JPH04153550A - Air liquefied engine - Google Patents
Air liquefied engineInfo
- Publication number
- JPH04153550A JPH04153550A JP27709490A JP27709490A JPH04153550A JP H04153550 A JPH04153550 A JP H04153550A JP 27709490 A JP27709490 A JP 27709490A JP 27709490 A JP27709490 A JP 27709490A JP H04153550 A JPH04153550 A JP H04153550A
- Authority
- JP
- Japan
- Prior art keywords
- air
- oxygen
- flow path
- hydrogen
- liquid
- 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.)
- Granted
Links
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 43
- 239000001301 oxygen Substances 0.000 claims abstract description 43
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 43
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 41
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 18
- 239000001257 hydrogen Substances 0.000 claims description 30
- 229910052739 hydrogen Inorganic materials 0.000 claims description 30
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 28
- 239000007788 liquid Substances 0.000 claims description 19
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 16
- 239000007789 gas Substances 0.000 abstract description 6
- 229910001873 dinitrogen Inorganic materials 0.000 abstract description 5
- 230000006835 compression Effects 0.000 abstract description 4
- 238000007906 compression Methods 0.000 abstract description 4
- LPLLVINFLBSFRP-UHFFFAOYSA-N 2-methylamino-1-phenylpropan-1-one Chemical compound CNC(C)C(=O)C1=CC=CC=C1 LPLLVINFLBSFRP-UHFFFAOYSA-N 0.000 abstract 2
- 241000132539 Cosmos Species 0.000 abstract 2
- 235000005956 Cosmos caudatus Nutrition 0.000 abstract 2
- 238000002485 combustion reaction Methods 0.000 description 5
- 239000007800 oxidant agent Substances 0.000 description 5
- 239000000446 fuel Substances 0.000 description 3
- 239000003380 propellant Substances 0.000 description 3
- 239000003507 refrigerant Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 150000002431 hydrogen Chemical class 0.000 description 2
- -1 Of the total weight Substances 0.000 description 1
- 230000002250 progressing effect Effects 0.000 description 1
Abstract
Description
【発明の詳細な説明】 ［産業上の利用分野］ 本発明は空気液化エンジンに関するものである。[Detailed description of the invention] [Industrial application field] The present invention relates to air liquefaction engines.
［従来の技術］
近年、宇宙往還機の開発か活発に進められつつあるか、
特に近年では大気中を飛行する間は燃料の燃焼に必要Ｉ
；酸素を空気中から取り入れて、宇宙往還機に搭載する
酸化剤の量を節約するようにした空気液化エンノンか研
究されている。[Conventional technology] In recent years, the development of spacecraft has been actively progressing.
Particularly in recent years, during flight in the atmosphere, the I
Research is being conducted on air liquefaction ennon, which takes oxygen from the air and saves on the amount of oxidizing agent carried on spacecraft.
現在のロケ・ノドは、スペース・ンヤトルも含め、必要
な酸化剤はすべて搭載している。代表的な酸化剤は温度
−１８３℃の液体酸素であり、その重量は、代表的な燃
料である水素の６倍、スペース・シャトルでは、全重量
の約１／３にも達する。このため人口衛星などのペイロ
ードは、全体の約１〜２％程度の重ごてしかない。The current Roque Nodo is equipped with all the necessary oxidizers, including the Space Nyatle. A typical oxidizing agent is liquid oxygen at a temperature of -183° C., and its weight is six times that of hydrogen, a typical fuel, and about one-third of the total weight of the space shuttle. For this reason, the payload of artificial satellites only accounts for about 1 to 2% of the total weight.
これに比へ、空気中の酸素を用いる航空機の場合には、
全重量のうち、燃料（この場合はジェット燃料）か約４
０％、ペイロードは１０％強まて上る。このことから、
酸化剤搭載量を最小にし、ペイロード率を高めて経済的
な宇宙輸送を実現する上で空気液化エンジンの開発が望
まれている。In contrast, in the case of aircraft that use atmospheric oxygen,
Of the total weight, fuel (in this case jet fuel) or approx.
0%, and the payload increases by just over 10%. From this,
The development of an air-liquefaction engine is desired to minimize the amount of oxidizer carried and increase the payload rate to realize economical space transportation.
