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1. 发明授权

US5604430A Solar array maximum power tracker with arcjet load 失效
标题翻译：太阳能阵列最大功率跟踪器，具有电弧喷射负载
公开(公告)号：US5604430A
公开(公告)日：1997-02-18
申请号：US322122
申请日：1994-10-11
申请人： Darwin K. Decker , Donald L. Baxter , Oded Lerner , Jeffrey D. Campbell , Richard A. Rosenthal , Michael J. Cook
发明人： Darwin K. Decker , Donald L. Baxter , Oded Lerner , Jeffrey D. Campbell , Richard A. Rosenthal , Michael J. Cook
IPC分类号： G05F1/67 , G05F1/565 , G05F5/00 , H02J7/00 , H02M7/44
CPC分类号： G05F1/67 , Y02E10/58 , Y10S136/293 , Y10S323/906
摘要： A solar array maximum power point tracking system for regulating the power output of a solar array associated with a spacecraft. An on-board computer measures the bus voltage and current from the solar array and generates a power calculation of the solar array power output. The on-board computer applies a first reference signal to a remote error amplifier representative of an incremental change in the solar array power. Additionally, the solar array bus voltage is applied to the remote error amplifier such that the remote error amplifier senses the solar array bus voltage and generates an output voltage indicative of the change of the solar array power. The output voltage of the error amplifier is applied to a power processor unit. The output voltage from the remote error amplifier and the bus voltage are applied to a power stage within the power processor unit. The power stage generates an output current that is applied to an arcjet thruster. The output current is also applied to a transconductive circuit that converts the output current to a voltage so as to condition the input voltage to the power stage.
摘要翻译：一种用于调节与航天器相关联的太阳能阵列的功率输出的太阳能阵列最大功率点跟踪系统。车载计算机测量来自太阳能阵列的总线电压和电流，并产生太阳能阵列功率输出的功率计算。车载计算机将第一参考信号施加到代表太阳能阵列功率的增量变化的远程误差放大器。此外，将太阳能阵列总线电压施加到远程误差放大器，使得远程误差放大器感测太阳能阵列总线电压并产生指示太阳能阵列功率变化的输出电压。误差放大器的输出电压被施加到功率处理器单元。远程误差放大器的输出电压和总线电压被施加到功率处理器单元内的功率级。功率级产生施加到电弧喷射推进器的输出电流。输出电流也被施加到将输出电流转换为电压以便将输入电压调节到功率级的导电电路。

2. 发明授权

US5530335A Battery regulated bus spacecraft power control system 失效
标题翻译：电池调节总线航天器功率控制系统
公开(公告)号：US5530335A
公开(公告)日：1996-06-25
申请号：US60103
申请日：1993-05-11
申请人： Darwin K. Decker , Charles B. Loftis, Jr.
发明人： Darwin K. Decker , Charles B. Loftis, Jr.
IPC分类号： G05F1/67 , H01M10/46 , H02J4/00 , H02J7/35
CPC分类号： G05F1/67 , H01M10/465 , H02J4/00 , H02J7/35 , Y02E10/566 , Y02E10/58 , Y10S136/293
摘要： A system for supplying d.c. power to an electrical load, in which such load includes a rechargeable battery, is characterized by a plurality of power sources connected in common to the electrical load, wherein the current generated by the multiple power sources is combined to supply such electrical load. Each of the power sources includes a solar panel and a controlled variable transconductance device, such as a Buck converter, connected in electrical series circuit. A digital processor, including a stored program, coupled to the control inputs of the variable transconductance devices, selectively individually sets the duty cycle of each transconductance device under control of a stored program, whereby the electrical power supplied by said power sources to said electrical load is individually controlled by the digital processor.
摘要翻译：提供直流电源的系统其中这种负载包括可再充电电池的电负载的功率的特征在于多个电源连接到电负载，其中由多个电源产生的电流被组合以提供这种电负载。每个电源包括连接在电气串联电路中的太阳能电池板和控制可变跨导装置，例如降压转换器。耦合到可变跨导装置的控制输入的数字处理器，包括存储的程序，在存储的程序的控制下，选择性地单独地设置每个跨导装置的占空比，由此由所述电源提供给所述电负载的电力由数字处理器单独控制。

