JPH05203095A - Heat protecting system - Google Patents
Heat protecting systemInfo
- Publication number
- JPH05203095A JPH05203095A JP1077692A JP1077692A JPH05203095A JP H05203095 A JPH05203095 A JP H05203095A JP 1077692 A JP1077692 A JP 1077692A JP 1077692 A JP1077692 A JP 1077692A JP H05203095 A JPH05203095 A JP H05203095A
- Authority
- JP
- Japan
- Prior art keywords
- heat
- resistant shield
- structural body
- shield
- protection system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/12—Arrangements for supporting insulation from the wall or body insulated, e.g. by means of spacers between pipe and heat-insulating material; Arrangements specially adapted for supporting insulated bodies
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Thermal Insulation (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、航空機あるいは宇宙機
のような高熱を受ける物体に用いられる再使用可能な熱
防護システムに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a reusable thermal protection system for an object that is subject to high heat, such as an aircraft or spacecraft.
【０００２】[0002]
【従来の技術】宇宙機は、宇宙から大気圏に突入する
際、極めて高い空力加熱を受ける。この加熱時間は再突
入の軌道によって異なるが、一般に約１５〜２５分継続
する。この時の空力加熱率は、図２に示すように、宇宙
機の機首１および翼前縁２ａで最も高く、翼の下面２ｂ
および機体の側部３がそれに次ぎ、さらに翼の上面２ｃ
がそれに次ぐが、ここにおいてもかなりの局部加熱を受
ける。これらの部分の温度は、一般的に、１０００℃を
超え、ある部分では２０００℃に達することもあるの
で、機体および搭載機器の機能低下を防ぎ、機体の損傷
を防ぐために保護することが必要である。2. Description of the Related Art Spacecraft undergo extremely high aerodynamic heating when entering the atmosphere from space. This heating time varies depending on the reentry trajectory, but generally lasts about 15 to 25 minutes. As shown in FIG. 2, the aerodynamic heating rate at this time is highest at the nose 1 and the wing leading edge 2a of the spacecraft, and is at the lower surface 2b of the wing.
And the side 3 of the fuselage is next, and the upper surface 2c of the wing
Is second only to that, but is subject to considerable local heating. Since the temperature of these parts generally exceeds 1000 ° C and may reach 2000 ° C in some parts, it is necessary to protect the aircraft and the equipment onboard to prevent functional deterioration and to prevent damage to the aircraft. is there.
【０００３】従来の熱防護システムとしては、例えば、
図３に示すようなものがある。この熱防護システムは、
機体構造体４の外側に断熱材５ａ，５ｂを配し、さらに
その外側をリフレクタ６および耐熱遮蔽体７で覆い、耐
熱遮蔽体７をボルト８と機体構造体４に溶着されている
ナット９とを用いて、機体構造体４に固定するというも
のである。As a conventional thermal protection system, for example,
There is one as shown in FIG. This thermal protection system
The heat insulating materials 5a and 5b are arranged on the outer side of the body structure 4, and the outer sides of the heat insulating material 5a and 5b are covered with a reflector 6 and a heat-resistant shield 7. It is to be fixed to the body structure 4 using.
【０００４】[0004]
【発明が解決しようとする課題】しかしながら、このよ
うな従来技術では、断熱材５ａ，５ｂの厚さとほぼ同じ
長さのボルト８を用いているために、ボルト８の外側端
８ａの熱がボルト８を通して機体構造体４に伝わりやす
く、機体構造体４に、特に温度の高い部分、いわゆるホ
ットスポットが生じてしまう。このため、機体構造体４
の耐久性が低下してしまうという問題点がある。これを
解決するために、機体構造体４とボルト８との連結部８
ｂの温度が機体構造体８の許容温度以下になるよう、単
にボルト８の長さを長くすると、熱防護システムの厚さ
が厚くかつ重くなってしまう。However, in such a prior art, since the bolt 8 having a length substantially the same as the thickness of the heat insulating materials 5a and 5b is used, the heat of the outer end 8a of the bolt 8 is generated by the bolt. 8 is easily transmitted to the body structure 4 through 8, and a particularly high temperature portion, a so-called hot spot, is generated in the body structure 4. Therefore, the airframe structure 4
However, there is a problem in that the durability of the In order to solve this, a connecting portion 8 between the airframe structure 4 and the bolt 8
If the length of the bolt 8 is simply increased so that the temperature of b is equal to or lower than the allowable temperature of the airframe structure 8, the thickness of the thermal protection system becomes thick and heavy.
