Solar power sail mission of OKEANOS

Mori, Osamu; Matsumoto, Jun; Chujo, Toshihiro; Matsushita, Masanori; Kato, Hideki; Saiki, Takanao; Tsuda, Yuichi; Kawaguchi, Jun’ichiro; Terui, Fuyuto; Mimasu, Yuya; Ono, Go; Ogawa, Naoko; Takao, Yuki; Kubo, Yasunori; Ohashi, Kunihide; Maghraby, Ahmed Kiyoshi Sugihara El; Okada, Tatsuaki; Iwata, T.; Yano, Hajime

doi:10.1007/s42064-019-0067-8

Cited by 35 publications

(8 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The development towards this point happened in trajectory analysis and technology development during more than a decade, on the background of a sustained resurgence of interest in small solar system bodies (SSSB). It saw the successful conclusion of the HAYABUSA and ROSETTA/PHILAE missions, the launch of HAYABUSA2 [29] with the small lander MASCOT aboard [34], the launch of OSIRIS-REx [31], the flight of the IKAROS [46] [60] [75] [76] [77] [78], and the first steps towards a long-term Solar Power Sail (SPS) propelled sample-return mission to the Trojan asteroids of Jupiter [79] [80] [81]. Among small solar system bodies, the near-Earth asteroids (NEA) in many ways may hold keys to our future on Earth and in space: for planetary science, they appear to represent a fairly good mix of the building blocks of the terrestrial planets while orbiting at an accessible distance; for planetary defence, they are the reservoir of almost all potential threats which we need to understand to protect Earth from dangerous impacts; and for the new emerging field of asteroid mining, their surfaces and interiors are the promising terra incognita to be mapped and prospected.…”

Section: The Gossamer-1 Qualification Modelmentioning

confidence: 99%

Capabilities of Gossamer-1 derived small spacecraft solar sails carrying Mascot-derived nanolanders for in-situ surveying of NEAs

et al. 2019

View full text Add to dashboard Cite

Any effort which intends to physically interact with specific asteroids requires understanding at least of the composition and multi-scale structure of the surface layers, sometimes also of the interior. Therefore, it is necessary first to characterize each target object sufficiently by a precursor mission to design the mission which then interacts with the object. In small solar system body (SSSB) science missions, this trend towards landing and sample-return missions is most apparent. It also has led to much interest in MASCOT-like landing modules and instrument carriers. They integrate at the instrument level to their mothership and by their size are compatible even with small interplanetary missions.The DLR-ESTEC GOSSAMER Roadmap NEA Science Working Groups' studies identified Multiple NEA Rendezvous (MNR) as one of the space science missions only feasible with solar sail propulsion. Parallel studies of Solar Polar Orbiter (SPO) and Displaced L1 (DL1) space weather early warning missions studies outlined very lightweight sailcraft and the use of separable payload modules for operations close to Earth as well as the ability to access any inclination and a wide range of heliocentric distances. These and many other studies outline the unique capability of solar sails to provide access to all SSSB, at least within the orbit of Jupiter. Since the original MNR study, significant progress has been made to explore the performance envelope of nearterm solar sails for multiple NEA rendezvous.However, although it is comparatively easy for solar sails to reach and rendezvous with objects in any inclination and in the complete range of semi-major axis and eccentricity relevant to NEOs and PHOs, it remains notoriously difficult for sailcraft to interact physically with a SSSB target object as e.g. the HAYABUSA missions do.The German Aerospace Center, DLR, recently brought the GOSSAMER solar sail deployment technology to qualification status in the GOSSAMER-1 project. Development of closely related technologies is continued for very large deployable membrane-based photovoltaic arrays in the GOSOLAR project.We expand the philosophy of the GOSSAMER solar sail concept of efficient multiple sub-spacecraft integration to also include landers for one-way in-situ investigations and sample-return missions. These are equally useful for planetary defence scenarios, SSSB science and NEO utilization. We outline the technological concept used to complete such missions and the synergetic integration and operation of sail and lander. We similarly extend the philosophy of MASCOT and use its characteristic features as well as the concept of Constraints-Driven Engineering for a wider range of operations.

show abstract

Section: The Gossamer-1 Qualification Modelmentioning

confidence: 99%

Capabilities of Gossamer-1 derived small spacecraft solar sails carrying Mascot-derived nanolanders for in-situ surveying of NEAs

et al. 2019

View full text Add to dashboard Cite

show abstract

“…An in-orbit variation of the clock angle may be obtained using a reaction wheel [25] capable of generating a torque along the spacecraft body axis aligned with the Sun-spacecraft line. The optimal steering law was then used to analyze typical heliocentric transfer trajectories in the preliminary mission design phase, including a transfer toward an asteroid [33][34][35].…”

Section: Introductionmentioning

confidence: 99%

Optimal interplanetary trajectories for Sun-facing ideal diffractive sails

et al. 2023

View full text Add to dashboard Cite

A diffractive sail is a solar sail whose exposed surface is covered by an advanced diffractive metamaterial film with engineered optical properties. This study examines the optimal performance of a diffractive solar sail with a Sun-facing attitude in a typical orbit-to-orbit heliocentric transfer. A Sun-facing attitude, which can be passively maintained through the suitable design of the sail shape, is obtained when the sail nominal plane is perpendicular to the Sun–spacecraft line. Unlike an ideal reflective sail, a Sun-facing diffractive sail generates a large transverse thrust component that can be effectively exploited to change the orbital angular momentum. Using a recent thrust model, this study determines the optimal control law of a Sun-facing ideal diffractive sail and simulates the minimum transfer times for a set of interplanetary mission scenarios. It also quantifies the performance difference between Sun-facing diffractive sail and reflective sail. A case study presents the results of a potential mission to the asteroid 16 Psyche.

show abstract

“…There are many applications based on the PF phenomenon. The most recognizable technologies are manipulations of fine particles in optical tweezers 11 , and the force induced by photons is also considered a potential propulsion drive in space solutions 12 .…”

Section: Introductionmentioning

confidence: 99%

Microcantilever-based current balance for precise measurement of the photon force

Pruchnik

Orłowska

Świadkowski

et al. 2023

Sci Rep

View full text Add to dashboard Cite

We present a method for the quantitative determination of the photon force (PF)—the force generated by the radiation pressure of photons reflected from the surface. We propose an experimental setup integrating innovative microelectromechanical system (MEMS) optimized for the detection of photon force (pfMEMS). An active microcantilever was used as the force detector, while the measurement was conducted in a closed-loop setup with electromagnetic force compensation. In opposition to our previous works, this measurement method provides quantitative not qualitative assessment of PF interaction. Final current-balance setup is suitable for light sources from tens of microwatts to few watts. In our article, we present the results of the performed experiments, in which we measured the PF interactions in the range up to 67.5 pN with resolution of 30 fN in the static measurement.

show abstract

Solar power sail mission of OKEANOS

Cited by 35 publications

References 6 publications

Capabilities of Gossamer-1 derived small spacecraft solar sails carrying Mascot-derived nanolanders for in-situ surveying of NEAs

Capabilities of Gossamer-1 derived small spacecraft solar sails carrying Mascot-derived nanolanders for in-situ surveying of NEAs

Optimal interplanetary trajectories for Sun-facing ideal diffractive sails

Microcantilever-based current balance for precise measurement of the photon force

Contact Info

Product

Resources

About