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Author : P. M. Lion
Publisher :
ISBN 13 :
Total Pages : 9 pages
Book Rating : 4.:/5 (45 download)
Download or read book Low Thrust Mission Analysis Using an Analytical Trajectory Optimization Model written by P. M. Lion and published by . This book was released on 1970 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Bernd Dachwald
Publisher :
ISBN 13 :
Total Pages : 135 pages
Book Rating : 4.:/5 (634 download)
Download or read book Low-thrust Trajectory Optimization and Interplanetary Mission Analysis Using Evolutionary Neurocontrol written by Bernd Dachwald and published by . This book was released on 2004 with total page 135 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Bruce A. Conway
Publisher : Cambridge University Press
ISBN 13 : 113949077X
Total Pages : 313 pages
Book Rating : 4.1/5 (394 download)
Download or read book Spacecraft Trajectory Optimization written by Bruce A. Conway and published by Cambridge University Press. This book was released on 2010-08-23 with total page 313 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 : Dilmurat M. Azimov
Publisher : Butterworth-Heinemann
ISBN 13 : 0128140593
Total Pages : 332 pages
Book Rating : 4.1/5 (281 download)
Download or read book Analytical Solutions for Extremal Space Trajectories written by Dilmurat M. Azimov and published by Butterworth-Heinemann. This book was released on 2017-08-23 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analytical Solutions for Extremal Space Trajectories presents an overall treatment of the general optimal control problem, in particular, the Mayer’s variational problem, with necessary and sufficient conditions of optimality. It also provides a detailed derivation of the analytical solutions of these problems for thrust arcs for the Newtonian, linear central and uniform gravitational fields. These solutions are then used to analytically synthesize the extremal and optimal trajectories for the design of various orbital transfer and powered descent and landing maneuvers. Many numerical examples utilizing the proposed analytical synthesis of the space trajectories and comparison analyses with numerically integrated solutions are provided. This book will be helpful for engineers and researchers of industrial and government organizations, and is also a great resource for university faculty and graduate and undergraduate students working, specializing or majoring in the fields of aerospace engineering, applied celestial mechanics, and guidance, navigation and control technologies, applied mathematics and analytical dynamics, and avionics software design and development. Features an analyses of Pontryagin extremals and/or Pontryagin minimum in the context of space trajectory design Presents the general methodology of an analytical synthesis of the extremal and optimal trajectories for the design of various orbital transfer and powered descent and landing maneuvers Assists in developing the optimal control theory for applications in aerospace technology and space mission design
Author : Iman Alizadeh
Publisher :
ISBN 13 : 9781124867373
Total Pages : 148 pages
Book Rating : 4.8/5 (673 download)
Download or read book Sensitivity Analysis and Mitigation with Applications to Ballistic and Low-thrust Trajectory Design written by Iman Alizadeh and published by . This book was released on 2011 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt: The ever increasing desire to expand space mission capabilities within the limited budgets of space industries requires new approaches to the old problem of spacecraft trajectory design. For example, recent initiatives for space exploration involve developing new tools to design low-cost, fail-safe trajectories to visit several potential destinations beyond our celestial neighborhood such as Jupiter's moons, asteroids, etc. Designing and navigating spacecraft trajectories to reach these destinations safely are complex and challenging. In particular, fundamental questions of orbital stability imposed by planetary protection requirements are not easily taken into account by standard optimal control schemes. The event of temporary engine loss or an unexpected missed thrust can indeed quickly lead to impact with planetary bodies or other unrecoverable trajectories. While electric propulsion technology provides superior efficiency compared to chemical engines, the very low-control authority and engine performance degradation can impose higher risk to the mission in strongly perturbed orbital environments. The risk is due to the complex gravitational field and its associated chaotic dynamics which causes large navigation dispersions in a short time if left un-controlled. Moreover, in these situations it can be outside the low-thrust propulsion system capability to correct the spacecraft trajectory in a reasonable time frame. These concerns can lead to complete or partial mission failure or even an infeasible mission concept at the early design stage. The goal of this research is to assess and increase orbital stability of ballistic and low-thrust transfer trajectories in multi-body systems. In particular, novel techniques are presented to characterize sensitivity and improve recovery characteristics of ballistic and low-thrust trajectories in unstable orbital environments. The techniques developed are based on perturbation analysis around ballistic trajectories to determine analytically the maximum divergence directions and also optimal control theory with nonstandard cost functions along with inverse dynamics applied to low-thrust trajectories. Several mission scenarios are shown to demonstrate the applicability of the techniques in the Earth-Moon and the Jupiter-Europa system. In addition, the results provide fundamental insight into design, stability analysis and guidance, navigation and control of low-thrust trajectories to meet challenging mission requirements in support of NASA's vision for space exploration.
