JP3462595B2 - Fuel piping for space equipment - Google Patents
Fuel piping for space equipmentInfo
- Publication number
- JP3462595B2 JP3462595B2 JP25186294A JP25186294A JP3462595B2 JP 3462595 B2 JP3462595 B2 JP 3462595B2 JP 25186294 A JP25186294 A JP 25186294A JP 25186294 A JP25186294 A JP 25186294A JP 3462595 B2 JP3462595 B2 JP 3462595B2
- Authority
- JP
- Japan
- Prior art keywords
- main body
- pipe
- adhesive
- fuel
- main structure
- 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.)
- Expired - Fee Related
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
- F16L3/00—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Supports For Pipes And Cables (AREA)
Description
【発明の詳細な説明】
【０００１】
【産業上の利用分野】本発明は、充分な保温効果もつ宇
宙機器の姿勢制御装置の燃料配管に関する。
【０００２】
【従来の技術】人工衛星やロケットの姿勢制御装置は、
スラスタおよび燃料供給系から構成される。スラスタや
燃料タンクは主構体上に取り付けられ、スラスタと燃料
タンクは燃料配管によって接続される。したがって、燃
料配管は主構体に沿って配置される。姿勢制御装置の燃
料は通常ヒドラジンであり、下限温度は燃料の凝固点：
−２℃であり、また燃料の反応性から配管温度の上限は
７１℃に規定されている。このため宇宙機器用の燃料配
管は−２〜７１℃の範囲に温度を制御する必要がある。
【０００３】宇宙機器の姿勢制御装置の主構体に取り付
けられた従来の一般的な燃料配管を図４および図５に示
す。図４に示すものでは、太陽光の輻射熱による温度上
昇の低減のため多層断熱材４２で輻射断熱を行った配管
本体４１を取付バンド４４を用いて主構体４５に取り付
けている。取付バンド４４は、図２（ｂ）に示すよう
に、互いに適当な間隔をおいて取り付けられる。
【０００４】図５に示すものは深宇宙への放熱が大きい
場合に用いられ、保温用ヒータ５６で配管本体５１の温
度保持を行った上、多層断熱材５２で輻射断熱を行って
いる。配管本体５１は、主構体５５上の支柱５３に取付
バンド５４を用いて取り付けられている。
【０００５】
【発明が解決しようとする課題】前記の従来の宇宙機器
の姿勢制御装置の燃料配管では、配管本体４１，５１の
熱容量は小さく放射冷却による温度低下が速い。また、
図５に示すように、ヒータ５６による保温を行うために
は電源の確保が必要で姿勢制御装置の重量が増加する。
さらに、取付バンド４４，５４や支柱５３を介した配管
本体４１，５１と主構体４５，５５との熱的な結合係数
の算出は困難で、熱設計時の解析誤差が大きい。またさ
らに、打ち上げ時の振動に耐える必要から配管本体４
５，５５の取付部（支柱５３・取付バンド４４，５４）
の強度確保が必要である。
【０００６】本発明は、以上の問題点を解決することが
できる宇宙機器用燃料配管を提供しようとするものであ
る。
【０００７】
【課題を解決するための手段】本発明の宇宙機器用燃料
配管は、燃料が流れる配管本体と姿勢制御装置の主構体
を、同配管本体と同主構体の接合面全体に同配管本体の
全長にわたって施工された接着剤によって一体化し、同
接着剤内の熱伝導により前記配管本体と前記主構体とを
熱的に結合した。
【０００８】
【作用】本発明では、燃料が流れる配管本体と姿勢制御
装置の主構体は、配管本体と主構体の接合面全体に配管
本体の全長にわたって施工された接着剤によって一体化
され、接着剤内の熱伝導により配管本体と主構体とを熱
的に結合されているので、接着剤内の熱伝導によって主
構体と配管本体との間の熱伝達が行われる。主構体は配
管本体に比べて熱容量が大きいために宇宙環境下での温
度変化が小さいが、主構体と配管本体との間の熱伝達
を、配管本体と主構体の接合面全体に配管本体の全長に
わたって施工された接着剤内の熱伝導によって行うよう
にしたために、配管本体の温度を主構体の温度に近づけ
温度変化を低下させることができる。また、接着剤によ
って配管本体と宇宙環境との輻射断熱が行われる。
【０００９】さらに、配管本体は接着剤によって主構体
と一体化され、取付強度が増加し、打ち上げ時等の振動
による破損が防止される。
【００１０】
【実施例】本発明の第１の実施例を、図１によって説明
する。１１はヒドラジン等の燃料が内部を流れる円管状
の配管本体であり、同配管本体１１と宇宙機器の姿勢制
御装置との接触面には接着剤１６が充填され、配管本体
１１は主構体１５上に接着剤１６によって接合されてい
て、配管本体１１と主構体１５は一体化されている。接
着剤１６は配管本体１１と主構体１５の接合面全体に配
管本体１１の全長にわたって施工されている。また、配
管本体１１と主構体１５との間には間隔をおいて複数の
取付バンド１４が配置されている。
【００１１】宇宙環境における真空中においては、微小
隙間内の気体の対流伝熱が得られず、接触面の熱抵抗は
大きいが、本実施例では配管本体１１と主構体１５の接
触部に接着剤１６を充填して両者を接合していることに
より、接着剤１６内の熱伝導により熱伝達を行うことが
できる。また、施工面積が配管本体１１の全長にわたる
ために接合面積が広いことから、配管本体１１と主構体
１５の熱的な結合が強くなる。一般に主構体１５は配管
本体１１に比べて熱容量が大きく宇宙環境下での温度変
化が小さい。配管本体１１と主構体１５の熱的な結合を
前記のように強化することにより、配管本体１１の温度
を主構体１５に近づけ温度変化を低下させることができ
る。
【００１２】さらに接着剤１６に加えて取付バンド１４
で配管本体１１を固定するため、取付強度が増加し打ち
上げ時の振動による破損を防止することができる。ま
