Test of filament wound CFRP prototype for cryogenic propellant tank of space plane

Takayuki Shimoda, Jianmei He, Yoshihiro Mizutani, Yoshiki Morino, Tetsuya Morimoto, Kenta Nagahama, Gandolfo di Vita, Stefania Cantoni

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

National Space Development Agency of Japan (NASDA) is conducting a feasibility study of applying CFRP to the cryogenic propellant tank of a reusable vehicle system. As a part of the feasibility study, we are now conducting tests of small filament winding (FW) tanks with 300mm diameter to study the possibility of the filament winding method for manufacturing. The first phase test of a FW tank was conducted in 1999. We analyzed the weak points of the first FW tank and conducted the second phase tank test under the collaboration works with Italian Aerospace Research Centre (CIRA). The design and manufacturing processes of the second phase test were improved, and the first tank was completed with half surface of the cylinder good (healthy surface) and another half no good with large wrinkles produced in the curing process. Leakage occurred in the first pressurization test at 0.3MPa at room temperature along a large wrinkle. After the leak points were repaired, the tank was used for waterproof testing at 1.0MPa and 1.5MPa and the strain data was obtained. Finally, we conducted a pressurization test at liquid nitrogen (LN2) temperature at 1.5MPa, 1.9MPa, and 2.0MPa. The healthy surface of the tank cylinder remained healthy even at 1.9MPa and there were no leaks occurred. The first leak occurred at 2.0MPa in the healthy area at LN2 temperature. This is a promising result for the next series for realizing a perfect tank.

Original languageEnglish
Title of host publicationAIAA/AAAF 11th International Space Planes and Hypersonic Systems and Technologies Conference
Publication statusPublished - 2002
Externally publishedYes
EventAIAA/AAAF 11th International Space Planes and Hypersonic Systems and Technologies Conference 2002 - Orleans
Duration: 2002 Sep 292002 Oct 4

Other

OtherAIAA/AAAF 11th International Space Planes and Hypersonic Systems and Technologies Conference 2002
CityOrleans
Period02/9/2902/10/4

Fingerprint

propellant tanks
Filament winding
carbon fiber reinforced plastics
Carbon fiber reinforced plastics
Propellants
Cryogenics
filament winding
cryogenics
filaments
prototypes
Pressurization
feasibility study
Liquid nitrogen
manufacturing
Temperature
Curing
temperature
conduction
leakage
test

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering
  • Control and Systems Engineering

Cite this

Shimoda, T., He, J., Mizutani, Y., Morino, Y., Morimoto, T., Nagahama, K., ... Cantoni, S. (2002). Test of filament wound CFRP prototype for cryogenic propellant tank of space plane. In AIAA/AAAF 11th International Space Planes and Hypersonic Systems and Technologies Conference

Test of filament wound CFRP prototype for cryogenic propellant tank of space plane. / Shimoda, Takayuki; He, Jianmei; Mizutani, Yoshihiro; Morino, Yoshiki; Morimoto, Tetsuya; Nagahama, Kenta; di Vita, Gandolfo; Cantoni, Stefania.

AIAA/AAAF 11th International Space Planes and Hypersonic Systems and Technologies Conference. 2002.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Shimoda, T, He, J, Mizutani, Y, Morino, Y, Morimoto, T, Nagahama, K, di Vita, G & Cantoni, S 2002, Test of filament wound CFRP prototype for cryogenic propellant tank of space plane. in AIAA/AAAF 11th International Space Planes and Hypersonic Systems and Technologies Conference. AIAA/AAAF 11th International Space Planes and Hypersonic Systems and Technologies Conference 2002, Orleans, 02/9/29.
Shimoda T, He J, Mizutani Y, Morino Y, Morimoto T, Nagahama K et al. Test of filament wound CFRP prototype for cryogenic propellant tank of space plane. In AIAA/AAAF 11th International Space Planes and Hypersonic Systems and Technologies Conference. 2002
Shimoda, Takayuki ; He, Jianmei ; Mizutani, Yoshihiro ; Morino, Yoshiki ; Morimoto, Tetsuya ; Nagahama, Kenta ; di Vita, Gandolfo ; Cantoni, Stefania. / Test of filament wound CFRP prototype for cryogenic propellant tank of space plane. AIAA/AAAF 11th International Space Planes and Hypersonic Systems and Technologies Conference. 2002.
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abstract = "National Space Development Agency of Japan (NASDA) is conducting a feasibility study of applying CFRP to the cryogenic propellant tank of a reusable vehicle system. As a part of the feasibility study, we are now conducting tests of small filament winding (FW) tanks with 300mm diameter to study the possibility of the filament winding method for manufacturing. The first phase test of a FW tank was conducted in 1999. We analyzed the weak points of the first FW tank and conducted the second phase tank test under the collaboration works with Italian Aerospace Research Centre (CIRA). The design and manufacturing processes of the second phase test were improved, and the first tank was completed with half surface of the cylinder good (healthy surface) and another half no good with large wrinkles produced in the curing process. Leakage occurred in the first pressurization test at 0.3MPa at room temperature along a large wrinkle. After the leak points were repaired, the tank was used for waterproof testing at 1.0MPa and 1.5MPa and the strain data was obtained. Finally, we conducted a pressurization test at liquid nitrogen (LN2) temperature at 1.5MPa, 1.9MPa, and 2.0MPa. The healthy surface of the tank cylinder remained healthy even at 1.9MPa and there were no leaks occurred. The first leak occurred at 2.0MPa in the healthy area at LN2 temperature. This is a promising result for the next series for realizing a perfect tank.",
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AU - Shimoda, Takayuki

AU - He, Jianmei

AU - Mizutani, Yoshihiro

AU - Morino, Yoshiki

AU - Morimoto, Tetsuya

AU - Nagahama, Kenta

AU - di Vita, Gandolfo

AU - Cantoni, Stefania

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