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公开(公告)号：US06901740B2
公开(公告)日：2005-06-07
申请号：US10436140
申请日：2003-05-13
申请人： Max Calabro
发明人： Max Calabro
CPC分类号： F02K9/976 , F05D2240/1281
摘要： The pointed end of a central spike, used in an engine of a space launcher, may have a deformable structure that can adopt either a folded position or a deployed position.
摘要翻译： 在空间发射器的发动机中使用的中心尖头的尖端可以具有可以采用折叠位置或展开位置的可变形结构。
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2.发明授权Solid propellant charge for a propulsion unit and propulsion unit equipped with such a charge 失效用于推进装置的固体推进剂装置和装有这种装料的推进装置
公开(公告)号：US6148610A
公开(公告)日：2000-11-21
申请号：US99067
申请日：1998-06-16
申请人： Max Calabro , Jean Thepenier
发明人： Max Calabro , Jean Thepenier
摘要： A solid propellant charge for a propulsion unit (1). The latter includes a casing (2) containing the solid propellant charge (3), in the form of an elongated body having a longitudinal axis (X--X), which charge (3) has, over part of its longitudinal extent, a propellant charge profile (4) of large combustion area and is subdivided, along the longitudinal axis (X--X), into at least two segments abutting one another with their respective mutually confronting faces. The propulsion unit furthermore includes a nozzle (5) and means (6) for igniting said charge. The propellant charge profile (4) of large combustion area is provided in that part of the propellant charge (3) which is intermediate along the longitudinal axis (X--X).
摘要翻译： 用于推进单元（1）的固体推进剂装药。 后者包括壳体（2），其包含具有纵向轴线（XX）的细长主体形式的固体推进剂装料（3），所述纵向轴线（XX）在其纵向范围的一部分上具有推进剂装料曲线 （4），并且沿着纵轴（XX）被细分成至少两个彼此相对的相互面对的部分。 推进单元还包括用于点燃所述电荷的喷嘴（5）和装置（6）。 在沿着纵向轴线（X-X）中间的推进剂装料（3）的那部分提供了大型燃烧区域的推进剂装料曲线（4）。
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公开(公告)号：US07743601B2
公开(公告)日：2010-06-29
申请号：US11575982
申请日：2005-10-13
申请人： Max Calabro
发明人： Max Calabro
IPC分类号： F03H1/00
摘要： The invention concerns an electrothermal thruster (1) comprising a heating section (20) through which a propellant fluid (4) is intended to pass so that it is heated before it is exhausted, the heating section (20) being supplied by an electric power source (22). According to the invention, the electric power source (22) comprises photovoltaic cells (24) mounted on the heat exchanger (10) through which the propellant fluid (4) is intended to pass before it reaches the heating section (20).Application to the area of spacecraft propulsion.
摘要翻译： 本发明涉及一种电热推进器（1），其包括加热部分（20），推进剂流体（4）将通过该加热部分通过，使得其在排出之前被加热，加热部分（20）由电力供应 来源（22）。 根据本发明，电源（22）包括安装在热交换器（10）上的光伏电池（24），推进剂流体（4）在其到达加热部分（20）之前通过该电池传递。 应用于航天器推进领域。
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公开(公告)号：US06915627B2
公开(公告)日：2005-07-12
申请号：US10476568
申请日：2003-02-27
申请人： Max Calabro
发明人： Max Calabro
CPC分类号： F02K9/64 , F02K9/52 , F02K9/97 , F05D2240/1281
摘要： The invention concerns a rocket engine wherein the combustion chamber includes at least one first monolithic component made of a thermostructural composite material comprising a porous wall through which the fuel is introduced in the core of the combustion chamber. A small part of the fuel is directed towards the neck for it to be cooled.
摘要翻译： 本发明涉及一种火箭发动机，其中燃烧室包括由包含多孔壁的热结构复合材料制成的至少一个第一整体部件，通过该多孔壁将燃料引入燃烧室的核心中。 一小部分燃料被引导到颈部以使其冷却。
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公开(公告)号：US20070295009A1
公开(公告)日：2007-12-27
申请号：US11575982
申请日：2005-10-13
申请人： Max Calabro
发明人： Max Calabro
IPC分类号： B64G1/44
摘要： An electrothermal thruster including a heating section through which a propellant fluid is intended to pass to be heated before being exhausted, the heating section being supplied by an electric power source The electric power source includes photovoltaic cells mounted on the heat exchanger through which the propellant fluid is intended to pass before reaching the heating section. Such a device may, for example, find application in the area of spacecraft propulsion.
摘要翻译： 一种电热推进器，其包括加热部分，推进剂流体在该部分被排放之前要被加热，加热部分由电源供应。电源包括安装在热交换器上的光伏电池，推进剂流体 打算在到达加热段之前通过。 例如，这种装置可以在航天器推进领域中得到应用。
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公开(公告)号：US4477025A
公开(公告)日：1984-10-16
申请号：US957309
申请日：1978-11-02
申请人： Max Calabro , Herve Girard , Alain Le Corre
发明人： Max Calabro , Herve Girard , Alain Le Corre
CPC分类号： F02K9/84
摘要： A hot nozzle formed by a single unitary element formed of a three-dimensional weaving of a carbon substrate. This element is girdled by two thermal insulation rings--which provide suspension and orientation control for the nozzle. Application to nozzles for solid propellant propulsion units.
摘要翻译： 由由碳基板的三维编织形成的单个整体元件形成的热喷嘴。 该元件由两个隔热环组成，为喷嘴提供悬挂和取向控制。 适用于固体推进剂推进装置的喷嘴。
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