【０００５】本発明は、このような従来の問題点につい
て着目してなされたもので、厚さが薄く、かつホットス
ポットが発生し難い熱防護システムを提供することを目
的とする。The present invention has been made by paying attention to such conventional problems, and an object of the present invention is to provide a thermal protection system having a small thickness and in which hot spots hardly occur.
【０００６】[0006]
【課題を解決するための手段】前記目的を達成するため
の熱防護システムは、構造体の外側に断熱材が配され、
さらにその外側が耐熱遮蔽体で覆われ、該耐熱遮蔽体が
連結固定具で前記構造体に固定されている熱防護システ
ムにおいて、前記連結固定具は、少なくともこの一部
が、前記耐熱遮蔽体との連結部から前記構造体までの最
短経路を通らないよう形成されていることを特徴とする
ものである。A thermal protection system for achieving the above-mentioned object comprises a heat insulating material arranged outside a structure.
Furthermore, in the thermal protection system in which the outer side is covered with a heat-resistant shield, and the heat-resistant shield is fixed to the structure by a connecting fixture, at least a part of the connecting fixture is the heat-resistant shield. It is characterized in that it is formed so as not to pass through the shortest path from the connecting portion to the structure.
【０００７】また、前記目的を達成するための他の熱防
護システムは、前記連結固定具が、前記耐熱遮蔽体との
連結部の数量よりも、前記構造体との連結部の数量の方
が多くなるよう形成されていることを特徴とするもので
ある。Further, in another thermal protection system for achieving the above object, the number of connecting portions of the connecting fixture with the structure is larger than that of the connecting fixture with the heat-resistant shield. It is characterized in that it is formed so as to be many.
【０００８】また、前記目的を達成するためのさらに他
の熱防護システムは、前記連結固定具が、前記耐熱遮蔽
体と連結する耐熱遮蔽体側連結具と、前記構造体と連結
し、前記耐熱遮蔽体側連結具から前記耐熱遮蔽体の幅方
向に所定距離離れている複数の構造体側連結具と、前記
耐熱遮蔽体側連結具と前記複数の構造体側連結具とを連
結する中間連結具とを備えていることを特徴とするもの
である。Further, in still another heat protection system for achieving the above object, the heat-resistant shield is connected by the connecting fixture with the heat-resistant shield, and the heat-resistant shield is connected with the heat-resistant shield. A plurality of structure-side connectors that are separated from the body-side connector by a predetermined distance in the width direction of the heat-resistant shield, and an intermediate connector that connects the heat-resistant shield-side connector and the plurality of structure-side connectors. It is characterized by being present.
【０００９】[0009]
【作用】連結固定具が、耐熱遮蔽体との連結部から構造
体までの最短経路を通らないよう形成されているもので
は、連結固定具が耐熱遮蔽体と機体構造体との間の最短
経路を通るものと異なり、熱防護システム自身の厚さを
厚くすることなく、耐熱遮蔽体との連結部から機体構造
体との連結部までの距離を長くすることができるので、
連結固定具の熱伝達性が低下し、ホットスポットを防止
することができる。 また、連結固定具が、耐熱遮蔽体
との連結部の数量よりも、構造体との連結部の数量の方
が多いものでは、連結固定具の外側端の受けた熱を分散
させて構造体に伝えるので、ホットスポットを防止する
ことができる。When the connecting fixture is formed so as not to pass through the shortest path from the connecting portion with the heat-resistant shield to the structure, the connecting fixture has the shortest path between the heat-shielding body and the airframe structure. Unlike the one passing through, because the distance from the connection part with the heat-resistant shield to the connection part with the airframe structure can be lengthened without increasing the thickness of the thermal protection system itself,
The heat transfer property of the connecting fixture is reduced, and hot spots can be prevented. If the connecting fixture has more connecting parts with the structure than the connecting parts with the heat-resistant shield, the heat received by the outer end of the connecting fixture is dispersed to the structure. So you can prevent hot spots.