た、図１（ａ）に示すように、配管本体１１は接着剤１
６によって部分的に覆われているために、配管本体１１
と宇宙環境との輻射断熱を行うことができ、配管本体１
１からの放熱を防ぐことができる。
【００１３】本発明の第２の実施例で、図２によって説
明する。本実施例は、前記第１の実施例において、配管
本体１１と接着剤１６を覆うように多層断熱材２２を被
覆したものである。
【００１４】本実施例では、前記第１の実施例の作用及
び効果に加えて、多層断熱材２２によって配管本体１１
から宇宙環境への放熱を更に効果的に防止することがで
きる。
【００１５】本発明の第３の実施例を、図３によって説
明する。本実施例は、前記第１の実施例の円管状の配管
本体１１を扁平な形状にしたものである。
【００１６】本実施例では、前記第１の実施例の作用及
び効果に加えて、配管本体１１と主構体１５との間の接
合面積が更に増加し、接着剤１６による結合を更に強化
することができる。
【００１７】なお、前記第１ないし第３の実施例におい
ては、配管本体１１の上部には接着剤１６が施工されて
いないが、配管本体１１の上部にも接着剤１６を施工す
れば、更に配管本体１１の放熱が減少し保温効果を高め
ることができる。
【００１８】
【発明の効果】本発明は、燃料が流れる宇宙機器の配管
本体を、同配管本体と同主構体の接合面全体に同配管本
体の全長にわたって施工された接着剤によって姿勢制御
装置の主構体と一体化し、同接着剤内の熱伝導により配
管本体と主構体とを熱的に結合しているので、接着剤に
よって配管本体と宇宙環境との輻射断熱が行われ、配管
本体から宇宙空間への放熱が減ると共に、主構体から、
配管本体と主構体の接合面全体に配管本体の全長にわた
って施工された接着剤を伝って配管本体へ熱が伝えられ
て、配管本体の保温効果が得られ、配管本体を所定温度
に保持することができる。これにより、配管本体を断熱
材で巻く必要がなくなるとともに主構体への取付工事が
容易となりコストダウンが可能になる。Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a fuel pipe of an attitude control device for space equipment having a sufficient heat retaining effect. [0002] Attitude control devices for satellites and rockets are:
It consists of a thruster and a fuel supply system. The thruster and the fuel tank are mounted on the main structure, and the thruster and the fuel tank are connected by a fuel pipe. Therefore, the fuel pipe is arranged along the main structure. The fuel in the attitude control device is usually hydrazine, and the minimum temperature is the freezing point of the fuel:
−2 ° C., and the upper limit of the pipe temperature is defined as 71 ° C. due to the reactivity of the fuel. For this reason, it is necessary to control the temperature of the fuel pipe for space equipment within the range of -2 to 71 ° C. FIGS. 4 and 5 show a conventional general fuel pipe attached to a main structure of an attitude control device for space equipment. In FIG. 4, a piping main body 41 radiated and insulated by a multilayer heat insulating material 42 to reduce a rise in temperature due to radiant heat of sunlight is attached to a main structure 45 using an attachment band 44. As shown in FIG. 2B, the attachment bands 44 are attached at appropriate intervals. FIG. 5 shows a case where the heat radiation to the deep space is large. The heat insulation heater 56 keeps the temperature of the pipe body 51, and the multilayer insulation 52 performs radiation insulation. The piping main body 51 is attached to a support column 53 on a main structure 55 using an attachment band 54. [0005] In the fuel pipe of the conventional attitude control device for space equipment, the heat capacity of the pipe bodies 41 and 51 is small, and the temperature drop due to radiant cooling is fast. Also,
As shown in FIG. 5, in order to maintain the temperature by the heater 56, it is necessary to secure a power source, and the weight of the attitude control device increases.
