Bounded lunar relative orbits

Nie, Tao; Gurfil, Pini; Zhang, Shijie

doi:10.1016/j.actaastro.2019.01.018

Cited by 11 publications

(3 citation statements)

References 32 publications

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“…According to previous studies, 𝐽 2 and 𝐶 22 are the most significant terms of the lunar gravity field function. Thus, the perturbation potential leveraged in this study will feature the gravity model of the Moon until the 𝐶 22 term, while higher order terms will be neglected [13].…”

Section: A Lunar Orbital Forcesmentioning

confidence: 99%

Surrogate Modeling of Orbital Decay of Lunar Orbits

Varoqui

Steffens

Mavris

2023

AIAA SCITECH 2023 Forum

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Operations in cislunar space are expected to greatly increase over the next decade, which will place a heightened demand on satellites operating in cislunar space. The orbit selection of the satellites is a key parameter of the mission. Orbital decay can present significant challenges for some lunar orbits due to gravitational perturbations. This study focuses on developing a fast method to assess the decay of lunar orbits. The method is based on modeling lunar orbits propagation in the presence of these perturbations to quantify orbital decay as a function of orbital parameters, then using the model to generate data and fit surrogate models. Results from this effort will enable decision makers to trade performance and station-keeping costs associated with relevant lunar orbits.

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Section: A Lunar Orbital Forcesmentioning

confidence: 99%

Surrogate Modeling of Orbital Decay of Lunar Orbits

Varoqui

Steffens

Mavris

2023

AIAA SCITECH 2023 Forum

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“…Extensive research is ongoing also on orbits and trajectories in more general contexts. [3,4,7,9,10,11,12] The Apollo missions have shown that free-return ballistic figure eight shaped trajectories have required only minor orbit adjustments to traverse between Earth and Moon [14]. However such trajectories provide only for one round trip between the Earth and the Moon.…”

Section: Introductionmentioning

confidence: 99%

Determination of the Optimal Elliptical Trajectories Around the Earth and Moon

Carter

Humi

2023

Preprint

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Current space exploration programs call for the establishment of a permanent Human presence on the Moon. This paper considers periodic orbits of a shuttle between the Earth and the Moon. Such a shuttle will be needed to bring supplies to the Moon outpost and carry back those resources that are in short supply on Earth. To keep this shuttle in permanent periodic orbit it must have a thruster that forces it into an elliptical orbit from perigee near Earth to an apogee just beyond the Moon and back to perigee. The impacts of the Earth, Moon and Sun gravity on this orbit are considered. For this model we determine the eccentricity that minimizes the thrust requirements and the lunar ∆ υ requirements. We show that optimal placements of the eccentricity of the shuttle orbit can produce significant improvement in thrust (and fuel) requirements.

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“…The overall objective of Chandrayaan-2 was to collect samples from the lunar surface and analyze them on-site, relaying data to Earth via the orbiter. Unfortunately, Vikram lander lost control 500 m short of the lunar surface and crashed (Jones, 2015;Sahinoz, 2012;Battrick et al, 1992;Huang et al, 2015;Borowski et al, 2018). The glitch was unexpected since the software was functioning well throughout the trial period.…”

Section: Introductionmentioning

confidence: 99%

Design and Analysis of a Lunar Lander's Landing System

Talekar¹,

Dabholkar²,

Thombe³

et al. 2021

Journal of Aircraft and Spacecraft Technology

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In the overall design and performance prediction of spacecraft intended to accomplish delicate landing on the moon, touchdown dynamics analysis during the landing phase is one of the most important task. Missions in the past have experienced toppling of the lander due to the surface on the lunar body being covered with dead volcanoes and impact craters that restrict the smooth landing of the lander. Similar problem may arise in the future too. The main aim of work is to ensure that six feet touch the oblique terrain at the same time so that the capsule remains horizontally parallel to the ground and intact during landing. When the lander hits the ground, the force will propagate from the ground to the skid pads, then to the lower leg part and finally to the damper. Then, the damper absorbs the impact caused by the landing. The honeycomb structure consumes the applied force by getting crushed vertically. At a particular point, this force won't be sufficient to further crush the structure and the crumpling stops and the lander achieves its stability. The simulations of damper design and landing gear designs are carried out to attain lunar landing stability.

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Bounded lunar relative orbits

Cited by 11 publications

References 32 publications

Surrogate Modeling of Orbital Decay of Lunar Orbits

Surrogate Modeling of Orbital Decay of Lunar Orbits

Determination of the Optimal Elliptical Trajectories Around the Earth and Moon

Design and Analysis of a Lunar Lander's Landing System

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