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51.发明公开
公开(公告)号：EP1270411A1
公开(公告)日：2003-01-02
申请号：EP01202486.5
申请日：2001-06-28
申请人： Dutch Space B.V.
发明人： Zwanenburg, Robert
IPC分类号： B64G1/44 , H01L31/045
CPC分类号： B64G1/222 , B64G1/44 , B64G1/443 , H02S20/00 , H02S30/20 , Y02E10/50 , Y10S136/291 , Y10S136/292
摘要： Solar panel (11) comprising solar cells affixed to one or more sheet elements (17) and a frame (12,13) for supporting said sheet elements (17), wherein the frame (12,13) is provided with attachment means for attaching said sheet elements to the frame, wherein that, the attachment means comprise one or more pretensioned strings (20,21), the sheet elements (17) being attached to said strings (20,21). According to the invention it is preferred that the sheet elements (17) are composed of flexible material and are attached to the string (20,21) in a corrugated shape, wherein the sheet elements are provided with at least one row of apertures for weaving a string (20,21) through successive apertures of said row.
摘要翻译： 太阳能电池板（11）包括固定到一个或多个薄片元件（17）上的太阳能电池和用于支撑所述薄片元件（17）的框架（12,13），其中所述框架（12,13）设置有附接装置 所述片材元件到所述框架，其中，所述附接装置包括一个或多个预张紧绳（20,21），所述片元件（17）附接到所述绳（20,21）。 根据本发明，优选的是，片状元件（17）由柔性材料构成并且以波纹形状附接到线（20,21），其中片元件设置有至少一排用于编织的孔 通过所述行的连续孔径的绳（20,21）。
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53.发明公开Space photovoltaic power generation system, power satellite, and electric power producing ground station 有权系统zur photovoltaischen Energieerzeugung im Weltraum
公开(公告)号：EP1189328A2
公开(公告)日：2002-03-20
申请号：EP01120034.2
申请日：2001-08-20
摘要： A space photovoltaic power generation system comprises a plurality of power satellites (1) arranged in space, each of which converts electric energy, into which sunlight has been photoelectrically converted, into a microwave, and transmits the microwave to an electric power base (2). The system can thus transmit a microwave of high power to the electric power base (2). Each of the plurality of power satellites (1) modulates the generated microwave so as to generate an incoherent microwave before transmitting it to the electric power base (2), thus reducing the power density of the electric power transmitted to the electric power base (2) on the earth and hence a loss in the total amount of energy transmitted to the electric power base (2) on the earth.
摘要翻译： 空间光伏发电系统包括多个布置在空间中的功率卫星（1），每个功率卫星将太阳光被光电转换的电能转换成微波，并将微波传输到电力基座（2） 。 因此，该系统可以将高功率的微波传输到电力基座（2）。 多个功率卫星（1）中的每一个调制所生成的微波，以便在将其发送到电力基座（2）之前产生非相干微波，从而降低传输到电力基座（2）的电力的功率密度 ），因此传输到地球上的电力基地（2）的能量总量的损失。
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54.发明公开Sun-seeking solar array control system and method 审中-公开Regelungssystem und -verfahrenfürsonnesuchende Sonnenpaneele
公开(公告)号：EP1172294A2
公开(公告)日：2002-01-16
申请号：EP01304349.2
申请日：2001-05-16
发明人： Higham, John S. , Rotlisberger, Lee
摘要： A control system and method that keeps solar arrays on a satellite pointing toward the sun. Exemplary control systems and methods are implemented as follows. An orbit propagator (11) computes satellite orbital location data and computes a sun vector (12) referenced to an inertial reference frame. A coordinate transformation processor (13) processes the sun vector in the inertial reference frame and a sensed satellite attitude signal to generate a sun vector referenced to a satellite body reference frame. A solar array position processor (14) processes a step count derived from a solar array pointing control system and sensed solar array position to generate an estimate of the position of the solar array. A summing device (16) sums the solar array position estimate output, the body frame sun vector, and a bias signal derived from a ground command, to produce a solar array position error signal. A filter (17) filters the solar array position error signal. A current regulator processor (15) processes a measured solar array current to produce another solar array position error signal based on current output. An eclipse processor (18) processes the satellite orbital location data, the solar array position error output signal, and the low pass filtered solar array position error signal to generate a step command. The solar array pointing control system processes the step command to generate control signals that point the solar array at the sun.
摘要翻译： 将太阳能阵列保持在指向太阳的卫星上的控制系统和方法。 示例性控制系统和方法如下实现。 轨道传播器（11）计算卫星轨道位置数据并计算参考惯性参考系的太阳矢量（12）。 坐标变换处理器（13）处理惯性参考系中的太阳矢量和感测的卫星姿态信号，以产生参考卫星体参考系的太阳矢量。 太阳能阵列位置处理器（14）处理从太阳能阵列指向控制系统和感测的太阳能阵列位置导出的步数，以产生太阳能阵列的位置的估计。 求和装置（16）将太阳能阵列位置估计输出，车身框架太阳向量和从地面命令导出的偏置信号相加，以产生太阳能阵列位置误差信号。 滤波器（17）对太阳能阵列位置误差信号进行滤波。 电流调节器处理器（15）处理测量的太阳能阵列电流以产生基于电流输出的另一太阳能阵列位置误差信号。 日食处理器（18）处理卫星轨道位置数据，太阳能阵列位置误差输出信号和低通滤波太阳能阵列位置误差信号以产生步进命令。 太阳能阵列指向控制系统处理步进命令以产生将太阳能阵列指向太阳的控制信号。
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公开(公告)号：EP0984511A3
公开(公告)日：2001-08-16
申请号：EP99115200.0
申请日：1999-08-17
申请人： TRW INC.
