JP2015063118A - 可撓性熱制御材料 - Google Patents
可撓性熱制御材料 Download PDFInfo
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- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 15
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- 239000001257 hydrogen Substances 0.000 claims description 15
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- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 14
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- SKRWFPLZQAAQSU-UHFFFAOYSA-N stibanylidynetin;hydrate Chemical compound O.[Sn].[Sb] SKRWFPLZQAAQSU-UHFFFAOYSA-N 0.000 description 2
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- AMGQUBHHOARCQH-UHFFFAOYSA-N indium;oxotin Chemical compound [In].[Sn]=O AMGQUBHHOARCQH-UHFFFAOYSA-N 0.000 description 1
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- 229910052759 nickel Inorganic materials 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
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Images
Classifications
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Abstract
Description
反射層12は、高反射性材料層であることが好ましい。それにより太陽光を反射することで、機体への入熱を低減することが可能となる。ここで、高反射性材料層とは、高反射性金属と称される材料等で構成された層である。そのような高反射性金属の具体例としては、例えば、銀(Ag)、アルミニウム(Al)、及び金(Au)等を挙げることができるが、これらに限定されない。また高反射性材料層としては、金属元素の単体のみならず、合金、化合物、それらの複合材料等を使用することができる。
赤外線放射層13は、反射層12で反射された太陽光を宇宙空間に放射する機能を有する層である。宇宙空間においては、酸素のない真空状態となるため、熱移動媒体を必要としない輻射による熱移動が支配的となる。機体側20の熱は、赤外線放射率が大きいほど、宇宙空間へ放射されやすい。したがって、赤外線放射層13では、太陽光波長域の吸収が小さく、且つ、赤外線の放射率が大きい程、機体の温度上昇を抑制することができる。
また、シルセスキオキサン層13cを形成するのは、耐原子状酸素性がシリコーン材料の中で高いこと及びタックが無いことで好ましいものとなる。
図7は、可撓性熱制御材料を被着体へ施工する一例を示す模式図である。図示の例においては、被着体は、ロケットの推進薬タンク(例えば、液体水素タンク)である。図8〜図10は、図7におけるA部分を拡大した拡大模式断面図である。
ポリイミド発泡体断熱層41は、気泡がオープンセル構造の発泡体であり、真空断熱効果を発揮するものとなる。PIF断熱層31とポリイミド発泡体断熱層41との2層の断熱層42の厚さは、例えば10〜50mm程度とするのが好ましい。
図11は、ロケットの模式図の一例を示す図である。図11に示すように、推進薬タンクである液体水素タンク51の頭部側には台座52を介して衛星53が設けられている。液体水素タンク51の後方側にはロッド54を介して液体酸素タンク55が設けられ、エンジン56側に供給している。
本実施例では、液体水素タンク51の表面に、PIF断熱層31が形成されており、このPIF断熱層31の表面に、前述した実施例に係る可撓性熱制御材料10(10A〜10F)が被覆されている。なお、可撓性熱制御材料10(10A〜10E)は実施例1乃至6と同一であるので、その説明は省略する。
これにより、PIF断熱層31の表面に形成される可撓性熱制御材料10(10A〜10E)や衛星53に対して、出ガス33による蒸着等の悪影響を抑制するようにし、衛星53を保護するようにしている。
本実施例では、液体水素タンク51のタンク本体30aの表面に、PIF断熱層31とポリイミド発泡体断熱層41との2層構造の断熱層42が形成されており、この2層構造の断熱層42の表面に、前述した実施例に係る可撓性熱制御材料10(10A〜10E)が被覆されている。
12 反射層
13 赤外線放射層
14 酸化防止層
15 支持層
16 保護層
17 導電層
18 接合層
20 機体側(被着体側)
21 宇宙空間側
30 推進薬タンク(被着体)
31 PIF断熱層
41 ポリイミド発泡体断熱層
Claims (14)
- 太陽光を反射する反射層と、
赤外線を放射する赤外線放射層とを積層してなり、
前記赤外線放射層は、シリコーン材料で構成される可撓性熱制御材料。 - 前記赤外線放射層は、シリコーン材料で構成されるシリコーン層と、粘着剤層とを備え、
