Trajectory Design in the Sun-Earth-Moon System Using Lunar Gravity Assists

1998 ◽  
Vol 35 (2) ◽  
pp. 191-198 ◽  
Author(s):  
Roby S. Wilson ◽  
Kathleen C. Howell
Keyword(s):  
Trajectory Design ◽  
The Sun ◽  
Lunar Gravity ◽  
Moon System ◽  
Gravity Assists

Leveraging L3 to transfer to L4 in the Sun-perturbed Earth-Moon system

2021 ◽  
Author(s):  
Yuying Liang ◽  
Begoña Nicolás ◽  
Àngel Jorba
Keyword(s):  
The Sun ◽  
Moon System

Addendum 2020 to ‘Measurement of the Earth’s rotation: 720 BC to AD 2015’

2021 ◽  
Vol 477 (2246) ◽  
pp. 20200776
Author(s):  
L. V. Morrison ◽  
F. R. Stephenson ◽  
C. Y. Hohenkerk ◽  
M. Zawilski
Keyword(s):  
Angular Momentum ◽  
Earth’S Rotation ◽  
The Sun ◽  
Earth's Rotation ◽  
Moon System ◽  
Link Type ◽  
The Earth ◽  
Solar Eclipses ◽  
Rotation Of The Earth

Historical reports of solar eclipses are added to our previous dataset (Stephenson et al. 2016 Proc. R. Soc. A 472 , 20160404 ( doi:10.1098/rspa.2016.0404 )) in order to refine our determination of centennial and longer-term changes since 720 BC in the rate of rotation of the Earth. The revised observed deceleration is −4.59 ± 0.08 × 10 −22  rad s −2 . By comparison the predicted tidal deceleration based on the conservation of angular momentum in the Sun–Earth–Moon system is −6.39 ± 0.03 × 10 −22  rad s −2 . These signify a mean accelerative component of +1.8 ± 0.1 × 10 −22  rad s −2 . There is also evidence of an oscillatory variation in the rate with a period of about 14 centuries.

scholarly journals On the Initial Distance of the Moon Forming in the Circumterrestrial Swarm

1972 ◽  
Vol 47 ◽  
pp. 402-404
Author(s):  
E. L. Ruskol
Keyword(s):  
Angular Momentum ◽  
Total Angular Momentum ◽  
Outer Boundary ◽  
The Sun ◽  
The Moon ◽  
Present Value ◽  
Primitive Earth ◽  
Moon System ◽  
Initial Distance ◽  
The Earth

According to the Radzievskij-Artemjev hypothesis of the ‘locked’ revolution of the circumplanetary swarms around the Sun, the initial Moon-to-Earth distance and the angular momentum acquired by the Earth through the accretion of the inner part of the swarm can be evaluated. Depending on the concentration of the density to the centre of the swarm we obtain the initial distance for a single protomoon in the range 15–26 Earth radii R and for a system of 3-4 protomoons in the range 3–78 R, if the outer boundary of the swarm equals to the radius of the Hill's sphere (235 R). The total angular momentum acquired by the primitive Earth-Moon system through the accretion of the swarm particles is ½–⅔ of its present value. The rest of it should be acquired from the direct accretion of interplanetary particles by the Earth. The contribution of satellite swarms into the rotation of other planets is relatively less.

scholarly journals Design Of Lunar-Gravity-Assisted Escape Trajectories

2020 ◽  
Vol 67 (4) ◽  
pp. 1374-1390
Author(s):  
Lorenzo Casalino ◽  
Gregory Lantoine
Keyword(s):  
Lunar Gravity ◽  
Gravity Assist ◽  
Analytical Treatment ◽  
Direct Optimization ◽  
Earth Asteroid ◽  
Combined Use ◽  
Escape Trajectories ◽  
Gravity Assists ◽  
Lunar Gravity Assist ◽  
Near Earth Asteroids

AbstractLunar gravity assist is a means to boost the energy and C3 of an escape trajectory. Trajectories with two lunar gravity assists are considered and analyzed. Two approaches are applied and tested for the design of missions aimed at Near-Earth asteroids. In the first method, indirect optimization of the heliocentric leg is combined to an approximate analytical treatment of the geocentric phase for short escape trajectories. In the second method, the results of pre-computed maps of escape C3 are employed for the design of longer Sun-perturbed escape sequences combined with direct optimization of the heliocentric leg. Features are compared and suggestions about a combined use of the approaches are presented. The techniques are efficiently applied to the design of a mission to a near-Earth asteroid.

scholarly journals An Earth–Moon system trajectory design reference catalog

2015 ◽  
Vol 110 ◽  
pp. 341-353 ◽  
Author(s):  
David C. Folta ◽  
Natasha Bosanac ◽  
Davide Guzzetti ◽  
Kathleen C. Howell
Keyword(s):  
Trajectory Design ◽  
Moon System ◽  
System Trajectory

scholarly journals Qualitative Dynamics of the Sun-Jupiter-Saturn System

1978 ◽  
Vol 41 ◽  
pp. 53-55
Author(s):  
V. Szebehely
Keyword(s):  
Body Problem ◽  
Stellar Systems ◽  
The Sun ◽  
Three Body Problem ◽  
Moon System ◽  
The Earth ◽  
Qualitative Dynamics ◽  
Binary Orbit ◽  
The Stability ◽  
Three Body

AbstractThe stability of the three-body problem formed by the Sun, Jupiter and Saturn is investigated using surfaces of zero velocity. The results obtained with the models of the restricted and general problems of three bodies are compared with numerical integration. The system is found to be stable in the sense that Saturn will neither interrupt the (perturbed) binary orbit of Jupiter around the Sun, nor will it escape from the system. It is shown that the known classical triple stellar systems are “more stable” than the solar system, which in turn is “more stable” than the Earth-Moon system.

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