-
公开(公告)号：US20170283095A1
公开(公告)日：2017-10-05
申请号：US15091008
申请日：2016-04-05
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
CPC classification number: B64G1/403 , B33Y70/00 , B33Y80/00 , B64G1/10 , B64G1/26 , F02K9/80 , F02K99/00 , F05D2210/20 , F05D2230/31
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.
-
公开(公告)号：US20170284339A1
公开(公告)日：2017-10-05
申请号：US15091245
申请日：2016-04-05
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
IPC: F02K9/28
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.
-
Patent Agency Ranking
公开(公告)号：US20160352864A1
公开(公告)日：2016-12-01
申请号：US14725239
申请日：2015-05-29
Applicant: Raytheon Company
Inventor： Jared D. Stallings , Jared B. Dorny , Michael A. Young , Michael P. Highfill , Rob J. Lawrence
IPC: H04L29/08
CPC classification number: H04L67/34 , H04L67/125 , H04L67/141
Abstract: There is a mission management system includes core software modules instantiable, configurable, and deployable at runtime to complete a mission objective. The system also includes asset platforms directable to complete the mission objective or another mission objective. An operational node is further included for instantiating and configuring the core software modules at runtime to direct the asset platforms to complete the mission objective or the another mission objective. The asset platforms are connectable to establish a session with the operational node to enable the direction. The configured software modules are migratable between the operational node and the asset platforms at runtime. A computer-readable medium is active across the system to provide architecture and processor-executable instructions for the instantiation, configuration, and deployment of software modules.
Abstract translation: 任务管理系统包括可在运行时实例化，可配置和部署的核心软件模块，以完成任务目标。 该系统还包括可以完成任务目标或另一个任务目标的资产平台。 还包括运行节点，用于在运行时实例化和配置核心软件模块，以指导资产平台完成任务目标或另一个任务目标。 资产平台可连接以与运营节点建立会话以实现方向。 配置的软件模块可以在运行时在运行节点和资产平台之间迁移。 计算机可读介质在系统中是有效的，以提供用于软件模块的实例化，配置和部署的架构和处理器可执行指令。
-
公开(公告)号：US11174048B2
公开(公告)日：2021-11-16
申请号：US16266520
申请日：2019-02-04
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
IPC: B64G1/40 , F02K9/24 , F02K9/95 , B33Y80/00 , B64G1/26 , F02K9/80 , B64G1/10 , F02K99/00 , F02K9/94 , B33Y70/00
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.
-
公开(公告)号：US20200024003A1
公开(公告)日：2020-01-23
申请号：US16266520
申请日：2019-02-04
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
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.
-
公开(公告)号：US10220966B2
公开(公告)日：2019-03-05
申请号：US15091008
申请日：2016-04-05
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
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.
-
公开(公告)号：US10110703B2
公开(公告)日：2018-10-23
申请号：US14725239
申请日：2015-05-29
Applicant: Raytheon Company
Inventor： Jared D. Stallings , Jared B. Dorny , Michael A. Young , Michael P. Highfill , Rob J. Lawrence
Abstract: There is a mission management system includes core software modules instantiable, configurable, and deployable at runtime to complete a mission objective. The system also includes asset platforms directable to complete the mission objective or another mission objective. An operational node is further included for instantiating and configuring the core software modules at runtime to direct the asset platforms to complete the mission objective or the another mission objective. The asset platforms are connectable to establish a session with the operational node to enable the direction. The configured software modules are migratable between the operational node and the asset platforms at runtime. A computer-readable medium is active across the system to provide architecture and processor-executable instructions for the instantiation, configuration, and deployment of software modules.
-
-
-
-
-
-
Search Results
7
records
(took 0.012 seconds)