前記空気液化エンジンは、離陸から宇宙に飛びだすまで
すべて一本のエンジンで済ませようとの考え方で、ロケ
ットの形態を基本として考えられたエンジンであり、原
理は、吸入した空気を、−２５３℃の液体水素を冷媒と
して液化し、これを酸化剤としてロケット燃焼室に高圧
で送り込み、液体水素／液体空気ロケットエンジンとし
て燃焼・噴出させるものである。従って空気取入口と空
気の液化器を除けはロケットと同様の構成となる。The above-mentioned air liquefaction engine is an engine designed based on the form of a rocket, with the idea that a single engine can be used for everything from takeoff to space flight. Liquid hydrogen is liquefied as a refrigerant, and this is sent as an oxidizer into the rocket combustion chamber at high pressure, where it is combusted and ejected as a liquid hydrogen/liquid air rocket engine. Therefore, the structure is similar to that of a rocket, except for the air intake and air liquefier.
［発明か解決しようとする課題］
しかし、上記空気液化エンジンには解決しなけれはなら
ない種々の技術的課題か山積みされている。[Problems to be Solved by the Invention] However, the above-mentioned air liquefaction engine has a large number of various technical problems that must be solved.
本発明は特に宇宙往還機に搭載する酸化剤の量の節約と
、推進効率の増加を図ることを目的としている。The present invention is particularly aimed at saving the amount of oxidizing agent carried in a spacecraft and increasing propulsion efficiency.
［課題を解決するための手段］
本発明はジェット部とロケット部とを備えた空気液化エ
ンジンであって、空気取入口と、水素タンクと、該水素
タンクの液体水素を前記空気取入口に配した空気予冷器
を経た後前記ジェット部とロケット部とに切換え可能に
供給する水素流路と、酸素タンクと、該酸素タンクの液
体酸素を前記ジェット部とロケット部とに切換え可能に
供給する酸素流路と、前記空気取入口から取入れた加圧
空気を前記水素流路の液体水素により冷却して液化し液
体酸素と液体窒素に分離する液化分離器と、該液化性Ｍ
器にて分離した液体酸素を前記酸素流路に導く酸素供給
流路と、前記液化分離器で分離した液体窒素を前記空気
取入口に配した空気予冷器を経た後前記ジェット部に導
く窒素流路とを備えたことを特徴とする空気液化エンジ
ンにかかるものである。[Means for Solving the Problems] The present invention is an air liquefaction engine equipped with a jet section and a rocket section, which includes an air intake port, a hydrogen tank, and liquid hydrogen in the hydrogen tank disposed in the air intake port. a hydrogen flow path that selectively supplies liquid oxygen to the jet section and the rocket section after passing through an air precooler; an oxygen tank; a flow path, a liquefaction separator that cools and liquefies pressurized air taken in from the air intake port with liquid hydrogen in the hydrogen flow path and separates it into liquid oxygen and liquid nitrogen;
an oxygen supply flow path that leads liquid oxygen separated by the liquefier to the oxygen flow path; and a nitrogen flow that leads the liquid nitrogen separated by the liquefaction separator to the jet section after passing through an air precooler disposed at the air intake port. The present invention relates to an air liquefaction engine characterized in that the air liquefaction engine is equipped with a duct.
［作 用〕
大気中を飛行する際、液化分離器で分離した液化酸素を
ジェット部に供給すると共に、余剰分を酸素タンクに貯
えておくことにより、ロケット部による宇宙空間の推進
に利用できる。[Function] When flying in the atmosphere, the liquefied oxygen separated by the liquefaction separator is supplied to the jet section, and the surplus is stored in the oxygen tank, which allows the rocket section to use it for propulsion into space.
又、液化分離器で分離され液化窒素ガスを空気取入口の
空気予冷器に導いて空気の冷却を行うことにより、空気
の圧縮比が高められ、且つ前記窒素かジェット部に供給
されて排出ガスのホリュームか増加することによって推
力か増加する。In addition, the liquefied nitrogen gas separated by the liquefaction separator is guided to the air precooler at the air intake port to cool the air, thereby increasing the compression ratio of the air and supplying the nitrogen to the jet section to reduce the exhaust gas. Thrust increases by increasing the volume of.
［実 施 例コ 以下、本発明の実施例を図面を参照しつつ説明する。[Implementation example] Embodiments of the present invention will be described below with reference to the drawings.
第１図は本発明の一実施例であり、飛行体の進行方向前
方に向けて開口させた空気取入口ｌから取入れた空気２
を空気流路３に有したポンプ４により昇圧して液化分離
器５に導き、且つ水素タンク６からの液体水素Ｈ２（−
２５３℃〕を水素流路７により熱交換器８及びポンプ９
を介して前記液化分離器５に冷媒として導くことにより
冷却、液化し、液体酸素０２、液体窒素Ｎ２を分離して
取出すようにしている。FIG. 1 shows an embodiment of the present invention, in which air 2 is taken in from an air intake port 1 opened toward the front in the direction of movement of the aircraft.
