Accurate orbit predictions for debris orbit manoeuvre using ground-based lasers
TL;DR: In this paper, the authors presented the method and results of a short-term accurate low Earth orbiting (LEO) trajectory prediction using ground-based laser-based ground-BSs.
About: This article is published in Advances in Space Research.The article was published on 2013-12-01. It has received 31 citations till now. The article focuses on the topics: Space debris & Debris.
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TL;DR: This paper provides review and comparison of the existing technologies on active space debris capturing and removal, and reviews research areas worth investigating under each capture and removal method.
527 citations
TL;DR: The Environmental Satellite (Envisat) mission was finished on April 8, 2012, and since that time, the attitude of the satellite has undergone significant changes, so determination of the attitude and the spin period of Envisat during seven months of 2013 is made.
Abstract: The Environmental Satellite (Envisat) mission was finished on April 8, 2012, and since that time, the attitude of the satellite has undergone significant changes. During the International Laser Ranging Service campaign, the Satellite Laser Ranging (SLR) stations have performed the range measurements to the satellite that allowed determination of the attitude and the spin period of Envisat during seven months of 2013. The spin axis of the satellite is stable within the radial coordinate system (RCS; fixed with the orbit) and is pointing in the direction opposite to the normal vector of the orbital plane in such a way that the spin axis makes an angle of 61.86 $^{\circ}$ with the nadir vector and 90.69 $^{\circ}$ with the along-track vector. The offset between the symmetry axis of the retroreflector panel and the spin axis of the satellite is 2.52 m and causes the meter-scale oscillations of the range measurements between the ground SLR system and the satellite during a pass. Envisat rotates in the counterclockwise (CCW) direction, with an inertial period of 134.74 s (September 25, 2013), and the spin period increases by 36.7 ms/day.
109 citations
Cites methods from "Accurate orbit predictions for debr..."
...The spinning array of the CCRs causes a millimeter-scale modulation of the range measurements that engraves a frequency signal on the SLR data....
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TL;DR: A novel approach is proposed for the mission planning of on-orbit servicing such as visual inspection, active debris removal and refueling through multiple servicing satellites (SSs) that reduces the fuel consumption and the mission duration significantly in comparison with the conventional approaches.
33 citations
TL;DR: In this paper, the authors used bi-static laser observations for orbit determination and prediction of the defunct ENVISAT satellite and found that the concept of bistatic laser observation improves the prediction accuracy by one order of magnitude compared to the results based on two-way laser ranges only.
27 citations
TL;DR: In this article, the authors presented comprehensive results and analyses for the assessment of short-term orbital prediction accuracy. But the main objectives of the analysis were to assess the performance of shortterm (1-2 days) orbital prediction using single-station tracking data from Mt. Stromlo.
24 citations
References
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01 Jan 2001
TL;DR: In this article, the authors present a dictionary of symbols for modeling the atmosphere, including equations of motion, coordinate and time systems, and initial orbit determination and estimation, as well as various perturbation techniques.
Abstract: 1. Equations of Motion. 2. Kepler's Equation and Kepler's Problem. 3. Coordinate and Time Systems. 4. Observations. 5. Celestial Phenomena. 6. Orbital Maneuvering. 7. Initial Orbit Determination. 8. Special Perturbation Techniques. 9. General Perturbation Techniques. 10. Orbit Determination and Estimation. 11. Mission Analysis. Appendix A: Dictionary of Symbols. Appendix B: Modeling the Atmosphere. Appendix C: Mathematical Fundamentals. Appendix D: Constants and Expansions.
2,095 citations
Book•
01 Mar 1997
TL;DR: In this article, the authors present a dictionary of symbols for modeling the atmosphere, including equations of motion, coordinate and time systems, and initial orbit determination and estimation, as well as various perturbation techniques.
Abstract: 1. Equations of Motion. 2. Kepler's Equation and Kepler's Problem. 3. Coordinate and Time Systems. 4. Observations. 5. Celestial Phenomena. 6. Orbital Maneuvering. 7. Initial Orbit Determination. 8. Special Perturbation Techniques. 9. General Perturbation Techniques. 10. Orbit Determination and Estimation. 11. Mission Analysis. Appendix A: Dictionary of Symbols. Appendix B: Modeling the Atmosphere. Appendix C: Mathematical Fundamentals. Appendix D: Constants and Expansions.
