-
公开(公告)号：US10220965B2
公开(公告)日：2019-03-05
申请号：US15725478
申请日：2017-10-05
Applicant: Massachusetts Institute of Technology
Inventor： Tam Nguyen Thuc Nguyen , Kerri L. Cahoy , Meghan K. Quadrino
Abstract: 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.
-
公开(公告)号：US20180290769A1
公开(公告)日：2018-10-11
申请号：US15993302
申请日：2018-05-30
Applicant: Japan Aerospace Exploration Agency
Inventor： Osamu MORI , Junichiro KAWAGUCHI , Yoji SHIRASAWA , Toshihiro CHUJO , Kosuke AKATSUKA
Abstract: A torque generation system includes: a plurality of solar array panels and/or solar array panel divisions; and a torque controller configured to control an electricity generation ratio of each of the plurality of solar array panels and/or solar array panel divisions to generate torque.
-
公开(公告)号：US20180257795A1
公开(公告)日：2018-09-13
申请号：US15932669
申请日：2018-04-05
Applicant: Frank Werner Ellinghaus
Inventor： Frank Werner Ellinghaus
CPC classification number: B64G1/641 , B64G1/00 , B64G1/002 , B64G1/10 , B64G1/24 , B64G1/26 , B64G1/34 , B64G1/407 , B64G1/44 , B64G1/443 , B64G2001/643
Abstract: The PanelSat Launch System consists of PanelSat(s) and it's/their Launcher. It serves to launch one, better several satellites into space, whereby besides unfurling of the thin film solar cell panels off their rolls no further deployment is needed.PanelSats are small agile spacecraft thought especially for observation and communication services in LEO, which are using their thin film solar cell panels for both, harvesting electric energy as well as for fuel less station keeping, steering, pointing and propulsion.In contrast to conventional satellites with their 3-axis control design, PanelSats are not locked to only 3 axles and can tilt and point into several directions (depending on the number of panels).Besides Roller Reefing for fuel less attitude control PanelSats feature “Soso Steering” (switch on, switch off) which adds even better fuel less agility compared to prior art satellites.
-
公开(公告)号：US20180111706A1
公开(公告)日：2018-04-26
申请号：US15725478
申请日：2017-10-05
Applicant: Massachusetts Institute of Technology
Inventor： Tam Nguyen Thuc Nguyen , Kerri L. Cahoy , Meghan K. Quadrino
CPC classification number: 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
Abstract: 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.
-
5.发明授权Methods for reducing solar array power variations while managing the system influences of operating with off-pointed solar wings 失效减少太阳能阵列功率变化的方法，同时管理系统对偏光太阳能翅膀的操作影响
公开(公告)号：US6070833A
公开(公告)日：2000-06-06
申请号：US58058
申请日：1998-04-09
Applicant: Stephen D. Burke , Umesh S. Ketkar
Inventor： Stephen D. Burke , Umesh S. Ketkar
CPC classification number: B64G1/36 , B64G1/24 , B64G1/34 , B64G1/407 , B64G1/443 , G05D1/0883 , B64G1/26
Abstract: Solar wing positioning methods are provided which favorably reduce seasonal variation of generated power in a satellite while simultaneously managing the composite system influence that off-pointed solar wing operation imposes on the satellite. The composite system influence includes environmental torques and may also include other system influences such as wing-to-body thermal radiation, thruster plume impingement and antenna/sensor field of view encroachment. In the simplest method embodiment, the solar wings are tilted asymmetrically from a nominal position to reduce seasonal power variations and are further tilted symmetrically to generate a solar pressure torque component which, on a diurnal average basis, compensates a gravity gradient torque component that is substantially generated by the net, off-pointed configuration of the wings.