The pressure of hydrogen H2 (-
253°C] through the hydrogen flow path 7 to the heat exchanger 8 and pump 9.
It is cooled and liquefied by guiding it as a refrigerant to the liquefaction separator 5 via the liquefaction separator 5, and liquid oxygen 02 and liquid nitrogen N2 are separated and taken out.
前記液化分離器５にて空気の冷却・液化を行った水素Ｈ
２は、水素流路７により前記空気取入口１に備えた空気
予冷器１０に導かれて取入れる空気の予冷を行い、自身
は昇温された後、ジェット部１１及びロケット部１２に
切換えて供給されるようになっている。Hydrogen H obtained by cooling and liquefying the air in the liquefaction separator 5
2 pre-cools the air that is introduced by the hydrogen flow path 7 to the air precooler 10 provided in the air intake port 1, and after the air itself is heated, it is switched to the jet section 11 and the rocket section 12. It is now being supplied.
又、酸素タンク１３の液体酸素０２を酸素流路１４によ
り前記熱交換器８及びポンプ１５を介して前記ロケット
部１２に導いて昇温を行った後、前記／エツト部ＩＩ及
びロケット部１２に切換えて供給するようにしている。Further, the liquid oxygen 02 in the oxygen tank 13 is guided to the rocket part 12 through the oxygen flow path 14 via the heat exchanger 8 and the pump 15 to raise its temperature, and then is introduced into the /et part II and the rocket part 12. I am trying to switch the supply.
更に、前記液化分離器５にて分離された液体酸素０２は
、酸素供給流路１６により前記熱交換器８とポンプ１５
との間の酸素流路１４に供給するようにしである。Furthermore, the liquid oxygen 02 separated in the liquefaction separator 5 is transferred to the heat exchanger 8 and the pump 15 through the oxygen supply channel 16.
The oxygen flow path 14 between the two is supplied with oxygen.
又、前記液化性Ｍ器５にて分離された液体窒素Ｎ２は、
窒素流路１７により前記空気取入口１に備えた空気予冷
器１８に導かれて取入れる空気の予冷を行い、自身は昇
温された後、前記ジェット部１１に供給されるようにな
っている。Moreover, the liquid nitrogen N2 separated in the liquefiable M vessel 5 is
The nitrogen flow path 17 guides the air to the air precooler 18 provided in the air intake port 1 to pre-cool the air taken in, and after the air itself is heated, it is supplied to the jet section 11. .
上記空気液化エンジンによって大気中を飛行する間は、
水素タンク６の液体水素Ｈ２か、水素流路７により熱交
換器８、ポンプ９、液化分離器５、空気予冷器１０を介
し、気化された状態でジェット部１１に導かれると共に
、空気取入口ｌから取入れられ空気予冷器１０により予
冷された空気２かポンプ４によって加圧された後、前記
液化分離器５に導かれて前記液体水素Ｈ２を冷媒とする
冷却によって液化され、更に、液体酸素０２と液体窒素
Ｎ２に分離され、該分離された液体酸素０２か酸素供給
流路１６及びポンプ１５を存した酸素流路１４を介して
前記ジェット部１１に供給され、これによりジェット部
１１にて燃焼か行われて推力か発生する。尚、地上から
の発進時、燃焼のための酸素０２の量か足りない分は、
酸素タック１３の液体酸素０２を酸素流路１４を介して
補給する。While flying through the atmosphere with the air liquefaction engine,
The liquid hydrogen H2 in the hydrogen tank 6 is guided in a vaporized state to the jet section 11 by the hydrogen flow path 7 via the heat exchanger 8, pump 9, liquefaction separator 5, and air precooler 10, and is also introduced into the jet section 11 through the air intake port. The air 2 taken in from 1 and precooled by the air precooler 10 is pressurized by the pump 4, and then led to the liquefaction separator 5 where it is liquefied by cooling using the liquid hydrogen H2 as a refrigerant. 02 and liquid nitrogen N2, and the separated liquid oxygen 02 is supplied to the jet section 11 through the oxygen flow channel 14 which includes an oxygen supply channel 16 and a pump 15. Combustion occurs and thrust is generated. In addition, when starting from the ground, the amount of oxygen 02 for combustion is insufficient.
Liquid oxygen 02 in the oxygen tack 13 is replenished via the oxygen flow path 14.
