Title:
DEPLOYABLE STRUCTURE AND DEPLOYABLE METHOD THEREFOR
Document Type and Number:
WIPO Patent Application WO/2019/138788
Kind Code:
A1
Abstract:
Provided is a deployable structure which can be compact in form while being stored before or after deployment and which does not retain fold lines. The nozzle 10 of a rocket motor 1 is constituted by a fixed nozzle 11 and a distortable nozzle 12, and the distortable nozzle 12 is attached and affixed to the rear end (lower side in Fig. 1) of the fixed nozzle 11. The distortable nozzle 12 has a truncated cone shape, and the rear end of the fixed nozzle 11 and the leading end (upper side in Fig. 1) of the distortable nozzle 12 have substantially the same diameter. The fixed nozzle 11 is composed of a material similar to that used in regular nozzles, such as a fiber-reinforced composite material. The distortable nozzle 12 is composed of a superelastic alloy.
Inventors:
TAKEUCHI SHINSUKE (JP)
SATO EIICHI (JP)
TOBE HIROBUMI (JP)
SATO EIICHI (JP)
TOBE HIROBUMI (JP)
Application Number:
PCT/JP2018/046315
Publication Date:
July 18, 2019
Filing Date:
December 17, 2018
Export Citation:
Assignee:
JAPAN AEROSPACE EXPLORATION (JP)
International Classes:
B64G1/00; B64G1/22
Foreign References:
| JPS6277135A | 1987-04-09 | |||
| JP2006521865A | 2006-09-28 | |||
| JP2003531673A | 2003-10-28 | |||
| JPH08509899A | 1996-10-22 |
Attorney, Agent or Firm:
TANAKA Shinichiro et al. (JP)
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