JPH0544678Y2 - - Google Patents
Info
- Publication number
- JPH0544678Y2 JPH0544678Y2 JP9297487U JP9297487U JPH0544678Y2 JP H0544678 Y2 JPH0544678 Y2 JP H0544678Y2 JP 9297487 U JP9297487 U JP 9297487U JP 9297487 U JP9297487 U JP 9297487U JP H0544678 Y2 JPH0544678 Y2 JP H0544678Y2
- Authority
- JP
- Japan
- Prior art keywords
- heat
- pump
- branch point
- pipe line
- valve
- 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 - Lifetime
Links
- 239000007788 liquid Substances 0.000 claims description 28
- 239000012071 phase Substances 0.000 claims description 25
- 239000012530 fluid Substances 0.000 claims description 18
- 239000006096 absorbing agent Substances 0.000 claims description 9
- 230000005514 two-phase flow Effects 0.000 claims description 9
- 239000007791 liquid phase Substances 0.000 claims description 6
- 239000003507 refrigerant Substances 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 13
- 238000010586 diagram Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 230000017525 heat dissipation Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000002918 waste heat Substances 0.000 description 1
Landscapes
- Electromagnetic Pumps, Or The Like (AREA)
- Devices That Are Associated With Refrigeration Equipment (AREA)
Description
【考案の詳細な説明】
〔産業上の利用分野〕
本考案はスペースステーシヨン用放熱器等に適
用される宇宙用熱制御装置に関する。[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a space heat control device applied to a space station radiator, etc.
例えば人工衛星においては、機械式ポンプを使
わないヒートパイプ式熱制御装置等が使われてい
るが、例えば、スペースシヤトルにおいては、排
熱量が人工衛星より大きいので、流体ループを利
用した熱制御が行なわれており、例えば、放熱器
の熱輸送装置としては液単相流専用ポンプが用い
られている。
For example, in artificial satellites, heat pipe type thermal control devices that do not use mechanical pumps are used, but in space shuttles, for example, the amount of waste heat is larger than that of artificial satellites, so thermal control using fluid loops is used. For example, a pump dedicated to liquid single-phase flow is used as a heat transport device for a radiator.
宇宙における放熱器の熱輸送装置としては、前
記の如く、人工衛星の如く排熱量の小さいものに
対しては、ヒートパイプを介してラジエータに熱
を輸送したり、スペースシヤトルでは液単相流体
ループをポンプで駆動してラジエータに放熱して
いた。しかしながら、例えば、スペースステーシ
ヨンの如く、排熱量が特に大きくなると、気液二
相によるラジエータ部の排熱が必至となる。とこ
ろが、従来の機械式ポンプを使用した熱輸送装置
は、液単相流駆動に限られているので、ポンプ内
にガスが混人すると故障等の原因となる。従つ
て、特に二相流体ループに対するポンプ駆動の場
合には、気液分離器等の如く、ポンプ内へのガス
侵入を防ぐ装置を設置する必要があつた。しかし
ながら、宇宙では無重力であるので気液分離が困
難である。
As mentioned above, heat transport devices for radiators in space include transporting heat to radiators via heat pipes for objects with a small amount of exhaust heat such as artificial satellites, and liquid single-phase fluid loops for space shuttles. was driven by a pump and the heat was radiated to a radiator. However, when the amount of exhaust heat is particularly large, as in the case of a space station, for example, it is inevitable that the radiator section exhausts heat in a gas-liquid two-phase manner. However, since conventional heat transport devices using mechanical pumps are limited to liquid single-phase flow drive, if gas is mixed in the pump, it may cause malfunctions. Therefore, especially when driving a pump for a two-phase fluid loop, it is necessary to install a device such as a gas-liquid separator to prevent gas from entering the pump. However, since there is no gravity in space, gas-liquid separation is difficult.
またポンプを使つたループでは、放熱部温度は
熱源側の温度より必ず低くなり、コンプレツサを
使用した場合に比べ宇宙空間にふく射伝熱にて放
熱する場合の放熱パネル面積が大きくなる欠点が
あつた。 In addition, in a loop using a pump, the temperature of the heat dissipation part is always lower than the temperature on the heat source side, and the disadvantage is that the area of the heat dissipation panel is larger when heat is radiated into space by radiation heat transfer compared to when using a compressor. .
本考案は、上記の問題点を解決するため、一つ
のポンプによつて、液単相、ガス単相および気液
両相の何れでも駆動でき、排熱量を増大させるこ
とができる宇宙用熱制御装置を提供することを目
的とする。 In order to solve the above-mentioned problems, the present invention is a space thermal control system that can drive single-phase liquid, single-phase gas, and both gas-liquid phases with a single pump, and can increase the amount of exhaust heat. The purpose is to provide equipment.
