Design Exploration of Low-Thrust Space Trajectory Problem for DESTINY Mission

Watanabe, Takeshi; Tatsukawa, Tomoaki; Yamamoto, Takayuki; Oyama, Akira; Kawakatsu, Yasuhiro

doi:10.2514/1.a33646

Cited by 5 publications

(5 citation statements)

References 7 publications

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“…The SOR trajectory design significantly impacts the spacecraft system design, including radiation tolerance, power budget during eclipses, lifetime, and IES ∆V budget. In the preliminary analyses, we apply a Multi-Objective Evolutionary Algorithm (MOEA) [6] to the entire SOR trajectory considering the radiation environment, eclipse duration, time of flight, and fuel consumption. The result showed that the trajectory could be divided into three sub-phases for an enhanced optimization.…”

Section: Spiral Orbit-raising Phasementioning

confidence: 99%

“…To tackle the com-plex trajectory design, we divide the entire mission into three phases: the Spiral Orbit-Raising (SOR) phase, the Moon Flyby (MFB) phase, and the Interplanetary Transfer (IPT) phase. The SOR trajectory design needs to optimize a low-thrust manyrevolutions trajectory considering the system constraints [6,7,8]. ESA's SMART-1 mission also relied on spiral orbit raising to insert the spacecraft into orbit around the Moon [9].…”

Section: Introductionmentioning

confidence: 99%

“…DESTINY + equips a low-thrust propulsion system with larger maneuverability, making the trajectory design more complex. Although previous studies tackled some parts of the trajectory design [6,7,14,15,16,17], the overall mission design and its methodology that patches all segments together have not been reported yet.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Mission design of DESTINY+: Toward active asteroid (3200) Phaethon and multiple small bodies

Ozaki

Yamamoto²,

Gonzalez-Franquesa

et al. 2022

Acta Astronautica

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Section: Spiral Orbit-raising Phasementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Mission design of DESTINY+: Toward active asteroid (3200) Phaethon and multiple small bodies

Ozaki

Yamamoto²,

Gonzalez-Franquesa

et al. 2022

Acta Astronautica

Self Cite

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“…In the third subphase, SOR-3, we initiate coasting arcs in order to reduce the fuel consumption and design low-thrust many-revolution trajectories by solving multi-objective optimization. To solve the SOR-3 problem, we employ an averaging method to propagate the low-thrust many-revolutions trajectory [36] and employ a Multi-Objective Evolutionary Algorithm (MOEA) [6].…”

Section: Spiral Orbit-raising Phasementioning

confidence: 99%

Mission Design of DESTINY+: Toward Active Asteroid (3200) Phaethon and Multiple Small Bodies

Ozaki,

Yamamoto,

Gonzalez-Franquesa

et al. 2022

Preprint

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DESTINY + is an upcoming JAXA Epsilon medium-class mission to flyby the Geminids meteor shower parent body (3200) Phaethon. It will be the world's first spacecraft to escape from a near-geostationary transfer orbit into deep space using a lowthrust propulsion system. In doing so, DESTINY + will demonstrate a number of technologies that include a highly efficient ion engine system, lightweight solar array panels, and advanced asteroid flyby observation instruments. These demonstrations will pave the way for JAXA's envisioned low-cost, high-frequency space exploration plans. Following the Phaethon flyby observation, DESTINY + will visit additional asteroids as its extended mission. The mission design is divided into three phases: a spiralshaped apogee-raising phase, a multi-lunar-flyby phase to escape Earth, and an interplanetary and asteroids flyby phase. The main challenges include the optimization of the many-revolution low-thrust spiral phase under operational constraints; the design of a multi-lunar-flyby sequence in a multi-body environment; and the design of multiple asteroid flybys connected via Earth gravity assists. This paper shows a novel, practical approach to tackle these complex problems, and presents feasible solutions found within the mass budget and mission constraints. Among them, the baseline solution is shown and discussed in depth; DESTINY + will spend two years raising its apogee with ion engines, followed by four lunar gravity assists, and a flyby of asteroids (3200) Phaethon and (155140) 2005 UD. Finally, the flight operations plan for the spiral phase and the asteroid flyby phase are presented in detail.

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“…MOEAs have excellent features, such as the capability to obtain the Pareto optimal solutions. In the field of aerospace engineering, this approach has been employed to optimize the design of space trajectories [1][2][3], mission planning of satellite operators [4], and design of rocket engines [5][6][7][8], flame deflectors [9], and aerodynamic design [10][11][12][13][14][15][16][17][18][19]. Pareto optimal solutions or suitable design candidates were obtained.…”

Section: Introductionmentioning

confidence: 99%

Accuracy Improvement Technique of DNN for Accelerating CFD Simulator

Tsunoda¹,

Mori²,

Akima³

et al. 2022

AIAA SCITECH 2022 Forum

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There is a Computational fluid dynamics (CFD) method of incorporating the DNN inference to reduce the computational cost. The reduction is realized by replacing some calculations by DNN inference. The cost reduction depends on the implementation method of the DNN and the accuracy of the DNN inference. Thus, we propose two techniques suitable to infer flow field on the CFD grid. The first technique is to infer the flow field of the steady state from the airfoil shape. We use the position on the coordinates of the grid point and the distance from the surface of the airfoil as input information for the DNN. The second method uses the customized mean square error as a loss function. The size of the associated area for each grid point was multiplied by the square error. This method compensates for the effect caused by the size of the associated area of nonuniform allocation of grid points. The evaluation results show that the CFD incorporated first technique achieves 1.7x speedup against the CFD without DNN, while maintaining equivalent result quality. By implementing the second technique, the CFD realized further 2.3x speed up against the CFD with first technique only.

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Design Exploration of Low-Thrust Space Trajectory Problem for DESTINY Mission

Cited by 5 publications

References 7 publications

Mission design of DESTINY+: Toward active asteroid (3200) Phaethon and multiple small bodies

Mission design of DESTINY+: Toward active asteroid (3200) Phaethon and multiple small bodies

Mission Design of DESTINY+: Toward Active Asteroid (3200) Phaethon and Multiple Small Bodies

Accuracy Improvement Technique of DNN for Accelerating CFD Simulator

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