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公开(公告)号：US12103713B1
公开(公告)日：2024-10-01
申请号：US16049942
申请日：2018-07-31
发明人： Nicholas Dallmann , James Wren , Michael Proicou , Hannah Mohr , Jerry Delapp , John Martinez , Daniel Seitz , Paul Stein , Adam Warniment
摘要： An attitude determination and control system (ADCS) may include relatively large momentum wheels (i.e., reaction wheels) for improved momentum storage and magnetic torque rods that enable low power sun pointing and dissipate angular momentum imparted during deployment or by differential drag on the space vehicle. The momentum wheels, magnetic torque rods, or both may be algorithmically selected and driven to perform various maneuvers.
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公开(公告)号：US20180273212A1
公开(公告)日：2018-09-27
申请号：US15760540
申请日：2016-07-18
发明人： Yu ZHU , Anlin CHEN , Ming ZHANG , Kaiming YANG , Rong CHENG
CPC分类号： B64G1/285 , G01C19/24 , H02K5/1282 , H02K16/00 , H02K16/04 , H02K41/031 , H02K2201/18
摘要： Disclosed is a magnetic-fluid momentum sphere, which is used for satellite attitude adjustment. The magnetic-fluid momentum sphere comprises stators and a spherical shell. The stators are classified into three groups, axes of the three groups of stators are orthogonal to each other, each group comprises two stators arranged symmetrically about the center of the spherical shell, and the inner surfaces of the stators are spherical surfaces. The spherical shell is formed by combining two hemispherical shells, the material of the spherical shell is a non-ferromagnetic material, the inner surfaces of the stators closely adhere to the outer surface of the spherical shell, there is no relative movement between the spherical shell and the inner surfaces of the stators, and the spherical shell is filled with magnetic fluid. The magnetic-fluid momentum sphere achieves a small size and mass, low costs, and small coupling among the axes.
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公开(公告)号：US09809328B2
公开(公告)日：2017-11-07
申请号：US14644425
申请日：2015-03-11
CPC分类号： B64G1/365 , B64G1/26 , B64G1/281 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/288 , B64G1/32 , B64G1/34 , B64G1/36 , B64G1/363 , B64G1/366 , B64G1/407 , B64G2001/245
摘要： Described herein are systems and methods for attitude determination using infrared Earth horizon sensors (EHSs) with Gaussian response characteristics. Attitude information is acquired by detecting Earth's infrared electromagnetic radiation and, subsequently, determining the region obscured by Earth in the sensors' fields of view to compute a nadir vector estimation in the spacecraft's body frame. The method can be applied when two sensors, each with known and distinct pointing directions, detect the horizon, which is defined as having their fields of view partially obscured by Earth. The method can be implemented compactly to provide high-accuracy attitude within small spacecraft, such as CubeSat-based satellites.
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公开(公告)号：US20170225805A1
公开(公告)日：2017-08-10
申请号：US15016204
申请日：2016-02-04
申请人： The Boeing Company
发明人： Qinghong W. Wang , Alexander Jacob Sobel , Gary Lemke , Timothy Lui , Kangsik Lee , Glenn N. Caplin , Troy Allen Fontana
CPC分类号： B64G1/24 , B64G1/007 , B64G1/26 , B64G1/281 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/36 , B64G1/405 , B64G2001/245
摘要： Apparatus and methods for controlling a spacecraft for a transfer orbit. The spacecraft includes a momentum subsystem that stores angular momentum relative to a center of mass of the spacecraft, and a propulsion subsystem that includes electric thrusters. A controller identifies a target spin axis for the spacecraft, determines gimbal angles for electric thruster(s) that so that thrust forces from the electric thrusters are parallel to the target spin axis, and initiates a burn of the electric thruster(s) at the gimbal angles. The controller controls the momentum subsystem to compensate for a thruster torque produced by the burn of the electric thrusters. The momentum subsystem is able to produce a target angular momentum about the center of mass, where a coupling between the target angular momentum and an angular velocity of the spacecraft creates an offset torque to counteract the thruster torque.