Abstract translation: 提供太阳能翼定位方法，有利于减少卫星中发电功率的季节变化，同时管理复合系统对太阳能翼翼操作对卫星的影响。 复合系统的影响包括环境转矩，还可能包括其他系统影响，如机体对身体热辐射，推进器羽流冲击和天线/传感器视野侵占。 在最简单的方法实施例中，太阳能翼从标称位置不对称地倾斜以减少季节性功率变化并进一步对称地倾斜以产生太阳能压力扭矩分量，其在日间平均的基础上补偿基本上 由网络产生，偏角配置的翅膀。
-
Patent Agency Ranking6.发明授权
公开(公告)号：US6059233A
公开(公告)日：2000-05-09
申请号：US896
申请日：1997-12-30
Applicant: Christophe Koppel , Dominique Valentian
Inventor： Christophe Koppel , Dominique Valentian
CPC classification number: B64G1/1085 , B64G1/007 , B64G1/242 , B64G1/002
Abstract: A first satellite is placed practically directly by a launcher on a first final orbit. A second satellite is placed on the same launcher is initially transferred to a highly elliptical waiting orbit whose semi-major axis points to intercept the torus formed by the sphere of influence of the moon on its orbit, and then during a maneuver at the perigee of the highly elliptical orbit, the second satellite is transferred to lunar transfer orbit. Changes in the perigee altitude and the inclination of an intermediate orbit on which the second satellite is to be found are obtained mainly by gravitational reaction in the sphere of influence of the moon, and during a last maneuver, the second satellite is placed on a final orbit having orbital parameter values that are quite different from those of the orbital parameters of the first final orbit.
Abstract translation: 第一颗卫星实际上直接由第一个最终轨道上的发射器放置。 第二颗卫星放置在同一发射器上，最初被转移到一个高度椭圆形的等待轨道上，其半长轴指向截取由月球在其轨道上的影响范围形成的环面，然后在近地点 高度椭圆轨道，第二颗卫星转移到月球转移轨道。 主要通过月球影响范围内的引力反应获得近地点高度的变化和第二颗卫星所在的中间轨道的倾斜度，而在最后一次演习中，第二颗卫星被置于最后 轨道具有与第一最终轨道的轨道参数的轨道参数值完全不同的轨道参数值。
-
公开(公告)号：US5887827A
公开(公告)日：1999-03-30
申请号：US285219
申请日：1994-08-03
Applicant: Alvin Joyner Sanders , William Edward Deeds , Mark Edward Rupright
Inventor： Alvin Joyner Sanders , William Edward Deeds , Mark Edward Rupright
CPC classification number: C30B30/08 , B64G1/105 , B64G1/24 , B64G1/28 , B64G1/34 , B64G1/46 , B64G1/66
Abstract: An apparatus and method for use thereof in the creating of a nanogravity environment substantially throughout a working volume sufficient for performing a desired operation and existing for a length of time sufficient for performing the desired operation are disclosed. Involved in the creation of the nanogravity environment are the use of an apparatus in which the mass density of the walls are distributed (either directly or by the attachment of compensating masses) so that the surface density of the mass is directly proportional to the electric charge density along the walls which would be sufficient to neutralize the interior electric field, the orbiting of the apparatus around a planetary mass, and the minimization of disruptive accelerations on the apparatus by the selective transfer of the momentum of solar photons to the apparatus.
-
8.发明授权Method for controlling the pitch attitude of a satellite by means of solar radiation pressure 失效通过太阳辐射压力控制卫星的俯仰姿态的方法
公开(公告)号：US5850992A
公开(公告)日：1998-12-22
申请号：US779509
申请日：1997-01-07
Applicant: Patrick Flament , Michel Perdu , Jean Portier , Pierre Brunet
Inventor： Patrick Flament , Michel Perdu , Jean Portier , Pierre Brunet
IPC: B64G1/24 , B64G1/26 , B64G1/28 , B64G1/32 , B64G1/34 , B64G1/36 , B64G1/40 , B64G1/44 , F03H1/00
CPC classification number: B64G1/407 , B64G1/24 , B64G1/28 , B64G1/283 , B64G1/34 , B64G1/36 , B64G1/44 , B64G1/26 , B64G1/32 , B64G2001/245 , Y10S136/292
Abstract: A satellite embodying at least one surface intended mainly for exposure to solar radiation and extending away from the satellite in a predetermined direction (Y), an on board computer having connected thereto an attitude sensing system, an orbit control system for imparting thrust to the satellite along predetermined axes, and an attitude control system. The satellite further embodies a device for controlling the tilt of the surface in parallel with a plurality of planes containing the predetermined direction; and, therefore, particularly in parallel with the plane of a solar panel forming the surface. The tilt control device is controlled by the on-board computer. The tilting can generate a moment of pitch or relocate the center of gravity onto the axis of the orbit control system.
