-
公开(公告)号：US20130047578A1
公开(公告)日：2013-02-28
申请号：US13223041
申请日：2011-08-31
Applicant: Nicolas Claude Gascon , Mark Antony Cappelli , Ronald W. King
Inventor： Nicolas Claude Gascon , Mark Antony Cappelli , Ronald W. King
CPC classification number: B64G1/402 , B64G1/404 , F02K9/72 , F02K9/94 , F03H1/00 , F03H1/0006 , F03H1/0012 , F03H1/0043 , F03H1/005 , F03H1/0062 , F03H1/0068 , F03H1/0075
Abstract: A spacecraft propulsion system has at least one chemical thruster, at least one electric thruster, a propellant supply arrangement that stores a propellant and a propellant conditioning arrangement configured to convert propellant into chemical species in a thermodynamic phase that can be readily ionized. The propellant is commonly supplied from the propellant storage device to each of the chemical thruster and the electric thruster. The chemical thruster has a gas generator and a high thrust accelerator; the electric thruster has a plasma generator and a high specific impulse accelerator. The propellant supply arrangement is configured to control flow of the propellant from the propellant supply arrangement to the gas generator and the propellant conditioning arrangement, and a first flow path connects propellant supply arrangement with the gas generator, and a second flow path connects propellant supply arrangement with the plasma generator.
Abstract translation: 航天器推进系统具有至少一个化学推进器，至少一个电推进器，推进剂供应装置，其存储推进剂和推进剂调节装置，所述推进剂调节装置构造成将推进剂转化为能容易地电离的热力学相中的化学物质。 推进剂通常从推进剂储存装置提供给每个化学推进器和电推进器。 化学推进器具有气体发生器和高推力加速器; 电推进器具有等离子体发生器和高比冲速加速器。 推进剂供应装置被配置为控制推进剂从推进剂供应装置到气体发生器和推进剂调节装置的流动，并且第一流动路径将推进剂供应装置与气体发生器连接，第二流动路径连接推进剂供应装置 与等离子发生器。
-
公开(公告)号：US08365512B2
公开(公告)日：2013-02-05
申请号：US12527916
申请日：2008-02-21
Applicant: Dominique Valentian
Inventor： Dominique Valentian
IPC: F03H1/00
Abstract: An emitter for an ion thruster. The emitter is a field-effect emitter for a field emission electric propulsion or colloid thruster. The field-effect emitter has a first and second portions defining an internal reservoir for supplying a liquid metal or a conducting ionic liquid and has a slit connecting the internal reservoir to an exit orifice.
Abstract translation: 离子推进器的发射器。 发射极是用于场发射电推进器或胶体推进器的场效应发射器。 场效应发射器具有限定用于供应液体金属或导电离子液体的内部储存器的第一和第二部分，并且具有将内部储存器连接到出口孔的狭缝。
-
公开(公告)号：US09145216B2
公开(公告)日：2015-09-29
申请号：US13223041
申请日：2011-08-31
Applicant: Nicolas Claude Gascon , Mark Antony Cappelli , Ronald W. King
Inventor： Nicolas Claude Gascon , Mark Antony Cappelli , Ronald W. King
CPC classification number: B64G1/402 , B64G1/404 , F02K9/72 , F02K9/94 , F03H1/00 , F03H1/0006 , F03H1/0012 , F03H1/0043 , F03H1/005 , F03H1/0062 , F03H1/0068 , F03H1/0075
Abstract: A spacecraft propulsion system has at least one chemical thruster, at least one electric thruster, a propellant supply arrangement that stores a propellant and a propellant conditioning arrangement configured to convert propellant into chemical species in a thermodynamic phase that can be readily ionized. The propellant is commonly supplied from the propellant storage device to each of the chemical thruster and the electric thruster. The chemical thruster has a gas generator and a high thrust accelerator; the electric thruster has a plasma generator and a high specific impulse accelerator. The propellant supply arrangement is configured to control flow of the propellant from the propellant supply arrangement to the gas generator and the propellant conditioning arrangement, and a first flow path connects propellant supply arrangement with the gas generator, and a second flow path connects propellant supply arrangement with the plasma generator.
