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公开(公告)号：US5954298A
公开(公告)日：1999-09-21
申请号：US842106
申请日：1997-04-28
摘要： A spacecraft (10) has combined propulsion and active thermal control systems. A propellant storage tank (20) couples to a pressurant storage tank (18). A working fluid (52) resides in the pressurant storage tank (18) and propels propellant when needed while concurrently acting as a thermal working fluid. The working fluid (52) is expanded then routed to selected cooled components (64). After passing by the cooled components (64), the working fluid (52) is compressed and passed by selected heated components (82). A controller (36) monitors temperature sensors (88) and controls valve assemblies (60, 78) to determine the components (64, 82) to which the working fluid (52) is routed.
摘要翻译： 航天器（10）组合了推进和主动热控制系统。 推进剂储罐（20）联接到加压储存罐（18）。 工作流体（52）位于加压储存罐（18）中，并且当需要时推进推进剂同时充当热工作流体。 工作流体（52）膨胀然后被路由到选定的冷却部件（64）。 在被冷却的部件（64）通过之后，工作流体（52）被选定的加热部件（82）压缩并通过。 控制器（36）监测温度传感器（88）并且控制阀组件（60,78）以确定工作流体（52）所路由的部件（64,82）。
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公开(公告)号：US6003817A
公开(公告)日：1999-12-21
申请号：US746587
申请日：1996-11-12
摘要： One or more deployable thermal panels (24, 28, 70) are actively controlled throughout the orbit of a satellite (20) to provide thermal dissipation. Adjusting the incident angle between the panel (24, 28, 70) and the sun and controlling the flow of fluid through optional flexible heat pipes loads and unloads heat to provide thermal stability for components (62) which have special thermal requirements. An optional antenna panel (70) on a nadir side (64) of the satellite (20) offers an antenna side (74) on one surface and a thermal radiating side (72) on an opposing surface. In addition, thermal panel movements are controlled (96) to provide counter-disturbance torques (140).
摘要翻译： 在卫星（20）的整个轨道上主动地控制一个或多个可展开的散热板（24,28,70）以提供散热。 调整面板（24,28,70）与太阳之间的入射角度并通过可选的柔性热管来控制流体的流动，加载并卸载热量，以为具有特殊热量要求的部件（62）提供热稳定性。 在卫星（20）的最低侧（64）上的可选的天线面板（70）在一个表面上提供天线侧（74），在对置的表面上提供热辐射侧（72）。 此外，控制热板运动（96）以提供反扰动力矩（140）。
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公开(公告)号：US5411227A
公开(公告)日：1995-05-02
申请号：US996241
申请日：1992-12-23
CPC分类号： G05D1/0883 , B64G1/26
摘要： The estimation and compensation of fixed, but unknown uncertainties of a thruster (22) for improving satellite attitude estimation and control as well as eliminating the need for nutation damping devices is disclosed. A thruster (22) is fired and an attitude state is estimated using an estimator (116). A commanded rate change (122) is calculated, which is modified using a compensating feedforward command (126) as updated by a fixed uncertainty estimator (124) unless an estimated rate is less than an absolute value of a threshold rate. The modified commanded rate change (130) is used to incrementally adjust thruster fire on-time (104) until a predetermined satellite trajectory is reached.
摘要翻译： 公开了用于改善卫星姿态估计和控制以及消除对章动阻尼装置的需要的推进器（22）的固定但未知的不确定性的估计和补偿。 推进器（22）被点燃并且使用估计器（116）来估计姿态状态。 计算命令速率改变（122），其使用由固定不确定性估计器（124）更新的补偿前馈命令（126）进行修改，除非估计速率小于阈值速率的绝对值。 改变的命令速率改变（130）用于逐渐地调整推进器火焰的时间（104）直到达到预定的卫星轨迹。
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公开(公告)号：US5779195A
公开(公告)日：1998-07-14
申请号：US642713
申请日：1996-05-03
CPC分类号： H04B7/18515 , B64G1/007 , B64G1/10 , B64G1/1085 , B64G1/22 , B64G1/641 , B64G1/002 , B64G2001/1092
摘要： A satellite assembly (60, 68, 70) is formed from any number of bus modules (22) which have a substantially common shape and interior space volume. Each bus module (22) includes a structural frame (20) which is part of a structural subsystem and at least one and possibly all of a propulsion subsystem (28), a power subsystem (30), a thermal subsystem (32), an attitude, orientation and control subsystem (34), a telemetry, tracking and control subsystem (42) and a payload subsystem (44). Within each bus module (22), the subsystems are substantially non-redundant. Bus modules (22) attach together permanently or temporarily through attachment mechanisms (36). Permanent attachment is used to form large and/or redundancy within the satellites. Temporary attachment is used to increase the structural rigidity of individual bus modules (22) for launch purposes, then the assembly (60) is decomposed into individual satellites.
