Searched for: subject%3A%22Circular%255C+restricted%255C+three%255C-body%255C+problem%22
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Gwalani, Punit (author)
With a dedicated mission to the Martian moons, Phobos and Deimos, set to launch soon, there is a growing interest in further exploring these moons using low-thrust propulsion. This paper investigates the trajectory design for a sample-return mission from Deimos using fuel-free solar sail propulsion technology, aiming to maximize operational time...
master thesis 2024
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Liu, Y. (author)
The gravity assist (GA) plays an important role in space missions since itwas first applied by the Luna 3 vehicle in 1959. For preliminary trajectory design, the so-called patchedconics model provides a simple model for a gravity assist. This approach, based on twobody formulations, splits amulti-body probleminto a succession of two-body...
doctoral thesis 2021
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Liu, Y. (author), Noomen, R. (author), Visser, P.N.A.M. (author)
We develop a Gravity Assist Mapping to quantify the effects of a flyby in a two-dimensional circular restricted three-body situation based on Gaussian Process Regression (GPR). This work is inspired by the Keplerian Map and Flyby Map. The flyby is allowed to occur anywhere above 300 km altitude at the Earth in the system of Sun-(Earth+Moon)...
journal article 2021
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de Boer, Roderick (author)
This paper presents time-optimal transfer trajectories between planar solar-sail displaced libration point orbits around the $L_1$ and $L_2$ points of the Sun-Earth and Earth-Moon systems. Initial guesses for these transfers are generated as two-segment trajectories, with a fixed sail attitude along each segment. The position and velocity...
master thesis 2020
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Gamez Losada, Fernando (author)
The propellantless nature of solar-sail propulsion allows researchers to design completely new sets of orbits unreachable or not-maintainable by means of conventional propulsion. The advantage of this somewhat new type of low-thrust propulsion system becomes more evident for long-duration missions where chemical or electrical rocket engines...
master thesis 2019
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Langemeijer, Koen (author)
The three-body problem (3BP) formulated by I. Newton has inspired many great mathematicians like L. Euler (1707-1783), J.L. Lagrange (1736-1813), K.G.J. Jacobi (1804-1851), W.R. Hamilton (1805-1865) and J.H. Poincaré (1854-1912) to develop mathematical studies, methods and theories in an attempt to solve this problem. Although these concepts...
master thesis 2018
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Bonasera, Stefano (author)
Many interplanetary missions massively leverage the lunar gravitational pull in the so-called low-energy regime to converge to their aim, saving consistent amount of fuel. Among these, two future Japanese spacecraft are expected to repeatedly encounter the Moon along their trajectories to either facilitate the escape from the Earth–Moon system...
master thesis 2017
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Van der Ham, L. (author)
Instead of the two-body problem commonly used in interplanetary trajectory design, also three bodies can be considered: the satellite, a planet and the Sun. Knowing that planet and Sun orbit one another in almost circular orbits, and the mass of the satellite is negligible compared to the mass of these bodies, the model of the circular...
master thesis 2012
Searched for: subject%3A%22Circular%255C+restricted%255C+three%255C-body%255C+problem%22
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