Abstract translation: 航天器推进系统具有至少一个化学推进器，至少一个电推进器，推进剂供应装置，其存储推进剂和推进剂调节装置，所述推进剂调节装置构造成将推进剂转化为能容易地电离的热力学相中的化学物质。 推进剂通常从推进剂储存装置提供给每个化学推进器和电推进器。 化学推进器具有气体发生器和高推力加速器; 电推进器具有等离子体发生器和高比冲速加速器。 推进剂供应装置被配置为控制推进剂从推进剂供应装置到气体发生器和推进剂调节装置的流动，并且第一流动路径将推进剂供应装置与气体发生器连接，第二流动路径连接推进剂供应装置 与等离子发生器。
-
公开(公告)号：US07204078B2
公开(公告)日：2007-04-17
申请号：US10895775
申请日：2004-07-21
Applicant: Alan B. Minick , Benjamin Goldberg
Inventor： Alan B. Minick , Benjamin Goldberg
IPC: F03H1/00
Abstract: An ion drive system for creating a propulsion force or thrust has at least one stage having an emitter and an attractor spaced from the emitter by a gap. An ionizable dielectric media is located within the gap. The drive system further has a propellant source for introducing a propellant in the vicinity of the emitter and a power source for creating a high intensity field in the vicinity of the emitter to ionize the dielectric media and a diffused field in the vicinity of the attractor to accelerate the ions away from the emitter and thereby create a propulsive force. In a preferred embodiment, the ion drive system has a plurality of stages.
Abstract translation: 用于产生推进力或推力的离子驱动系统具有至少一个级，其具有发射极和与发射极间隔开的吸引子。 可离子化介电介质位于间隙内。 驱动系统还具有用于在发射器附近引入推进剂的推进剂源和用于在发射器附近产生高强度场的电源，以将电介质和吸引子附近的扩散场离子化 将离子加速离开发射器，从而产生推进力。 在优选实施例中，离子驱动系统具有多个级。
-
公开(公告)号：US20060017004A1
公开(公告)日：2006-01-26
申请号：US10895775
申请日：2004-07-21
Applicant: Alan Minick , Benjamin Goldberg
Inventor： Alan Minick , Benjamin Goldberg
IPC: H01J27/00
Abstract: An ion drive system for creating a propulsion force or thrust has at least one stage having an emitter and an attractor spaced from the emitter by a gap. An ionizable dielectric media is located within the gap. The drive system further has a propellant source for introducing a propellant in the vicinity of the emitter and a power source for creating a high intensity field in the vicinity of the emitter to ionize the dielectric media and a diffused field in the vicinity of the attractor to accelerate the ions away from the emitter and thereby create a propulsive force. In a preferred embodiment, the ion drive system has a plurality of stages.
Abstract translation: 用于产生推进力或推力的离子驱动系统具有至少一个级，其具有发射极和与发射极间隔开的吸引子。 可离子化介电介质位于间隙内。 驱动系统还具有用于在发射器附近引入推进剂的推进剂源和用于在发射器附近产生高强度场的电源，以将电介质和吸引子附近的扩散场离子化 将离子加速离开发射器，从而产生推进力。 在优选实施例中，离子驱动系统具有多个级。
-
Patent Agency Ranking
公开(公告)号：US08453426B2
公开(公告)日：2013-06-04
申请号：US12419258
申请日：2009-04-06
Applicant: James D. Kueneman , Anton Vanderwyst
Inventor： James D. Kueneman , Anton Vanderwyst
CPC classification number: F03H1/005
Abstract: There is disclosed a field emission electric propulsion (FEEP) system including a FEEP thruster having at least one emitter and an extractor electrode, and a power supply. The power supply may provide an extractor voltage applied between the emitter and the extractor electrode. The power supply may be operable in a constant current mode in which the extractor voltage is controlled to set an ion current flowing from the emitter at a target current level.
Abstract translation: 公开了一种场致发射电推进系统（FEEP），其包括具有至少一个发射器和抽出电极的FEEP推进器和电源。 电源可以提供施加在发射器和提取器电极之间的提取器电压。 电源可以在恒定电流模式下操作，其中提取器电压被控制以将从发射器流出的离子电流设置在目标电流水平。
-
公开(公告)号：US20100018185A1
公开(公告)日：2010-01-28
申请号：US12527916
申请日：2008-02-21
Applicant: Dominique Valentian
Inventor： Dominique Valentian
Abstract: The invention relates to a field effect emitter for a field emission thruster or colloid thrusters, that comprises first and second revolution parts (110, 120) defining an inner tank (160) for supplying a conductive liquid metal or ionic liquid, and a circular slot (170) for communication between the inner tank (160) and an outlet opening (171). The first part (110) includes a polished outer face (111) and an inner face (112) made by precision-machining and having conical portions with a predetermined single slope of between 5 and 8°. The second part (120) includes an inner face (121) and an outer face (122) made by precision-machining and having conical portions with a predetermined single slope of between 5 and 8°. Metallic studs (123, 124, 125) are formed by deposition on the outer surface (122) of the inner part (120) so as to define a slot (170) thickness of between 1 and 2 micrometers, and the outer part (110) is maintained against the inner part (120) by connection means (140), a sealing and adjustment spacer (130) being provided between the outer (110) and inner (120) parts.
