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Space Science Reviews

, Volume 208, Issue 1–4, pp 125–142 | Cite as

System Configuration and Operation Plan of Hayabusa2 DCAM3-D Camera System for Scientific Observation During SCI Impact Experiment

  • Kazunori OgawaEmail author
  • Kei Shirai
  • Hirotaka Sawada
  • Masahiko Arakawa
  • Rie Honda
  • Koji Wada
  • Ko Ishibashi
  • Yu-ichi Iijima
  • Naoya Sakatani
  • Satoru Nakazawa
  • Hajime Hayakawa
Article

Abstract

An artificial impact experiment is scheduled for 2018–2019 in which an impactor will collide with asteroid 162137 Ryugu (1999 \(\mathrm{JU}_{3}\)) during the asteroid rendezvous phase of the Hayabusa2 spacecraft. The small carry-on impactor (SCI) will shoot a 2-kg projectile at 2 km/s to create a crater 1–10 m in diameter with an expected subsequent ejecta curtain of a 100-m scale on an ideal sandy surface. A miniaturized deployable camera (DCAM3) unit will separate from the spacecraft at about 1 km from impact, and simultaneously conduct optical observations of the experiment. We designed and developed a camera system (DCAM3-D) in the DCAM3, specialized for scientific observations of impact phenomenon, in order to clarify the subsurface structure, construct theories of impact applicable in a microgravity environment, and identify the impact point on the asteroid. The DCAM3-D system consists of a miniaturized camera with a wide-angle and high-focusing performance, high-speed radio communication devices, and control units with large data storage on both the DCAM3 unit and the spacecraft. These components were successfully developed under severe constraints of size, mass and power, and the whole DCAM3-D system has passed all tests verifying functions, performance, and environmental tolerance. Results indicated sufficient potential to conduct the scientific observations during the SCI impact experiment. An operation plan was carefully considered along with the configuration and a time schedule of the impact experiment, and pre-programed into the control unit before the launch. In this paper, we describe details of the system design concept, specifications, and the operating plan of the DCAM3-D system, focusing on the feasibility of scientific observations.

Keywords

DCAM3 SCI Hayabusa2 Impact experiment Asteroid 

Notes

Acknowledgements

The authors gratefully acknowledge the dedicated efforts of Mr. Osamu Nara and the engineers of Meisei Electric Co., Ltd., and Dr. Yuji Ikeda of Photocoding Inc., Japan. We also acknowledge the important advice on the radio communication unit provided by Dr. Tomoaki Toda of the Japan Aerospace Exploration Agency. The authors thank two anonymous reviewers for helpful comments that improved this paper.

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Copyright information

© Springer Science+Business Media Dordrecht 2017

Authors and Affiliations

  • Kazunori Ogawa
    • 1
    Email author
  • Kei Shirai
    • 2
  • Hirotaka Sawada
    • 3
  • Masahiko Arakawa
    • 1
  • Rie Honda
    • 4
  • Koji Wada
    • 5
  • Ko Ishibashi
    • 5
  • Yu-ichi Iijima
    • 2
  • Naoya Sakatani
    • 6
  • Satoru Nakazawa
    • 2
  • Hajime Hayakawa
    • 2
  1. 1.Department of PlanetologyKobe UniversityHyogoJapan
  2. 2.Institute of Space and Astronautical ScienceJapan Aerospace Exploration AgencySagamiharaJapan
  3. 3.Space Exploration Innovation HubJapan Aerospace Exploration AgencySagamiharaJapan
  4. 4.Department of Information ScienceKochi UniversityKochiJapan
  5. 5.Planetary Exploration Research CenterChiba Institute of TechnologyNarashinoJapan
  6. 6.Department of PhysicsMeiji UniversityKawasakiJapan

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