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公开(公告)号：WO2017176311A1
公开(公告)日：2017-10-12
申请号：PCT/US2016/056387
申请日：2016-10-11
Applicant: RAYTHEON COMPANY
Inventor： KOEHLER, Frederick B. , DANFORTH, Jeremy C. , LYMAN, Ward D. , LANGHENRY, Mark T. , SUMMERS, Matt H. , PONTIUS, Paul E. , PAPE, Brian M. , STALLINGS, Jared D. , VILLARREAL, James K. , VILLARREAL, Thomas
Abstract: A thruster includes multiple segments of electrically-operated propellant, electrodes for igniting one or a few of the electrically-operated propellant segments at a time, and a propellant feeder for moving further propellant segments into engagement with the electrodes. The segments may be configured to provide equal increments of thrust, or different amounts of thrust. The segments may each include an electrically-operated propellant material surrounded by a sealing material, so as to keep the propellant material away from moisture and other contaminants (and/or the vacuum of space) before each individual segment is to be used. The thruster may be included in any of a variety of flight vehicles, for example in a small satellite such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
Abstract translation: 推进器包括多个电动推进剂段，用于一次点燃一个或几个电动推进剂段的电极，以及推进剂供给器，用于将另外的推进剂段移动到与 电极。 这些段可以被配置成提供相等的推力增量或不同的推力量。 这些区段可以各自包括由密封材料围绕的电操作推进剂材料，以便在每个单独的区段将被使用之前使推进剂材料远离湿气和其他污染物（和/或空间的真空）。 推进器可以包括在各种飞行器中的任何一种中，例如在诸如CubeSat卫星的小卫星中，例如具有大约1升的体积和不大于大约1.33kg的质量。
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公开(公告)号：EP3778404A1
公开(公告)日：2021-02-17
申请号：EP20176085.7
申请日：2016-10-11
Applicant: Raytheon Company
Inventor： KOEHLER, Frederick B. , DANFORTH, Jeremy C. , LYMAN, Ward D. , LANGHENRY, Mark T. , SUMMERS, Matt H. , PONTIUS, Paul E. , PAPE, Brian M. , STALLINGS, Jared D. , VILLARREAL, James K. , VILLARREAL, Thomas
Abstract: A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
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公开(公告)号：EP3440332A1
公开(公告)日：2019-02-13
申请号：EP16788851.0
申请日：2016-10-11
Applicant: Raytheon Company
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