3. 发明授权

US06541916B2 Method for providing discharge power to electric propulsion thrusters 有权
公开(公告)号：US06541916B2
公开(公告)日：2003-04-01
申请号：US09774378
申请日：2001-01-30
申请人： Darwin K. Decker
发明人： Darwin K. Decker
IPC分类号： B64D3100
CPC分类号： B64G1/406 , B64G1/405 , B64G1/425 , B64G1/426 , B64G1/428 , B64G1/443 , F03H1/0018
摘要： A satellite power distribution method for efficiently distributing power to satellite electric propulsion thrusters (24) is provided. The satellite includes spacecraft loads (20), an electric propulsion thruster (24), thruster auxiliary circuits (22), and a first power transformer (30). The first power transformer (30) has a primary winding (32) coupled to a first energy source (12) that supplies satellite power. A first secondary winding (36) of the first power transformer (30) is coupled to the spacecraft loads (20) for supplying primary power. The power distribution method includes the steps of first coupling a second secondary winding (34) to the first power transformer (30) for converting the satellite power to thruster discharge power which is rectified. The rectified discharge power is filtered to obtain power that is supplied to the electric propulsion thruster (24). Finally, satellite power is converted to auxiliary power for powering the thruster auxiliary circuits (22).

4. 发明授权

US06234427B1 Solar array regulation and spacecraft pointing using flywheel energy storage with programmable voltage control 失效
标题翻译：太阳能阵列调节和飞船指向使用飞轮储能与可编程电压控制
公开(公告)号：US06234427B1
公开(公告)日：2001-05-22
申请号：US08988055
申请日：1997-12-10
申请人： Darwin K. Decker
发明人： Darwin K. Decker
IPC分类号： B64G144
CPC分类号： G05F1/67 , B64G1/283 , B64G1/426 , B64G1/428 , H02J3/30
摘要： A satellite power regulation and pointing system is disclosed that comprises a power bus (104) and first and second flywheels (114-116) capable of storing rotational energy. Each flywheel (114-118) comprises a flywheel motor/generator (202) for increasing the rotational energy in its associated flywheel when storing power in its associated flywheel and for reducing the associated flywheel rotational energy when drawing power from its associated flywheel. The system also includes individual flywheel regulators (108-112) connected to the power bus (104) and to the flywheel motor/generators (202). Each flywheel regulator (108-112) includes a power control circuit (204) that allows power to flow to a flywheel motor/generator (202) from the power bus (104) during an energy storage period and that allows power to flow to the power bus (104) from the flywheel motor/generator (202) during an energy drawing period. The flywheel regulators (108-112) also include feedback control loops (206) connected to the power control circuits (204) and to the power bus (104). The feedback control loops (206) determine the energy storage period and the energy drawing period based upon a predetermined voltage reference (Vref) and a power bus voltage reference (207).
摘要翻译：公开了一种卫星功率调节和指示系统，其包括能够存储旋转能量的电力总线（104）和第一和第二飞轮（114-116）。每个飞轮（114-118）包括飞轮马达/发电机（202），用于在将功率存储在其相关联的飞轮中时增加其相关飞轮中的旋转能量，并且用于当从其相关联的飞轮吸取功率时减小相关联的飞轮旋转能量。该系统还包括连接到电力总线（104）和飞轮马达/发电机（202）的单独的飞轮调节器（108-112）。每个飞轮调节器（108-112）包括功率控制电路（204），其在能量储存期间允许功率从功率总线（104）流到飞轮马达/发电机（202），并且允许功率流向在能量抽取期间，来自飞轮马达/发电机（202）的电力总线（104）。飞轮调节器（108-112）还包括连接到功率控制电路（204）和电力总线（104）的反馈控制回路（206）。反馈控制回路（206）基于预定的电压基准（Vref）和电力总线电压基准（207）确定能量存储周期和能量描绘周期。

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