Overview of IKAROS Mission

Mori, Osamu; Shirasawa, Yoji; Mimasu, Yuya; Tsuda, Yuichi; Sawada, Hirotaka; Saiki, Takanao; Yamamoto, Takayuki; Yonekura, Katsuhide; Hoshino, Hiroo; Kawaguchi, Jun’ichiro; Funase, Ryu

doi:10.1007/978-3-642-34907-2_3

Cited by 38 publications

(20 citation statements)

References 7 publications

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“…To this aim, the paper investigates the possibility of controlling the surface figure through solar radiation pressure (SRP). Although being relatively small in magnitude, about 10 µN m −2 at the Earth's distance from the Sun, SRP has already been used successfully for passive attitude control of satellites [8] and for continuous propulsion of solar sails [9]. As the aperture size of a space reflector is expected to be as large as 100 m in diameter, solar pressure provides a force sufficient to deflect the thin reflective film.…”

Section: MC 0000-0001-6819-7178mentioning

confidence: 99%

“…The reflectivity can be modified using electrochromic coatings, which consist of an electroactive material that changes its surface reflectivity according to an applied electric potential [10,11], or the required reflectivity could be pre-fabricated through the surface coating. Electrochromic coatings have already been employed successfully for attitude control on the IKAROS solar sail (JAXA, Japan), in 2010 [9].…”

Section: Introductionmentioning

confidence: 99%

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Shape control of slack space reflectors using modulated solar pressure

et al. 2015

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The static deflection profile of a large spin-stabilized space reflector because of solar radiation pressure acting on its surface is investigated. Such a spacecraft consists of a thin reflective circular film, which is deployed from a supporting hoop structure in an untensioned, slack manner. This paper investigates the use of a variable reflectivity distribution across the surface to control the solar pressure force and hence the deflected shape. In this first analysis, the film material is modelled as one-dimensional slack radial strings with no resistance to bending or transverse shear, which enables a semi-analytic derivation of the nominal deflection profile. An inverse method is then used to find the reflectivity distribution that generates a specific, for example, parabolic deflection shape of the strings. Applying these results to a parabolic reflector, short focal distances can be obtained when large slack lengths of the film are employed. The development of such optically controlled reflector films enables future key mission applications such as solar power collection, radio-frequency antennae and optical telescopes.

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Section: MC 0000-0001-6819-7178mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Shape control of slack space reflectors using modulated solar pressure

et al. 2015

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“…With previous and planned solar-sail missions reaching lightness numbers of up to 0.015 (e.g. IKAROS:  = 0.001 (Mori, Shirasawa, Mimasu et al 2013), NanoSail-D2:  = 0.003 (Johnson, Whorton, Heaton et al 2011), LightSail-1:  = 0.011 (Biddy and Svitek 2012), and NEA Scout:  = 0.010 (Heaton, Ahmad and Miller 2017)) and estimates for near-term solar-sail technology reaching  = 0.04 (Heiligers, Fernandez, Stohlman et al 2019), this paper will consider a lightness number range of up to  = 0.1 to also reflect solar-sail technology expected in the farterm (Dachwald 2005). Returning to Eq.…”

Section: Solar-sail Induced Accelerationmentioning

confidence: 99%

“…This can be achieved through the use of vanes, by adopting an area-changing sail configuration (e.g. a rhombic sail (Ceriotti, Harkness and McRobb 2014), by using reflectivity control devices (Mori, Shirasawa, Mimasu et al 2013), or by adopting a heliogyro sail configuration (MacNeal 1967, Heiligers, Guerrant andLawrence 2017)).…”

Section: Trajectory and Orbit Controlmentioning

confidence: 99%

End-to-end trajectory design for a solar-sail-only pole-sitter at Venus, Earth, and Mars

Heiligers

Vergaaij

Ceriotti

2021

Advances in Space Research

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The concept of a pole-sitter has been under investigation for many years, showing the capability of a low-thrust propulsion system to maintain a spacecraft at a static position along a planet's polar axis.From such a position, the spacecraft has a view of the planet's polar regions equivalent to that of the low-and mid-latitudes from geostationary orbit. Previous work has hinted at the existence of polesitters that would only require a solar sail to provide the necessary propulsive thrust if a slight deviation from a position exactly along the polar axis is allowed, without compromising on the continuous view of the planet's polar region (a so-called quasi-pole-sitter). This paper conducts a further in-depth analysis of these high-potential solar-sail-only quasi-pole-sitters and presents a full end-to-end trajectory design: from launch and transfer to orbit design and orbit control. The results are the next steppingstone towards strengthening the feasibility and utility of these orbits for continuous planetary polar observation.

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“…The electrochromic layers should be on the edge of the mirror in order not to aect the collection of solar power. Electrochromic coatings have been successfully employed on the IKAROS solar sail for attitude control in 2010 [22].…”

Section: F Attitude Control and Shape Of The Reectormentioning

confidence: 99%

Space-Enhanced Terrestrial Solar Power for Equatorial Regions

Bonetti

McInnes

2019

Journal of Spacecraft and Rockets

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This paper investigates the concept of solar mirrors in a Earth orbit to provide large-scale terrestrial equatorial solar farms with additional solar power during the hours of darkness. A ower constellation of mirrors is considered in highly-eccentric orbits (semi-major axis=20270.4 km) in order to increase the time of visibility over the solar farms and, through this architecture, only two mirrors are needed to provide a complete night-coverage over three equatorial locations. Selecting the proper value for the orbit eccentricity, solar radiation pressure and Earth's oblateness perturbations act on the mirrors so that the apsidal motion of the orbit due to these perturbations is synchronized with the apparent motion of the Sun. Therefore, it can be guaranteed that the perigee always points towards the Sun and that the mirrors orbit mostly above the night side of the Earth. With respect to Geostationary orbit (GEO), the family of orbits considered in this paper allow a passive means to overcome issues related to orbital perturbations. Moreover, because of the large slant range from GEOs, a larger mirror is required to deliver the same energy that could be delivered from a lower orbit with a smaller mirror. As a result, a single anti-heliotropic ower constellation comprised of two mirrors of 50 km 2 would be able to deliver energy in the range of 4.60 − 5.20 GW h per day to 1000 km 2-solar farms on the equator. Finally, it is estimated that, deploying 90 of these constellations, the price of electricity could be reduced from 9.1 cents to 6 cents per kWh.

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Overview of IKAROS Mission

Cited by 38 publications

References 7 publications

Shape control of slack space reflectors using modulated solar pressure

Shape control of slack space reflectors using modulated solar pressure

End-to-end trajectory design for a solar-sail-only pole-sitter at Venus, Earth, and Mars

Space-Enhanced Terrestrial Solar Power for Equatorial Regions

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