Rocket Propulsion Systems, and Related Methods
    2.
    发明申请
    Rocket Propulsion Systems, and Related Methods 审中-公开
    火箭推进系统及相关方法

    公开(公告)号:US20140182265A1

    公开(公告)日:2014-07-03

    申请号:US13733502

    申请日:2013-01-03

    Applicant: Jordin Kare

    Inventor: Jordin Kare

    CPC classification number: F02K9/44

    Abstract: In an aspect of the invention, a system for rocket propulsion includes a heater operable to generate thermal energy from energy supplied from a non-chemical energy source, and to supply the thermal energy to a non-cryogenic fuel to thermally decompose the fuel into components that include at least a first component and a second component. The rocket propulsion system also includes a combustion chamber and a nozzle. The combustion chamber is operable to receive an oxidizer and at least a portion of the thermally decomposed fuel, and allow the two to combust. The nozzle generates thrust by directing the products of the combustion out of the system.

    Abstract translation: 在本发明的一个方面,一种用于火箭推进的系统包括可操作以从由非化学能源供应的能量产生热能的加热器,以及将热能提供给非低温燃料以将燃料热分解成部件 其包括至少第一组分和第二组分。 火箭推进系统还包括燃烧室和喷嘴。 燃烧室可操作以接收氧化剂和至少一部分热分解燃料,并允许两者燃烧。 喷嘴通过将燃烧产物引导出系统来产生推力。

    Rocket Propulsion Systems, and Related Methods
    3.
    发明申请
    Rocket Propulsion Systems, and Related Methods 审中-公开
    火箭推进系统及相关方法

    公开(公告)号:US20130199155A1

    公开(公告)日:2013-08-08

    申请号:US13733100

    申请日:2013-01-03

    Applicant: Jordin Kare

    Inventor: Jordin Kare

    CPC classification number: F02K9/00 F02K9/42

    Abstract: In an aspect of the invention, a system for rocket propulsion includes a heater operable to generate thermal energy from energy supplied from a non-chemical energy source, and to supply the thermal energy to a non-cryogenic fuel to thermally decompose the fuel into components that include at least a first component and a second component. The rocket propulsion system also includes a combustion chamber and a nozzle. The combustion chamber is operable to receive an oxidizer and at least a portion of the thermally decomposed fuel, and allow the two to combust. The nozzle generates thrust by directing the products of the combustion out of the system.

    Abstract translation: 在本发明的一个方面,一种用于火箭推进的系统包括可操作以从由非化学能源供应的能量产生热能的加热器,以及将热能提供给非低温燃料以将燃料热分解成部件 其包括至少第一组分和第二组分。 火箭推进系统还包括燃烧室和喷嘴。 燃烧室可操作以接收氧化剂和至少一部分热分解燃料,并允许两者燃烧。 喷嘴通过将燃烧产物引导出系统来产生推力。

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