Close approach of a cloud of particles around an oblate planet

Gomes, Vivian Martins; Oliveira, Geraldo Magela Couto; Prado, A. F. B. A.; Sanchez, Diogo M.

doi:10.1007/s40314-015-0264-x

Cited by 4 publications

(6 citation statements)

References 24 publications

(24 reference statements)

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“…Our proposal is then directly related to the gravity-assisted maneuver [20][21][22][23][24][25], where the asteroid will make a swing-by with the Earth that changes its orbit and avoid the collision to occur.…”

Section: Resultsmentioning

confidence: 99%

“…Therefore, the present paper is a sequence of this study and focus in the situation where the impulse is applied close to this previous passage, instead of well before the collision. The idea follows the concept of "powered swing-by" used to maneuver a spacecraft [20][21][22], which is considered an alternative to the pure gravity swing-by [23][24][25]. The main idea is to change the trajectory of the spacecraft a little bit to get a more adequate geometry in this passage of the Earth such that it makes a swing-by that generates larger changes in the orbit of the asteroid around the Sun, so making larger deviations in the asteroid-Earth distance in the next passage.…”

Section: Introductionmentioning

confidence: 99%

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Deflecting an Asteroid on a Collision Course with Earth Using a Powered Swing-By Maneuver

2022

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The deflection of potentially dangerous asteroids has been treated with great intensity and has gained more and more attention in scientific research. Different techniques are developed over the years. Among these techniques, we found the kinetic impact deflection technique to be the most viable at the moment. In this work we address the kinetic impact deflection technique, but in a scenario where we have a short time to deflect an asteroid that will collide with Earth. For this, we also use a maneuver similar to a powered gravity-assisted maneuver with Earth in a previous passage to change the trajectory of the asteroid to avoid the collision. We apply this technique in three scenarios: (i) impulse before the close encounter, (ii) impulse during the close encounter, and (iii) impulse after the close encounter. We observe that some trajectories are symmetric with respect to the line Sun–Earth, and others are asymmetric. We show that, using this technique, it is possible to change the trajectory of the asteroid, even in a short period, to avoid the collision without using a large variation of velocity in the orbit of the asteroid.

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Deflecting an Asteroid on a Collision Course with Earth Using a Powered Swing-By Maneuver

2022

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“…A cloud of particles with an initial distribution of semi-major axis and eccentricity makes a close approach with the Earth (Formiga et al 2017;Gomes et al 2008Gomes et al , 2010Gomes et al , 2016. The goal is first to obtain the new distribution of semi-major axis and eccentricity after this close approach.…”

Section: Definition Of the Problemmentioning

confidence: 99%

Study of collision probability considering a non-uniform cloud of space debris

et al. 2019

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The present paper aims to study the cumulative collision probability of a target that crosses a cloud of particles that has the orbital parameters of each individual element modified by a close approach with the Earth. Clouds of this type are formed when natural or man-made bodies explode for some reason. After an explosion like that, the individual particles have different trajectories. The clouds are specified by a non-uniform distribution of semi-major axis and eccentricity of their particles which are assumed to pass close to the Earth, making a close approach that modifies the trajectory of every single particle that belongs to the cloud. This study makes simulations considering separately two different clouds based on the patched conics model to obtain the new trajectories of each particle and to analyze the density of the whole cloud. Then it is possible to map the new distribution of the orbital elements of the fragments that constituted the cloud, using the distribution as initial conditions. After calculating the spatial density for the whole cloud, it is possible to obtain the cumulative collision probability for one space vehicle that crosses the cloud. These pieces of information are important when planning satellite missions where a spacecraft passes close to a cloud of this type, because we can determine values to study the risks of collision and the possible maneuvers that need to be made to avoid them.

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“…Gomes et al. 18 investigated the J2 perturbed motion of a cloud of particles around an oblate planet. Liu et al.…”

Section: Introductionmentioning

confidence: 99%

“…Srivastava et al 17 studied the effects of oblateness and solar radiation pressure on halo orbits around the collinear Lagrangian points L1 and L2. Gomes et al 18 investigated the J2 perturbed motion of a cloud of particles around an oblate planet. Liu et al 19 derived the orbital and attitude dynamical equations of a solar power satellite with flexible vibration under the influence of gravitational perturbation generated by the Sun, the Moon and the oblateness of the Earth.…”

Section: Introductionmentioning

confidence: 99%

Approximate analytic solution of motion for spacecraft around an oblate planet

Wang

Zheng

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The oblateness of a planet has an important effect on the surrounding spacecraft and is usually regarded as a significant perturbation factor to spacecraft’s motion. In this paper, an approximate analytic solution of motion for spacecraft which considering this perturbation factor is investigated. The perturbed dynamic model which taking true anomaly as the independent variable is firstly built in non-inertial coordinate system moving with a Kepler two-body orbit, then the six-dimensional state transition matrix about the state deviation vector is introduced. After that, the expression of J2 term’s gravitational potential in this non-inertial coordinate system is obtained based on spherical trigonometry, and the analytic solution for every variable of the state deviation vector is then derived by complicated mathematic transformation. Numerical simulation results done by the presented method have been compared with that done by numerical integration as well as an existing first-order analytic solution. The comparison results show that the presented method has high accuracy, and is more accurate than the first-order analytic solution within one or few orbit revolutions, which makes it more suitable for short-term orbit prediction of the satellites, especially for those suborbital flight vehicles.

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Close approach of a cloud of particles around an oblate planet

Cited by 4 publications

References 24 publications

Deflecting an Asteroid on a Collision Course with Earth Using a Powered Swing-By Maneuver

Deflecting an Asteroid on a Collision Course with Earth Using a Powered Swing-By Maneuver

Study of collision probability considering a non-uniform cloud of space debris

Approximate analytic solution of motion for spacecraft around an oblate planet

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