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1. WO1995026467 - BIPROPELLANT ROCKET MOTOR

Publication Number WO/1995/026467
Publication Date 05.10.1995
International Application No. PCT/SI1995/000008
International Filing Date 28.03.1995
IPC
F02K 9/42 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
9Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
42using liquid or gaseous propellants
F02K 9/44 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
9Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
42using liquid or gaseous propellants
44Feeding propellants
F02K 9/64 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
9Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
42using liquid or gaseous propellants
60Constructional parts; Details
62Combustion or thrust chambers
64having cooling arrangements
CPC
F02K 9/425
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
9Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
42using liquid or gaseous propellants
425propellants
F02K 9/44
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
9Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
42using liquid or gaseous propellants
44Feeding propellants
F02K 9/64
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
9Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
42using liquid or gaseous propellants
60Constructional parts; Details
62Combustion or thrust chambers
64having cooling arrangements
F05D 2260/205
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2260Function
20Heat transfer, e.g. cooling
205Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
F05D 2260/232
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2260Function
20Heat transfer, e.g. cooling
232characterized by the cooling medium
Applicants
  • URBAN, Igor [SI]/[SI]
Inventors
  • URBAN, Igor
Agents
  • PIPAN, Marjan
Priority Data
P-940015429.03.1994SI
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) BIPROPELLANT ROCKET MOTOR
(FR) MOTEUR A REACTION A DEUX COMBUSTIBLES
Abstract
(EN)
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.
(FR)
Moteur à réaction à combustible synthétique pour fusée, fonctionnant à l'aide de combustibles à base de composés labiles qui ne peuvent s'utiliser comme combustible que s'ils ont préalablement subi une synthèse ou un traitement. Ce moteur à réaction à combustible synthétique pour fusée comporte deux composés de synthèse stockés dans des réservoirs (1, 2) indépendants et destinés à se réunir dans une préchambre et à entrer en réaction dans une chambre de combustion (4). Les gaz ainsi produits créent la poussée nécessaire.
Also published as
Latest bibliographic data on file with the International Bureau