Practical Systems Design for an Earth-Magnetotail-Monitoring Solar Sail Mission

Lappas,; Mengali, Giovanni; Quarta, Alessandro A.; Gil-Fernández, Jesús; Schmidt, Tanja D.; Wie, Bong

doi:10.2514/1.32040

Cited by 16 publications

(5 citation statements)

References 25 publications

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“…Solar sailing is a method of space propulsion where a spacecraft is propelled and sent potentially anywhere using the solar radiation pressure coming from the sun (McInnes, 2004;Vulpetti et al, 2014;Gong & Macdonald, 2019). The large ∆V changes in the solar sailing spacecraft caused by the continuous thrust generated by solar radiation pressure makes solar sails viable in missions beyond the solar system and involving deep space (Vulpetti, 2012;Lingam & Loeb, 2020), missions monitoring a planet's activity (Lappas et al, 2009;Macdonald et al, 2007;Ozimek et al, 2009) or harnessing materials from asteroids (Morrow et al, 2001;Peloni et al, 2016;Song & Gong, 2019).…”

Section: Introductionmentioning

confidence: 99%

A surface constraint approach for solar sail orbits

Garrido¹,

Esguerra²

2022

Preprint

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In this paper, a surface geometric constraint approach is used in designing the orbits of a solar sail. We solve the solar sail equation of motion by obtaining a generalized Laplace-Runge-Lenz (LRL) vector with the assumption that the cone angle is constant throughout the mission. A family of orbit equation solutions can then be specified by defining a constraint equation that relates the radial and polar velocities of the spacecraft and is dependent on the geometry of the surface where the spacecraft is expected to move. The proposed method is successfully applied in the design of orbits constrained on cylinders and to displaced non-Keplerian orbits.

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Section: Introductionmentioning

confidence: 99%

A surface constraint approach for solar sail orbits

Garrido¹,

Esguerra²

2022

Preprint

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“…Later, Mengali et al [14] developed an optimal steering law to trade off the apse-line precession capability. Based on the mission and system design requirements from ESA's technology reference studies, Lappas et al [15] proposed an alternate GeoSail design for the Earth's magnetotail study.…”

Section: Introductionmentioning

confidence: 99%

Dynamics and control of high area-to-mass ratio spacecraft and its application to geomagnetic exploration

Luo

Colombo

2018

Acta Astronautica

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“…However, actuators are necessary for the active schemes. For example, small reflective control vanes, gimbals, motors, translating and/or tilting sail panels, translating ballast mass, thrusters, or micro-PPT [1,4,[6][7][8][9][10][11][12] are usually used. These additional devices add additional mass and cost to the sailcraft, present additional demands for the sailcraft structural design, and introduce additional risk of failure [8].…”

Section: Introductionmentioning

confidence: 99%

Sensitivity analysis for a type of statically stable sailcrafts

Baoyin

2012

Acta Mech Sin

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Two types of sensitivities are proposed for statically stable sailcrafts. One type is the sensitivities of solar-radiation-pressure force with respect to position of the center of mass, and the other type is the sensitivities of solar-radiation-pressure force with respect to attitude. The two types of sensitivities represent how the solar-radiationpressure force changes with the position of mass center and the attitude. Sailcrafts with larger sensitivities undergo larger error of the solar-radiation-pressure force, leading to larger orbit error, as demonstrated by simulation. Then as a case study, detailed formulas are derived to calculate the sensitivities for sailcrafts with four triangular sails. According to these formulas, in order to reduce both types of sensitivities, the angle between opposed sails should not be too large, and the center of mass should be as close to the axis of symmetry of the four sails as possible and as far away from the center of pressure of the sailcraft as possible.Keywords Statically stable sailcraft · Sensitivity · Solarradiation-pressure force error · Mass center and pressure center errors · Attitude and orbit errorsDirection cosine matrix corresponding to rotation of φ rad about the λ-axis (λ = x, y, z)e 2 , e 3 [1 0 0] T , [0 1 0] T , [0 0 1] T F Resultant solar-radiation-pressure force represented in the body-fixed frame (N) F r , F ri Resultant solar-radiation-pressure force in the reference frame, the i-th component ofF r (N) n i Normal vector of S i O, O Apex of the cone formed by the four sails, center of the square A 1 A 2 B 2 B 1 O c , O i Center of mass of the whole sailcraft, pressure center of S i Ox b y b z b Body-fixed frame O r x r y r z r Reference frame P Pressure center of the sailcraft P 0 Nominal solar-radiation-pressure constant 1 AU from the Sun (N/m 2 ) R r Position vector of the sailcraft represented in the reference frame (AU) r, r c , r i Vector from P to O c , vector of mass center position, the i-th component of r (m)

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Practical Systems Design for an Earth-Magnetotail-Monitoring Solar Sail Mission

Cited by 16 publications

References 25 publications

A surface constraint approach for solar sail orbits

A surface constraint approach for solar sail orbits

Dynamics and control of high area-to-mass ratio spacecraft and its application to geomagnetic exploration

Sensitivity analysis for a type of statically stable sailcrafts

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