Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 56
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Book Description
A Halo orbit about a libration point of a restricted three-body system provides additional opportunities for surveillance communication and exploratory missions in lieu of the classical spacecraft orbit. Historically libration point missions have focused on Halo orbits and trajectories about the Sun-Earth System. This thesis will focus on libration point orbit solutions in the Earth-Moon system using the restricted three body equations of motion with three low-thrust control functions. These classical dynamics are used to design and optimize orbital trajectories about stable and unstable libration points of the Earth-Moon system using DIDO, a dynamic optimization software. The solutions for the optimized performance are based on a quadratic cost function. Specific constraints and bounds were placed on the potential solution set in order to ensure correct target trajectories. This approach revealed locally optimal solutions for orbits about a stable and unstable libration point.
Author: Emmanuel Blazquez
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
In the context of Human Spaceflight exploration mission scenario, with the Deep Space Gateway (DSG) on a Near Rectilinear Halo Orbit (NRHO) about Earth-Moon Lagrangian Point (EML), Rendezvous and Docking (RVD) operational activities are mandatory and critical for assembly of the DSG to be performed by the Orion spacecraft. Orion will also handle cargo delivery and crew exchange missions and they all require RVD. There is extensive experience with RVD in the two-body problem in Low Earth Orbit to various space stations or around Low Lunar Orbit quasi circular, the latter by Apollo in manual RVD. Despite that no operational RVD has yet been performed in the vicinity of the Lagrangian points, where Keplerian dynamics is not applicable. There are some drawbacks from the complexity, but also some strong advantages that need to be researched in depth by the work proposed here. Despite vast literature on families of trajectories about the Lagrangian points and transfers in the Cis-Lunar realm, the scientific community has, at the moment, very few relevant research results in the non Keplerian dynamic domain. However, in recent years one can be seen the emergence of some sparse publications on the subject, which can be explained by the studies related to DSG and Orion missions. Within the partners, semi-analytical tools have been developed to compute and model families of orbits like NRHO, DRO, Lyapunov, Halo and Lissajous about the Lagrangian points in the Circular Restricted Three Body Problem (CR3BP). Hence there is a good starting point for the research for the overall rendezvous strategy considering vehicle and operations constraints. The proposed PhD project is expected to further and strengthen the work already carried out and some of the celestial mechanics tools developed. Further to that research shall be performed regarding the GNC design for such missions and the accuracies that can be achieved with today technologies and what is required. Assuming the DSG to be the target, RVD will be performed in this project by visiting vehicles arriving from the Earth.
Author: Mohammad Azhar
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Halo orbits are a special case of orbits, occurring as stable saddle points in the circular restricted 3-body problem, which considers the motion of a satellite under the gravitational influence of two planetary bodies orbiting around a common barycenter. These orbits are a result of the gravitational pull of the two primary planetary bodies and the Coriolis and centrifugal acceleration on the orbiting satellite due to those bodies. Thus, these orbits exist in any three body system such as the Earth-Moon system, Earth-Sun system and so on. With the interest in the advantages of halo orbits, it is inevitable that transfers between these orbits will be an important aspect of future missions. Generally, impulsive transfers have been used in mission studies for transfers from or to halo orbits, these result in relatively higher propellant consumption; therefore this thesis examines low thrust orbital transfers.Halo orbits around Lagrange point L1 and L2 in the Earth-Moon system are the targeted orbits and transfers between halo orbits around these points are proposed using low thrust. The initial conditions for the lower amplitude halo orbits (5000-30000 km) around these points was calculated using the differential correction algorithm targeting the orbit amplitude in the out-of-plane direction, that is, the size of the orbit along the z-axis, which utilizes the state transition matrix to produce a periodic orbit around the Lagrange points.Particle Swarm Optimization (PSO) was used to calculate the initial conditions for higher amplitude orbits (35000-70000 km), which is a heuristic optimization method that utilizes "swarm intelligence", and allows the particles to search for an optimal solution through interaction and cooperation. The circular restricted 3-body dynamics were used to derive the initial conditions of the targeted orbits, and then the same equations were derived including the thrust of the spacecraft. The in-plane and out-of-plane thrust pointing angles for the transfer trajectory were represented using third-degree polynomials as a function of time, and PSO was used to determine the optimal solutions for the coefficients of the thrust pointing angles and the transfer trajectory time.Simulations were run for different amplitude halo orbits and for spacecraft with different specific impulses. The results are discussed for all the different amplitude orbits and the feasibility of each orbit type transfer is included. The simulations were first run for different amplitude orbits with constant thrust magnitude throughout the transfer trajectory, and then the simulations were run to include a coasting phase in the transfer trajectory to further minimize the fuel consumption. The simulations were carried out for three different cases, where a Hall thruster was utilized for test case 1, and a chemical thruster was utilized for test case 2, in order to optimize continuous thrust trajectories from one halo orbit to another. For test case 3 the same chemical thruster was utilized but with the inclusion of a thrust arc for the same orbits.The PSO was run for 1000 iterations with 250 particles for test case 1 and 2, and it was found that the maximum error in position was 0.038 km for the 20000 km amplitude halo orbit and in velocity it was 1.2 1010 km/s for the same 20000 km z-amplitude halo orbit, using a Hall thruster. For trajectories using a chemical thruster, it was found that the maximum error in position was 0.067 km and in velocity it was 5.27 1012 km/s. With the inclusion of thrust arc the time of flight increased but the algorithm proved to be more accurate with the maximum error in position being 0.00384 km and in velocity being 4.89 1010 km/s. These results demonstrated that PSO is able to determine optimum transfer trajectories between halo orbits around Earth-Moon L1 and L2 libration points for continuous low-thrust trajectories, as well as for finite-thrust trajectories with and without an assumed coasting arc.
