping Zhang ◽  
Ki-Pyoung Sung ◽  
Jong Uk Park ◽  
Simon Kim ◽  
...  
Keyword(s):  
Laser Pulse ◽  
Numerical Simulations ◽  
Adaptive Optics ◽  
Space Debris ◽  
Pulse Waveform ◽  
Modeling And Analysis ◽  
Gaussian Decomposition ◽  
Orientation Information ◽  
Orientation Determination

Orientation information of space debris is required to improve the orbital prediction accuracy for mitigation or elimination of a significant threat to not only human space activities but also operational satellites. Obtaining orientation information is currently achievable by applying photometry, adaptive optics (AO) and satellite laser ranging (SLR) technologies. In this study, a new method is proposed based on an echo laser pulse waveform (ELPW) for the orientation determination of space debris; its feasibility was also investigated by numerical simulations. Unlike the photometry and AO technologies available just under the sun-illumination condition and the SLR technology applicable only for cooperative targets, the ELPW is achievable by using a high power laser regardless of the above measurement constraints. A mathematical model is derived to generate the ELPW, and the beam broadening and spreading due to the atmospheric turbulence is taken into account. The Gaussian decomposition based on a genetic algorithm was employed to the ELPWs in order to analyze the orientation features. It is demonstrated from the numerical simulations that the ELPWs have distinctive shapes characterizing the orientation of space debris and therefore our approach was capable of providing orientation information.

scholarly journals Precise Orbit Determination of BDS MEO Satellites Based on Satellite TT&C Stations

2016 ◽  
Vol 2016 ◽  
pp. 1-13
Author(s):  
Kezhao Li ◽  
Zhiwei Li ◽  
Lin Chai ◽  
An-min Ding ◽  
Jin-ben Wei ◽  
...  
Keyword(s):  
Orbit Determination ◽  
Precise Orbit Determination ◽  
Satellite System ◽  
Calculation Model ◽  
Geostationary Orbit ◽  
Precise Orbit ◽  
Triple Frequency ◽  
Relative Orbit ◽  
Sufficient And Necessary Conditions

A novel method, which is based on the triple-frequency combination and Space-Based Telemetry, Tracking, and Command (STT&C) stations, is proposed in this paper. Considering BeiDou Navigation Satellite System (BDS) Geostationary Orbit (GEO) and Inclined Geostationary Orbit (IGSO) satellites as the STT&C facilities, firstly, we presented the BDS Medium Earth Orbit (MEO) satellites’ precise orbit determination scheme based on triple-frequency combination. Then, we gave the sufficient and necessary conditions about the visibility and the coverage rate calculation model of STT&C to BDS MEO satellite. And then we deduced the model of BDS MEO satellites precise orbit determination based on triple-frequency combination observations. At last, we designed the simulation calculation. The simulation results show that orbit determination of BDS MEO satellite based on STT&C station can be realized at all times. And most of the simulation period time, under the condition of the dm level orbit determination for GEO/IGSO satellites, the position accuracy of the relative orbit determination is better than 4 m, the horizontal accuracy of the relative orbit determination is within 2.5 m, and the vertical accuracy of the relative orbit determination is less than 3.5 m.

scholarly journals Robust Positioning, Preliminary Orbit Determination, and Trajectory Prediction of Space Debris using In-Space Iterative-Bearing-Only Observations

2017 ◽  
Vol 70 (4) ◽  
pp. 789-809 ◽  
Author(s):  
MA Amiri Atashgah ◽  
MR Torkamani ◽  
Abolfazl Lavaei
Keyword(s):  
Kalman Filter ◽  
Extended Kalman Filter ◽  
Orbit Determination ◽  
Space Debris ◽  
Position Vector ◽  
Hybrid Technique ◽  
Orbital Elements ◽  
Trajectory Prediction ◽  
Distance Vector

This paper is concerned with the preliminary localisation, orbit determination and model-based path forecasting of space debris based on a robust procedure. In this work, an in-orbit observer utilises only relative bearing observations iteratively. To this end, the problem is first formulated in order to calculate the distance vector between the space debris and any orbiting observer. Afterwards, the obtained position vector is corrected through an Extended Kalman Filter (EKF) for shrinking the sensor and process errors and increasing robustness of the computations in the presence of uncertainties. After preliminary positioning, the related classical orbital elements are acquired via the predicted position and velocity vectors using a hybrid technique. Extensive simulations demonstrate the efficacy and robustness of the aforementioned method, and in particular it is verified that the proposed scheme is capable of producing a suitable solution for preliminary localisation and orbit determination of space debris based on the presented space-based observation, which is practical in phasing and chasing manoeuvres of any grabber space robot.

scholarly journals Orbit determination of space debris: admissible regions

2007 ◽  
Vol 97 (4) ◽  
pp. 289-304 ◽  
Author(s):  
G. Tommei ◽  
A. Milani ◽  
A. Rossi
Keyword(s):  
Orbit Determination ◽  
Space Debris

scholarly journals A Second-Order Time-Difference Position Constrained Reduced-Dynamic Technique for the Precise Orbit Determination of LEOs Using GPS

2021 ◽  
Vol 13 (15) ◽  
pp. 3033
Author(s):  
Hui Wei ◽  
Jiancheng Li ◽  
Xinyu Xu ◽  
Shoujian Zhang ◽  
Kaifa Kuang
Keyword(s):  
Orbit Determination ◽  
Dynamic Models ◽  
Precise Orbit Determination ◽  
Second Order ◽  
Time Difference ◽  
Error Sources ◽  
Precise Orbit ◽  
Unmodeled Dynamic ◽  
Reduced Dynamic

In this paper, we propose a new reduced-dynamic (RD) method by introducing the second-order time-difference position (STP) as additional pseudo-observations (named the RD_STP method) for the precise orbit determination (POD) of low Earth orbiters (LEOs) from GPS observations. Theoretical and numerical analyses show that the accuracies of integrating the STPs of LEOs at 30 s intervals are better than 0.01 m when the forces (<10−5 ms−2) acting on the LEOs are ignored. Therefore, only using the Earth’s gravity model is good enough for the proposed RD_STP method. All unmodeled dynamic models (e.g., luni-solar gravitation, tide forces) are treated as the error sources of the STP pseudo-observation. In addition, there are no pseudo-stochastic orbit parameters to be estimated in the RD_STP method. Finally, we use the RD_STP method to process 15 days of GPS data from the GOCE mission. The results show that the accuracy of the RD_STP solution is more accurate and smoother than the kinematic solution in nearly polar and equatorial regions, and consistent with the RD solution. The 3D RMS of the differences between the RD_STP and RD solutions is 1.93 cm for 1 s sampling. This indicates that the proposed method has a performance comparable to the RD method, and could be an alternative for the POD of LEOs.

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