WO1995026467A2 - Bipropellant rocket motor - Google Patents
Bipropellant rocket motor Download PDFInfo
- Publication number
- WO1995026467A2 WO1995026467A2 PCT/SI1995/000008 SI9500008W WO9526467A2 WO 1995026467 A2 WO1995026467 A2 WO 1995026467A2 SI 9500008 W SI9500008 W SI 9500008W WO 9526467 A2 WO9526467 A2 WO 9526467A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- synthesised
- fuel
- rocket motor
- tank
- powered
- 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.)
- Ceased
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/425—Propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
Definitions
- the invention is a sythesised fuel-powered reaction rocket motor, powered by fuels based on labile compounds which can be used as fuel only if they have previously been synthesised or processed.
- the technical problem successfully solved by this invention is the use of compounds which are basically very labile and which cannot be used as fuel for rocket or similar motors under normal circumstances.
- Standard rocket motors are fuelled by a mixture of fuel and oxidant, kept separately in two tanks. Combination of the two components in the combustion chamber causes a chemical reaction and the thrust to move the rocket.
- This synthesised fuel-powered reaction rocket motor uses two synthesised compounds stored in separate tanks, which are combined in an antechamber and react in a fusion nozzle. The synthesised fuel burns in the combustion chamber and the resulting gases provide the necessary thrust.
- the synthesised fuel-powered reaction rocket motor shown in Fig. 1 has: two tanks 1 and 2, a combustion chamber 4 and a thrust nozzle 5.
- tanks 1 and 2 there are two compounds.
- Tank 1 holds nitric acid HNO3 and tank 2 holds NH3.
- Both tanks have preheater units for controlled heating of the compounds in the tanks.
- the water which surrounds the tanks with the compounds can be heated by microwave heaters controlled by a microprocessor 11 until the motor is started.
- Both tanks are surrounded by a preheating system 8 consisting of water pipes fitted around the tanks.
- the water in the preheating system is heated by means of the cooling grid 13 and kept at 85°C with an electric thermostat valve 7 and pump 14.
- HNO 3 boils at 85°C and the acid vapours are conducted through a fuel pipe and pump 9 and regulator 10 to the combustion chamber 4.
- the NH 3 in tank 2 is heated to an equal temperature and the vapour is conducted via pump 9' and regulator 10'.
- Both regulators 10 and 10' are controlled by a microprocessor 11.
- Regulators 10 and 10' control the dosage of the compound and safety valves 12 and 12' control reverse pressure.
- Regulators 10 and 10' at the exits of both tanks 1 and 2 provide conditions for the heated compounds from the tanks to mix in a fixed ratio, which is, in this version, 1:1.
- a fixed ratio which is, in this version, 1:1.
- small drops of the now synthesised fuel NH4NO3 go through the mixing nozzle 3 to the combustion chamber 4 and through the cooling grid 13, which wards off the blast resulting from the explosion of the drops of fuel.
- the cooling grid 13 is cooled by the water from the preheating system 8.
- As the drops leave the cooling grid they travel down the combustion chamber 4 where an ignition coil 6 is mounted. With the help of the ignition coil 6, the drops of fuel explode, producing a temperature of 2710°C.
- the pressure at this moment is 994 MPa.
- tank 2 contains glycerol.
- the ratio between the glycerol from the tank 2 and the HNO3 from tank 1 is 3:1.
- the glycerol in tank 2 is preheated to 85°C and then vaporised by pressure.
- the HNO3 is also vaporised.
- the vapours of both compounds are mixed in a ratio of 3:1. Because of the high temperature, glycerol and HNO3 combine into small drops of the fuel - nitroglycerin. These drops explode at the ignition coil 6.
- the gases (which have a temperature of 4250°C) are thrust through the Laval nozzle, where they expand. The inner energy is partially transformed into kinetic energy and we get the reaction.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
Abstract
The invention is a synthesised fuel-powered reaction rocket motor, powered by fuels based on labile compounds which can be used as fuel only if they have previously been synthesised or processed. The synthesised fuel-powered reaction rocket motor has two synthesised compounds stored in separate tanks (1, 2), which are combined in the antechamber and which react in the combustion chamber (4). The resulting gases give the required thrust.