Author: Ying Tan
Publisher: Springer
ISBN: 3662463539
Category : Computers
Languages : en
Pages : 344
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Book Description
This book is devoted to the state-of-the-art in all aspects of fireworks algorithm (FWA), with particular emphasis on the efficient improved versions of FWA. It describes the most substantial theoretical analysis including basic principle and implementation of FWA and modeling and theoretical analysis of FWA. It covers exhaustively the key recent significant research into the improvements of FWA so far. In addition, the book describes a few advanced topics in the research of FWA, including multi-objective optimization (MOO), discrete FWA (DFWA) for combinatorial optimization, and GPU-based FWA for parallel implementation. In sequels, several successful applications of FWA on non-negative matrix factorization (NMF), text clustering, pattern recognition, and seismic inversion problem, and swarm robotics, are illustrated in details, which might shed new light on more real-world applications in future. Addressing a multidisciplinary topic, it will appeal to researchers and professionals in the areas of metahuristics, swarm intelligence, evolutionary computation, complex optimization solving, etc.
Author: Jeffrey S. Parker
Publisher: John Wiley & Sons
ISBN: 1118855310
Category : Technology & Engineering
Languages : en
Pages : 452
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Book Description
Based on years of research conducted at the NASA Jet Propulsion Laboratory, Low-Energy Lunar Trajectory Design provides high-level information to mission managers and detailed information to mission designers about low-energy transfers between Earth and the moon. The book answers high-level questions about the availability and performance of such transfers in any given month and year. Low-energy lunar transfers are compared with various other types of transfers, and placed within the context of historical missions. Using this book, designers may reconstruct any transfer described therein, as well as design similar transfers with particular design parameters. An Appendix, “Locating the Lagrange Points,” and a useful list of terms and constants completes this technical reference. Surveys thousands of possible trajectories that may be used to transfer spacecraft between Earth and the moon, including transfers to lunar libration orbits, low lunar orbits, and the lunar surface Provides information about the methods, models, and tools used to design low-energy lunar transfers Includes discussion about the variations of these transfers from one month to the next, and the important operational aspects of implementing a low-energy lunar transfer Additional discussions address navigation, station-keeping, and spacecraft systems issues
Author: Wang Sang Koon
Publisher: Springer
ISBN: 9780387495156
Category : Mathematics
Languages : en
Pages : 336
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Book Description
This book considers global solutions to the restricted three-body problem from a geometric point of view. The authors seek dynamical channels in the phase space which wind around the planets and moons and naturally connect them. These low energy passageways could slash the amount of fuel spacecraft need to explore and develop our solar system. In order to effectively exploit these passageways, the book addresses the global transport. It goes beyond the traditional scope of libration point mission design, developing tools for the design of trajectories which take full advantage of natural three or more body dynamics, thereby saving precious fuel and gaining flexibility in mission planning. This is the key for the development of some NASA mission trajectories, such as low energy libration point orbit missions (e.g., the sample return Genesis Discovery Mission), low energy lunar missions and low energy tours of outer planet moon systems, such as a mission to tour and explore in detail the icy moons of Jupiter. This book can serve as a valuable resource for graduate students and advanced undergraduates in applied mathematics and aerospace engineering, as well as a manual for practitioners who work on libration point and deep space missions in industry and at government laboratories. the authors include a wealth of background material, but also bring the reader up to a portion of the research frontier.