【００１０】また、連結固定具が、耐熱遮蔽体側連結具
と構造体側連結具と中間連結具とを備えているもので
は、複数の部材から構成されているため、各部材間の接
触抵抗により、連結固定具の熱伝達性を前述したものよ
りもさらに低下させることができ、ホットスポットの防
止効果をさらに高めることができる。Further, in the case where the connecting fixture includes the heat-resistant shield-side connecting device, the structure-side connecting device, and the intermediate connecting device, since the connecting fixing device is composed of a plurality of members, contact resistance between the members causes The heat transfer property of the connecting fixture can be further reduced than that described above, and the effect of preventing hot spots can be further enhanced.
【００１１】[0011]
【実施例】以下、本発明の一実施例を図１および図２を
用いて説明する。図２は、軌道上にて作業を実施し地上
へ帰還する宇宙機を示す。大気圏突入時に、宇宙機は、
前述したように、機首１と同時に翼の前縁２ａが極めて
高温になり、翼下面２ｂも高温になる。一方、胴体３お
よび翼上面２ｃは、上記部分ほど高温にならない。この
発明による熱防護システムは、特に、機体の胴体３、翼
上面２ｃおよび翼下面２ｂに対して使用する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to FIGS. FIG. 2 shows a spacecraft performing work in orbit and returning to the ground. When entering the atmosphere, the spacecraft
As described above, the front edge 2a of the wing becomes extremely hot at the same time as the nose 1, and the wing lower surface 2b also becomes hot. On the other hand, the body 3 and the wing upper surface 2c are not as hot as the above portion. The thermal protection system according to the invention is used especially for the fuselage 3, the upper surface 2c and the lower surface 2b of the fuselage.
【００１２】図１に、本発明に係る熱防護システムの一
例を示す。機体構造体３０の外側に高温用断熱材３２お
よび高性能断熱材３１が配され、このさらに外側が耐熱
遮蔽体３４で覆われている。高温用断熱材３２は、耐熱
温度が非常に高く、耐熱遮蔽体３４側に配されるもので
ある。また、高性能断熱材３１は、熱伝導率が非常に小
さく機体構造体３０側に配されるものである。断熱材３
１，３２および耐熱遮蔽体３４は、連結固定具により機
体構造体３０に固定されている。連結固定具は、耐熱遮
蔽体３４と連結する耐熱遮蔽体側連結具１０と、機体構
造体３０と連結する２個の構造体側連結具２０，２０
と、１個の耐熱遮蔽体側連結具１０と２個の構造体側連
結具２０，２０とを連結する中間連結具１５とで構成さ
れている。構造体側連結具２０，２０は、耐熱遮蔽体側
連結具１０から耐熱遮蔽体３４の幅方向に所定距離離れ
た位置に配されている。FIG. 1 shows an example of a thermal protection system according to the present invention. A high-temperature heat insulating material 32 and a high-performance heat insulating material 31 are arranged on the outer side of the machine body structure 30, and the outer side is covered with a heat-resistant shield 34. The high temperature heat insulating material 32 has a very high heat resistance temperature and is arranged on the heat resistant shield 34 side. Further, the high-performance heat insulating material 31 has a very small thermal conductivity and is arranged on the airframe structure 30 side. Insulation 3
1, 32 and the heat-resistant shield 34 are fixed to the body structure 30 by a connecting fixture. The connection fixing device includes the heat-resistant shield-side connector 10 that is connected to the heat-resistant shield 34 and the two structure-side connectors 20 and 20 that are connected to the airframe structure 30.
And one heat-resistant shield-side connecting tool 10 and two structure-side connecting tools 20, 20. The structure-side connectors 20, 20 are arranged at positions separated from the heat-resistant shield-side connector 10 by a predetermined distance in the width direction of the heat-resistant shield 34.
【００１３】以下に、熱防護システムの機体への取付手
順に従って、その構造について具体的に説明する。ま
ず、機体構造体３０と中間連結具１５の間に台座２２を
挾んでボルト２１とナット２３で固定する。機体構造体
３０と中間連結具１５との間には、空間を設けるか、断
熱材を設ける。中間連結具１５には、耐熱遮蔽体３４側
にポスト１２を立てるために、ナット１１をロ−付けし
ておき、このナット１１にポスト１２を立てる。中間連
結具１５は、自身の断熱性を高めると供に軽量化を図る
ために、複数の金属性薄板を用いて、ディンプル構造化
あるいはコルゲ−ト構造化したものである。また、ポス
ト１２は、同一形状の２個の部材を組み合わせたもの
で、内部が中空になっている。The structure of the thermal protection system will be described in detail below in accordance with the procedure for mounting it on the machine body. First, the pedestal 22 is sandwiched between the airframe structure 30 and the intermediate connector 15, and fixed by the bolts 21 and the nuts 23. A space or a heat insulating material is provided between the airframe structure 30 and the intermediate connector 15. The nut 11 is attached to the intermediate connector 15 in order to stand the post 12 on the heat-resistant shield 34 side, and the post 12 is set on the nut 11. The intermediate connector 15 has a dimple structure or a corrugated structure using a plurality of thin metal plates in order to improve the heat insulation property and to reduce the weight. The post 12 is a combination of two members having the same shape, and has a hollow inside.
