Three-stage approach to optimal low-thrust Earth-moon trajectories

Pierson, Bion L.; Kluever, Craig A.

doi:10.2514/3.21344

Cited by 71 publications

(48 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The overall trajectory is divided in a sequence of problems, each of them expressed in the primary body reference frame; different segments are then patched together, through boundary constraints at the edge of each segment (direct methods), or through conditions on states and costates (indirect methods). Many applications have been presented, making use of direct methods (Tang and Conway 1995;Herman and Spencer 2002;, indirect methods (Guelman 1995;Vadali et al 2000;Nah et al 2001;Ranieri and Ocampo 2005), or hybrid methods (Pierson and Kluever 1994;Kluever and Pierson 1995).…”

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

View full text Add to dashboard Cite

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

show abstract

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

View full text Add to dashboard Cite

show abstract

“…4 Trajectory design with a constant-thrust electric propulsion system has been studied by Kluever, Pierson, and Chang, [5][6][7][8][9][10] and Enright, Herman, and Conway. 11,12 More recent work can be found in Betts et al, 13 and Yagasaki.…”

Section: Introductionmentioning

confidence: 99%

Fuel-Optimal Design of Moon-Earth Trajectories Using Legendre Pseudospectral Method

Park¹,

Ross

Sekhavat

2008

AIAA/AAS Astrodynamics Specialist Conference and Exhibit

View full text Add to dashboard Cite

A fuel-optimal trans-Earth trajectory design for manned lunar missions is presented. The gravitational effects of the Moon, Earth, and Sun constitute a 4-body problem. Imposing maximum thrust, fuel budget, and flight time as design constraints, we formulate a nonlinear constrained fuel-optimal control problem to obtain an optimal trajectory from a low lunar parking orbit to an Earth interface condition. The resulting optimal control problem is solved using Legendre pseudospectral method. An anti-aliasing method based on Bellman's principle of optimality is employed to test and improve the accuracy of the solution. All results are developed and obtained using the software package DIDO c .

show abstract

“…In general, a Moon exploration spacecraft must make a series of maneuvers and they are composed of trans-lunar trajectory injection, trajectory correction maneuvers and lunar orbit injection, in that sequence [1]. The nature of this series of maneuvers is determined by the type of the launch vehicle and the onboard spacecraft rockets.…”

Section: Introductionmentioning

confidence: 99%

“…Pierson and Kleuver [1] found out minimum-fuel planar trajectories from a circular low Earth parking orbit (LEO) to a circular low lunar parking orbit (LLO). The optimal low-thrust transfer problem studied in the classical CRTBP is solved by formulating and successively solving a hierarchy of subproblems.…”

Section: Introductionmentioning

confidence: 99%

A Study on Earth-Moon Transfer Orbit Design

No¹,

Lee²,

Jeon³

et al. 2012

International Journal of Aeronautical and Space Sciences

View full text Add to dashboard Cite

Optimal transfer trajectories based on the planar circular restricted three body problem are designed by using mixed impulsive and continuous thrust. Continuous and dynamic trajectory optimization is reformulated in the form of discrete optimization problem. This is done by the method of direct transcription and collocation. It is then solved by using nonlinear programming software. Two very different transfer trajectories can be obtained by the different combinations of the design parameters. Furthermore, it was found out that all designed trajectories permit a ballistic capture by the Moon's gravity. Finally, the required thrust profiles are presented and they are analyzed in detail.

show abstract

Three-stage approach to optimal low-thrust Earth-moon trajectories

Cited by 71 publications

References 8 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 Design of Moon-Earth Trajectories Using Legendre Pseudospectral Method

A Study on Earth-Moon Transfer Orbit Design

Contact Info

Product

Resources

About