Abstract translation: 一种体现在主要用于暴露于太阳辐射并沿着预定方向（Y）延伸远离卫星的至少一个表面的卫星，与其连接的车载计算机的姿态感测系统，用于向卫星施加推力的轨道控制系统 沿预定轴线和姿态控制系统。 该卫星还具有用于控制表面与包含预定方向的多个平面平行的倾斜的装置; 因此特别是与形成表面的太阳能电池板的平面平行。 倾斜控制装置由车载计算机控制。 倾斜可以产生俯仰的力矩或将重心定位在轨道控制系统的轴上。
-
9.发明授权Method and apparatus for compensating for magnetic disturbance torques on a satellite 失效用于补偿卫星上的磁扰动转矩的方法和装置
公开(公告)号：US5540405A
公开(公告)日：1996-07-30
申请号：US89381
申请日：1993-07-09
Applicant: Douglas J. Bender , William F. Hummel
Inventor： Douglas J. Bender , William F. Hummel
CPC classification number: G05D1/0883 , B64G1/24 , B64G1/32 , B64G1/34 , B64G1/366 , B64G1/285 , B64G1/288 , B64G1/361 , B64G1/363 , B64G1/365
Abstract: This invention discloses a method for compensating for the disturbance torque on an orbiting satellite (10) from the interference of the earth's magnetic field lines with particular current loops associated with the satellite (10). The current flow in these current loops on the satellite (10) is measured by a current sensing device (42). A scaling factor (44,46) is applied to the measured currents to derive an estimated disturbance torque in particular axes of the satellite's attitude. The estimated magnetic disturbance torques are applied, along with other control torques, to a satellite actuation device (38). The actuation device (38) actuates the satellite (10) in the particular axes to compensate for the disturbance torques being applied to the satellite (10).
Abstract translation: 本发明公开了一种用于补偿轨道卫星（10）上的干扰转矩与地球磁场线与卫星（10）相关联的特定电流环路的干扰的方法。 在卫星（10）上的这些电流回路中的电流通过电流检测装置（42）测量。 对测量的电流施加比例因子（44,46）以导出卫星姿态的特定轴的估计扰动转矩。 估计的磁干扰转矩与其他控制转矩一起施加到卫星致动装置（38）。 致动装置（38）在特定轴线上致动卫星（10），以补偿施加于卫星（10）的干扰转矩。
-
10.发明授权
公开(公告)号：US5508932A
公开(公告)日：1996-04-16
申请号：US061615
申请日：1993-05-13
Applicant: Issam-Maurice Achkar , Pierre Guillermin , Herve Renault
Inventor： Issam-Maurice Achkar , Pierre Guillermin , Herve Renault
Abstract: Earth acquisition from the Sun pointing attitude starts with angular displacement of the satellite so that, in the field of view of a Sun sensing system, the direction of the Sun is brought into an orientation S' such that subsequent rotation of the satellite about the orientation S' brings the Pole Star into the field of view of a star sensing system whose optical axis is substantially parallel to the pitch axis. During this rotation the stars sensed are compared with those in a catalog containing, in addition to the Pole Star, stars likely to be encountered upon such movement. At least two of these stars are identified and then the Pole Star is captured. The satellite is then rotated in pitch until the Earth is sensed and captured.
Abstract translation: 从太阳指向态度的地球采集从卫星的角位移开始，使得在太阳感测系统的视野中，太阳的方向被带入方向S'，使得卫星绕着取向继续旋转 S'将极星引入星光感测系统的视野，其光轴基本上平行于俯仰轴。 在这次旋转期间，感觉到的星星与目录中的星星进行比较，除了极星之外，还有可能在这种运动中遇到的星星。 这些星星中至少有两颗被识别出来，然后捕获极星。 卫星然后以俯仰旋转直到地球被感测和捕获。
-
-
-
-
-
-
-
-
-
Search Results
95
records
(took 0.021 seconds)