本考案による宇宙用熱制御装置は、
熱負荷から吸熱した熱を流体冷媒を介して放熱
器により宇宙空間に排熱する宇宙用熱制御装置に
おいて、流体冷媒の輸送手段として気相、液相お
よび気液二相の何れでも作動できるポンプ１を具
備するとともに、
液単相流のループの管路Ｓ１と、二相流ループ
の管路Ｓ２を有し、前記流単相流のループの管路
Ｓ１は、ポンプ１と、分岐点Ａと弁６と分岐点Ｂ
と吸熱器３と、弁４と、放熱器２と、分岐点Ｃ
と、分岐点Ｄとポンプ１を、前記順に配置した管
路から成り、前記二相流ループの管路Ｓ２は、ポ
ンプ１と、分岐点Ａと、弁５と、分岐点Ｃと、放
熱器２と、弁４と、吸熱器３と、分岐点Ｂと、弁
７と、分岐点Ｄと、ポンプ１を、前記順に配置し
た管路から成り、
前記管路Ｓ１と管路Ｓ２は、共通の管路とし
て、管路Ｂ−Ｃと管路Ｄ−Ａを有し、
前記管路Ｂ−Ｃは、分岐点Ｂと吸熱器３と弁４
と放熱器２と分岐点Ｃを、前記順々配置した管路
からなり、
前記管路Ｄ−Ａは、分岐点Ｄと、ポンプ１と、
分岐点Ａを、前記順に配置した管路からなり、液
単相流のループの場合は、弁５および７は閉、弁
４および６は開の状態にあり、二相流ループの場
合は、弁５，４，７は開，弁６は閉の状態となる
ことを特徴とする。
The space heat control device according to the present invention is a space heat control device that exhausts heat absorbed from a heat load into space by a radiator via a fluid refrigerant. It is equipped with a pump 1 that can operate in either gas or liquid two phases, and has a pipe line S1 for a liquid single-phase flow loop, and a pipe line S2 for a two-phase flow loop, and the pipe line for the single-phase flow loop. S1 is pump 1, branch point A, valve 6, and branch point B.
and heat absorber 3, valve 4, heat radiator 2, and branch point C
The pipe line S2 of the two-phase flow loop includes the pump 1, the branch point A, the valve 5, the branch point C, and the radiator. 2, a valve 4, a heat absorber 3, a branch point B, a valve 7, a branch point D, and a pump 1 are arranged in the above order, and the pipeline S1 and S2 are common. The pipes include a pipe B-C and a pipe D-A, and the pipe B-C has a branch point B, a heat absorber 3, and a valve 4.
, the radiator 2 and the branch point C are arranged in this order, and the pipeline D-A includes the branch point D, the pump 1,
It consists of a pipe line in which the branch points A are arranged in the above order, and in the case of a liquid single-phase flow loop, valves 5 and 7 are closed, and valves 4 and 6 are open, and in the case of a two-phase flow loop, It is characterized in that valves 5, 4, and 7 are open, and valve 6 is closed.
本考案によれば、気相、液相および気液二相の
何れでも駆動できるため、液単相駆動ポンプを使
用した二相流体ループに比べ、気液分離器を不用
とし、また、ガスの駆動も可能なため、コンプレ
ツサとしても使用でき、さらに、排熱温度を熱源
側より高くできるため、排熱量を大きくとること
ができる。
According to the present invention, since it can be driven in any of the gas phase, liquid phase, and gas-liquid two-phase, it eliminates the need for a gas-liquid separator compared to a two-phase fluid loop that uses a liquid single-phase drive pump. Since it can also be driven, it can also be used as a compressor, and since the exhaust heat temperature can be higher than that on the heat source side, a large amount of exhaust heat can be obtained.
