Optimal longitudes determination for the station keeping of areostationary satellites

Silva, Juan J.; Romero, P.

doi:10.1016/j.pss.2012.11.013

Cited by 16 publications

(6 citation statements)

References 10 publications

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“…Mars has a very uneven gravitational pull due to large asymmetries in mass, making station keeping particularly problematic, especially for LMO. This would require considerable delta-V to maintain the orbit [60]. If a solenoid were to be placed in an areostationary orbit for Mars (the equivalent of Earth's geostationary) of a R 0 = 6R M then the much wider loop radius drastically reduces the magnetic field intensity needed to reach ∼100nT at R S =10R M of 460nT and consequently requires more than an order of magnitude less current at < 0.2GAmps.…”

Section: Solenoid Locations In Spacementioning

confidence: 99%

How to create an artificial magnetosphere for Mars

Bamford

Kellett

Green³

et al. 2022

Acta Astronautica

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Section: Solenoid Locations In Spacementioning

confidence: 99%

How to create an artificial magnetosphere for Mars

Bamford

Kellett

Green³

et al. 2022

Acta Astronautica

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“…This term is responsible for the existence of two stable and two unstable geographical longitudes for an aerostationary satellite. The two unstable Martian longitudes equal − 105° and 75° [12]. Therefore, the following equally-spaced geographical longitudes are chosen for the three satellites placed in areostationary orbit: − 135°, − 15°, 105°.…”

Section: Coverage Analysis For 3 Satellites In Areostationary Orbitmentioning

confidence: 99%

Mars Constellation Design and Low-Thrust Deployment Using Nonlinear Orbit Control

2022

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This research addresses the design of a Mars constellation composed of 12 satellites and devoted to telecommunications. While 3 satellites travel areostationary orbits, the remaining 9 satellites are placed in three distinct quasi-synchronous, inclined, circular orbits. The constellation at hand provides continuous global coverage, over the entire Martian surface. The use of 4 carrier vehicles, departing from a 4-sol orbit, is proposed as an affordable option for the purpose of deploying the entire constellation, even starting from dispersed initial conditions. Each carrier is driven toward the respective operational orbit using steerable and throttleable low-thrust propulsion, in conjunction with nonlinear orbit control. Lyapunov stability analysis leads to defining a feedback law that enjoys quasi-global stability properties. Orbit phasing concludes the constellation deployment, and is carried out by each satellite. The tradeoff between phasing time and propellant expenditure is characterized.

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“…Satellites in an areostationary orbit are subject to natural perturbations, which will incur added station keeping costs to maintain the spacecraft within prescribed mission required boundaries. ere exist four regions of longitudinal stability for areostationary satellites, which require minimal station keeping costs [7]. However, these locations are evenly distributed and continuous coverage from these points can only be ensured by a constellation of minimum four spacecraft.…”

Section: Mars Communications Constellation Missionmentioning

confidence: 99%

Small Mars Mission Architecture Study

Parfitt

McSweeney

Backer

et al. 2021

Advances in Astronomy

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While the vast majority of ESA’s funding for Mars exploration in the 2020s is planned to be invested in ExoMars and Mars Sample Return, there is an interest to assess the possibility of implementing a small mission to Mars in parallel with, or soon after, the completion of the MSR programme. A study was undertaken in the Concurrent Design Facility at ESA ESTEC to assess low-cost mission architectures for small satellite missions to Mars. Given strict programmatic constraints, the focus of the study was on a low-cost (<250MEuro Cost at Completion), short mission development schedule with a cost-driven spacecraft design and mission architecture. The study concluded that small, low-cost Mars missions are technically feasible for launch within the decade.

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Optimal longitudes determination for the station keeping of areostationary satellites

Cited by 16 publications

References 10 publications

How to create an artificial magnetosphere for Mars

How to create an artificial magnetosphere for Mars

Mars Constellation Design and Low-Thrust Deployment Using Nonlinear Orbit Control

Small Mars Mission Architecture Study

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