Mission Analysis of Sample Return from Jovian Trojan Asteroid by Solar Power Sail

Matsumoto, Jun; Funase, Ryu; Mori, Osamu; Shirasawa, Yoji; Ono, Go; Hamasaki, Taku; Hayashi, Naohiro; Chujo, Toshihiro; Motooka, Norizumi; Tanaka, Keita

doi:10.2322/tastj.12.pk_43

Cited by 4 publications

(4 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…An increase in the reliability of the analysis model is required; this can be achieved through comparison and validation with experiments (e.g., in an expansion tube or an arc-heated wind tunnel). 7 3.68 Table 6 Grid sensitivity for the HVRC without a rigid flare between present and fine grids Present Fine Error, % Number of grids 150 × 202 250 × 395 --Heat flux, W∕m 2 1.86 × 10 7 1.98 × 10 7 6.34 Table 7 Grid sensitivity for the HVRC with a rigid flare between present and fine grids Present Fine Error, % Number of grids 100 × 362 200 × 703 --Heat flux, W∕m 2 9.19 × 10 6 9.42 × 10 6 2.41 a) HVRC without the rigid flare at an altitude of 58 km b) HVRC with the rigid flare at an altitude of 64 km Fig. 19 Comparison of translational and electron temperatures for HVRCs using present and fine grids as grid sensitivity.…”

Section: Discussionmentioning

confidence: 99%

“…Examples of sample-return missions at high reentry velocity are Hayabusa [1,2] by the Japan Aerospace Exploration Agency (JAXA) and Stardust [3,4] by the NASA. Recently, a new mission for Jupiter Trojan-asteroid exploration with a solar sail was proposed by JAXA [5,6]. Moreover, sample-return missions from outer planets and their moons in the solar system have been proposed [7].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Aerodynamic-Heating Analysis of Sample-Return Capsule in Future Trojan-Asteroid Exploration

Takahashi

Yamada

2018

Journal of Thermophysics and Heat Transfer

View full text Add to dashboard Cite

In sample-return missions, the reentry velocity of a sample-return capsule is expected to be approximately 15 km∕s; however, the reentry velocity of the Hayabusa sample-return capsule was 11.8 km∕s. Strong aerodynamic heating caused by a high velocity can damage the capsule during reentry. To overcome this, two designs of highvelocity reentry capsules were proposed. In one design, a rigid flare was attached to decrease the ballistic coefficient by increasing the front projected area. In the other design, the conventional Hayabusa sample-return capsule was used with no modifications. In this study, the aerodynamic heating of the high-velocity reentry capsules and the Hayabusa sample-return capsule was analyzed using numerical simulations. Plasma flow in the shock layer at the front of the capsules and expansion flow in the wake region around the capsules were investigated. The profiles of convective and radiative heat fluxes on the surfaces of these capsules were predicted. The heat fluxes at the stagnation points predicted by the present numerical simulation were in good agreement with that of the empirical models. At the strongest aerodynamic-heating altitude, the total heat fluxes at the rear of the high-velocity reentry capsules and the Hayabusa sample-return capsule were approximately 2% of those in front of the capsules. Nomenclature A = area, m 2 a = model parameter B = blackbody function, W∕m 3 B C = ballistic coefficient C = mass fraction C d = drag coefficient D = effective diffusion coefficient, m 2 ∕s f = function h = enthalpy, J∕kg I = radiation intensity, W∕m 3 Kn GLL = gradient-length-local Knudsen number k = Boltzmann constant, J∕K M = molar mass, kg∕mol m = mass, kg N A = Avogadro constant, mol −1 n = normal direction coordinate, m q = heat flux, W∕m 2 R N = nose radius, m s = one-dimensional coordinate, m T = temperature, K u, V = velocity, m∕s γ = catalytic coefficient θ = angle, rad κ = absorption coefficient, m −1 λ = mean free path, m ρ = density, kg∕m 3 Ω = solid angle, sr Subscripts ele, e = electron i = chemical species rot, R = rotation stag = stagnation trs, T = translation vib, V = vibration w = wall λ = wavelength ∞ = freestream Superscripts conv = convection rad = radiation

show abstract

Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Aerodynamic-Heating Analysis of Sample-Return Capsule in Future Trojan-Asteroid Exploration

