Mitigation Rules Compliance in Low Earth Orbit

Morand, Vincent; Dolado-Perez, J.C.; Philippe, Thomas; Handschuh, David-Alexis

doi:10.1016/s2468-8967(16)30085-4

Cited by 6 publications

(5 citation statements)

References 3 publications

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“…After choosing the target debris of the flyby, the following optimization problem is to be solved: find the departure time τ 0 on DRO and two maneuvers Γ 0 (X 0 ) and Γ 1 (X 1 ) such that the total impulse ||∆V 0 ||+||∆V 1 || is minimized and the flyby condition of one piece of SSO target debris is satisfied. The framework of the optimization problem is shown in Equation (18). The minimization strategy is obtained via the built-in fmincon tool.…”

Section: Local Optimizationmentioning

confidence: 99%

“…Space debris has seriously affected the safety of space missions. Between the years 2000 and 2013, only 12% of spacecraft performed reentry or deorbit maneuvers at their endof-life, and only 10% of spacecraft successfully performed 25-year deorbit maneuvers [18]. NASA research shows that even if 90% of constellations successfully perform 25-year deorbit maneuvers, there will still be 290% more space debris in the next 200 years than if there were no giant constellations [19].…”

Section: Introductionmentioning

confidence: 99%

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Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit

Zhang,

Wang

2024

Universe

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This paper investigates the trajectory design problem in the scenario of a multiple Sun-synchronous Orbit (SSO) space debris flyby mission from a DRO space station. At first, the characteristics of non-planar transfer from DRO to SSO in the Earth–Moon system are analyzed. The methods of large-scale ergodicity and pruning are utilized to investigate single-impulse and two-impulse DRO–Earth transfers. Using a powered lunar flyby, the two-impulse DRO–Earth transfer is able to fly by SSO debris while satisfying the requirements of the mission. After the local optimization, the optimal result of two-impulse DRO–Earth transfer and flyby is obtained. A multi-objective evolutionary algorithm is used to design the Pareto-optimal trajectories of multiple flybys. The semi-analytical optimization method is developed to provide the estimations of the transfer parameters in order to reduce the computations caused by the evolutionary algorithm. Simulations show that transferring from the 3:2 resonant DRO to a near-coplanar flyby of a SSO target debris using a powered lunar gravity assist needs a 0.47 km/s velocity increment. The mission’s total velocity increment is 1.39 km/s, and the total transfer time is 2.23 years.

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Section: Local Optimizationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit

Zhang,

Wang

2024

Universe

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“…Semi-analytical methods are an intermediate approach, whereby short-period motions are modeled analytically, and long-term secular effects are solved with numerical integrators (Morand et al 2013;Lara et al 2016;Lévy et al 2021).…”

Section: Orbital Propagatorsmentioning

confidence: 99%

asteRisk - Integration and Analysis of Satellite Positional Data in R

Ayala,

Sellés Vidal

et al. 2023

The R Journal

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Over the past few years, the amount of artificial satellites orbiting Earth has grown fast, with close to a thousand new launches per year. Reliable calculation of the evolution of the satellites' position over time is required in order to efficiently plan the launch and operation of such satellites, as well as to avoid collisions that could lead to considerable losses and generation of harmful space debris. Here, we present asteRisk, the first R package for analysis of the trajectory of satellites. The package provides native implementations of different methods to calculate the orbit of satellites, as well as tools for importing standard file formats typically used to store satellite position data and to convert satellite coordinates between different frames of reference. Such functionalities provide the foundation for integrating orbital data and astrodynamics analysis in R.

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“…As most satellites launched above 600 Km, this is the main reason why retired satellites and rocket bodies are still out in orbit after decades. Secondly, international guidelines suggest the proper disposal of satellites into graveyard orbits after the end of a satellite's life, but only approximately 60% of the satellites are appropriately managed [15]. This noncompliance with international mitigation recommendations is another reason.…”

Section: Sources Of Space Debrismentioning

confidence: 99%

“…However, studies show that the global compliance rate of the 25-year post-mission guideline is 59% between 2000 and 2013 [15], [45]. Among these, the vast majority are naturally compliant due to orbit, and only 10% of spacecraft performed a successful deorbit maneuver [15].…”

Section: The Proper End Of Mission Disposal Of Spacecraft; Inmentioning

confidence: 99%

Orbital Debris Threat for Space Sustainability and Way Forward (Review Article)

Murtaza

Pirzada

et al. 2020

IEEE Access

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Over the past 60 years, satellite technology has demonstrated its usefulness successfully. However, this usefulness is at stake from a future point of view, due to the well-admitted orbital/space debris threat. This article thoroughly reviews all aspects of space debris issue including causes, amount and sizes of orbital debris, potential threats, counter-strategies with their latest status and related legal issues to highlight the criticality and urgency of the problem. This review elaborates the fact that despite all the worries and threats, the efforts to confront this challenge are considerably insufficient until today. This bitter reality demands for at-least curtailing the number of future launches to ensure the long-term sustainability of space, until the improvement in debris situation. However, contradictory to this necessity, large satellite constellations have been proposed that can drastically increase the existing orbital population in coming years. This approach will certainly not help in improving the space environment in the future; instead, it can worsen the space environment situation as recent studies shows. Also, space resources (i.e. orbital slots and frequencies) are limited to accommodate many more satellite projects from commercial and government organization in the future. So, there is a serious question of how the space industry can move forward to maintain a balance in controlling the future number of the satellite while accommodating many commercial or government space entities. This article also identifies two optimized approaches as a way forward for future satellite projects that can also enhance the effectiveness of space technology in the future.

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Mitigation Rules Compliance in Low Earth Orbit

Cited by 6 publications

References 3 publications

Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit

Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit

asteRisk - Integration and Analysis of Satellite Positional Data in R

Orbital Debris Threat for Space Sustainability and Way Forward (Review Article)

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