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Shape-Based Approximation of Constrained Low-Thrust Space Trajectories Using Fourier Series
2012
Journal of Spacecraft and Rockets
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Conclusions
A new method is developed to provide feasible low-thrust trajectories based on using the finite Fourier series to approximate the shape of the trajectories inversely. ...
To thai end, shape-based (SB) methods were developed to provide a fast initial guess for the continuous-thrust trajectory. ...
doi:10.2514/1.a32099
fatcat:wpgvlygg3veatkte4wd7pbccfi
Shape Based Approximation of Constrained Low-Thrust Space Trajectories using Fourier Series
2012
Journal of Spacecraft and Rockets
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Conclusions
A new method is developed to provide feasible low-thrust trajectories based on using the finite Fourier series to approximate the shape of the trajectories inversely. ...
To thai end, shape-based (SB) methods were developed to provide a fast initial guess for the continuous-thrust trajectory. ...
doi:10.2514/1.58789
fatcat:nwwcq45m3zc57p2lmcc5id6cwe
A Shape-Based Method for Continuous Low-Thrust Trajectory Design between Circular Coplanar Orbits
2017
International Journal of Aerospace Engineering
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The shape-based method can provide suitable initial guesses for trajectory optimization, which are useful for quickly converging a more accurate trajectory. ...
The Earth-Mars case and the LEO-GEO case are used to verify the optimized shape-based method's feasibility for time-fixed and time-free continuous low-thrust trajectory design between circular coplanar ...
Acknowledgments This research is supported by the National Natural Science Foundation of China (Grant no. 11272255). ...
doi:10.1155/2017/9234905
fatcat:aixatx77tbgenc2aykw6jv7vpi
Shape-Based Approach to Low-Thrust Rendezvous Trajectory Design
2009
Journal of Guidance Control and Dynamics
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A simpler shape-based method is derived here that is capable of determining low-thrust rendezvous trajectories for both time-free and time-fixed cases. ...
The trajectory chosen as an example of the application of the shape-based method to an interception problem is a minimum AV trajectory in a fixed final time, 10 TU, from a circular orbit with a radius ...
doi:10.2514/1.36848
fatcat:mb5cizbpyjevfbfsbksr5n3sui
Minimum-fuel, power-limited transfers between coplanar elliptical orbits
1993
Acta Astronautica
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Two methods of computing coplanar, minimum-fuel, power-limited transfers are developed, based on approximate solutions obtained by the averaging method. ...
These trajectories and thrust profiles are compared to analytical results obtained using the averaging method and to the analytic solution for infinitesimal transfer. ...
Numerical methods have been used for low thrust levels [28] [29] [30] . ...
doi:10.1016/0094-5765(93)90064-4
fatcat:uxflkqqldvbnjbzs6vkxkjjz7m
Near-optimal low-thrust lunar trajectories
1996
Journal of Guidance Control and Dynamics
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nature of low-thrust trajectories. ...
Our approximate so- lution method replaces the long-duration, many-revolution escape and capture spiral trajectories with curve fits of universal low-thrust trajectory solutions. ...
doi:10.2514/3.21645
fatcat:otluwncyfreybd622nmvuirkpq
Low-Thrust to Solar-Sail Trajectories: A Homotopic Approach
2017
Journal of Guidance Control and Dynamics
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This paper describes a novel method to compute minimum-time solar-sail trajectories starting from a given low-thrust solution. The method is based on the use homotopy and numerical continuation. ...
Homotopy is used to link the low-thrust with the solar-sail optimal control problem. ...
In fact, in 2012, Picot [25] computed 6 minimum-time-of-flight and minimum-energy Earth-L2 and Earth-Moon low-thrust trajectories by means of the homotopy method. ...
doi:10.2514/1.g002552
fatcat:gb3daazwsvd2fec6s6poetdfcy
Automated Trajectory Optimizer for Solar Sailing (ATOSS)
2018
Aerospace Science and Technology
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Value dependent on boundary conditions at initial time min Minimum pSS Pseudo solar sail Abstract The problem of finding an optimal solar-sail trajectory must be solved by means of numerical methods, since ...
Once the initial guess is generated by means of the shape-based method, the above mentioned two-stage approach works as follows. ...