Abstract translation: 本发明涉及一种用于场发射推进器或胶体推进器的场效应发射器，其包括限定用于供应导电液体金属或离子液体的内槽（160）的第一和第二转动部分（110,120），以及圆形槽 （170），用于内罐（160）和出口开口（171）之间的连通。 第一部分（110）包括抛光的外表面（111）和通过精密加工制成的内表面（112），并且具有在5-8°之间的预定单斜率的锥形部分。 第二部分（120）包括通过精密加工制成的内表面（121）和外表面（122），并且具有预定的单斜率在5和8°之间的锥形部分。 通过沉积在内部部件（120）的外表面（122）上形成金属螺柱（123,124,125），以便限定1至2微米之间的狭槽（170）厚度和外部部件（110） ）通过连接装置（140）保持抵靠内部部分（120），密封和调节间隔件（130）设置在外部（110）和内部（120）部分之间。
-
8.发明授权Field-emission ion source and ion thruster apparatus comprising such sources 失效场致发射离子源和包括这种源的离子推进器装置
公开(公告)号：US4328667A
公开(公告)日：1982-05-11
申请号：US25348
申请日：1979-03-30
Applicant: Dominique R. Valentian , Cesare M. Bartoli , Heinrich A. Pfeffer , Hans-Joachim Herhudt V. Rohden , Duncan Stewart
Inventor： Dominique R. Valentian , Cesare M. Bartoli , Heinrich A. Pfeffer , Hans-Joachim Herhudt V. Rohden , Duncan Stewart
Abstract: A field-emission ion source in which, under the influence of an electric field, ions are released from a metal or metal alloy present in an enclosed space in the liquid state. The ions are emitted from this space through a very narrow slit. This slit may be straight or curved. The field-emission ion source can be used in an ion thruster apparatus comprising an emitter module, an electrode system, and a power supply unit. A plurality of emitter modules can be combined to form an ion thruster apparatus having a greater ion current output. Instead of a liquid metal as the propellant, a metal in the solid phase can be supplied to the emitter module, which metal is melted in the emitter module.
Abstract translation: 一种场致发射离子源，其中在电场的影响下，离子从处于液态的封闭空间中的金属或金属合金释放出来。 离子通过非常狭窄的狭缝从该空间发射。 该狭缝可以是直的或弯曲的。 场致发射离子源可用于包括发射器模块，电极系统和电源单元的离子推进器装置中。 多个发射器模块可以组合以形成具有更大离子电流输出的离子推进器装置。 代替液体金属作为推进剂，可以将固相中的金属供应到发射器模块，该发射器模块中的金属在发射器模块中熔化。
-
公开(公告)号：US20240263623A1
公开(公告)日：2024-08-08
申请号：US18611296
申请日：2024-03-20
Applicant: Accion Systems, Inc.
Inventor： Adam Zachar , Christy Petruczok , William Maulbetsch , Kellen Blake , Carlee Schmidt , Dakota Freeman , Bradley Kaanta , Louis Perna
IPC: F03H1/00
CPC classification number: F03H1/0043 , F03H1/005
Abstract: An electrospray emitter can include an emitter structure connected to a reservoir containing a working material in electrical communication with a first electrode and an electrode separated from an apex of the emitter structure by a distance, wherein a surface of the grid electrode proximal the emitter structure comprises at least one coating.
-
公开(公告)号：US11905936B2
公开(公告)日：2024-02-20
申请号：US17264893
申请日：2019-05-17
Applicant: ENPULSION GmbH
Inventor： Nembo Buldrini , Bernhard Seifert , Alexander Reissner
CPC classification number: F03H1/005 , B64G1/402 , B64G1/405 , F03H1/0037
Abstract: The disclosed subject matter relates to an ion thruster for thrust vectored propulsion of a spacecraft, comprising a reservoir for a propellant, an emitter having a base and, on one side of the base, at least one outlet for emitting ions of the propellant, wherein the base is connected to the reservoir for providing flow of propellant from the reservoir to said at least one outlet, and an extractor facing said one side of the emitter for extracting and accelerating the ions from the emitter, wherein the extractor is split into sectors about an axis which orthogonally runs through said one side of the emitter, wherein said sectors are electrically insulated from one another.
-
-
-
-
-
-
-
-
-
Search Results
19
records
(took 0.018 seconds)