【００１４】次に、断熱材３１，３２を機体構造体３０
上に配置する。この断熱材３１，３２は、パッケ−ジ化
されており、連結固定具部分は予め中空に形成されてい
る。高温用断熱材３２の上には熱遮蔽用のリフレクタ３
３を貼る。最後に、高温用断熱材３２の上を耐熱遮蔽体
３４で被い、この耐熱遮蔽体３４を、シム３５を介して
ボルト１３でポスト１４に固定する。耐熱遮蔽体３４
は、炭素繊維強化炭素複合材料で造られ、その表面は耐
酸化コ−ティングが施されている。Next, the heat insulating materials 31 and 32 are attached to the airframe structure 30.
Place it on top. The heat insulating materials 31 and 32 are packaged, and the connecting and fixing parts are preliminarily hollow. A heat shield reflector 3 is provided on the high temperature heat insulating material 32.
Paste 3. Finally, the high temperature heat insulating material 32 is covered with the heat resistant shield 34, and the heat resistant shield 34 is fixed to the post 14 with the bolt 13 via the shim 35. Heat-resistant shield 34
Is made of a carbon fiber reinforced carbon composite material, the surface of which is subjected to oxidation-resistant coating.
【００１５】なお、耐熱遮蔽体側連結具１０は、ナット
１１とポスト１２とボルト１３とで構成されている。ま
た、構造体側連結具２０は、ボルト２１と台座２２とナ
ット２３とで構成されている。The heat-resistant shield side connector 10 is composed of a nut 11, a post 12 and a bolt 13. The structure-side connector 20 includes a bolt 21, a pedestal 22, and a nut 23.
【００１６】本実施例によれば、例えば、耐熱遮蔽体３
４と機体構造体３０とを単にボルトとナットを用いて連
結するように、連結固定具がこれらの間の最短経路を通
るものと異なり、連結固定具の、耐熱遮蔽体３４との連
結部から機体構造体３０との連結部までの距離が長くな
るので、連結固定具の熱伝達性を低下させることができ
る。この他、連結固定具の熱伝達性を低下させている要
因としては、連結固定具が複数の部材１１，１２，…か
ら構成されているため、各部材間の接触抵抗が生じるこ
と、連結固定具を構成するポスト１２や中間連結具１５
が熱伝熱率の低い構造物であることが上げられる。ま
た、本実施例の連結固定具は、１個の耐熱遮蔽体側連結
具１０に対して２個の構造体側連結具２０が連結されて
いるので、耐熱遮蔽体側連結具１０のボルト１３が受け
た熱を分散させることができる。According to this embodiment, for example, the heat resistant shield 3
4 and the airframe structure 30 are simply connected by using bolts and nuts, unlike a connecting fixture that passes through the shortest path between them, from the connecting portion of the connecting fixture with the heat-resistant shield 34. Since the distance to the connecting portion with the machine body structure 30 becomes long, the heat transferability of the connecting fixture can be reduced. In addition to this, as a factor that lowers the heat transferability of the connecting fixture, since the connecting fixture is composed of a plurality of members 11, 12, ... Posts 12 and intermediate connectors 15 that make up the tool
Is a structure with a low heat transfer coefficient. Further, in the connecting fixture of the present embodiment, since two structure-side connecting tools 20 are connected to one heat-resistant shield-side connecting tool 10, the bolts 13 of the heat-resistant shield-side connecting tool 10 receive it. The heat can be dispersed.