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公开(公告)号：US09551994B2
公开(公告)日：2017-01-24
申请号：US14739563
申请日：2015-06-15
申请人： The Boeing Company
CPC分类号： G05D1/0883 , B64G1/00 , B64G1/283 , B64G1/285 , B64G2001/245
摘要： A dual stage vehicle attitude control system includes a first attitude control module having at least two momentum wheels arranged to provide zero momentum vehicle attitude control, each momentum wheel comprises a limited travel two axis gimbal that pivots the momentum wheel along two of the three axes of the vehicle, a second attitude control module having reaction wheels arranged in a pyramid configuration to provide vehicle attitude control along at least one control axis that is common with a control axis of the at least two momentum wheels, and a controller connected to the first attitude control module and the second attitude control module, the controller being configured to coordinate actuation of the first attitude control module and the second attitude control module to rotate the vehicle in at least one of three axes of a vehicle.
摘要翻译： 双级车辆姿态控制系统包括具有布置成提供零动量车辆姿态控制的至少两个动量轮的第一姿态控制模块，每个动量轮包括有限行程双轴万向架，其将动量轮沿着三个轴的两个轴线 所述车辆具有第二姿态控制模块，所述第二姿势控制模块具有以锥体结构布置的反作用轮，以沿着与所述至少两个动量轮的控制轴共同的至少一个控制轴提供车辆姿态控制;以及控制器，其连接到所述第一姿态 控制模块和第二姿势控制模块，所述控制器被配置为协调所述第一姿态控制模块和所述第二姿态控制模块的致动，以使车辆在车辆的三个轴线中的至少一个轴线上旋转。
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6.发明申请公开(公告)号：US20160236801A1
公开(公告)日：2016-08-18
申请号：US14620617
申请日：2015-02-12
申请人： NOVAWURKS, INC.
发明人： TALBOT JAEGER
CPC分类号： B64G1/425 , B64G1/10 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/402 , B64G1/428 , B64G1/44 , B64G1/64 , B64G2001/1092
摘要： An improved spacecraft actuator wheel is provided which can be operated as a momentum wheel, a reaction wheel or a gimbal. The actuator wheel has a central cavity. One or more battery modules are located within the actuator wheel's central cavity. The battery modules supply power to one or more electronic components affixed to the actuator wheel or mounted on the spacecraft frame via an electrical harness. In addition, the actuator wheel's central cavity is pressurizeable for storing spacecraft propellant which can be controllably diverted to the spacecraft's thrusters through conduits and flow valves.
摘要翻译： 提供了一种改进的航天器致动器轮，其可以作为动量轮，反作用轮或万向节来操作。 致动器轮具有中心腔。 一个或多个电池模块位于致动器轮的中心腔内。 电池模块通过电气线束向固定到致动器轮上的一个或多个电子部件供电或安装在航天器框架上。 此外，执行器轮的中心空腔是可加压的，用于存储航天器推进剂，其可以通过导管和流量阀被可控地转移到航天器的推进器。
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公开(公告)号：US20150166200A1
公开(公告)日：2015-06-18
申请号：US14414852
申请日：2013-07-24
发明人： Dae-Kwan Kim , Hyungjoo Yoon , Wooyong Kang , Yong Bok Kim , Hong-Taek Choi
CPC分类号： B64G1/285 , B64G1/24 , B64G1/32 , G05D1/0808 , H02K5/173 , H02K5/1737 , H02K7/088 , H02K16/04 , H02K17/16 , H02K41/025 , H02K2201/18
摘要： Provided is a three-dimensional rigid ball driving system including: a support frame having a polyhedral shape; a rigid ball positioned at the center of an inner portion of the support frame; a plurality of ball bearings installed at corners of inner sides of the support frame, respectively, and contacting a surface of the rigid ball; and a plurality of electromagnets disposed around the ball bearings and generating magnetic fields to rotate the rigid ball; and a controller controlling the electromagnets to control a rotation direction and a rotation speed of the rigid ball.
摘要翻译： 本发明提供一种三维刚性球驱动系统，包括：具有多面体形状的支撑框架; 位于所述支撑框架的内部的中心的刚性球; 多个球轴承分别安装在支撑架的内侧的拐角处，并接触刚性球的表面; 以及设置在所述球轴承周围并产生磁场以使所述刚性球旋转的多个电磁体; 以及控制电磁体以控制刚性球的旋转方向和旋转速度的控制器。
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8.发明授权公开(公告)号：US08873168B2
公开(公告)日：2014-10-28
申请号：US13330602
申请日：2011-12-19
申请人： Bradley G. Boone
发明人： Bradley G. Boone
CPC分类号： B64G1/52 , B64G1/222 , B64G1/24 , B64G1/26 , B64G1/285 , B64G1/32 , B64G1/361 , B64G1/363 , B64G1/44 , B64G1/66 , F24S23/31 , G02B3/08
摘要： A system for concentrating solar radiation onto a space debris object to vaporize includes a focusing system, an object tracking system and a positioning system. The focusing system has a total focal length fT, and includes a first focusing device and a second focusing device. The first focusing devices change from a compact state to a deployed state, and the compact surface area is less than the deployed surface area. The object tracking system determines the location of the object. The positioning system orients the focusing system such that solar radiation focuses on the space debris object.
