Global ETD Search
Search theses and dissertations gathered from participating repositories worldwide. Every result links back to the library that holds it. No account is needed.
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Showing 1 to 20 of 27 for “"Earth–Moon System"”.
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A transfer network linking Earth, Moon, and the triangular libration point regions in the Earth-Moon system
… near future, several space applications in the Earth-Moon system may require a spacecraft to hold a stable motion, but the transfer trajectory infrastructure to access such stable motions has not been fully investigated yet. The triangular libration points, <em>L</em> 4and <em>L</em>5, in the …
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Promoting mental model-building in astronomy education
… which is a representation of part of the solar system. This study investigated how pupils can be helped to construct the scientists’ mental model of the Sun-Earth-Moon system. It used an approach suggested by Hesse (1966) in which a model is repeatedly critiqued with respect to the extent that …
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An arbitrarily shaped satellite in the restricted problem of three bodies
… orbit about the L₄ triangular point in the earth moon system for the purpose of communication and possibly astronomical observations. Within limits of a linear analysis, an exhaustive and general approach to the dynamical problem is presented. The equations of motion for a finite sized body …
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Investigation of a Lagrangian-point Propellant Depot Rendezvous Approach for an Interplanetary Mission to Mars
… feasibility of a refueling station for a beyond Earth orbit (BEO) mission. The propellant depot is located at the <em> L</em><sub>2</sub> -Lagrangian point within the Earth-Moon system. This investigation determines if a refueling mission will reduce propulsive energy requirements necessary for …
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A new numerical optimization method based on Taylor series for challenging trajectory optimization problems
… programming. In direct transcription the system equations must be converted into algebraic constraints. Existing methods use only zeroth and first order derivatives of the system equations to formulate these constraints. The techniques of automatic differentiation allow the computation of …
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Using the Circular Restricted Three-Body Problem to Design an Earth-Moon Orbit Architecture for Asteroid Mining
… is the design of an orbit architecture in the Earth-Moon system (EMS) that facilitates these resources through the mining cycle. In this thesis, it is proposed to use the Circular Restricted 3-Body Problem (CR3BP) to design an orbit architecture composed of L3 Lyapunov orbits, hyperbolic …
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Design of transfers from Earth-Moon L 1/L2 libration point orbits to a destination object
… robotic spaceflight activities, orbits near the Earth-Moon L1 and L2 libration points could support lunar surface operations and serve as staging areas for future missions to near-Earth asteroids as well as Mars. In fact, an Earth-Moon L2 libration point orbit has been proposed as a potential hub …
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A Comparison of Autonomous Navigation Methods for Earth-Moon Halo Orbits
… of satellite tracking for spacecraft around the Moon are unequipped to handle this increase in demand. Therefore, a reliable method of performing autonomous navigation in lunar space is required to facilitate this new interest. Many methods of performing this autonomous navigation have been …
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Trajectory design in the spatial circular restricted three-body problem exploiting higher-dimensional Poincare maps
… point orbit transfers is developed in the Earth-Moon system, and observations about the catalog solutions yields insight into the existence of these transfers. The application of Poincaré maps to compute transfers between libration point orbits in different three-body systems is …
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Spacecraft formation flight at sun-earth/moon libration points
… positioned near the libration points of the Sun- Earth/Moon system, have recently received an increase in interest in response to a variety of mission needs. Specifically, missions such as the Micro Arcsecond X-Ray Imaging Mission (MAXIM), Terrestrial Pathfinder (TPF), Stellar Imager (SI) and the …
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A Solution to the Circular Restricted N Body Problem in Planetary Systems
… - the N body problem. By focusing on planetary systems, satellite dynamics can be modeled in a fashion similar to the Circular Restricted Three Body Problem (CR3BP) with the Circular Restricted N Body Problem (CRNBP). It was found that this new formulation of the dynamics can then utilize the …
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Investigation Into Geometry and Behavior of Cislunar GEO-Grazer Orbits
… to as GEO-grazers: orbits that traverse the Earth–Moon system while grazing or passing below geosynchronous Earth orbit (GEO). These trajectories are of interest for cislunar space domain awareness (SDA) because they provide natural dynamical pathways by which spacecraft or debris originating …
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On the dynamics, stability and control of displaced lunar orbits
… of transportation throughout the solar system. By exploiting the momentum transported by solar photons, solar sails can perform new high-energy mission concepts, which are essentially impossible for conventional propulsion, without the need for reaction mass. In this thesis, novel …
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Investigating the Distribution and Source(s) of Lunar Volatiles
… interest in the volatile inventory of the Moon witnessed in the last decade, from both sample studies and data from orbital missions, it is timely to reassess the distribution and likely source(s) of light element volatiles (C, N, He, Ne, and Ar) in a diverse suite of lunar mare basalts and …
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Coupled orbit-attitude mission design in the circular restricted three-body problem
… for the targeting algorithm is described. In the Earth-Moon system, representative scenarios are explored for axisymmetric vehicles with various inertia characteristics, assuming that the vehicles move along Lyapunov, halo as well as distant retrograde orbits. A rich structure of possible periodic …
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Multiple Asteroid Retrieval Mission
… a fleet of spacecraft capable of reaching Near-Earth asteroids. To analyze this idea, the goal of this problem is to maximize the asteroid mass retrieved within a spacecraft max life span. Explicitly, the maximum lifetime of the spacecraft fleet is set at 30 years. A fuel supply-chain is …
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A dynamo case study of Mercury, and the early orbital and thermal evolution of the Moon
… features is difficult to be explained with an Earth-like dynamo. We enhance the traditional dynamo model by adding a stably stratified layer in Mercury's core and a north-south asymmetric heat flux pattern at the core-mantle boundary, and find multiple cases in which the surface magnetic field …
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Solar Sailing Adaptive Control Around the Earth-Moon Lagrange Point L4 for Stellar Observations
… the solar corona from L<sub>4</sub> of the Earth-Moon system. Single and multiple shooting techniques are described along with a pseudo arc-length continuation method for preliminary orbit design. Periodic orbits in the vicinity of L<sub>4</sub> are obtained in the context of the Earth-Moon …
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Low thrust augmented periodic orbits in the two- and three-body problems
… circular restricted three-body problem. In the Earth-Moon system, position-only feedback is used to stabilise the local dynamics, and interesting new multiply-periodic orbits are generated. The in-plane and out-of plane natural frequencies are then synchronised, allowing the generation of stable …
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Space logistics network optimization with embedded propulsion technology selection
Establishing long-term human presence beyond low Earth-orbit will require cooperative use of emerging technologies, such as low-thrust solar electric propulsion, along with existing space exploration technologies. Trajectory analysis plays a key role in deciding the costs of using different …
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