【００１７】このように、本実施例の連結固定具では、
自身の熱伝達性が低く、かつ連結具の外側端が受けた熱
を分散させて機体構造体３０に伝えるため、耐熱遮蔽体
３４と機体構造体３０と距離を長くすることなく、機体
構造体３０にホットスポットが生じることを防ぐことが
できる。As described above, in the connecting fixture of this embodiment,
Since the heat transfer of itself is low and the heat received by the outer end of the connector is dispersed and transmitted to the airframe structure 30, the airframe structure does not need to be extended and the heatproof shield 34 and the airframe structure 30 need not be extended. It is possible to prevent hot spots from occurring in 30.
【００１８】なお、本実施例では、１個の耐熱遮蔽体側
連結具１０に対して２個の構造体側連結具２０，２０を
連結させたが、１個の耐熱遮蔽体側連結具１０に対して
さらに多数の構造体側連結具２０，２０，…を連結させ
ても良い。In this embodiment, the two heat-resistant shield-side couplers 20 and 20 are connected to one heat-resistant shield-side coupler 10, but one heat-resistant shield-side coupler 10 is used. Further, a large number of structure-side connecting tools 20, 20, ... May be connected.
【００１９】[0019]
【発明の効果】本発明によれば、厚さを厚くすることな
く、ホットスポットの発生を防ぐことができる。According to the present invention, it is possible to prevent the generation of hot spots without increasing the thickness.
【図１】本発明に係る熱防護システムの断面図である。1 is a cross-sectional view of a thermal protection system according to the present invention.
【図２】本発明を適用する宇宙機の全体側面図である。FIG. 2 is an overall side view of a spacecraft to which the present invention is applied.
【図３】従来の熱防護システムの断面図である。FIG. 3 is a cross-sectional view of a conventional thermal protection system.
１０…耐熱遮蔽体側連結具、１５…中間連結具、２０…
構造体側連結具、３０…機体構造体、３１，３２…断熱
材、３４…耐熱遮蔽体。10 ... Heat-resistant shield side connector, 15 ... Intermediate connector, 20 ...
Structure-side connector, 30 ... Airframe structure, 31, 32 ... Insulation material, 34 ... Heat-resistant shield.
───────────────────────────────────────────────────── フロントページの続き (72)発明者 和田 靱彦 茨城県日立市幸町三丁目１番１号 株式会 社日立製作所日立工場内 (72)発明者 児島 慶享 茨城県日立市久慈町4026番地 株式会社日 立製作所日立研究所内 (72)発明者 山口 静 茨城県日立市久慈町4026番地 株式会社日 立製作所日立研究所内 (72)発明者 吉岡 孝利 茨城県日立市久慈町4026番地 株式会社日 立製作所日立研究所内 (72)発明者 三津間 秀彦 茨城県つくば市千現２丁目１番地の１ 宇 宙開発事業団筑波宇宙センター内 (72)発明者 小林 智之 茨城県つくば市千現２丁目１番地の１ 宇 宙開発事業団筑波宇宙センター内 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Takehiko Wada 3-1-1, Saiwaicho, Hitachi-shi, Ibaraki Hitachi Ltd. Hitachi factory (72) Inventor Keiho Kojima 4026 Kuji-cho, Hitachi-shi, Ibaraki Address: Hitachi Research Laboratory, Hitachi, Ltd. (72) Shizuka Yamaguchi 4026, Kuji Town, Hitachi City, Hitachi, Ibaraki Prefecture Hitachi Research Laboratory, Hitachi, Ltd. (72) Takatoshi Yoshioka 4026, Kuji Town, Hitachi City, Ibaraki Prefecture Hitachi, Ltd. (72) Hidehiko Mitsuma, Inventor Hidehiko Mitsuma 2-1-1 Sengen, Tsukuba-shi, Ibaraki Uchu Space Development Center Tsukuba Space Center (72) Inventor Tomoyuki Kobayashi 2-1-1, Sengen, Tsukuba-shi, Ibaraki No. 1 Uchu Development Center Tsukuba Space Center
Claims (3)
の外側が耐熱遮蔽体で覆われ、該耐熱遮蔽体が連結固定
具で前記構造体に固定されている熱防護システムにおい
て、 前記連結固定具は、少なくともこの一部が、前記耐熱遮
蔽体との連結部から前記構造体までの最短経路を通らな
いよう形成されていることを特徴とする熱防護システ
ム。1. A thermal protection system in which a heat insulating material is disposed on the outside of a structure, the outside is further covered with a heat-resistant shield, and the heat-resistant shield is fixed to the structure with a connecting fixture. The thermal protection system, wherein at least a part of the connecting fixture is formed so as not to pass through the shortest path from the connecting portion with the heat-resistant shield to the structure.