前記大気中の飛行時に液化分離器５て作り出される液体
酸素０２の量かジェット部１１で燃焼に供される酸素０
２の量を少し上回るように各装置の容量等を選定してお
き、その余剰分を酸素供給流路１６及び酸素流路１４に
備えた熱交換器８を介して前記酸素タンク１３に戻すよ
うにする。The amount of liquid oxygen 02 produced in the liquefied separator 5 during flight in the atmosphere or the amount of oxygen 02 provided for combustion in the jet section 11
The capacity of each device is selected so as to slightly exceed the amount of 2, and the surplus is returned to the oxygen tank 13 via the heat exchanger 8 provided in the oxygen supply flow path 16 and the oxygen flow path 14. Make it.
このとき、酸素タンク１３に戻される酸素０２は、熱交
換器８での液体水素Ｈ２による冷却によって確実に液化
されている。At this time, the oxygen 02 returned to the oxygen tank 13 is reliably liquefied by being cooled by the liquid hydrogen H2 in the heat exchanger 8.
一方、前記液化分離器５にて液化分離された液体窒素Ｎ
２は、窒素流路１７により空気取入口ｌの空気予冷器１
８に導かれて、取入れる空気２の予冷を更に行い、自身
は昇温ガス化されてジェット部１１に供給される。On the other hand, liquid nitrogen N liquefied and separated in the liquefaction separator 5
2 is an air precooler 1 at the air intake port l by a nitrogen flow path 17.
8 , the air 2 to be taken in is further precooled, and the air 2 itself is heated and gasified and supplied to the jet section 11 .
このとき、ジェット部１１による推力は、該ジェット部
１１から後方に排出される排出ガスのボリュームに大き
く影響されるため、推力を増大させるためには水素Ｈ２
及び酸素０２の推進剤の供給を増加すれは良いか、その
場合には推進剤の消費量か増加し、又燃焼温度も上昇す
るのてそのための対策を講しる必要かある。At this time, the thrust by the jet section 11 is greatly influenced by the volume of the exhaust gas discharged backward from the jet section 11, so in order to increase the thrust, hydrogen H2
Is it a good idea to increase the supply of propellant for oxygen 02? In that case, the amount of propellant consumed will increase, and the combustion temperature will also rise, so it is necessary to take measures to prevent this.
これに対し、前記窒素Ｎ２をジェット部１１に供給する
ことにより、排出ガスの温度を上昇させることなく排出
ガスのボリュームを増加させることかでき、よって窒素
Ｎ２を推進剤の一部として利用し、水素Ｈ２、酸素０２
の消費量を少なくしてしかも推力を高めることができる
。On the other hand, by supplying the nitrogen N2 to the jet section 11, the volume of the exhaust gas can be increased without increasing the temperature of the exhaust gas, and therefore, the nitrogen N2 can be used as part of the propellant. Hydrogen H2, Oxygen 02
It is possible to reduce consumption amount and increase thrust.
一方、宇宙空間を飛行する際は、水素タンク６の液体水
素Ｈ２及び酸素タンク１３の液体酸素０２をロケット部
１２に供給するように切換えて、ロケット部１２により
推力を得るようにする。On the other hand, when flying in outer space, the liquid hydrogen H2 in the hydrogen tank 6 and the liquid oxygen 02 in the oxygen tank 13 are switched to be supplied to the rocket section 12, so that the rocket section 12 obtains thrust.
尚、本発明の空気液化エンジンは、上述の実施例にのみ
限定されるものではなく、本発明の要旨を逸脱しない範
囲内において種々変更を加え得ることは勿論である。It should be noted that the air liquefaction engine of the present invention is not limited to the above-described embodiments, and it goes without saying that various changes may be made without departing from the gist of the present invention.
［発明の効果〕
以上説明したように、本発明の空気液化エンノンによれ
は、下記の如き種々の優れた効果を奏し得る。[Effects of the Invention] As explained above, the air-liquefied enone of the present invention can produce various excellent effects as described below.
（ｉ） 大気中を飛行する際、液化分離器で分離した
液化酸素をジェット部に供給すると共に、余剰分を酸素
タンクに貯えておくことにより、ロケット部による宇宙
空間での推進に利用することかでき、よって宇宙往還機
への液体酸素の搭載量を削減できる。(i) When flying in the atmosphere, liquefied oxygen separated by a liquefaction separator is supplied to the jet section, and the surplus is stored in an oxygen tank so that it can be used for propulsion in space by the rocket section. Therefore, the amount of liquid oxygen carried on spacecraft can be reduced.