Furthermore, it is difficult to calculate the thermal coupling coefficient between the pipe main bodies 41, 51 and the main structures 45, 55 via the mounting bands 44, 54 and the struts 53, and an analysis error at the time of thermal design is large. Furthermore, since it is necessary to withstand vibration during launch,
5, 55 mounting parts (post 53, mounting bands 44, 54)
It is necessary to secure the strength. An object of the present invention is to provide a fuel pipe for space equipment which can solve the above problems. A fuel pipe for space equipment according to the present invention has a pipe main body through which fuel flows and a main structure of an attitude control device , and the pipe main body and an entire joint surface between the main body and the pipe main body. Body
The pipe body and the main structure were thermally coupled by an adhesive applied over the entire length and by heat conduction in the adhesive. According to the present invention, the main body of the piping main body and the attitude control device through which the fuel flows is connected to the entire joint surface between the main body and the main body.
Since the pipe body and the main structure are thermally connected by the heat conduction in the adhesive, the main structure and the pipe body are integrated by the heat conduction in the adhesive. Heat transfer takes place between the two. Although the main structure has a large heat capacity compared to the pipe body, the temperature change in the space environment is small.However, heat transfer between the main body and the pipe body is distributed over the entire joint surface between the pipe body and the main body. Over the entire length
Since the heat treatment is performed by the heat conduction in the adhesive applied over the entire area, the temperature of the pipe main body can be made close to the temperature of the main structure to reduce the temperature change. Further, radiation insulation between the pipe body and the space environment is performed by the adhesive. Further, the pipe main body is integrated with the main structure by an adhesive, so that the mounting strength is increased and breakage due to vibration at the time of launching or the like is prevented. FIG. 1 shows a first embodiment of the present invention. Reference numeral 11 denotes a tubular pipe main body through which a fuel such as hydrazine flows. The contact surface between the pipe main body 11 and the attitude control device of the space device is filled with an adhesive 16. And the main body 15 is integrated with the main body 15. The adhesive 16 is applied to the entire joint surface between the pipe main body 11 and the main structure 15 over the entire length of the pipe main body 11. In addition, a plurality of mounting bands 14 are arranged between the piping main body 11 and the main structure 15 at intervals. In a vacuum in a space environment, convective heat transfer of the gas in the minute gap is not obtained, and the thermal resistance of the contact surface is large. However, in the present embodiment, the gas is adhered to the contact portion between the pipe body 11 and the main structure 15. By filling the agent 16 and joining the two, heat can be transferred by heat conduction in the adhesive 16. In addition, since the construction area extends over the entire length of the pipe main body 11, the joint area is large, so that the thermal connection between the pipe main body 11 and the main structure 15 is enhanced. In general, the main structure 15 has a larger heat capacity than the pipe main body 11 and a small temperature change in a space environment. By strengthening the thermal coupling between the pipe main body 11 and the main structure 15 as described above, the temperature of the pipe main body 11 can be made closer to the main structure 15 and the temperature change can be reduced. [0012] In addition to the adhesive 16, the mounting band 14
Since the pipe main body 11 is fixed by the above, the mounting strength is increased, and damage due to vibration at the time of launch can be prevented. Further, as shown in FIG.
6 is partially covered by the pipe body 11
Radiation insulation between the space and the space environment.
The heat radiation from 1 can be prevented. A second embodiment of the present invention will be described with reference to FIG. This embodiment is different from the first embodiment in that the multilayer heat insulating material 22 is covered so as to cover the pipe body 11 and the adhesive 16. In the present embodiment, in addition to the functions and effects of the first embodiment, the pipe body 11
Radiation from the space environment can be more effectively prevented. A third embodiment of the present invention will be described with reference to FIG. In this embodiment, the tubular pipe main body 11 of the first embodiment is formed into a flat shape. In this embodiment, in addition to the functions and effects of the first embodiment, the joint area between the pipe main body 11 and the main structure 15 is further increased, and the connection by the adhesive 16 is further strengthened. Can be. In the first to third embodiments, the adhesive 16 is not applied to the upper part of the pipe main body 11, but if the adhesive 16 is applied to the upper part of the pipe main body 11 as well, The heat radiation of the pipe body 11 is reduced, and the heat retaining effect can be enhanced. According to the present invention , the piping main body of a space appliance through which fuel flows is provided on the entire joint surface between the main body and the piping main body.
