Transfer orbit design of LEO to moon using earth-moon system lagrangian points in the presence of disturbances

Document Type : Research Paper

Authors

1 Assistant Professor, Aerospace Engineering Department, Malek Ashtar University of Technology

2 Graduated Student, Aerospace Engineering Department, Malek Ashtar University of Technology

Abstract

In this paper, an improved trajectory design to reach LEO orbit to an orbital near the moon called Lunar is investigated in the presence of disturbances using Lagrangian points of the Earth-Moon system. For this purpose, the Lagrangian L1 point in the system, due to its proper position, plays the role of the mediator for the desired transfer, so that, first, the equations of motion of three finite objects to reach the LEO orbit to the adjacency of L1 and then to go to the Lunar orbit L1 is solved, eventually the periodic orbits around L1 are used to connect two trajectories to achieve the desired trajectory. In the following, the disturbance model is also added to the equations of motion of the restricted 3-body problem in order to evaluate its effect on the results. The simulation results show that the required impulse is better than the Hohmann transfer method even in the presence of disturbances.

Keywords

References

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Aerospace Knowledge and Technology Journal
Volume 9, Issue 2 - Serial Number 2
October 2020
Pages 193-206

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