前記粘着剤層は、前記シリコーン層と前記反射層との間に設けられる請求項1に記載の可撓性熱制御材料。 - 前記粘着剤層は、シリコーン系粘着剤層である請求項2に記載の可撓性熱制御材料。
- 前記反射層において、前記赤外線放射層が積層された面とは反対側の面に、支持層を更に積層してなる請求項1から3いずれか1つに記載の可撓性熱制御材料。
- 前記赤外線放射層において、前記反射層が積層された面とは反対側の面に、保護層を更に積層してなる請求項1から4いずれか1つに記載の可撓性熱制御材料。
- 前記保護層の上に導電層を更に積層してなる請求項5に記載の可撓性熱制御材料。
- 前記反射層において、前記赤外線放射層が積層された面とは反対側の面に、酸化防止層を更に積層してなる請求項1から6いずれか1つに記載の可撓性熱制御材料。
- 前記酸化防止層は、前記反射層と前記支持層との間に設けられる請求項7に記載の可撓性熱制御材料。
- 接合層により被着体の表面に固定される請求項1から8いずれか1つに記載の可撓性熱制御材料。
- 締結部材により被着体の表面に固定される請求項1から9いずれか1つに記載の可撓性熱制御材料。
- 前記被着体が宇宙空間で使用されるロケット又は人工衛星の推進薬タンクである請求項9又は10に記載の可撓性熱制御材料。
- 前記推進薬タンクが液体水素タンクである請求項11に記載の可撓性熱制御材料。
- 前記被着体の表面にポリイソシアヌレートフォーム(PIF)断熱層又はポリイミド発泡体断熱層のいずれか一方又はこれらの積層体の断熱層である請求項9から12いずれか1つに記載の可撓性熱制御材料。
- 前記被着体の表面がポリイソシアヌレートフォーム(PIF)断熱層又はポリイミド発泡体断熱層のいずれか一方又はこれらの積層体にガス抜き用溝を有する請求項13に記載の可撓性熱制御材料。
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2014072893A JP6539429B2 (ja) | 2013-08-28 | 2014-03-31 | 可撓性熱制御材料及び推進薬タンク |
PCT/JP2014/072240 WO2015029974A1 (ja) | 2013-08-28 | 2014-08-26 | 可撓性熱制御材料 |
EP14839959.5A EP3015262B1 (en) | 2013-08-28 | 2014-08-26 | Flexible thermal-control material |
US14/904,727 US10220967B2 (en) | 2013-08-28 | 2014-08-26 | Flexible thermal-control material |
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JP2013177362 | 2013-08-28 | ||
JP2013177362 | 2013-08-28 | ||
JP2014072893A JP6539429B2 (ja) | 2013-08-28 | 2014-03-31 | 可撓性熱制御材料及び推進薬タンク |
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JP2015063118A true JP2015063118A (ja) | 2015-04-09 |
JP2015063118A5 JP2015063118A5 (ja) | 2017-04-13 |
JP6539429B2 JP6539429B2 (ja) | 2019-07-03 |
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KR101732488B1 (ko) | 2015-06-15 | 2017-05-04 | 한국과학기술원 | 전단농화유체를 이용한 내충격 플렉서블 복합체 및 이를 이용한 형태 가변 보호장치 |
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JP2019147540A (ja) * | 2017-11-22 | 2019-09-05 | ザ・ボーイング・カンパニーThe Boeing Company | 熱制御テープ、熱制御テープ系、及び宇宙船構造のための方法 |
JP2020182428A (ja) * | 2019-05-09 | 2020-11-12 | 大阪瓦斯株式会社 | 農業用ハウス |
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JP7213062B2 (ja) | 2017-11-22 | 2023-01-26 | ザ・ボーイング・カンパニー | 熱制御テープ、熱制御テープ系、及び宇宙船構造のための方法 |
JP2020182428A (ja) * | 2019-05-09 | 2020-11-12 | 大阪瓦斯株式会社 | 農業用ハウス |
JP7320982B2 (ja) | 2019-05-09 | 2023-08-04 | 大阪瓦斯株式会社 | 農業用ハウス |
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WO2015029974A1 (ja) | 2015-03-05 |
US20160159501A1 (en) | 2016-06-09 |
US10220967B2 (en) | 2019-03-05 |
EP3015262B1 (en) | 2020-11-04 |
EP3015262A4 (en) | 2016-05-25 |
JP6539429B2 (ja) | 2019-07-03 |
EP3015262A1 (en) | 2016-05-04 |
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