０）液化分離器で分離され液化窒素ガスを空気取入口の
空気予冷器に導いて空気の冷却を行うことにより、空気
の圧縮比を高めることかでき、且つ前記窒素をジェット
部に供給することにより排出ガスのボリュームが増加さ
れて推力か増大される。0) By guiding the liquefied nitrogen gas separated by the liquefaction separator to the air precooler at the air intake port to cool the air, the compression ratio of the air can be increased, and the nitrogen is supplied to the jet section. This increases the volume of exhaust gas and increases the thrust.
第１図は本発明の一実施例を示すフローチャトである。
１は空気取入口、５は液化分離器、６は水素タンク、７
は水素流路、１０は空気予冷器、１１はジェット部、１
２はロケット部、１３は酸素タンク、１４は酸素流路、
１６は酸素供給流路、１７は窒素流路、１８は空気予冷
器を示す。FIG. 1 is a flowchart showing one embodiment of the present invention. 1 is an air intake port, 5 is a liquefaction separator, 6 is a hydrogen tank, 7
1 is a hydrogen flow path, 10 is an air precooler, 11 is a jet part, 1
2 is a rocket part, 13 is an oxygen tank, 14 is an oxygen flow path,
16 is an oxygen supply flow path, 17 is a nitrogen flow path, and 18 is an air precooler.
Claims (1)
ンであって、空気取入口と、水素タンクと、該水素タン
クの液体水素を前記空気取入口に配した空気予冷器を経
た後前記ジェット部とロケット部とに切換え可能に供給
する水素流路と、酸素タンクと、該酸素タンクの液体酸
素を前記ジェット部とロケット部とに切換え可能に供給
する酸素流路と、前記空気取入口から取入れた加圧空気
を前記水素流路の液体水素により冷却して液化し液体酸
素と液体窒素に分離する液化分離器と、該液化分離器に
て分離した液体酸素を前記酸素流路に導く酸素供給流路
と、前記液化分離器で分離した液体窒素を前記空気取入
口に配した空気予冷器を経た後前記ジェット部に導く窒
素流路とを備えたことを特徴とする空気液化エンジン。1) An air liquefaction engine comprising a jet section and a rocket section, wherein the air liquefaction engine includes an air intake port, a hydrogen tank, and the liquid hydrogen in the hydrogen tank passes through an air precooler disposed in the air intake port, and then the jet section a hydrogen flow path for switchably supplying liquid oxygen to the jet portion and the rocket portion; an oxygen tank; an oxygen flow path for switchably supplying liquid oxygen from the oxygen tank to the jet portion and the rocket portion; a liquefaction separator that cools and liquefies the pressurized air with liquid hydrogen in the hydrogen flow path and separates it into liquid oxygen and liquid nitrogen; and an oxygen supply that guides the liquid oxygen separated by the liquefaction separator to the oxygen flow path. An air liquefaction engine comprising: a flow path; and a nitrogen flow path that guides the liquid nitrogen separated by the liquefaction separator to the jet section after passing through an air precooler disposed at the air intake port.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2277094A JP2882023B2 (en) | 1990-10-16 | 1990-10-16 | Air liquefaction engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2277094A JP2882023B2 (en) | 1990-10-16 | 1990-10-16 | Air liquefaction engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH04153550A true JPH04153550A (en) | 1992-05-27 |
| JP2882023B2 JP2882023B2 (en) | 1999-04-12 |
Family
ID=17578692
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2277094A Expired - Lifetime JP2882023B2 (en) | 1990-10-16 | 1990-10-16 | Air liquefaction engine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2882023B2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2766911A1 (en) * | 1997-08-04 | 1999-02-05 | Air Liquide | Material transfer between liquid and counter-flowing gas for two-stage rocket |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3768254A (en) * | 1962-07-09 | 1973-10-30 | Boeing Co | Rocket propulsion method and means |
| JPS63302166A (en) * | 1987-06-01 | 1988-12-09 | Natl Aerospace Lab | Separated type liquid-air cycle engine |
-
1990
- 1990-10-16 JP JP2277094A patent/JP2882023B2/en not_active Expired - Lifetime
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3768254A (en) * | 1962-07-09 | 1973-10-30 | Boeing Co | Rocket propulsion method and means |
| JPS63302166A (en) * | 1987-06-01 | 1988-12-09 | Natl Aerospace Lab | Separated type liquid-air cycle engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2766911A1 (en) * | 1997-08-04 | 1999-02-05 | Air Liquide | Material transfer between liquid and counter-flowing gas for two-stage rocket |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2882023B2 (en) | 1999-04-12 |
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