の外側が耐熱遮蔽体で覆われ、該耐熱遮蔽体が連結固定
具で前記構造体に固定されている熱防護システムにおい
て、 前記連結固定具は、前記耐熱遮蔽体との連結部の数量よ
りも、前記構造体との連結部の数量の方が多くなるよう
形成されていることを特徴とする熱防護システム。2. A thermal protection system in which a heat insulating material is arranged on the outside of a structure, and the outside is covered with a heat-resistant shield, and the heat-resistant shield is fixed to the structure with a connecting fixture. The thermal protection system, wherein the connecting fixture is formed such that the number of connecting portions with the heat-resistant shield is larger than the number of connecting portions with the heat-resistant shield.
の外側が耐熱遮蔽体で覆われ、該耐熱遮蔽体が連結固定
具で前記構造体に固定されている熱防護システムにおい
て、 前記連結固定具は、 前記耐熱遮蔽体と連結する耐熱遮蔽体側連結具と、 前記構造体と連結し、前記耐熱遮蔽体側連結具から前記
耐熱遮蔽体の幅方向に所定距離離れている複数の構造体
側連結具と、 前記耐熱遮蔽体側連結具と前記複数の構造体側連結具と
を連結する中間連結具とを備えていることを特徴とする
熱防護システム。3. A thermal protection system in which a heat insulating material is arranged on the outside of a structure, the outside of which is covered with a heat-resistant shield, and the heat-resistant shield is fixed to the structure with a connecting fixture. The connecting fixture is a heat-resistant shield side connector that is connected to the heat-resistant shield, and a plurality of structure sides that are connected to the structure and are apart from the heat-resistant shield-side connector by a predetermined distance in the width direction of the heat-resistant shield. A thermal protection system comprising: a connector, and an intermediate connector that connects the heat-resistant shield-side connector and the plurality of structure-side connectors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1077692A JPH05203095A (en) | 1992-01-24 | 1992-01-24 | Heat protecting system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1077692A JPH05203095A (en) | 1992-01-24 | 1992-01-24 | Heat protecting system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH05203095A true JPH05203095A (en) | 1993-08-10 |
Family
ID=11759737
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1077692A Pending JPH05203095A (en) | 1992-01-24 | 1992-01-24 | Heat protecting system |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH05203095A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06321199A (en) * | 1993-04-01 | 1994-11-22 | Soc Europ Propulsion <Sep> | Heat insulating protector for aircraft |
| CN101909990A (en) * | 2008-08-08 | 2010-12-08 | 空中客车营运有限公司 | The thermal insulation harmony non-conductive insulation system that is used for aircraft |
| JP2019120442A (en) * | 2017-12-28 | 2019-07-22 | 三菱電機株式会社 | Flying object |
| CN110723275A (en) * | 2019-10-24 | 2020-01-24 | 湖北航天技术研究院总体设计所 | High-temperature heat-proof opening cover structure |
| CN113978696A (en) * | 2021-11-08 | 2022-01-28 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
-
1992
- 1992-01-24 JP JP1077692A patent/JPH05203095A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06321199A (en) * | 1993-04-01 | 1994-11-22 | Soc Europ Propulsion <Sep> | Heat insulating protector for aircraft |
| CN101909990A (en) * | 2008-08-08 | 2010-12-08 | 空中客车营运有限公司 | The thermal insulation harmony non-conductive insulation system that is used for aircraft |
| JP2010538898A (en) * | 2008-08-08 | 2010-12-16 | エアバス・オペレーションズ・ゲーエムベーハー | Shielding structure for insulating and soundproofing aircraft |
| US8327976B2 (en) | 2008-08-08 | 2012-12-11 | Airbus Operations Gmbh | Insulation design for thermal and acoustic insulation of an aircraft |
| JP2019120442A (en) * | 2017-12-28 | 2019-07-22 | 三菱電機株式会社 | Flying object |
| CN110723275A (en) * | 2019-10-24 | 2020-01-24 | 湖北航天技术研究院总体设计所 | High-temperature heat-proof opening cover structure |
| CN113978696A (en) * | 2021-11-08 | 2022-01-28 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
| CN113978696B (en) * | 2021-11-08 | 2024-04-09 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
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