Optimal Low-Thrust Escape Trajectories Using Gravity Assist

Casalino, Lorenzo; Colasurdo, Guido; Pastrone, Dario Giuseppe

doi:10.2514/2.4451

Cited by 136 publications

(60 citation statements)

References 7 publications

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“…Common applications usually focus on a single phase of the mission, in which the primary body does not change, such as Earth centred transfers (Ranieri and Ocampo 2006) or heliocentric leg Casalino et al 1999).…”

mentioning

confidence: 99%

Optimal low-thrust trajectories to asteroids through an algorithm based on differential dynamic programming

Colombo

Vasile

Radice

2009

Celest Mech Dyn Astr

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In this paper an optimisation algorithm based on Differential dynamic programming is applied to the design of rendezvous and fly-by trajectories to near Earth objects. Differential dynamic programming is a successive approximation technique that computes a feedback control law in correspondence of a fixed number of decision times. In this way the high dimensional problem characteristic of low-thrust optimisation is reduced into a series of small dimensional problems. The proposed method exploits the stage-wise approach to incorporate an adaptive refinement of the discretisation mesh within the optimisation process. A particular interpolation technique was used to preserve the feedback nature of the control law, thus improving robustness against some approximation errors introduced during the adaptation process. The algorithm implements global variations of the control law, which ensure a further increase in robustness. The results presented show how the proposed approach is capable of fully exploiting the multi-body dynamics of the problem; in fact, in one of the study cases, a fly-by of the Earth is scheduled, which was not included in the first guess solution. © Springer Science+Business Media B.V. 2009

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confidence: 99%

Optimal low-thrust trajectories to asteroids through an algorithm based on differential dynamic programming

Colombo

Vasile

Radice

2009

Celest Mech Dyn Astr

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“…[21], and actually this is one of the characteristics of interior constraints introduced by GA, i.e., part of the state variables are discontinuous while the remaining are not. The above notation conventions will be used in the following.…”

Section: Optimal Rendezvous Via Multiple Gravity Assistmentioning

confidence: 98%

“…Actually some missions like Mariner 10 and Voyager 1 have utilized intermediate GA and various problems associated with GA are treated in refs. [19][20][21][22]. However, most of the researchers formulate the problem as a parameter optimization problem or consider only the impulsive case.…”

Section: Introductionmentioning

confidence: 99%

Fuel optimal low thrust rendezvous with outer planets via gravity assist

Guo

Jiang

Baoyin

2011

Sci. China Phys. Mech. Astron.

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“…Other results and references can be found in Prado (1989), Prado and Rios-Neto (1993), Casalino and Colasurdo [1], Santos [2]. The most used method in this model is the so called "primer-vector theory", developed by Lawden (1953 and1954) [4,5], according to Prado [6,7], Santos [8,9]. In this paper, theory of optimal control is applied and a procedure based on the Newton's Method to decide the boundary problems is developed.…”

Section: Introductionmentioning

confidence: 99%

Optimal trajectories towards near-earth-objects using solar electric propulsion (SEP) and gravity assisted maneuver

Santos¹,

Casalino²,

Colasurdo³

et al. 2008

JAESA

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Abstract:The solar electric propulsion could be the best option for the transports of the future due to its high specific impulse when compared to the chemical propulsion. Electric propellants are being extensively used to assist the propulsion of terrestrial satellites for the maneuvers of orbit correction and as primary propulsion in missions toward other bodies of the solar system. In this work the optimization of interplanetary missions using solar electric propulsion (SEP) and Gravity Assisted Maneuver to reduce the costs of the mission, is considered. The high specific impulse of electric propulsion makes a Gravity Assisted Maneuver 1 year after departure convenient. Missions for several Near Earth Asteroids will be considered. The analysis suggests criteria for the definition of initial solutions demanded for the process of optimization of trajectories. Trajectories to the asteroid 2002TC70 are analyzed. Direct trajectories, trajectories with 1 gravity assisted at the Earth and with 2 gravity assisted with the Earth and either Mars are presented. Shall be analyzed missions with thrusters PPS1350 and the Phall 1 for performance comparison. An indirect optimization method will be used in the simulations.

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Optimal Low-Thrust Escape Trajectories Using Gravity Assist

Cited by 136 publications

References 7 publications

Optimal low-thrust trajectories to asteroids through an algorithm based on differential dynamic programming

Optimal low-thrust trajectories to asteroids through an algorithm based on differential dynamic programming

Fuel optimal low thrust rendezvous with outer planets via gravity assist

Optimal trajectories towards near-earth-objects using solar electric propulsion (SEP) and gravity assisted maneuver

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