A Study on Earth-Moon Transfer Orbit Design

No, Tae Soo; Lee, Ji Marn; Jeon, Gyeong Eon; Lee, Daero; Kim, Ghangho

doi:10.5139/ijass.2012.13.1.106

Cited by 6 publications

(3 citation statements)

References 22 publications

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“…Then, the whole transfer trajectory is divided into three segments: (1) perilune-boundary of the SOI of the Moon; (2) boundary of the SOI of the Moon-one day before re-entry; and (3) one day before re-entry-re-entry. Three impulses are applied in the whole process, that is, the connection impulse between every two segments in addition to the departure impulse at the perilune of Equation (28).…”

Section: Boundary Of Soi To the Day Before Re-entrymentioning

confidence: 99%

“…For the Earth-to-Moon trajectory design, researchers have developed multiple trajectory design technologies. The traditional impulse transfer is the classic method adopted by the first Moon exploration missions [27,28], while the small thrust transfer [29][30][31][32][33][34][35] and the weak stable boundary (WSB) transfer methods [36][37][38] appeared in the 1990s. In recent years, there have been the use of Moon flybys to achieve libration point transfers and even the deployment of Earth's high-orbit satellites [39,40].…”

Section: Introductionmentioning

confidence: 99%

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Integrated Design of Moon-to-Earth Transfer Trajectory Considering Re-Entry Constraints

et al. 2022

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The exploration of the Moon has always been a hot topic. The determination of the Moon-to-Earth transfer opportunity and the design of the precise transfer trajectory play important roles in manned Moon exploration missions. It is still a difficult problem to determine the Moon-to-Earth return opportunity for accurate atmospheric re-entry and landing, through which the actual return trajectory can be easily obtained later. This paper proposes an efficient integrated design method for Moon-to-Earth window searching and precise trajectory optimization considering the constraints of Earth re-entry and landing. First, an analytical geometry-based method is proposed to determine the state of the re-entry point according to the landing field and re-entry constraints to ensure accurate landing. Next, the transfer window is determined with the perilune heights, which are acquired by inversely integrating the re-entry state under the simplified dynamics as criterion. Then, the precise Moon-to-Earth trajectory is quickly obtained by a three-impulse correction. Simulations show the accuracy and efficiency of the proposed method compared with methods such as the patched-conic method and provide an explicit reference for future Moon exploration missions.

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Section: Boundary Of Soi To the Day Before Re-entrymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Integrated Design of Moon-to-Earth Transfer Trajectory Considering Re-Entry Constraints

et al. 2022

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“…A fundamental problem of astrodynamics is concerned with computing intercept trajectories or interplanetary mission orbit for objects in space [1,2]. These calculations are often performed assuming a predetermined time-of-flight (TOF).…”

Section: Introductionmentioning

confidence: 99%

Solution for Nonlinear Three-Dimensional Intercept Problem with Minimum Energy

Leeghim

Kim

Turner

2013

Mathematical Problems in Engineering

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Classical orbit intercept applications are commonly formulated and solved as Lambert-type problems, where the time-of-flight (TOF) is prescribed. For general three-dimensional intercept problems, selecting a meaningful TOF is often a difficult and an iterative process. This work overcomes this limitation of classical Lambert’s problem by reformulating the intercept problem in terms of a minimum-energy application, which then generates both the desired initial interceptor velocity and the TOF for the minimum-energy transfer. The optimization problem is formulated by using the classical Lagrangianfandgcoefficients, which map initial position and velocity vectors to future times, and a universal time variablex. A Newton-Raphson iteration algorithm is introduced for iteratively solving the problem. A generalized problem formulation is introduced for minimizing the TOF as part of the optimization problem. Several examples are presented, and the results are compared with the Hohmann transfer solution approaches. The resulting minimum-energy intercept solution algorithm is expected to be broadly useful as a starting iterative for applications spanning: targeting, rendezvous, interplanetary trajectory design, and so on.

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