Orbital control of a satellite using the gravity of the Moon

Prado, A. F. B. A.

doi:10.1590/s1678-58782006000100012

Cited by 5 publications

(4 citation statements)

References 14 publications

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“…Research on lunar swing-by maneuvers is also present in many works. For example, Dunham and Davis [24] investigated missions with multiple encounters with the Moon, and Prado [25] considered lunar swing-bys to change the inclination of Earth orbits that leave and return to the same altitudes. As examples of missions that performed lunar swing-bys, the ISEE-3, the Nozomi, STEREO probes, and the HGS1 satellite can be highlighted.…”

Section: Introductionmentioning

confidence: 99%

Trajectories Derived from Periodic Orbits around the Lagrangian Point L1 and Lunar Swing-Bys: Application in Transfers to Near-Earth Asteroids

2022

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To present a set of trajectories derived from the retrograde periodic orbits around the Lagrangian equilibrium point L1, this paper considers the Circular Restricted Three-body Problem with Earth-Moon masses (CR3BP), the Restricted Bicircular, and Full Four-Body Sun-Earth-Moon-spacecraft Problems (BCR4BP and FR4BP, respectively). These periodic orbits are predicted by the dynamics of the CR3BP. To generate the trajectories of this set, first, slightly different increments of velocity (∆Vs) from those needed to generate periodic orbits around L1 are applied to a spacecraft in circular low Earth orbits in the same direction of their motion when the Earth, the spacecraft, and the Moon are aligned in this order. Thus, translunar trajectories derived from the periodic orbits are obtained and they will lead the spacecraft to the vicinity of the Moon. Depending on the values of the |∆Vs|, which are also functions of the relative positioning between the Sun, the Earth, and the Moon, three types of trajectories of interest are found: Collision with the Moon, escape, and geocentric orbits with large semi-major axes. For a well-defined interval of the |∆Vs|, the trajectories accomplish swing-bys with the Moon and obtain energy to escape from the Earth–Moon system and reach Near-Earth Asteroids (NEAs) between the orbits of Venus and Mars. This procedure reduces the costs of inserting spacecraft into transfer trajectories to a set of NEAs in terms of the required |∆V| by up to 5% when compared to Lambert’s problem, for example. This work also presents analyses of examples of transfers to the NEAs 3361 Orpheus, 99942 Apophis, and 65803 Didymos, from 2025 on.

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Section: Introductionmentioning

confidence: 99%

Trajectories Derived from Periodic Orbits around the Lagrangian Point L1 and Lunar Swing-Bys: Application in Transfers to Near-Earth Asteroids

2022

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“…The Voyager mission visited several planets of the Solar System gaining energy from successive close approaches [1][2][3][4]. Other applications of this maneuver are available in the literature, like: the use of Swing-Bys in the inner Solar System to send a spacecraft to the giant planets [5] or even to the Sun [6]; the use of Venus in a trip to Mars [7,8]; studies to make a three-dimensional close approach to Jupiter to change the orbital plane of the spacecraft [9]; use of one [10] or two [11] passages by the Moon to increase the energy of the spacecraft; the use of multiple passages by the secondary body to find trajectories linking the primaries [12] or the Lagrangian points [13,14].…”

Section: Introductionmentioning

confidence: 99%

Studying Close Approaches for a Cloud of Particles Considering Atmospheric Drag

Gomes

Formiga

Moraes

2013

Mathematical Problems in Engineering

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The present paper has the goal of studying close approaches between a planet and a group of particles. The mathematical model includes the presence of the atmosphere of the planet. This cloud is assumed to be created by the passage of the spacecraft in the atmosphere of the planet, which can cause the explosion of the spacecraft. The system is assumed to be formed by the Sun, the planet, and the spacecraft that explodes and becomes a cloud of particles. The Sun and the planet are assumed to be in circular orbits and the motion is planar. The equations of motion are the ones given by the circular planar restricted three-body problem combined with the forces given by the atmospheric drag. In the numerical simulations, the planet Jupiter is the celestial body used for the close approaches. The initial positions and velocities of the spacecraft and the particles are specified at the periapsis, because it is assumed that this is the point where the explosion occurs.

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“…There are many studies in the literature that consider a low thrust propulsion system [8][9][10][11][12][13][14] or an impulsive propulsion system [15][16][17][18][19][20][21][22][23]. Another kind of orbital transfer is the gravity-assisted maneuver (or swing-by) that consists in the use of the gravity of a planet or other celestial body to alter the path and speed of a spacecraft, typically in order to save propellant, time, and expense [24][25][26][27][28][29][30][31][32][33].…”

Section: Introductionmentioning

confidence: 99%

Application of the Kalman Filter to Estimate the State of an Aerobraking Maneuver

Santos

Kuga

Rocco

2013

Mathematical Problems in Engineering

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This paper presents a study about the application of a Kalman filter to estimate the position and velocity of a spacecraft in an aerobraking maneuver around the Earth. The cis-lunar aerobraking of the Hiten spacecraft as well as an aerobraking in a LEO orbit are simulated in this paper. The simulator developed considers a reference trajectory and a trajectory perturbed by external disturbances combined with nonidealities of sensors and actuators. It is able to operate in closed loop controlling the trajectory at each instant of time using a PID controller and propulsive jets. A Kalman filter utilizes the sensor data to estimate the state of the spacecraft. The estimation algorithms and propagation equations used in this process are presented. The U.S. Standard Atmosphere is adopted as the atmospheric model. The main results are compared with the case where the Kalman filter is not used. Therefore, it was possible to perform an analysis of the Kalman filter importance applied to an aerobraking maneuver.

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Orbital control of a satellite using the gravity of the Moon

Abstract: Abstract. In this paper, a study is made in the problem of the orbital control of an Earth´s

Cited by 5 publications

References 14 publications

Trajectories Derived from Periodic Orbits around the Lagrangian Point L1 and Lunar Swing-Bys: Application in Transfers to Near-Earth Asteroids

Trajectories Derived from Periodic Orbits around the Lagrangian Point L1 and Lunar Swing-Bys: Application in Transfers to Near-Earth Asteroids

Studying Close Approaches for a Cloud of Particles Considering Atmospheric Drag

Application of the Kalman Filter to Estimate the State of an Aerobraking Maneuver

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