In this paper, a simple analytical method is developed to accurately approximate the transfer costs between two objects of the removal sequence. The accuracy of these estimations is verified by comparison with existing optimized solutions.Rendezvous transfers between two given orbits are dealt with using an accurate dynamic model that takes J2 perturbation into account. The state-of-the-art solution winner of the ninth Global Trajectory Optimization Competition (GTOC9) by the Jet Propulsion Laboratory (JPL) is used as benchmark to verify the accuracy of the method presented in this paper
We have considered one of the ways to clean the near-Earth orbits from space debris implying the rem...
This paper presents a high-accuracy fully analytical formulation to compute the miss distance and co...
Debris in Low Earth Orbit (LEO) poses a great risk to humanity’s access to space in the coming years...
In this paper, detailed mission design for multiple debris removal is performed by selecting the mos...
In order to keep a safe access to space in the coming years, it will be necessary to clean the near ...
This paper presents a novel approach for the preliminary design of Low-Thrust (LT), many-revolution ...
The paper compares two variants of re-orbiting space debris objects from the geosynchronous (GEO) re...
We investigated the applicability of the Lambert solver (Izzo, 2014) for preliminary design of Multi...
The concentration of spacecraft residual parts in Low Earth Orbits, known as Space Debris is of the ...
This paper presents a novel approach for the preliminary design of Low-Thrust, many-revolution trans...
In this paper two strategies are proposed to de-orbit up to 10 non-cooperative objects per year from...
The problem of spacecraft transferring to the vicinity of space debris object in close low-eccentric...
The paper compares two variants of re-orbiting space debris objects from the geosynchronous (GEO) re...
Abstract: The paper regards the problem of finding the optimal sequence of transfers betwe...
In this paper two novel strategies to automatically design an optimized mission to de-orbit up to 10...
We have considered one of the ways to clean the near-Earth orbits from space debris implying the rem...
This paper presents a high-accuracy fully analytical formulation to compute the miss distance and co...
Debris in Low Earth Orbit (LEO) poses a great risk to humanity’s access to space in the coming years...
In this paper, detailed mission design for multiple debris removal is performed by selecting the mos...
In order to keep a safe access to space in the coming years, it will be necessary to clean the near ...
This paper presents a novel approach for the preliminary design of Low-Thrust (LT), many-revolution ...
The paper compares two variants of re-orbiting space debris objects from the geosynchronous (GEO) re...
We investigated the applicability of the Lambert solver (Izzo, 2014) for preliminary design of Multi...
The concentration of spacecraft residual parts in Low Earth Orbits, known as Space Debris is of the ...
This paper presents a novel approach for the preliminary design of Low-Thrust, many-revolution trans...
In this paper two strategies are proposed to de-orbit up to 10 non-cooperative objects per year from...
The problem of spacecraft transferring to the vicinity of space debris object in close low-eccentric...
The paper compares two variants of re-orbiting space debris objects from the geosynchronous (GEO) re...
Abstract: The paper regards the problem of finding the optimal sequence of transfers betwe...
In this paper two novel strategies to automatically design an optimized mission to de-orbit up to 10...
We have considered one of the ways to clean the near-Earth orbits from space debris implying the rem...
This paper presents a high-accuracy fully analytical formulation to compute the miss distance and co...
Debris in Low Earth Orbit (LEO) poses a great risk to humanity’s access to space in the coming years...