| (19) |
 |
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(11) |
EP 1 460 048 A8 |
| (12) |
CORRECTED EUROPEAN PATENT APPLICATION |
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published in accordance with Art. 158(3) EPC |
| (48) |
Corrigendum issued on: |
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19.01.2005 Bulletin 2005/03 |
| (43) |
Date of publication: |
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22.09.2004 Bulletin 2004/39 |
| (22) |
Date of filing: 25.12.2002 |
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| (86) |
International application number: |
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PCT/JP2002/013503 |
| (87) |
International publication number: |
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WO 2003/055825 (10.07.2003 Gazette 2003/28) |
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| (84) |
Designated Contracting States: |
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AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SI SK TR |
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Designated Extension States: |
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AL LT LV MK RO |
| (30) |
Priority: |
26.12.2001 JP 2001392961
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| (71) |
Applicant: Mitsubishi Heavy Industries, Ltd. |
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Tokyo 100-8315 (JP) |
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| (72) |
Inventors: |
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- OGURI, Kazuyuki Mitsubishi Heavy Industries, Ltd.
Nagoya-shi, Aichi 455-8515 (JP)
- SEKIGAWA, Takahiro Mitsubishi Heavy Industries,Ltd
Nagoya-shi, Aichi 455-8515 (JP)
|
| (74) |
Representative: Henkel, Feiler & Hänzel |
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Möhlstrasse 37
81675 München
81675 München (DE) |
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| |
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| (54) |
HEAT-RESISTANT MATERIAL AND HOT STRUCTURE MEMBER BOTH FOR SPACE SHUTTLE, SPACE SHUTTLE,
AND METHOD FOR PRODUCING HEAT-RESISTANT MATERIAL FOR SPACE SHUTTLE |
(57) An inexpensive high temperature oxidation resistant material for spacecraft, having
a higher heat resistance than a conventional oxidation resistant material of a silicon
carbide coating system, which may be readily formed into a desired shape, a hot structure
part including the oxidation resistant material for spacecraft, a spacecraft provided
with the hot structure part, and a method for producing the oxidation resistant material
for spacecraft are provided. The oxidation resistant material for spacecraft includes
a ceramic material in which silicon carbide is included in zirconium boride. The method
for producing the oxidation resistant material for spacecraft includes the steps of
including SiC in zirconium boride, and molding by means of a normal pressure sintering
method.