Mission to Retrograde Geo-equatorial Orbit (RGEO) using lunar swing-by

Aravind, R.; Harsh, Saurabh; Bandyopadhyay, Priyankar

doi:10.1109/aero.2012.6187036

Cited by 3 publications

(3 citation statements)

References 4 publications

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“…Considering that the transfers solved by the previous work (Zeng et al 2000;Aravind et al 2012) did not completely satisfy the constraints, an explanation of the existence of this transfer without middle way maneuver is firstly given. The six-dimensional phase space of this transfer offers the perfect demonstration of the existential explanation, but Poincaré proves that there is no analytical mathematical procedure to the transfers in the three-body problem.…”

Section: Existential Analysismentioning

confidence: 96%

“…To sum up, the retro-GEO gives all of the GEO-assets debris-warning per 12 hour, and the flight-manner saves fuel-cost to deploy a monitor-satellite to the retro-GEO by lunar swing-by. But, the cases until now in both reference (Zeng et al 2000;Aravind et al 2012) did not satisfy the orbital altitude constraints of the LEO departure and the retro-GEO insertion. The purpose of this paper is to discover the fundamental properties of the transfers in a three-body model, such as, whether the transfer with the free-return manner using the lunar swing-by is existed or not?…”

mentioning

confidence: 94%

“…Kawase et al (2001;2010) advanced the reasonable proposal that a monitor-satellite on the retro-GEO plays the debris-warning alertor for all of the GEO-assets. Aravind et al (2012) compared the final left-fuel of the same satellite using typical flight-manners to the same retro-GEO with different number of maneuvers. They also tried to calculate the final left-fuel of the lunar swing-by flight-manner, but the perigee-altitude of the return-earth phase is 124.75 km, it is far below the desired orbital altitude of the retro-GEO.…”

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confidence: 99%

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Properties of the Transfers from LEO to the Retrograde-GEO using Lunar Swing-by in a Three-Body Model

2021

Preprint

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A monitor-satellite on a retrograde geostationary earth orbit (retro-GEO) gives the GEO-assets debris-warnings per 12 hour. The properties of the transfers from a low earth orbit to the retro-GEO using lunar swing-by without middle-way maneuver are exhibited in a three-body model. Based on the Poincaré-section methodology, the proof of the existence of this transfer is proven in the planar circular restricted three-body problem (CR3BP) model. Then, the maximum altitude of the perilune of this transfer is solved using the sequence quadratic programming optimization algorithm. Besides, the orbital inclination changeable capacity of this transfer is calculated in the spatial CR3BP model by the continuation of the orbital design values in the planar CR3BP model. The numerical results show that the maximum altitude of the perilune is 892 km and the maximum orbital inclination changeable capacity is 138 degree relative to the plane of the Moon’s path. Further analysis show that the minimum sum of the two-impulse velocity increments (i.e., departure from LEO and insert into the retro-GEO) is 4.224 km/s, the change of the orbital inclination is 107 degree relative to the plane of the Moon’s path in this case. Due to the maximum angle of the plane of the Moon’s path on the equator is 28.6 degree per Metonic cycle (i.e., 18.6 years), everyday has a month window to match the longitude of the launch-site for trans-lunar injection.

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Section: Existential Analysismentioning

confidence: 96%

mentioning

confidence: 94%

mentioning

confidence: 99%

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Properties of the Transfers from LEO to the Retrograde-GEO using Lunar Swing-by in a Three-Body Model

2021

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A robust semi-analytic method to solve the minimumΔVtwo-impulse rendezvous problem

Koblick

2019

Advances in Space Research

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Properties of the lunar gravity assisted transfers from LEO to the retrograde-GEO

2021

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The 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.

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Mission to Retrograde Geo-equatorial Orbit (RGEO) using lunar swing-by

Cited by 3 publications

References 4 publications

Properties of the Transfers from LEO to the Retrograde-GEO using Lunar Swing-by in a Three-Body Model

Properties of the Transfers from LEO to the Retrograde-GEO using Lunar Swing-by in a Three-Body Model

A robust semi-analytic method to solve the minimumΔVtwo-impulse rendezvous problem

Properties of the lunar gravity assisted transfers from LEO to the retrograde-GEO

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