Author : Jianping Yuan
Publisher : Springer
ISBN 13 : 9811361304
Total Pages : 209 pages
Book Rating : 4.8/5 (113 download)
Download or read book Low Energy Flight: Orbital Dynamics and Mission Trajectory Design written by Jianping Yuan and published by Springer. This book was released on 2019-03-19 with total page 209 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722945305
Total Pages : 188 pages
Book Rating : 4.9/5 (453 download)
Download or read book Analytical Investigations in Aircraft and Spacecraft Trajectory Optimization and Optimal Guidance written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt: A collection of analytical studies is presented related to unconstrained and constrained aircraft (a/c) energy-state modeling and to spacecraft (s/c) motion under continuous thrust. With regard to a/c unconstrained energy-state modeling, the physical origin of the singular perturbation parameter that accounts for the observed 2-time-scale behavior of a/c during energy climbs is identified and explained. With regard to the constrained energy-state modeling, optimal control problems are studied involving active state-variable inequality constraints. Departing from the practical deficiencies of the control programs for such problems that result from the traditional formulations, a complete reformulation is proposed for these problems which, in contrast to the old formulation, will presumably lead to practically useful controllers that can track an inequality constraint boundary asymptotically, and even in the presence of 2-sided perturbations about it. Finally, with regard to s/c motion under continuous thrust, a thrust program is proposed for which the equations of 2-dimensional motion of a space vehicle in orbit, viewed as a point mass, afford an exact analytic solution. The thrust program arises under the assumption of tangential thrust from the costate system corresponding to minimum-fuel, power-limited, coplanar transfers between two arbitrary conics. The thrust program can be used not only with power-limited propulsion systems, but also with any propulsion system capable of generating continuous thrust of controllable magnitude, and, for propulsion types and classes of transfers for which it is sufficiently optimal the results of this report suggest a method of maneuvering during planetocentric or heliocentric orbital operations, requiring a minimum amount of computation; thus uniquely suitable for real-time feedback guidance implementations. Markopoulos, Nikos and Calise, Anthony J. Unspecified Center AIRCRAFT GUIDANCE; CONTROLLERS; FLIGHT PATHS; OPTIMAL CONTROL...
Author : K. J. Schwenzfeger
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (317 download)
Download or read book Low Thrust Space Vehicle Trajectory Optimization Using Regularized Variables written by K. J. Schwenzfeger and published by . This book was released on 1974 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Optimizing the trajectory of a low thrust space vehicle usually means solving a nonlinear two point boundary value problem. In general, accuracy requirements necessitate extensive computation times. In celestial mechanics, regularizing transformations of the equations of motion are used to eliminate computational and analytical problems that occur during close approaches to gravitational force centers. It was shown in previous investigations that regularization in the formulation of the trajectory optimization problem may reduce the computation time. In this study, a set of regularized equations describing the optimal trajectory of a continuously thrusting space vehicle is derived. The computational characteristics of the set are investigated and compared to the classical Newtonian unregularized set of equations. The comparison is made for low thrust, minimum time, escape trajectories and numerical calculations of Keplerian orbits. The comparison indicates that in the cases investigated for bad initial guesses of the known boundary values a remarkable reduction in the computation time was achieved. Furthermore, the investigated set of regularized equations shows high numerical stability even for long duration flights and is less sensitive to errors in the guesses of the unknown boundary values.
Author : Ashish Tewari
Publisher : Springer
ISBN 13 : 3030037894
Total Pages : 270 pages
Book Rating : 4.0/5 (3 download)
Download or read book Optimal Space Flight Navigation written by Ashish Tewari and published by Springer. This book was released on 2018-12-20 with total page 270 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book consolidates decades of knowledge on space flight navigation theory, which has thus far been spread across various research articles. By gathering this research into a single text, it will be more accessible to students curious about the study of space flight navigation. Books on optimal control theory and orbital mechanics have not adequately explored the field of space flight navigation theory until this point. The opening chapters introduce essential concepts within optimal control theory, such as the optimization of static systems, special boundary conditions, and dynamic equality constraints. An analytical approach is focused on throughout, as opposed to computational. The result is a book that emphasizes simplicity and practicability, which makes it accessible and engaging. This holds true in later chapters that involve orbital mechanics, two-body maneuvers, bounded inputs, and flight in non-spherical gravity fields. The intended audience is primarily upper-undergraduate students, graduate students, and researchers of aerospace, mechanical, and/or electrical engineering. It will be especially valuable to those with interests in spacecraft dynamics and control. Readers should be familiar with basic dynamics and modern control theory. Additionally, a knowledge of linear algebra, variational methods, and ordinary differential equations is recommended.