Shape-based methodpropagated trajectory In the first method, the initial-guess trajectory is found propagating the initial state by using the acceleration given by the shape-based method. ...
doi:10.1016/j.ast.2017.11.025
fatcat:l5s7mxkbfrhhdozq7twgxj7tbe
Lyapunov-based Low-thrust Optimal Orbit Transfer: An approach in Cartesian coordinates
[article]
2013
arXiv
pre-print
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This paper presents a simple approach to low-thrust optimal-fuel and optimal-time transfer problems between two elliptic orbits using the Cartesian coordinates system. ...
Trajectory optimization with the pseudospectral method and nonlinear programming are supported by the initial guess generated from the Chang-Chichka-Marsden Lyapunov-based transfer controller. ...
The authors are indebted to Per Rutquist in TOMLAB for the advice on the use of the optimization software PROPT. ...
arXiv:1310.4201v1
fatcat:5eilyqn65nbstbvubksrxso4lm
Low-Thrust Trajectory Design Using Finite Fourier Series Approximation of Pseudoequinoctial Elements
2019
International Journal of Aerospace Engineering
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The low-thrust Earth-Moon transfer was analyzed, and the results show that this method improves window analysis efficiency and guarantees precision of the initial geocentric trajectory for the low-thrust ...
A new low-thrust trajectory design method is proposed that is based on the finite Fourier series method with pseudoequinoctial elements rather than the more common cylindrical coordinate components. ...
This study was cosupported by the National Natural Science Foundation of China (Nos. 11472301 and 11372345). ...
doi:10.1155/2019/1364834
fatcat:wayubq4tdfbmxa36mx6lqxiau4
Coplanar Low-Thrust Transfer with Eclipses Using Analytical Costate Guess
[article]
2018
arXiv
pre-print
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In the case of a coplanar minimum-time low-thrust transfer with eclipses, an analytical costate guess is proposed. ...
Low-thrust orbital transfers are difficult to optimize by indirect methods. The main issues come from the costate guess and from the numerical propagation accuracy required by the shooting method. ...
Minimum-time low thrust trajectories are consequently studied intensively for several decades. ...
arXiv:1802.06202v1
fatcat:rxxd5qys25g2xkvc62yqv25oye
Preliminary Design of Low-Thrust Multiple Gravity-Assist Trajectories
2006
Journal of Spacecraft and Rockets
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Shape of the Trajectory
The inverse method described previously requires the definition of the shape of a low-thrust trajectory connecting two points in space. ...
., “Shape-Based Analytical Representations of Low-Thrust Trajectories for Gravity- Assist Applications,” American Astronautical Society Paper 99-337, 1999
Petropoulos, A. f 4 Shape-Based Algorithm for ...
doi:10.2514/1.19646
fatcat:sdgcjzkaifhkxewcbz2qzgxsfm
Practical Method for Optimization of Low-Thrust Transfers
2010
Journal of Guidance Control and Dynamics
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Shape-based methods are quite popular and consist of assuming a certain shape of the trajectory and finding the parameters that fulfill the boundary conditions [3,4]. ...
., “Shape-Based Algorithm for the Automated Design of Low-Thrust, Gravity Assist Trajectories,” Journal of Spacecraft and Rockets, Vol. 41, No. 5, 2004, pp. 787-796. doi:10.2514/1.13095
Vasile, M., de ...
doi:10.2514/1.50739
fatcat:q3l44qj4zrafxg36qozspr2sj4
A Survey on Low-Thrust Trajectory Optimization Approaches
2021
Aerospace (Basel)
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In this paper, we provide a survey on available numerical approaches for solving low-thrust trajectory optimization problems. ...
Thereafter, solution approaches for classical continuous optimal control problems will be briefly introduced and their application to low-thrust trajectory optimization will be discussed. ...
Some of the analyses may be described as shape-based, that is, the trajectory shape is directly assumed, with the requisite thrust computed a posteriori. ...
doi:10.3390/aerospace8030088
fatcat:2gly3zfnyrcindqn3gpqsubaqq
Orbital Targeting Using Reduced Eccentric Anomaly Low-Thrust Coefficients
2011
Journal of Guidance Control and Dynamics
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A method to evaluate the trajectory dynamics of low-thrust spacecraft is applied to targeting and optimal control problems. ...
vector x = state vector of orbital elements x 0 = initial state x f = final state R;W;S k = cosine coefficient, Fourier series of thrust acceleration R;W;S k = sine coefficient, Fourier series of thrust ...
Acknowledgments This material is based upon work supported under a National Science Foundation Graduate Research Fellowship. ...
doi:10.2514/1.51336
fatcat:kxgcjazhlfdudbl5b5x4wwby6e
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