摘要翻译： 卫星组件（60,68,70）由任何数量的具有基本上共同的形状和内部空间体积的总线模块（22）形成。 每个总线模块（22）包括结构框架（20），其是结构子系统的一部分，并且至少一个并且可能全部的推进子系统（28），电力子系统（30），热子系统（32）， 姿态，导向和控制子系统（34），遥测，跟踪和控制子系统（42）和有效载荷子系统（44）。 在每个总线模块（22）内，子系统基本上是非冗余的。 总线模块（22）通过连接机构（36）永久地或临时地连接在一起。 永久附件用于在卫星内形成大的和/或冗余的。 临时附件用于增加单个总线模块（22）的结构刚度用于发射目的，则组件（60）被分解为单独的卫星。
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公开(公告)号：US5724659A
公开(公告)日：1998-03-03
申请号：US673584
申请日：1996-07-01
CPC分类号： H04B7/18578
摘要： An enhanced services communication system (10) has a standard services region and an enhanced services region (58) in which communication may be carried out. Subscriber units (49, 109) located within the enhanced services region (58) request enhanced services that include dynamic allocation of bandwidth. A variable bandwidth repeater switch (42) evaluates the availability of requested bandwidth and allocates the bandwidth to the subscriber units (49, 109) when available. Transmission of data using enhanced services occurs using wideband wired interfaces (115), wideband wireless interfaces (70), or PSTN interfaces (103). Selection of dynamic allocation of bandwidth may rely upon economic, propagation duration, or link quality factors, among other considerations.
摘要翻译： 增强服务通信系统（10）具有标准服务区域和可以进行通信的增强服务区域（58）。 位于增强服务区域（58）内的用户单元（49,109）请求包括动态分配带宽的增强业务。 可变带宽中继器交换机（42）评估所请求带宽的可用性，并且当可用时将带宽分配给用户单元（49,109）。 使用增强业务的数据传输是使用宽带有线接口（115），宽带无线接口（70）或PSTN接口（103）发生的。 选择动态带宽分配可能依赖于经济，传播持续时间或链路质量因素等因素。
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公开(公告)号：US5452869A
公开(公告)日：1995-09-26
申请号：US993948
申请日：1992-12-18
摘要： A method and system (12) for controlling the attitude of a spacecraft during its transfer orbit using an on-board, stand-alone, three-axes attitude determination and control system. The system utilizes a set of on-board sensors to define two independent angular measurements, which will initially identify the z-axis orientation of the spacecraft from an arbitrary attitude after launch vehicle separation. A set of three-axis gyros are then bias calibrated in order to measure the transverse rates of the spacecraft. The three-axis attitude of the spacecraft is continously determined by integrating the gyro outputs even if the Earth or Sun is not visible by an on-board sensor. A state estimator model is provided to determine the three-axis attitude of the spacecraft in the presence of large wobble and nutation. The system also utilizes a linear combination of the estimated attitude, rate and acceleration states to generate commanded rate increments with a pulse-width frequency modulator. The pulse-width frequency modulator seeks to linearize the inherently non-linear thruster duty cycle.
摘要翻译： 一种用于使用车载，独立的三轴姿态确定和控制系统来控制航天器在其转移轨道期间的姿态的方法和系统（12）。 该系统利用一组车载传感器来定义两个独立的角度测量，这将首先在运载火箭分离后从任意姿态识别航天器的z轴方位。 然后将一组三轴陀螺仪进行偏置校准，以测量航天器的横向速率。 航天器的三轴姿态通过集成陀螺仪输出来连续确定，即使地面或太阳不可见于机载传感器。 提供状态估计器模型来确定在存在大摆动和章动的情况下航天器的三轴姿态。 该系统还利用估计的姿态，速率和加速度状态的线性组合来产生具有脉冲宽度调制器的命令速率增量。 脉宽调制器寻求将固有的非线性推进器占空比线性化。
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公开(公告)号：US20070171932A1
公开(公告)日：2007-07-26
申请号：US11336592
申请日：2006-01-20
IPC分类号： H04B7/212
CPC分类号： H04B7/18539
摘要： Systems and methods are provided for dynamically allocating and routing resource in a wireless communication system. The system includes at least one scheduled resource, a first terminal having a resource requirement and configured to acquire an alternate resource in response to an out-of-band signal, and a controller. The controller is configured to determine the alternate resource from the scheduled resource, schedule the alternate resource for the first terminal based on the resource requirement, and direct the first terminal to a set of frequencies of the alternate resource via the out-of-band signal The method includes determining an alternate resource in the wireless communication system from scheduled resource uses, scheduling the alternate resource for a terminal based on a scheduled resource use of the terminal, and directing the terminal to acquire the alternate resource at a set of frequencies of the alternate resource.