摘要翻译： 用于将太阳辐射聚焦到空间碎片物体上以蒸发的系统包括聚焦系统，物体跟踪系统和定位系统。 聚焦系统具有总焦距fT，并且包括第一聚焦装置和第二聚焦装置。 第一聚焦装置从紧凑状态变为展开状态，并且紧凑的表面积小于展开的表面积。 对象跟踪系统确定对象的位置。 定位系统定向聚焦系统，使得太阳辐射聚焦在空间碎片物体上。
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9.发明授权公开(公告)号：US08640994B1
公开(公告)日：2014-02-04
申请号：US12891094
申请日：2010-09-27
CPC分类号： B64G1/286 , B64G1/1021 , B64G1/105 , B64G1/281 , B64G1/285 , B64G1/36 , B64G1/361 , B64G1/44 , B64G1/50 , B64G1/66 , B64G2001/1042 , B64G2001/1064
摘要： A system, method, and apparatus are disclosed for agile dedicated spacecrafts for spinning microwave imagers and sounders. In one or more embodiments, the system, method, and apparatus involve an agile, zero net-momentum, spinning space vehicle, which includes a body and an instrument package. In one or more embodiments, the instrument package is mounted directly onto the body such that the space vehicle can point the instrument package not only along the space vehicle's orbital velocity vector, but in any direction within the space vehicle's field of regard. The space vehicle's spin axis is aligned with the instrument package's scan axis. The space vehicle experiences zero net-momentum on orbit by including a counter-rotating momentum storage device. In one or more embodiments, the instrument package is a scanning microwave imaging/sounding instrument, which is utilized as an Earth climate and weather sensor.
摘要翻译： 公开了用于纺丝微波成像器和测深仪的敏捷专用航天器的系统，方法和装置。 在一个或多个实施例中，系统，方法和装置涉及包括主体和仪器包装的敏捷零净动量旋转空间车辆。 在一个或多个实施例中，仪器包被直接安装在身体上，使得空间车辆不仅可以沿着太空车的轨道速度矢量，而且在空间车辆的视野范围内的任何方向上指向仪器包装。 航天器的旋转轴与仪器组件的扫描轴对齐。 航天器通过包括反向旋转动量存储装置在轨道上经历零净动量。 在一个或多个实施例中，仪器包是用作地球气候和天气传感器的扫描微波成像/探测仪器。
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10.发明授权公开(公告)号：US08439312B2
公开(公告)日：2013-05-14
申请号：US12141832
申请日：2008-06-18
摘要： The present system and methods enable simultaneous momentum dumping and orbit control of a spacecraft, such as a geostationary satellite. Control equations according to the present system and methods generate accurate station-keeping commands quickly and efficiently, reducing the number of maneuvers needed to maintain station and allowing station-keeping maneuvers to be performed with a single burn. Additional benefits include increased efficiency in propellant usage, and extension of the satellite's lifespan. The present system and methods also enable tighter orbit control, reduction in transients and number of station-keeping thrusters aboard the satellite. The present methods also eliminate the need for the thrusters to point through the center of mass of the satellite, which in turn reduces the need for dedicated station-keeping thrusters. The present methods also facilitate completely autonomous orbit control and angular momentum control using.
摘要翻译： 目前的系统和方法可以实现对诸如地球静止卫星之类的航天器的动量倾倒和轨道控制。 根据本系统和方法的控制方程，可以快速有效地产生精确的站保持命令，减少维护站所需的机动次数，并允许在单次燃烧时进行站点保持机动。 额外的好处包括提高推进剂使用效率，延长卫星使用寿命。 目前的系统和方法还使轨道控制更加紧凑，减少了卫星上的驻车推进器的瞬变和数量。 目前的方法也消除了推进器指向卫星质量中心的需要，从而减少了专用的驻车推进器的需要。 本方法还有助于完全自主的轨道控制和角动量控制。
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