Description
SYNTHESISED FUEL-POWERED REACTION ROCKET
MOTOR
The invention is a sythesised fuel-powered reaction rocket motor, powered by fuels based on labile compounds which can be used as fuel only if they have previously been synthesised or processed.
The technical problem successfully solved by this invention is the use of compounds which are basically very labile and which cannot be used as fuel for rocket or similar motors under normal circumstances.
Standard rocket motors are fuelled by a mixture of fuel and oxidant, kept separately in two tanks. Combination of the two components in the combustion chamber causes a chemical reaction and the thrust to move the rocket.
This synthesised fuel-powered reaction rocket motor uses two synthesised compounds stored in separate tanks, which are combined in an antechamber and react in a fusion nozzle. The synthesised fuel burns in the combustion chamber and the resulting gases provide the necessary thrust.
I will describe the synthesised fuel-powered reaction rocket motor in more detail on the basis of the construction sample and the drawing, which shows:
Fig. 1 Scheme of the synthesised fuel-powered reaction rocket motor
The synthesised fuel-powered reaction rocket motor shown in Fig. 1 has: two tanks 1 and 2, a combustion chamber 4 and a thrust nozzle 5. In the tanks 1 and 2 there are two compounds. Tank 1 holds nitric acid HNO3 and tank 2 holds NH3. Both tanks have preheater units for controlled heating of the compounds in the tanks. The water which surrounds the tanks with the compounds can be heated by microwave heaters controlled by a microprocessor 11 until the motor is started. Both tanks are surrounded by a preheating system 8 consisting of water pipes fitted around the tanks. The water in the preheating system is heated by means
of the cooling grid 13 and kept at 85°C with an electric thermostat valve 7 and pump 14. HNO3 boils at 85°C and the acid vapours are condusted through a fuel pipe and pump 9 and regulator 10 to the combustion chamber 4. The NH3 in tank 2 is heated to an equal temperature and the vapour is conducted via pump 9' and regulator 10'. Both regulators 10 and 10' are controlled by a microprocessor 11. Regulators 10 and 10' control the dosage of the compound and safety valves 12 and 12' control reverse pressure.
Regulators 10 and 10' at the exits of both tanks 1 and 2 provide conditions for the heated compounds from the tanks to mix in a fixed ratio, which is, in this version, 1:1. From here small drops of the now synthesised fuel NH4NO3 go through the mixing nozzle 3 to the combustion chamber 4 and through the cooling grid 13, which wards off the blast resulting from the explosion of the drops of fuel. The cooling grid 13 is cooled by the water from the preheating system 8. As the drops leave the cooling grid, they travel down the combustion chamber 4 where an ignition coil 6 is mounted. With the help of the ignition coil 6, the drops of fuel explode, producing a temperature of 2710°C. The pressure at this moment is 994 MPa. The hot gases gush from the combustion chamber with supersonic speed through the narrow exit of the Laval nozzle and cause a reaction.
In the second version of the synthesised fuel-power reaction rocket motor, tank 2 contains glycerol. The ratio between the glycerol from the tank 2 and the HNO3 from tank 1 is 3:1.
The glycerol in tank 2 is preheated to 85°C and then vaporised by
pressure. The HNO3 is also vaporised. The vapours of both compounds are mixed in a ratio of 3:1. Because of the high temperature, glycerol and HNO3 combine into small drops of the fuel - nitroglycerin. These drops explode at the ignition coil 6. The gases (which have a temperature of 4250°C) are thrust through the Laval nozzle, where they expand. The inner energy is partially transformed into kinetic energy and we get the reaction.
Claims
1. Synthesised fuel-powered reaction rocket motor, characterised by
a process in which previously thermally-treated synthesised fuels stored in separate tanks (1,2), with the possibility of further thermal treatment, are conducted through a mixing nozzle (3) to a combustion chamber (4), where vapours of the synthesised fuels explode and the resulting gases gush through the thrust nozzle (5), causing a reaction.
2. Synthesised fuel-powered reaction rocket motor, under item 1 , characterised by the fact that tank (1) contains nitric acid HNO3 and tank (2) contains NH3, which are mixed in a ratio of 1 :1.
