EP0832349A2 - Synthesised fuel-powered reaction rocket motor - Google Patents

Synthesised fuel-powered reaction rocket motor

Info

Publication number
EP0832349A2
EP0832349A2 EP19950912545 EP95912545A EP0832349A2 EP 0832349 A2 EP0832349 A2 EP 0832349A2 EP 19950912545 EP19950912545 EP 19950912545 EP 95912545 A EP95912545 A EP 95912545A EP 0832349 A2 EP0832349 A2 EP 0832349A2
Authority
EP
European Patent Office
Prior art keywords
synthesised
fuel
rocket motor
powered
tank
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.)
Withdrawn
Application number
EP19950912545
Other languages
German (de)
French (fr)
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 SI9400015 priority Critical
Priority to SI9400015 priority
Application filed by Igor Urban filed Critical Igor Urban
Priority to PCT/SI1995/000008 priority patent/WO1995026467A2/en
Publication of EP0832349A2 publication Critical patent/EP0832349A2/en
Withdrawn legal-status Critical Current

Links

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.
EP19950912545 1994-03-29 1995-03-28 Synthesised fuel-powered reaction rocket motor Withdrawn EP0832349A2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
SI9400015 1994-03-29
SI9400015 1994-03-29
PCT/SI1995/000008 WO1995026467A2 (en) 1994-03-29 1995-03-28 Bipropellant rocket motor

Publications (1)

Publication Number Publication Date
EP0832349A2 true EP0832349A2 (en) 1998-04-01

Family

ID=20431311

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19950912545 Withdrawn EP0832349A2 (en) 1994-03-29 1995-03-28 Synthesised fuel-powered reaction rocket motor

Country Status (1)

Country Link
EP (1) EP0832349A2 (en)

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9526467A2 *

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Legal Events

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17P Request for examination filed

Effective date: 19960703

18D Deemed to be withdrawn

Effective date: 19981001