摘要翻译： 提供了用于在无线通信系统中动态分配和路由资源的系统和方法。 该系统包括至少一个调度资源，具有资源需求的第一终端，并且被配置为响应于带外信号获取替代资源，以及控制器。 所述控制器被配置为根据所述资源需求来调度所述第一终端的备用资源，并且经由所述带外信号将所述第一终端定向到所述备选资源的一组频率， 该方法包括：根据调度的资源使用确定无线通信系统中的替代资源，基于终端的调度的资源使用调度终端的备用资源，以及指导终端以一组频率 备用资源。
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公开(公告)号：US6089509A
公开(公告)日：2000-07-18
申请号：US831119
申请日：1997-04-01
CPC分类号： B64G1/32 , G05D1/0883 , B64G1/36
摘要： A spacecraft (10) body (20) located in an external magnetic field (12) has a substantially unbalanced electrical power bus (18) that generates a composite local magnetic field The electrical power bus (18) substantially surrounds an external surface (22) of the spacecraft (10). Current in the electrical power bus (18) is solar panel (14and 16) and/or battery (34) generated and can flow in different directions through different current paths. Electrical loads (58) are coupled to power converters (56) and current path switches (54) to couple the power converters (56) to the various current paths. A controller (28) takes sensor data (82), determines a required attitude adjustment torque (84), translates that adjustment torque into a composite magnetic field (86), determines an unbalanced bus current profile (88) to generate that composite magnetic field, selects a current source (90) and regulates current path switches (92) to achieve a desired attitude adjustment torque for the spacecraft (10).
摘要翻译： 位于外部磁场（12）中的航天器（10）主体（20）具有产生复合局部磁场的基本不平衡的电力总线（18）。电力总线（18）基本上围绕外表面（22） 的航天器（10）。 电力总线（18）中的电流是太阳能电池板（14和16）和/或电池（34），并且可以通过不同的电流路径沿不同的方向流动。 电负载（58）耦合到功率转换器（56）和电流路径开关（54），以将功率转换器（56）耦合到各种电流路径。 控制器（28）接收传感器数据（82），确定所需的姿态调节扭矩（84），将该调节转矩转换成复合磁场（86），确定不平衡总线电流分布（88）以产生该复合磁场 选择电流源（90）并且调节电流路径开关（92）以实现对于航天器（10）的期望的姿态调节扭矩。
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公开(公告)号：US6113034A
公开(公告)日：2000-09-05
申请号：US905627
申请日：1997-08-04
CPC分类号： G05D1/0883 , B64G1/32 , B64G1/36 , B64G1/26 , B64G1/285 , B64G2001/245
摘要： The attitude of a physical platform (62) is altered by a summation of forces from an attitude actuator (74), disturbance forces (80) and random noise (82). Attitude sensors (64) sense the attitude of the physical platform (62) and output measured attitude parameters to a disturbance force effects (DFE) filter (66) and an attitude filter (68). The DFE filter (66) outputs an attitude perturbation command to the attitude filter (68) and a command translator (72). Effects of the attitude perturbation are used by the DFE filter (66) to estimate the effects of disturbances on the physical platform (62). A trigger signal (76) from the attitude actuator (74) is used by DFE filter (66) to select an appropriate gain matrix used in the estimation process.
摘要翻译： 物理平台（62）的姿态通过来自姿态致动器（74），扰动力（80）和随机噪声（82）的力的总和而改变。 姿态传感器（64）感测物理平台（62）的姿态并将测量的姿态参数输出到扰动力效应（DFE）滤波器（66）和姿态滤波器（68）。 DFE滤波器（66）向姿态滤波器（68）和命令转换器（72）输出姿态扰动命令。 姿态扰动的影响被DFE滤波器（66）用于估计物理平台上扰动的影响（62）。 来自姿态致动器（74）的触发信号（76）由DFE滤波器（66）用于选择在估计过程中使用的适当的增益矩阵。
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公开(公告)号：US5906339A
公开(公告)日：1999-05-25
申请号：US743767
申请日：1996-11-07
摘要： In a satellite (20), two-axis solar panel drives (56, 58) allow two degrees of rotational freedom of movement for solar panels (22, 24). Regulation of electrical current loops (46, 48) within the solar panels (22, 24) generates a magnetic field. When the solar panels (22, 24) are tilted about an overturning axis (28), the magnetic field provides a component of a control torque about a pitch axis (30). An on-board processor (52) commands the panel drives (56, 58) and a magnetic torque actuator (60) to instantaneously and simultaneously damp disturbance torques about a windmill axis (26), an overturning axis (28), and a pitch axis (30). The processor (52) allows disturbance torque to be corrected continuously rather than periodically over the course of an orbit. Counter-disturbance torques (90) are applied (88) in synchronism with a satellite nutation frequency (76) but out of phase with the nutation so that nutation is damped.
摘要翻译： 在卫星（20）中，双轴太阳能电池板驱动器（56,58）允许太阳能电池板（22,24）的两度的运动自由度。 太阳能电池板（22,24）内的电流回路（46,48）的调节产生磁场。 当太阳能电池板（22,24）围绕翻转轴线（28）倾斜时，磁场提供围绕俯仰轴线（30）的控制扭矩的分量。 机载处理器（52）命令面板驱动器（56,58）和磁力矩致动器（60）瞬时并且同时地减小围绕风车轴线（26），翻转轴线（28）和俯仰轴线（28）的扰动扭矩 轴（30）。 处理器（52）允许在轨道的过程中连续而不是周期地校正扰动扭矩。 抗干扰转矩（90）与卫星章动频率（76）同步地施加（88），但是与章动异相，使得章动被阻尼。
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