3. Synthesised fuel-powered reaction rocket motor, under item 1 , characterised by teh fact that tank (1) contains nitric acid HNO3 and tank (2) contains glycerol, which are mixed at a ratio of 3:1.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP95912545A EP0832349A2 (en) | 1994-03-29 | 1995-03-28 | Synthesised fuel-powered reaction rocket motor |
| AU33334/95A AU3333495A (en) | 1994-03-29 | 1995-03-28 | Synthesised fuel-powered reaction rocket motor |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SIP-9400154 | 1994-03-29 | ||
| SI9400154A SI9400154A (en) | 1994-03-29 | 1994-03-29 | Reaction rocket engine with synthetic fuel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| WO1995026467A2 true WO1995026467A2 (en) | 1995-10-05 |
| WO1995026467A3 WO1995026467A3 (en) | 1995-11-09 |
Family
ID=20431365
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/SI1995/000008 Ceased WO1995026467A2 (en) | 1994-03-29 | 1995-03-28 | Bipropellant rocket motor |
Country Status (3)
| Country | Link |
|---|---|
| AU (1) | AU3333495A (en) |
| SI (1) | SI9400154A (en) |
| WO (1) | WO1995026467A2 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0916835A1 (en) * | 1997-11-14 | 1999-05-19 | TRW Inc. | Closed loop cooled rocket engine |
| WO2007003270A1 (en) | 2005-06-30 | 2007-01-11 | DEUTSCHES ZENTRUM FüR LUFT-UND RAUMFAHRT E.V. | Gel-type fuel based drive device and method for supplying fuel |
| US8875685B2 (en) | 2008-03-20 | 2014-11-04 | Aquafuel Research Limited | Combustion method and apparatus |
| JP2021183870A (en) * | 2020-05-20 | 2021-12-02 | アリアーヌグループ ソシエテ パ アクシオンス シンプリフィエ | Cooling valve for rocket engine with cryogenic propellant and rocket engine comprising the cooling valve |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2928240A (en) * | 1953-01-27 | 1960-03-15 | Thiokol Chemical Corp | Control system for reaction motor ignitors |
| GB792909A (en) * | 1953-06-19 | 1958-04-02 | Havilland Engine Co Ltd | Rocket motor cooling systems |
| US2981059A (en) * | 1958-02-04 | 1961-04-25 | Thompson Ramo Wooldridge Inc | Dual thrust chamber rocket |
| US3140582A (en) * | 1959-04-14 | 1964-07-14 | Olin Mathieson | Rocket propulsion method using boron and nitrogen compounds |
| GB2167401A (en) * | 1984-09-25 | 1986-05-29 | Kevin Maurice Buckley | Injection nitration engine |
-
1994
- 1994-03-29 SI SI9400154A patent/SI9400154A/en unknown
-
1995
- 1995-03-28 WO PCT/SI1995/000008 patent/WO1995026467A2/en not_active Ceased
- 1995-03-28 AU AU33334/95A patent/AU3333495A/en not_active Abandoned
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0916835A1 (en) * | 1997-11-14 | 1999-05-19 | TRW Inc. | Closed loop cooled rocket engine |
| US6052987A (en) * | 1997-11-14 | 2000-04-25 | Trw Inc. | Non-propellant fluid cooled space craft rocket engine |
| WO2007003270A1 (en) | 2005-06-30 | 2007-01-11 | DEUTSCHES ZENTRUM FüR LUFT-UND RAUMFAHRT E.V. | Gel-type fuel based drive device and method for supplying fuel |
| US8033095B2 (en) | 2005-06-30 | 2011-10-11 | Deutsches Zentrum Fuer Luft-Und Raumfahrt E.V. | Drive device on the basis of a gel-type propellant and method for conveying propellant |
| US8875685B2 (en) | 2008-03-20 | 2014-11-04 | Aquafuel Research Limited | Combustion method and apparatus |
| JP2021183870A (en) * | 2020-05-20 | 2021-12-02 | アリアーヌグループ ソシエテ パ アクシオンス シンプリフィエ | Cooling valve for rocket engine with cryogenic propellant and rocket engine comprising the cooling valve |
Also Published As
| Publication number | Publication date |
|---|---|
| AU3333495A (en) | 1995-10-17 |
| SI9400154A (en) | 1995-12-31 |
| WO1995026467A3 (en) | 1995-11-09 |
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