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In this study, the Collaborative Modeling for Parametric Assessment of Space Systems (COMPASS) team completed a design for a multi-asteroid (Nereus and 1996 FG3) sample return capable spacecraft for the NASA In-Space Propulsion Office. The objective of the study was to support technology development and assess the relative benefits of different electric propulsion systems on asteroid sample return design. The design uses a single, heritage Orion solar array (SA) (approx.6.5 kW at 1 AU) to power a single NASA Evolutionary Xenon Thruster ((NEXT) a spare NEXT is carried) to propel a lander to two near Earth asteroids. After landing and gathering science samples, the Solar Electric Propulsion (SEP) vehicle spirals back to Earth where it drops off the first sample s return capsule and performs an Earth flyby to assist the craft in rendezvousing with a second asteroid, which is then sampled. The second sample is returned in a similar fashion. The vehicle, dubbed Near Earth Asteroids Rendezvous and Sample Earth Returns (NEARER), easily fits in an Atlas 401 launcher and its cost estimates put the mission in the New Frontier s (NF's) class mission. Oleson, Steven R. and McGuire, Melissa L. Glenn Research Center ASTEROIDS; SOLAR ELECTRIC PROPULSION; SAMPLE RETURN MISSIONS; PROPULSION SYSTEM CONFIGURATIONS; SYSTEMS ENGINEERING; FLYBY MISSIONS; PROPULSION SYSTEM PERFORMANCE; ELECTRIC PROPULSION; COST ESTIMATES; SUPPORT SYSTEMS; SOLAR ARRAYS
Masters Theses in the Pure and Applied Sciences was first conceived, published, and disseminated by the Center for Information and Numerical Data Analysis and Synthesis (CINDAS)* at Purdue University in 1957, starting its coverage of theses with the academic year 1955. Beginning with Volume 13, the printing and dis semination phases of the activity were transferred to University Microfilms/Xerox of Ann Arbor, Michigan, with the thought that such an arrangement would be more beneficial to the academic and general scientific and technical community. After five years of this joint undertaking we had concluded that it was in the interest of all concerned if the printing and distribution of the volumes were handled by an international publishing house to assure improved service and broader dissemination. Hence, starting with Volume 18, Masters Theses in the Pure and Applied Sciences has been disseminated on a worldwide basis by Plenum Publishing Corporation of New York, and in the same year the coverage was broadened to include Canadian universities. All back issues can also be ordered from Plenum. We have reported in Volume 38 (thesis year 1993) a total of 13,787 thesis titles from 22 Canadian and 164 United States universities. We are sure that this broader base for these titles reported will greatly enhance the value of this impor tant annual reference work. While Volume 38 reports theses submitted in 1993, on occasion, certain uni versities do report theses submitted in previous years but not reported at the time.