1,765 citations
TL;DR: In this article, a mathematical model was used to predict the rate at which such a belt might form, under certain conditions the belt could begin to form within this century and could be a significant problem during the next century.
Abstract: As the number of artificial satellites in earth orbit increases, the probability of collisions between satellites also increases. Satellite collisions would produce orbiting fragments, each of which would increase the probability of further collisions, leading to the growth of a belt of debris around the earth. This process parallels certain theories concerning the growth of the asteroid belt. The debris flux in such an earth-orbiting belt could exceed the natural meteoroid flux, affecting future spacecraft designs. A mathematical model was used to predict the rate at which such a belt might form. Under certain conditions the belt could begin to form within this century and could be a significant problem during the next century. The possibility that numerous unobserved fragments already exist from spacecraft explosions would decrease this time interval. However, early implementation of specialized launch constraints and operational procedures could significantly delay the formation of the belt.
758 citations
TL;DR: In this article, the HWM90 thermospheric wind model has been revised in the lower thermosphere and extended into the mesosphere, stratosphere and lower atmosphere to provide a single analytic model for calculating zonal and meridional wind profiles representative of the climatological average for various geophysical conditions.
676 citations
"Accurate orbit predictions for debr..." refers background or methods in this paper
...The wind model (Hedin et al., 1996) is used to compute the atmospheric wind velocity in Eq....
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...The wind model (Hedin et al., 1996) is used to compute the atmospheric wind velocity in Eq. (4). The BCEM has been validated for LEO objects lower than 650 km in perigee altitude by Sang et al. (2013). For objects at about 800 km in perigee altitude, 4 geodetic satellites, Starlette, Stella, Westpac and ERS-2, are chosen to...
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...Methods to mitigate and potentially reverse the collisional cascading phenomenon have been widely investigated since Kessler and Cour-Palais (1978) predicted its onset....
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TL;DR: The LEGEND (LEO-to-GEO Environment Debris model) is a high-fidelity three-dimensional physical model developed by the U.S. National Aeronautics and Space Administration (NASA) that is capable of simulating the historical environment and the evolution of future debris populations as discussed by the authors.
Abstract: 340 C R E D IT : (T O P ) N A S A S ince the launch of Sputnik I, space activities have created an orbital debris environment that poses increasing impact risks to existing space systems, including human space flight and robotic missions (1, 2). Currently, more than 9000 Earth-orbiting man-made objects (including many breakup fragments), with a combined mass exceeding 5 million kg, are tracked by the U.S. Space Surveillance Network and maintained in the U.S. satellite catalog (3–5). Three accidental collisions between catalogued objects during the period from late 1991 to early 2005 have already been documented (6), although, fortunately, none resulted in the creation of large, trackable debris clouds. The most recent (January 2005) was between a 31-year-old U.S. rocket body and a fragment from the third stage of a Chinese CZ-4 launch vehicle that had exploded in March 2000. Several studies conducted during 1991–2001 demonstrated, with assumed future launch rates, the potential increase in the Earth satellite population, resulting from random, accidental collisions among resident space objects (7–13). In some low Earth orbit (LEO) altitude regimes, where the number density of objects is above a critical spatial density, the production rate of new debris due to collisions exceeds the loss of objects due to orbital decay. LEGEND (LEO-to-GEO Environment Debris model), is a highfidelity three-dimensional physical model developed by the U.S. National Aeronautics and Space Administration (NASA) that is capable of simulating the historical environment, as well as the evolution of future debris populations (14, 15). The LEGEND future projection adopts a Monte Carlo approach to simulate future onorbit explosions and collisions (16). A total of 50 (17), 200-year future projection Monte Carlo simulations were executed and evaluated, under the assumptions that no rocket bodies and spacecraft were launched after December 2004 and that no future disposal maneuvers were allowed for existing spacecraft (few of which currently have such a capability) (18). The simulated 10-cm and larger debris populations in LEO (defined as the region between altitudes of 200 and 2000 km) between 1957 and the end of a 200-year future projection period
324 citations