Author : Evgeniy Sklyanskiy
Publisher :
ISBN 13 :
Total Pages : 244 pages
Book Rating : 4.:/5 (587 download)
Download or read book Low-thrust Trajectory Optimization Using a Discretized Impulsive Thrust Model written by Evgeniy Sklyanskiy and published by . This book was released on 2004 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Zahi Bassem Tarzi
Publisher :
ISBN 13 :
Total Pages : 119 pages
Book Rating : 4.:/5 (816 download)
Download or read book Optimum Low Thrust Elliptic Orbit Transfer Using Numerical Averaging written by Zahi Bassem Tarzi and published by . This book was released on 2012 with total page 119 pages. Available in PDF, EPUB and Kindle. Book excerpt: Low-thrust electric propulsion is increasingly being used for spacecraft missions primarily due to its high propellant efficiency. Since analytical solutions for general low-thrust transfers are not available, a simple and fast method for low-thrust trajectory optimization is of great value for preliminary mission planning. However, few low-thrust trajectory tools are appropriate for preliminary mission design studies. The method presented in this paper provides quick and accurate solutions for a wide range of transfers by using numerical orbital averaging to improve solution convergence and include orbital perturbations. Thus allowing preliminary trajectories to be obtained for transfers which involve many revolutions about the primary body. This method considers minimum fuel transfers using first order averaging to obtain the fuel optimum rates of change of the equinoctial orbital elements in terms of each other and the Lagrange multipliers. Constraints on thrust and power, as well as minimum periapsis, are implemented and the equations are averaged numerically using a Gaussian quadrature. The use of numerical averaging allows for more complex orbital perturbations to be added without great difficulty. Orbital perturbations due to solar radiation pressure, atmospheric drag, a non-spherical central body, and third body gravitational effects have been included. These perturbations have not ben considered by previous methods using analytical averaging. Thrust limitations due to shadowing have also been considered in this study. To allow for faster convergence of a wider range of problems, the solution to a transfer which minimizes the square of the thrust magnitude is used as a preliminary guess for the minimum fuel problem. Thus, this method can be quickly applied to many different types of transfers which may include various perturbations. Results from this model are shown to provide a reduction in propellant mass required over previous minimum fuel solutions. Minimum time transfers are also solved and compared to minimum fuel.
Author : Suwat Sreesawet
Publisher :
ISBN 13 :
Total Pages : 54 pages
Book Rating : 4.:/5 (11 download)
Download or read book A New Algorithm to Generate Low-thrust Spacecraft Trajectories written by Suwat Sreesawet and published by . This book was released on 2014 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: All-electric satellites are gaining favor among the manufacturers and operators of satellites in Geostationary Earth Orbit (GEO) due to cost saving potential. These satellites have the capability of performing all propulsive tasks with electric propulsion including transfer to GEO. Although fuel-efficient, electric thrusters lead to long transfer, during which the health and the usability of spacecraft is affected due to its exposure to hazardous space radiation in the Van Allen belts. Hence, determining electric orbit-raising trajectory that minimize transfer time is crucial for all-electric satellite operation. This thesis proposes a novel method to determine minimum-time orbit-raising trajectory by blending the ideas of direct optimization and guidance-like trajectory optimization schemes. The proposed methodology is applicable for both planar and non-planar transfers and for transfers starting from arbitrary circular and elliptic orbits. Therefore, it can be used for rapidly analyzing various orbit-raising mission scenarios. The methodology utilizes the variational equations of motion of the satellite in the context of the two-body problem by considering the low-thrust of an electric engine as a perturbing force. The no-thrust condition due to Earth's shadow is also considered. The proposed methodology breaks the overall optimization problem into multiple sub-problems and each sub-problem minimizes a desired objective over the sun-lit part of the trajectory. Two different objective types are considered. Type I transfers minimize the deviation of the total energy and eccentricity of final position from the GEO, while type II transfers minimize the deviation of total energy and angular momentum. Using the developed tool, several mission scenarios are analyzed including, a new type of mission scenarios, in which more than one thruster type are used for the transfer. The thesis presents the result for all studied scenarios and compares the performance of Type I and Type II transfers.