Takahashi

Yamada

2018

Journal of Thermophysics and Heat Transfer

View full text Add to dashboard Cite

show abstract

“…Currently, the Japan Aerospace Exploration Agency is studying the use of a solar-powered sail exploration spacecraft, Oversize Kite-craft for Exploration and Astronautics in the Outer Solar System (OKEANOS), which has been proposed for exploring the Trojan asteroids of Jupiter. 4) OKEANOS will be equipped with thin-film solar cells over the entire sail to increase power generation. Because OKEANOS will sail to the Jupiter area, farther than IKAROS, it will experience a larger temperature change of -100 °C.…”

Section: Introductionmentioning

confidence: 99%

Deformation Direction and Curvature Control of Multilayer Thin Films Produced by Sputtering

Ryota

Mori

Sugawara

2019

AEROSPACE TECHNOLOGY JAPAN

Self Cite

View full text Add to dashboard Cite

IKAROS, a solar sail spacecraft launched in 2010, demonstrated that thin-film solar cells can generate electricity. During this demonstration, it was found that the cells became curved, which destabilized the attitude of the spacecraft. Therefore, this study focused on a sputtering deposition technique that generates internal stress during the formation of thin films. The objective of this study was to control the curvature of a multilayer film by sputtering with a pattern. The effect of sputtering on the thin film was analyzed through experiments and simulations, and it was clarified that the cause of shape non-reproducibility is sputtering-induced stress.

show abstract

“…After rendezvousing with the asteroid, a sample return mission is optionally planned where the spacecraft will capture a sample of the asteroid and then bring it back to Earth. 4) Trojan asteroids are located at Lagrange points L4 and L5 associated with the Sun-Jupiter system (Fig. 2).…”

Section: Introductionmentioning

confidence: 99%

Trajectory Design and System Feasibility Analysis for Jovian Trojan Asteroid Exploration Mission Using Solar Power Sail

Funase

Mori

Shirasawa

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

Self Cite

View full text Add to dashboard Cite

The solar power sail is a deep space probe that will be powered by a hybrid propulsion system with solar photon acceleration and ion engines to explore the outer planetary regions of the Solar System without having to rely on nuclear power. The Japan Aerospace Exploration Agency (JAXA) launched the world's first solar sail demonstration spacecraft, "IKAROS" (Interplanetary Kite-craft Accelerated by Radiation Of the Sun), in 2010. This spacecraft successfully demonstrated several key technologies related to the use of a solar power sail in a deep space flight environment. JAXA is currently planning an outer Solar System exploration mission using the demonstrated solar power sail technology, where the spacecraft will fly to Jupiter and perform a swing-by for a Jovian Trojan asteroid. This study undertook a trajectory design and system feasibility analysis for this mission. Candidate target asteroids were selected based on ballistic trajectory analysis, and then, electric-propulsion, continuous-thrust trajectory design was conducted to verify the conditions assumed for the ballistic analysis (e.g., estimate of steering loss due to the low-thrust trajectory). It was found that out of over 4000 Trojan asteroids, only 7 are feasible candidates considering the preliminary system design results. To broaden the choice of target asteroids, it will be necessary to reduce the weight of the solar power sail itself, its deployment mechanism, and the bus electronics.

show abstract

Mission Analysis of Sample Return from Jovian Trojan Asteroid by Solar Power Sail

Cited by 4 publications

References 7 publications

Aerodynamic-Heating Analysis of Sample-Return Capsule in Future Trojan-Asteroid Exploration

Aerodynamic-Heating Analysis of Sample-Return Capsule in Future Trojan-Asteroid Exploration

Deformation Direction and Curvature Control of Multilayer Thin Films Produced by Sputtering

Trajectory Design and System Feasibility Analysis for Jovian Trojan Asteroid Exploration Mission Using Solar Power Sail

Contact Info

Product

Resources

About