It is integrated with the main structure of the posture control device by the adhesive applied over the entire length of the body, and the pipe main body and the main structure are thermally connected by heat conduction in the adhesive, so the adhesive and the pipe main body Radiation insulation with the space environment is performed, heat dissipation from the pipe body to outer space is reduced, and from the main structure ,
The entire joint surface between the pipe body and the main structure extends over the entire length of the pipe body.
Then , heat is transmitted to the pipe main body through the applied adhesive, thereby obtaining a heat retaining effect of the pipe main body, and the pipe main body can be maintained at a predetermined temperature. This eliminates the need to wind the pipe main body with a heat insulating material, facilitates installation work on the main structure, and enables cost reduction.
【図面の簡単な説明】
【図１】本発明の第１の実施例を示し、図１（ａ）はそ
の断面図、図１（ｂ）はその斜視図である。
【図２】本発明の第２の実施例の断面図である。
【図３】本発明の第３の実施例の断面図である。
【図４】従来の宇宙機器用配管の１例を示し、図４
（ａ）はその断面図、図４（ｂ）はその斜視図である。
【図５】従来の宇宙機器用配管の他の例の断面図であ
る。
【符号の説明】
１１ 配管本体
１４ 取付バンド
１５ 主構体
１６ 接着剤
２２ 多層断熱材BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 shows a first embodiment of the present invention. FIG. 1 (a) is a cross-sectional view, and FIG. 1 (b) is a perspective view. FIG. 2 is a sectional view of a second embodiment of the present invention. FIG. 3 is a sectional view of a third embodiment of the present invention. FIG. 4 shows an example of a conventional space equipment pipe, and FIG.
(A) is a cross-sectional view thereof, and FIG. 4 (b) is a perspective view thereof. FIG. 5 is a cross-sectional view of another example of the conventional piping for space equipment. [Description of Signs] 11 Piping main body 14 Mounting band 15 Main structure 16 Adhesive 22 Multilayer heat insulating material
───────────────────────────────────────────────────── フロントページの続き (72)発明者 唐津 信弘 長崎市飽の浦町１番１号 三菱重工業株 式会社長崎造船所内 (56)参考文献 特開 平３−114998（ＪＰ，Ａ) 実開 昭53−1747（ＪＰ，Ｕ) (58)調査した分野(Int.Cl.7，ＤＢ名) F16L 3/00 B64G 1/22 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Nobuhiro Karatsu 1-1, Akunouramachi, Nagasaki City Inside Nagasaki Shipyard, Mitsubishi Heavy Industries, Ltd. -1747 (JP, U) (58) Field surveyed (Int. Cl. 7 , DB name) F16L 3/00 B64G 1/22
Claims (1)
主構体を、同配管本体と同主構体の接合面全体に同配管
本体の全長にわたって施工された接着剤によって一体化
し、同接着剤内の熱伝導により前記配管本体と前記主構
体とを熱的に結合してなることを特徴とする宇宙機器用
燃料配管。(57) [Claims] [Claim 1] The main body of the piping main body and the attitude control device through which the fuel flows, and the entire main surface of the main body and the same main body are connected by the same piping.
A fuel pipe for space equipment, wherein the fuel pipe is integrated by an adhesive applied over the entire length of the main body, and the pipe main body and the main structure are thermally connected by heat conduction in the adhesive.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP25186294A JP3462595B2 (en) | 1994-10-18 | 1994-10-18 | Fuel piping for space equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP25186294A JP3462595B2 (en) | 1994-10-18 | 1994-10-18 | Fuel piping for space equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH08114283A JPH08114283A (en) | 1996-05-07 |
| JP3462595B2 true JP3462595B2 (en) | 2003-11-05 |
Family
ID=17229034
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP25186294A Expired - Fee Related JP3462595B2 (en) | 1994-10-18 | 1994-10-18 | Fuel piping for space equipment |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3462595B2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10584927B2 (en) | 2015-12-30 | 2020-03-10 | General Electric Company | Tube thermal coupling assembly |
-
1994
- 1994-10-18 JP JP25186294A patent/JP3462595B2/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10584927B2 (en) | 2015-12-30 | 2020-03-10 | General Electric Company | Tube thermal coupling assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH08114283A (en) | 1996-05-07 |
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