scholarly journals Existence of Prograde Double-Double Orbits in the Equal-Mass Four-Body Problem

2018 ◽  
Vol 18 (4) ◽  
pp. 819-843 ◽  
Author(s):  
Wentian Kuang ◽  
Duokui Yan

AbstractBy introducing simple topological constraints and applying a binary decomposition method, we show the existence of a set of prograde double-double orbits for any rotation angle {\theta\in(0,\pi/7]} in the equal-mass four-body problem. A new geometric argument is introduced to show that for any {\theta\in(0,\pi/2)}, the action of the minimizer corresponding to the prograde double-double orbit is strictly greater than the action of the minimizer corresponding to the retrograde double-double orbit. This geometric argument can also be applied to study orbits in the planar three-body problem, such as the retrograde orbits, the prograde orbits, the Schubart orbit and the Hénon orbit.

2001 ◽  
Vol 27 (10) ◽  
pp. 678-682
Author(s):  
V. V. Orlov ◽  
A. V. Petrova ◽  
A. I. Martynova

2012 ◽  
Vol 45 (34) ◽  
pp. 345202 ◽  
Author(s):  
Toshiaki Fujiwara ◽  
Hiroshi Fukuda ◽  
Hiroshi Ozaki ◽  
Tetsuya Taniguchi

2018 ◽  
Vol 38 (4) ◽  
pp. 2187-2206
Author(s):  
Rongchang Liu ◽  
◽  
Jiangyuan Li ◽  
Duokui Yan

2016 ◽  
Vol 25 (3) ◽  
Author(s):  
A. Mylläri ◽  
V. Orlov ◽  
A. Chernin ◽  
A. Martynova ◽  
T. Mylläri

AbstractWe use symbolic dynamics in the classic equal-mass free-fall three-body problem. Different methods for constructing symbolic sequences (in the process of numerical integration of trajectories) allow one to demonstrate (and illustrate on the Agekian-Anosova map) sensitivity to initial conditions, estimate entropies (Shannon, Markov and others), plot binary collision curves, reveal systems with intensive triple interactions (interplay), etc.


2012 ◽  
Vol 45 (4) ◽  
pp. 045208 ◽  
Author(s):  
Toshiaki Fujiwara ◽  
Hiroshi Fukuda ◽  
Hiroshi Ozaki ◽  
Tetsuya Taniguchi

2021 ◽  
Vol 11 (1) ◽  
Author(s):  
Bo-yong He ◽  
Peng-bin Ma ◽  
Heng-nian Li

AbstractThe retrograde geostationary earth orbit (retro-GEO) is an Earth’s orbit. It has almost the same orbital altitude with that of a GEO, but an inclination of 180°. A retro-GEO monitor-satellite gives the GEO-assets vicinity space-debris warnings per 12 h. For various reasons, the westward launch direction is not compatible or economical. Thereby the transfer from a low earth orbit (LEO) to the retro-GEO via once lunar swing-by is a priority. The monitor-satellite departures from LEO and inserts into the retro-GEO both using only one tangential maneuver, in this paper, its transfer’s property is investigated. The existence of this transfer is verified firstly in the planar circular restricted three-body problem (CR3BP) model based on the Poincaré-section methodology. Then, the two-impulse values and the perilune altitudes are computed with different transfer durations in the planar CR3BP. Their dispersions are compared with different Sun azimuths in the planar bi-circular restricted four-body problem (BR4BP) model. Besides, the transfer’s inclination changeable capacity via lunar swing-by and the Sun-perturbed inclination changeable capacity are investigated. The results show that the two-impulse fuel-optimal transfer has the duration of 1.76 TU (i.e., 7.65 days) with the minimum values of 4.251 km s−1 in planar CR3BP, this value has a range of 4.249–4.252 km s−1 due to different Sun azimuths in planar BR4BP. Its perilune altitude changes from 552.6 to 621.9 km. In the spatial CR3BP, if the transfer duration is more than or equal to 4.00 TU (i.e., 17.59 days), the lunar gravity assisted transfer could insert the retro-GEO with any inclination. In the spatial BR4BP, the Sun’s perturbation does not affect this conclusion in most cases.


1973 ◽  
Vol 73 (1) ◽  
pp. 177-182 ◽  
Author(s):  
J. Lekner

AbstractWe consider the ground state of a system of three interacting particles of equal mass. An integro-differential equation is obtained for the optimum pair function f in the product wavefunction Ψ(123) = f(12)f(13)f(23). The solution for harmonic forces reproduces the known exact ground state. Approximate analytic solutions are obtained for inverse-square forces, and for a general force law in the semiclassical limit.


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