Author :
Publisher :
ISBN 13 :
Total Pages : 636 pages
Book Rating : 4.:/5 (26 download)
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1973 with total page 636 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Nikos Markopoulos
Publisher :
ISBN 13 :
Total Pages : 192 pages
Book Rating : 4.3/5 (126 download)
Download or read book Analytical Investigations in Aircraft and Spacecraft Trajectory Optimization and Optimal Guidance written by Nikos Markopoulos and published by . This book was released on 1995 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Alfred C. Mascy
Publisher :
ISBN 13 :
Total Pages : 74 pages
Book Rating : 4.:/5 (317 download)
Download or read book A Compilation of Current Computer Programs for Low-thrust Trajectory Analysis written by Alfred C. Mascy and published by . This book was released on 1969 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper provides a catalogue of brief descriptions of current lowthrust trajectory and mass computation programs. All known sources were contacted, and questionnaires were sent to those who indicated that they possessed such codes.
Author : Yang Gao
Publisher :
ISBN 13 :
Total Pages : 466 pages
Book Rating : 4.:/5 (556 download)
Download or read book Advances in Low-thrust Trajectory Optimization and Flight Mechanics written by Yang Gao and published by . This book was released on 2003 with total page 466 pages. Available in PDF, EPUB and Kindle. Book excerpt: The dissertation presents advances in trajectory optimization and flight mechanics of low-thrust spacecraft. With the aid of the extended multiple-shooting techniques with state and costate nodes, the hybrid method and the direct-shooting method are systematically described and used to solve a variety of optimal orbit transfer problems. The optimization methods are demonstrated by presenting solutions for optimal Earth-orbit and interplanetary trajectory examples, and complex interplanetary missions using solar electric propulsion (such as Eros sample return and Pluto-flyby missions). Alternative formulations of equations of motion are discussed, which include inertial frame transformation in terms of three Euler angles and a modified set of equinoctial elements using non-dimensional angular momentum. Finally, a low-thrust Earth-capture guidance scheme is developed and presented, which makes novel use of Perkins' low-thrust universal solution and doesn't require a stored reference trajectory. The simplicity and performance of this new guidance design makes it a viable candidate for onboard implementation.
Author : Guanwei He
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (127 download)
Download or read book Continuous Low-thrust Strategy for Space-asset Recycle Missions written by Guanwei He and published by . This book was released on 2021 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The research presented in this dissertation focuses on an Earth orbital mission aiming to analyze the visiting sequence planning and trajectory design of recycling operations for dysfunctional or partially functional space assets, i.e., the multiple space-asset recycle missions in Earth orbits. The whole vision of the space-asset recycle mission decomposes into several small sections, and two core sections form the basis of this research. The first is to determine the spacecraft's visiting sequence about the target objects. The second is to describe the nonlinear rendezvous operations of continuous low-thrust spacecraft between target objects. A heuristic optimization method applies to the first part to determine the optimal visiting sequence of the target objects, based on a simplified model of velocity changes and propellant consumption approximation, which serves as an initial guess for the second part. A new analytic approximate solution to the motion of continuous low-thrust spacecraft is developed to describe the thrust-on motion of the servicing spacecraft between target objects, where the two-variable expansion method is introduced. The proposed two-variable expansion method is shown to accurately describe the rendezvous motion of the continuous low-thrust spacecraft between target objects when the thrust control is constant, i.e., its thrusting angle is constant in a body-fixed reference frame and the thrust-level remains constant. The approximate analytic solution is compared to the ``exact'' solution, generated by numerically integrating the nonlinear equations of motion of continuous low-thrust spacecraft via a high-fidelity integrator. Example results of spacecraft trajectories obtained by the analytic approximation are presented, and their accuracy is characterized under different thrust levels and orbital conditions. Additionally, this method requires lower computational cost compared to the numerical integration, while providing acceptable accuracy. The designing process of an example end-to-end mission is presented to demonstrate the implementation of this method in preliminary mission design, where the servicing spacecraft is assigned to recycle multiple space assets in the proximity region of geostationary orbits. The optimal visiting sequence of the target space assets and the thrusting control of the servicing spacecraft are obtained by an optimization mechanism that combines the heuristic optimization and the analytic approximation. It is proved that the proposed methodologies in this research are able to design the trajectories of space-asset recycle missions at the preliminary level.