第１図は本考案の一実施例の流体回路図であ
り、１は気液併用ポンプ、２は放熱器、３は吸熱
器、４は弁（二相流の場合は膨張弁）、５〜７は
弁、１０は熱源、１０１〜１０４は管路、１１
０，１１１は管路を示す。液単相流のループの場
合、弁５および７は閉、弁４および６は開の状態
にある。流体は気液併用ポンプ１を出た後管路１
０１を通り吸熱器３に入る。ここで、熱源１０か
ら管路１１０および管路１１１を流れる流体と熱
交換し、弁４を通り放熱器２に入る。ここで宇宙
空間へ放熱するための機器（たとえばヒートパイ
プを介した放熱パネルまたは放熱パネルのみ）へ
放熱し、ポンプへ戻る。二相流ループで液を気液
併用ポンプ１で駆動する場合は、流体の流れは液
単相流ループと全く同じである。この場合３は蒸
発器、４は膨張弁、５は凝縮器として働く。二相
流ループでガスを気液併用ポンプ１（この場合は
コンプレツサとして作動する）で駆動する場合、
弁４，５および７は開、弁６は閉の状態となる。
コンプレツサを出た流体ガスは管路１０４を通
り、放熱器２（凝縮器）に入り、ここで宇宙空間
へ放熱するための機器に熱を与え、流体ガスは液
化し弁４（この場合は膨張弁）へ行き、ここで断
熱膨張し吸熱器３（蒸発器）へ入る。ここで熱源
１０から管路１１０，１１１を通つてきた流体と
熱交換し、再びガスとなつて出て行く。そしてこ
の流体は管路１０２を通つて気液併用ポンプ（コ
ンプレツサ）１に戻る。
FIG. 1 is a fluid circuit diagram of an embodiment of the present invention, in which 1 is a gas-liquid combined pump, 2 is a radiator, 3 is a heat absorber, 4 is a valve (in the case of two-phase flow, an expansion valve), 5- 7 is a valve, 10 is a heat source, 101 to 104 are pipes, 11
0,111 indicates a conduit. In the case of a liquid single-phase flow loop, valves 5 and 7 are closed and valves 4 and 6 are open. After the fluid exits the gas-liquid pump 1, it flows through the pipe line 1.
01 and enters the heat absorber 3. Here, it exchanges heat with the fluid flowing from the heat source 10 through the pipes 110 and 111, passes through the valve 4, and enters the radiator 2. Here, the heat is radiated to a device for radiating heat into space (for example, a heat radiating panel via a heat pipe or only a heat radiating panel), and then returned to the pump. When the liquid is driven by the gas-liquid pump 1 in a two-phase flow loop, the flow of the fluid is exactly the same as in the liquid single-phase flow loop. In this case, 3 works as an evaporator, 4 works as an expansion valve, and 5 works as a condenser. When gas is driven by a gas-liquid pump 1 (acting as a compressor in this case) in a two-phase flow loop,
Valves 4, 5 and 7 are open, and valve 6 is closed.
The fluid gas that exits the compressor passes through the pipe 104 and enters the radiator 2 (condenser), where it gives heat to equipment for radiating heat to outer space. valve), where it undergoes adiabatic expansion and enters heat absorber 3 (evaporator). Here, it exchanges heat with the fluid that has passed through the pipes 110 and 111 from the heat source 10, and exits again as a gas. This fluid then returns to the gas-liquid pump (compressor) 1 through the pipe line 102.
従来の二相流体ループにおけるポンプまたはコ
ンプレツサでは、蒸発器を出た後の流体はそれぞ
れ液単相、ガス単相状態である必要があり、その
ための気液分離器を設ける必要があつたが、本考
案によれば、それが不要となる。 In conventional pumps or compressors in two-phase fluid loops, the fluids after exiting the evaporator must be in a single liquid phase and a single gas phase, respectively, and it was necessary to provide a gas-liquid separator for this purpose. According to the present invention, this becomes unnecessary.
また上記本考案の一実施例では、ガスを断熱圧
縮することになるため、その出口は高温高圧とな
り、熱源１０の温度より高くすることができる。
従つて放熱器と連結した放熱パネルの温度を高く
でき、排熱能力を高めることができる。 Furthermore, in the embodiment of the present invention described above, since the gas is adiabatically compressed, the outlet becomes high temperature and high pressure, and can be made higher than the temperature of the heat source 10.
Therefore, the temperature of the heat radiating panel connected to the radiator can be increased, and the heat dissipation capacity can be increased.
第２図および第３図はそれぞれ本考案の一実施
例におけるポンプの模式図、第４図はそのポンプ
の羽根車の形状を示す図であり、２０１はポンプ
羽根車、２０２はマグネツトロータ、２０３はス
テータコイル、２０４はポジシヨンセンサを示
す。 2 and 3 are schematic diagrams of a pump according to an embodiment of the present invention, respectively, and FIG. 4 is a diagram showing the shape of the impeller of the pump, where 201 is a pump impeller, 202 is a magnetic rotor, 203 is a stator coil, and 204 is a position sensor.
本考案によれば、放熱器の流体ループに気液併
用ポンプを設置することにより、気相、液相およ
び気液両相の何れでも駆動できるため、液単相駆
動ポンプを使用した二相流体ループに比べ、気液
分離器を不用とし、また、ガスの駆動も可能なた
めコンプレツサとしても使用でき、さらに排熱温
度を熱源側より高くできるため、排熱量を大きく
とることができる等の優れた効果が奏せられる。
According to the present invention, by installing a gas-liquid combined pump in the fluid loop of the radiator, it is possible to drive gas phase, liquid phase, or both gas and liquid phases. Compared to a loop, it does not require a gas-liquid separator and can be driven by gas, so it can also be used as a compressor.Furthermore, the exhaust heat temperature can be higher than that on the heat source side, so a large amount of exhaust heat can be obtained. The effect is produced.
