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    DISPOSITIF DE PROPULSION HYBRIDE ANAÉROBIE À CARBURANT PRÉSENTE SOUS FORME DE SOLIDES DIVISÉS
    3.
    发明公开
    DISPOSITIF DE PROPULSION HYBRIDE ANAÉROBIE À CARBURANT PRÉSENTE SOUS FORME DE SOLIDES DIVISÉS 有权
    随着燃油厌氧混合动力驱动装置，分固体形式

    公开(公告)号：EP2895726A1

    公开(公告)日：2015-07-22

    申请号：EP13759751.4

    申请日：2013-09-10

    申请人： Airbus Defence and Space SAS

    发明人： FIGUS, Christophe

    IPC分类号： F02K9/10 ,  F02K9/72 ,  F02K9/94

    CPC分类号： F02K9/72 ,  F02K9/10 ,  F02K9/94 ,  F05D2300/501 ,  F05D2300/514

    摘要： The invention relates to an anaerobic propulsion device of hybrid type, said propulsion device comprising a combustion chamber (21) into which an oxidant is injected to come into contact with a fuel, said chamber (21) comprising an orifice (notably a nozzle) for the ejection of the combustion gases, characterized in that the fuel takes the form of solids divided into granules (typically grains, powder or beads). The propulsion device comprises a segregation device (22) arranged between a reservoir (27) for granules (23) of solid fuel, and a combustion chamber (21), the segregation device (22) being designed to prevent granules (23) of fuel in solid form from passing between the reservoir (27) and the combustion chamber (21), but comprising orifices allowing the passage of fuel, once this fuel has become pasty, liquid or vaporized.

    UNITIZED HYBRID ROCKET SYSTEM
    5.
    发明公开
    UNITIZED HYBRID ROCKET SYSTEM 有权
    MODULARISIERTES HYBRIDRAKETESYSTEM

    公开(公告)号：EP1608863A2

    公开(公告)日：2005-12-28

    申请号：EP04749523.9

    申请日：2004-03-29

    申请人： Mojave Aerospace Ventures, Llc

    发明人： RUTAN, Elbert, L.

    IPC分类号： F02K9/72

    CPC分类号： B64G1/404 ,  B64G1/14 ,  F02K9/32 ,  F02K9/34 ,  F02K9/343 ,  F02K9/60 ,  F02K9/605 ,  F02K9/72

    摘要： The hybrid rocket system of this invention is characterized by use of an oxidizer tank having a cylindrical midsection surrounded by a skirt and bonded thereto by a layer of elastomeric adhesive. The skirt outer surface is in turn adhesively secured to a spacecraft inner surface. An elongated solid-fuel motor case is mechanically rigidly secured to a central rear surface of the tank, and the case terminates in a throat and nozzle. The elastomeric-adhesive bonding of tank to skirt, and rigid adhesion of skirt to spacecraft forms the sole support for the rocket system, and separate support for the motor case is not required.

    UNITIZED HYBRID ROCKET SYSTEM
    8.
    发明授权
    UNITIZED HYBRID ROCKET SYSTEM 有权
    模块化混合火箭系统

    公开(公告)号：EP1608863B1

    公开(公告)日：2012-06-20

    申请号：EP04749523.9

    申请日：2004-03-29

    申请人： Mojave Aerospace Ventures, Llc

    发明人： RUTAN, Elbert, L.

    IPC分类号： B64G1/14 ,  F02K9/60 ,  F02K9/72

    CPC分类号： B64G1/404 ,  B64G1/14 ,  F02K9/32 ,  F02K9/34 ,  F02K9/343 ,  F02K9/60 ,  F02K9/605 ,  F02K9/72

    摘要： The hybrid rocket system of this invention is characterized by use of an oxidizer tank having a cylindrical midsection surrounded by a skirt and bonded thereto by a layer of elastomeric adhesive. The skirt outer surface is in turn adhesively secured to a spacecraft inner surface. An elongated solid-fuel motor case is mechanically rigidly secured to a central rear surface of the tank, and the case terminates in a throat and nozzle. The elastomeric-adhesive bonding of tank to skirt, and rigid adhesion of skirt to spacecraft forms the sole support for the rocket system, and separate support for the motor case is not required.

    UNITIZED HYBRID ROCKET SYSTEM
    10.
    发明公开
    UNITIZED HYBRID ROCKET SYSTEM 有权
    模块化混合火箭系统

    公开(公告)号：EP1608863A4

    公开(公告)日：2008-04-16

    申请号：EP04749523

    申请日：2004-03-29

    申请人： MOJAVE AEROSPACE VENTURES LLC

    发明人： RUTAN ELBERT L

    IPC分类号： B64G1/14 ,  F02K9/60 ,  F02K9/72

    CPC分类号： B64G1/404 ,  B64G1/14 ,  F02K9/32 ,  F02K9/34 ,  F02K9/343 ,  F02K9/60 ,  F02K9/605 ,  F02K9/72

    摘要： The hybrid rocket system of this invention is characterized by use of an oxidizer tank having a cylindrical midsection surrounded by a skirt and bonded thereto by a layer of elastomeric adhesive. The skirt outer surface is in turn adhesively secured to a spacecraft inner surface. An elongated solid-fuel motor case is mechanically rigidly secured to a central rear surface of the tank, and the case terminates in a throat and nozzle. The elastomeric-adhesive bonding of tank to skirt, and rigid adhesion of skirt to spacecraft forms the sole support for the rocket system, and separate support for the motor case is not required.