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1. 发明公开

EP1669292A1 Optimized land mobile satellite configuration and steering method 审中-公开
标题翻译： Optimierte移动irdische Satellitenkonfiguration和Steuerungsmethode
公开(公告)号：EP1669292A1
公开(公告)日：2006-06-14
申请号：EP05256912.6
申请日：2005-11-08
申请人： Lockheed Martin Corporation
发明人： Goodzeit, Neil E.
IPC分类号： B64G1/24 , B64G1/10 , G05D1/08
CPC分类号： B64G1/24 , B64G1/1007 , G05D1/0883
摘要： A method for configuring and operating a spacecraft (301) in an orbit that is inclined with respect to Earth's equatorial plane, the spacecraft (301) including at least a solar array (302), a receive antenna (305), a transmit antenna (306), and radiator panels. The method includes the step of nominally orienting the yaw axis of the spacecraft, the roll axis of the spacecraft, and the radiator panels substantially parallel to Earth's equatorial plane, the pitch axis of the spacecraft and rotation axis of the solar array substantially parallel to Earth's polar axis, the Nadir vector in the yaw-pitch plane of the spacecraft, and the transmit antenna and receive antenna to angle ϕ nom . The method also includes the step of correcting the attitude of the receive antenna (305) and the transmit antenna (306) to maintain a desired degree of the receive antenna (305) and the transmit antenna (306) steered toward a coverage region on Earth's surface.
摘要翻译：一种用于配置和操作相对于地球赤道平面倾斜的轨道中的航天器（301）的方法，所述航天器（301）至少包括太阳能阵列（302），接收天线（305），发射天线 306）和散热器面板。该方法包括以下步骤：将航天器的偏转轴线，航天器的滚动轴线和散热器面板大致平行于地球的赤道平面，航天器的俯仰轴线和太阳能阵列的旋转轴线基本上平行于地球的极轴，航天器偏航螺距平面中的天底矢量，以及发射天线和接收天线的角度。该方法还包括校正接收天线（305）和发射天线（306）的态度以维持接收天线（305）和发射天线（306）的期望程度朝着地球上的覆盖区域转向的步骤表面。

2. 发明公开

EP1669291A1 Optimized land mobile satellite system for north american coverage 审中-公开
标题翻译：优化手机irdisches Satellitensystem zur nordamerikanischen Abdeckung
公开(公告)号：EP1669291A1
公开(公告)日：2006-06-14
申请号：EP05256913.4
申请日：2005-11-08
申请人： Lockheed Martin Corporation
发明人： Goodzeit, Neil E.
IPC分类号： B64G1/10 , B64G1/24
CPC分类号： B64G1/1085 , B64G1/1007 , B64G1/242 , H04B7/195
摘要： A constellation, including a plurality of spacecraft, including a first, second and third spacecraft, each of the plurality of spacecraft including a broadcast capability, and each of the plurality of spacecraft in its own approximately 24-hour orbit (501). Each of the orbits (501) has a substantially teardrop-shaped or oval-shaped ground track, is optimized based upon elevation angle or probability of signal availability, and has an apogee longitude of approximately 90° west to approximately 100° west. Each of the orbits has a semi-major axis of approximately 42,164 kilometers, an argument of perigee of approximately 270°, an inclination of approximately 40° to approximately 60°, and an eccentricity of approximately 0.16 to approximately 0.4. The orbits of each of the plurality of spacecraft are selected to bring each of the spacecraft to apogee at time increments of approximately eight hours.
摘要翻译：包括多个航天器的星座，包括第一，第二和第三航天器，所述多个航天器中的每一个包括广播能力，并且所述多个航天器中的每一个在其自己的大约24小时轨道（501）中。每个轨道（501）具有基本上泪珠状或椭圆形的地面轨道，其基于仰角或信号可用性的概率进行优化，并且具有西约西约90度至约100度西的远地点经度。每个轨道具有大约42,164公里的半长轴，近地点约270°的倾角，大约40°至大约60°的倾斜度，以及大约0.16至大约0.4的偏心率。选择多个航天器中的每一个的轨道，以使每个航天器以大约八小时的时间增量进入远地点。

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