Near-future space missions demand the delivery of massive payloads to deep space destinations. Given foreseeable propulsion technology, this is feasible only if we can design trajectories that require the smallest possible propulsive energy input. This research aims to design interplanetary space missions by using new low-energy trajectory methods that take advantage of natural dynamics in the solar system. This energy efficient trajectory technology, called the Interplanetary Super Highway (IPSH), allows long duration space missions with minimum fuel requirements. To develop the IPSH trajectory design method, invariant manifolds of the three-body problem are used. The invariant manifolds, which are tube-like structures that issue from the periodic orbits around the L1 and L2 Lagrangian points, can be patched together to achieve voyages of immense distances while the spacecraft expends little or no energy. This patched three-body method of trajectory design is fairly well developed for impulsive propulsion. My research is dedicated to advance its capabilities by extending it to continuous, low-thrust, high specific impulse propulsion methods. The IPSH trajectory design method would be useful in designing many types of interplanetary missions. As one of its applications, my research is focused on Near-Earth Asteroids (NEAs) rendezvous mission design for exploration, mitigation, and mining. Asteroids have many valuable resources such as minerals and volatiles, which can be brought back to Earth or used in space for propulsion systems or space habitats and stations. Transportation to and from asteroids will require relatively massive vehicles capable of sustaining crew for long durations while economizing on propellant mass. Thus, in the design of advanced NEA rendezvous missions, developing new technology for low cost trajectories will play a key role. In a second application study, the solar sail mission for Mars exploration is considered. By using solar radiation pressure, solar sails provide propulsive power. This thrust affects the three-body system dynamics such that the Sun-Mars L1 and L2 Lagrangian points are shifted toward the Sun and the geometry of the invariant manifolds around L1 and L2 points is changed. By taking advantage of these features, a low-thrust trajectory for Mars exploration is developed. The electronic version of this dissertation is accessible from http://hdl.handle.net/1969.1/155436
This textbook introduces the theories and practical procedures used in planetary spacecraft navigation. Written by a former member of NASA's Jet Propulsion Laboratory (JPL) navigation team, it delves into the mathematics behind modern digital navigation programs, as well as the numerous technological resources used by JPL as a key player in the field. In addition, the text offers an analysis of navigation theory application in recent missions, with the goal of showing students the relationship between navigation theory and the real-world orchestration of mission operations.
Planets and Moons covers topics relating to the physics of the major planetary bodies in the solar system, starting with an introductory description of the solar system and collection of pertinent data, continuing with a discussion of the early history of the planets, and finishing with articles about planet dynamics, thermal evolution of planets and satellites, and descriptions of their magnetic fields and the processes that generate them. In addition to providing a review on the solid planets and the satellites, this volume addresses the interactions of solid surfaces and atmospheres as well as the roles of water and ice in shaping the surfaces of planetary bodies. Self-contained volume starts with an overview of the subject then explores each topic with in depth detail Extensive reference lists and cross references with other volumes to facilitate further research Full-color figures and tables support the text and aid in understanding Content suited for both the expert and non-expert
The book focuses on the orbital dynamics and mission trajectory (transfer or target trajectory) design of low-energy flight in the context of modern astrodynamics. It investigates various topics that either offer new methods for solving classical problems or address emerging problems that have yet to be studied, including low-thrust transfer trajectory design using the virtual gravity field method; transfer in the three-body system using invariant manifolds; formation flying under space-borne artificial magnetic fields; and the orbital dynamics of highly irregular asteroids. It also features an extensive study of the orbital dynamics in the vicinity of contact binary asteroids, including the 1:1 ground-track resonance, the equilibrium points and their stability, and the third-order analytical solution of orbital motion in the vicinity of the non-collinear equilibrium point. Given its breadth of coverage, the book offers a valuable reference guide for all engineers and researchers interested in the potential applications of low-energy space missions.
Vols. 1-2, 4 contain the Proceedings of the Society's 3rd (1956)-5th (1958) annual meeting; v. 3 contains the Proceedings of the Western Regional Meeting of the AAS, Aug. 1958.
The United States spends approximately $4 million each year searching for near-Earth objects (NEOs). The objective is to detect those that may collide with Earth. The majority of this funding supports the operation of several observatories that scan the sky searching for NEOs. This, however, is insufficient in detecting the majority of NEOs that may present a tangible threat to humanity. A significantly smaller amount of funding supports ways to protect the Earth from such a potential collision or "mitigation." In 2005, a Congressional mandate called for NASA to detect 90 percent of NEOs with diameters of 140 meters of greater by 2020. Defending Planet Earth: Near-Earth Object Surveys and Hazard Mitigation Strategies identifies the need for detection of objects as small as 30 to 50 meters as these can be highly destructive. The book explores four main types of mitigation including civil defense, "slow push" or "pull" methods, kinetic impactors and nuclear explosions. It also asserts that responding effectively to hazards posed by NEOs requires national and international cooperation. Defending Planet Earth: Near-Earth Object Surveys and Hazard Mitigation Strategies is a useful guide for scientists, astronomers, policy makers and engineers.