第１図は本考案の一実施例の流体回路を示す
図、第２図及び第３図は本考案の一実施例におけ
るポンプの詳細図、第４図は第２図および第３図
に示すポンプの羽根車の詳細図である。
１……気液併用ポンプ、２……放熱器、３……
吸熱器、４〜７……弁。
Figure 1 is a diagram showing a fluid circuit according to an embodiment of the present invention, Figures 2 and 3 are detailed diagrams of a pump according to an embodiment of the present invention, and Figure 4 is shown in Figures 2 and 3. FIG. 3 is a detailed view of the impeller of the pump. 1... Gas-liquid combined pump, 2... Heat radiator, 3...
Heat absorber, 4-7...valve.
Claims (1)
器により宇宙空間に排熱する宇宙用熱制御装置に
おいて、流体冷媒の輸送手段として気相、液相お
よび気液二相の何れでも作動できるポンプ１を具
備するとともに、 液単相流のループの管路Ｓ１と、二相流ループ
の管路Ｓ２を有し、 前記流単相流のループの管路Ｓ１は、ポンプ１
と、分岐点Ａと弁６と分岐点Ｂと吸熱器３と、弁
４と、放熱器２と、分岐点Ｃと、分岐点Ｄと、ポ
ンプ１を、前記順に配置した管路から成り、 前記二相流ループの管路Ｓ２は、ポンプ１と、
分岐点Ａと、弁５と、分岐点Ｃと、放熱器２と、
弁４と、吸熱器３と、分岐点Ｂと、 弁７と、分岐点Ｄと、ポンプ１を、 前記順に配置した管路から成り、 前記管路Ｓ１と管路Ｓ２は、共通の管路とし
て、管路Ｂ−Ｃと管路Ｄ−Ａを有し、 前記管路Ｂ−Ｃは、分岐点Ｂと吸熱器３と弁４
と放熱器２と分岐点Ｃを、前記順に配置した管路
からなり、 前記管路Ｄ−Ａは、分岐点Ｄと、ポンプ１と、
分岐点Ａを、前記順に配置した管路からなり、液
単相流のループの場合は、弁５および７は閉、弁
４および６は開の状態にあり、 二相流ループの場合は、弁５，４，７は開、弁
６は閉の状態となることを特徴とする宇宙用熱制
御装置。[Claim for Utility Model Registration] In a space thermal control device that exhausts heat absorbed from a heat load into space by a radiator via a fluid refrigerant, gas phase, liquid phase, and gas-liquid are used as means of transporting the fluid refrigerant. It is equipped with a pump 1 that can operate in either two phases, and has a pipe line S1 for a liquid single-phase flow loop and a pipe line S2 for a two-phase flow loop, wherein the pipe line S1 for the single-phase flow loop is , pump 1
It consists of a pipe line in which branch point A, valve 6, branch point B, heat absorber 3, valve 4, heat radiator 2, branch point C, branch point D, and pump 1 are arranged in the above order, The pipe line S2 of the two-phase flow loop includes a pump 1,
Branch point A, valve 5, branch point C, radiator 2,
It consists of a pipe line in which the valve 4, the heat absorber 3, the branch point B, the valve 7, the branch point D, and the pump 1 are arranged in the above order, and the pipe line S1 and the pipe line S2 are a common pipe line. As shown in FIG.
, the radiator 2 and the branch point C are arranged in the above order, and the pipeline D-A includes the branch point D, the pump 1,
Consisting of a pipe line with branch points A arranged in the above order, in the case of a liquid single-phase flow loop, valves 5 and 7 are closed, and valves 4 and 6 are open, and in the case of a two-phase flow loop, A space thermal control device characterized in that valves 5, 4, and 7 are open and valve 6 is closed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9297487U JPH0544678Y2 (en) | 1987-06-17 | 1987-06-17 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9297487U JPH0544678Y2 (en) | 1987-06-17 | 1987-06-17 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS63201968U JPS63201968U (en) | 1988-12-27 |
| JPH0544678Y2 true JPH0544678Y2 (en) | 1993-11-12 |
Family
ID=30955152
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9297487U Expired - Lifetime JPH0544678Y2 (en) | 1987-06-17 | 1987-06-17 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0544678Y2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3417211B1 (en) * | 2016-02-16 | 2020-09-30 | SABIC Global Technologies B.V. | Methods and systems of cooling process plant water |
-
1987
- 1987-06-17 JP JP9297487U patent/JPH0544678Y2/ja not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPS63201968U (en) | 1988-12-27 |
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