Author: National Research Council
Publisher: National Academies Press
ISBN: 0309224640
Category : Science
Languages : en
Pages : 399
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Book Description
In recent years, planetary science has seen a tremendous growth in new knowledge. Deposits of water ice exist at the Moon's poles. Discoveries on the surface of Mars point to an early warm wet climate, and perhaps conditions under which life could have emerged. Liquid methane rain falls on Saturn's moon Titan, creating rivers, lakes, and geologic landscapes with uncanny resemblances to Earth's. Vision and Voyages for Planetary Science in the Decade 2013-2022 surveys the current state of knowledge of the solar system and recommends a suite of planetary science flagship missions for the decade 2013-2022 that could provide a steady stream of important new discoveries about the solar system. Research priorities defined in the report were selected through a rigorous review that included input from five expert panels. NASA's highest priority large mission should be the Mars Astrobiology Explorer Cacher (MAX-C), a mission to Mars that could help determine whether the planet ever supported life and could also help answer questions about its geologic and climatic history. Other projects should include a mission to Jupiter's icy moon Europa and its subsurface ocean, and the Uranus Orbiter and Probe mission to investigate that planet's interior structure, atmosphere, and composition. For medium-size missions, Vision and Voyages for Planetary Science in the Decade 2013-2022 recommends that NASA select two new missions to be included in its New Frontiers program, which explores the solar system with frequent, mid-size spacecraft missions. If NASA cannot stay within budget for any of these proposed flagship projects, it should focus on smaller, less expensive missions first. Vision and Voyages for Planetary Science in the Decade 2013-2022 suggests that the National Science Foundation expand its funding for existing laboratories and establish new facilities as needed. It also recommends that the program enlist the participation of international partners. This report is a vital resource for government agencies supporting space science, the planetary science community, and the public.
Author: Jeffrey Small
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
The goal of halo orbit design is to find the initial conditions that lead to a periodic orbit with the desired characteristics. Conventionally, this is done by applying an analytical solution to get an approximation and refining that solution using differential correction to obtain a periodic orbit. Although this method has been used successfully in practice, it is highly dependent on the accuracy of the analytical solution and can lead to significant errors between the desired and achieved orbits. To improve this process, Nath and Ramanan developed a differential evolution scheme to compute halo orbits with a specified Z-amplitude. Differential evolution was shown to be more accurate than the conventional design method and does not require a good initial guess. In this work differential evolution is used to compute halo orbits in the Jupiter-Europa system. In addition to targeting orbits by Z-amplitude, a novel approach is presented to target orbits by X-amplitude and orbital period. It is found, in agreement with Nath et al., that differential evolution can target halo orbits by Z-amplitude more accurately than traditional methods. It is also shown that differential evolution can target halo orbits by X-amplitude and orbital period, but without additional constraints only planar orbits are computed. Finally, it is found that the use of a stochastic mutation factor in differential evolution reduces the chance of convergence to a non-optimal solution.
Author: Bruce A. Conway
Publisher: Cambridge University Press
ISBN: 113949077X
Category : Technology & Engineering
Languages : en
Pages : 313
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Book Description
This is a long-overdue volume dedicated to space trajectory optimization. Interest in the subject has grown, as space missions of increasing levels of sophistication, complexity, and scientific return - hardly imaginable in the 1960s - have been designed and flown. Although the basic tools of optimization theory remain an accepted canon, there has been a revolution in the manner in which they are applied and in the development of numerical optimization. This volume purposely includes a variety of both analytical and numerical approaches to trajectory optimization. The choice of authors has been guided by the editor's intention to assemble the most expert and active researchers in the various specialities presented. The authors were given considerable freedom to choose their subjects, and although this may yield a somewhat eclectic volume, it also yields chapters written with palpable enthusiasm and relevance to contemporary problems.
Author: Leping Yang
Publisher: Springer
ISBN: 1493908383
Category : Mathematics
Languages : en
Pages : 130
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Book Description
On-orbit operations optimization among multiple cooperative or noncooperative spacecraft, which is often challenged by tight constraints and shifting parameters, has grown to be a hot issue in recent years. The authors of this book summarize related optimization problems into four planning categories: spacecraft multi-mission planning, far-range orbital maneuver planning, proximity relative motion planning and multi-spacecraft coordinated planning. The authors then formulate models, introduce optimization methods, and investigate simulation cases that address problems in these four categories. This text will serve as a quick reference for engineers, graduate students, postgraduates in the fields of optimization research and on-orbit operation mission planning.