发明人： Gilger, L. Dwight
IPC分类号： H01Q15/16 , H01Q1/28 , B64G1/44 , H01L31/042
摘要： A new combination is formed of a deployable solar array and a deployable perimeter truss reflector within a single structure, defining a deployable perimeter truss reflector and solar array combination. In that combination the pliant reflective mesh, which serves as the RF reflector, is located at one circular end of the perimeter truss and the solar array is located at the other end. The solar array is formed with photovoltaic cells formed on both sides of a pliant film base. The photovoltaic cells are exposed to sunlight, either directly, or through the mesh, which is eighty percent porous to sunlight. Constructed in deployed form, for storage the truss contracts to the conventional non-deployed condition of a barrel-like configuration; and both the pliant reflective mesh that forms the reflector and the pliant base supporting the photovoltaic cells become tucked in place inside opposite ends of the barrel. Among other benefits, the integral structure obviates the complications resulting from use of two structures, such as shadowing, and eliminates the need for sun-tracking electronic systems used with prior solar arrays.
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56.发明公开An orbit raising system and method for geosynchronous satellites 审中-公开一种用于调整卫星到更高的轨道系统，和方法，用于地球同步卫星
公开(公告)号：EP1059232A2
公开(公告)日：2000-12-13
申请号：EP00304391.6
申请日：2000-05-24
摘要： A satellite (11) is launched that contains high thrust chemical propulsion thrusters, high specific impulse electric propulsion thrusters and a solar array. The satellite quickly escapes the Van Allen radiation belts by firing the high thrust chemical propulsion thrusters at apogees of intermediate orbits, staffing from the transfer orbit (14) initiated by a launch vehicle, to successively raise the perigees until the perigee clears the Van Allen radiation belts. The payload mass and mission life are maximized by firing high specific impulse electric propulsion thrusters to raise the satellite to near synchronous orbit, while steering the thrust vector and solar array to maintain the sun's illumination on the solar array. The chemical and/or electric propulsion thrusters are then fired to achieve geosynchronous orbit (15).
摘要翻译： 的卫星（11）被启动的确含有高推力化学推进加速器，高比冲电学推进加速器和一个太阳能电池阵列。 通过在中间轨道的远地点点火高推力化学推进加速器，由运载火箭开始转移轨道（14）人员配备，依次抬高近地点，直到近地点清除范艾伦辐射的卫星迅速逃逸的范艾伦辐射带 带。 所述有效载荷质量和任务寿命通过烧制高比冲电学推进加速器提高卫星到接近同步轨道，而转向的推力矢量和太阳能电池阵列，以保持太阳的太阳能电池阵列上照明最大化。 然后，将化学和/或电学推进加速器被烧制以达到地球同步轨道（15）。
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公开(公告)号：EP1043228A2
公开(公告)日：2000-10-11
申请号：EP00107487.1
申请日：2000-04-06
申请人： TRW Inc.
发明人： Dailey, Dean R. , Elliott, Lee E.
IPC分类号： B64G1/44 , H01L31/045
CPC分类号： B64G1/222 , B64G1/443 , Y10S136/292
摘要： The power to weight ratio obtained with a spacecraft's solar array (3) is enhanced by a factor of at least two to five through use of support structure for individual solar panels or solar arrays (31a-17a) containing a curved outwardly bowed surface as deployed that packs essentially flat for storage. Defining a D-shaped wing (15a) in cross-section as deployed, the support structure (4 & 6) for a string of solar cells (10, Fig. 3) provides greater inertia and thereby greater rigidity than prior designs. One member (4) to the support structure is relatively flexible. One-hundred and eighty degree strain energy hinges (19) carried by the other support member (6) outwardly bows that flexible to define a curved sector when the support structure is released from the stowed condition in which the support structure is held relatively thin and flat.
摘要翻译： 通过使用单个太阳能电池板或太阳能阵列（31a-17a）的支撑结构，使用航天器的太阳能电池阵列（3）获得的功率重量比通过至少2至5倍增加，所述太阳能电池板或太阳能阵列（31a-17a）包含弯曲的向外弯曲的表面， 这些包装基本上是平面的存储。 在部署的横截面中定义D形翼（15a），用于一串太阳能电池（图3中的10）的支撑结构（4和6）提供更大的惯性，从而提供比现有设计更大的刚性。 支撑结构的一个（4）比较灵活。 由另一个支撑构件（6）承载的一百零八个应变能量铰链（19）向外弯曲，当支撑结构从其中支撑结构保持相对较薄的收起状态被释放时，柔性以限定弯曲的扇形， 平面。
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公开(公告)号：EP0754625B1
公开(公告)日：2000-06-21
申请号：EP96305338.4
申请日：1996-07-19
IPC分类号： B64G1/44
CPC分类号： B64G1/443 , B64G1/222 , