WO1995026467A2 - Bipropellant rocket motor - Google Patents

Bipropellant rocket motor Download PDF

Info

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
Application number
PCT/SI1995/000008
Other languages
French (fr)
Other versions
WO1995026467A3 (en
Inventor
Igor Urban
Original Assignee
Igor Urban
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority to SIP-9400154 priority Critical
Priority to SI9400154A priority patent/SI9400154A/en
Application filed by Igor Urban filed Critical Igor Urban
Priority claimed from EP19950912545 external-priority patent/EP0832349A2/en
Publication of WO1995026467A2 publication Critical patent/WO1995026467A2/en
Publication of WO1995026467A3 publication Critical patent/WO1995026467A3/en

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/425Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants propellants
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44Feeding propellants
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60Constructional parts; Details
    • F02K9/62Combustion or thrust chambers
    • F02K9/64Combustion or thrust chambers having cooling arrangements
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/20Heat transfer, e.g. cooling
    • F05D2260/205Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/20Heat transfer, e.g. cooling
    • F05D2260/232Heat transfer, e.g. cooling characterized by the cooling medium

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

PATENT 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.
PCT/SI1995/000008 1994-03-29 1995-03-28 Bipropellant rocket motor WO1995026467A2 (en)

Priority Applications (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

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AU33334/95A AU3333495A (en) 1994-03-29 1995-03-28 Synthesised fuel-powered reaction rocket motor
EP19950912545 EP0832349A2 (en) 1994-03-29 1995-03-28 Synthesised fuel-powered reaction rocket motor

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 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 (3)

* Cited by examiner, † Cited by third party
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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB792909A (en) * 1953-06-19 1958-04-02 Havilland Engine Co Ltd Rocket motor cooling systems
US2928240A (en) * 1953-01-27 1960-03-15 Thiokol Chemical Corp Control system for reaction motor ignitors
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

Patent Citations (5)

* Cited by examiner, † Cited by third party
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

Cited By (5)

* Cited by examiner, † Cited by third party
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

Also Published As

Publication number Publication date
SI9400154A (en) 1995-12-31
WO1995026467A3 (en) 1995-11-09
AU3333495A (en) 1995-10-17

Similar Documents

Publication Publication Date Title
JP6257724B2 (en) Multistage combustor and method for starting a fuel cell system
Chiaverini Review of solid-fuel regression rate behavior in classical and nonclassical hybrid rocket motors
US4473622A (en) Rapid starting methanol reactor system
US7178339B2 (en) Closed-loop cooling system for a hydrogen/oxygen based combustor
US4771600A (en) Tripropellant rocket engine
US3968775A (en) Fuel system for internal combustion engines
EP0072675B1 (en) Combustor installation and process for producing a heated fluid
RU2158839C2 (en) Liquid-propellant rocket reheat engine
US7146801B2 (en) Fuel vaporizing device
Dressler et al. TRW pintle engine heritage and performance characteristics
DE60005497T2 (en) Hybrid rocket drive with an arrangement of additional rocket motors for position control
US7037349B2 (en) Method and apparatus for fuel/air preparation in a fuel cell
US5207185A (en) Emissions reduction system for internal combustion engines
US6863522B2 (en) Method for introducing fuel and/or thermal energy into a gas stream
US6250072B1 (en) Multi-ignition controllable solid-propellant gas generator
US4687491A (en) Fuel admixture for a catalytic combustor
CA2110057C (en) Satellite propulsion and power system
US2711630A (en) Rockets
US3682142A (en) Method and means for generating hydrogen and a motive source incorporating same
US5099645A (en) Liquid-solid propulsion system and method
US2683963A (en) Reaction engine with automatic pressure regulation
US20140260186A1 (en) Rocket engine systems with an independently regulated cooling system
US6968673B1 (en) Cool gas generator and ultra-safe rocket engine
US5634341A (en) System for generating hydrogen
US4583362A (en) Expander-cycle, turbine-drive, regenerative rocket engine

Legal Events

Date Code Title Description
AL Designated countries for regional patents

Kind code of ref document: A2

Designated state(s): AT BE CH DE DK ES FR GB GR IE IT LU MC NL PT SE

AK Designated states

Kind code of ref document: A2

Designated state(s): AM AT AU BB BG BR BY CA CH CN CZ DE DK ES FI GB GE HU JP KE KG KP KR KZ LK LT LU LV MD MG MN MW NL NO NZ PL PT RO RU SD SE SK TJ TT UA US UZ VN

AK Designated states

Kind code of ref document: A3

Designated state(s): AM AT AU BB BG BR BY CA CH CN CZ DE DK ES FI GB GE HU JP KE KG KP KR KZ LK LT LU LV MD MG MN MW NL NO NZ PL PT RO RU SD SE SK TJ TT UA US UZ VN

AL Designated countries for regional patents

Kind code of ref document: A3

Designated state(s): AT BE CH DE DK ES FR GB GR IE IT LU MC NL PT SE

121 Ep: the epo has been informed by wipo that ep was designated in this application
WWE Wipo information: entry into national phase

Ref document number: 1995912545

Country of ref document: EP

REG Reference to national code

Ref country code: DE

Ref legal event code: 8642

NENP Non-entry into the national phase in:

Ref country code: CA

WWP Wipo information: published in national office

Ref document number: 1995912545

Country of ref document: EP

WWW Wipo information: withdrawn in national office

Ref document number: 1995912545

Country of ref document: EP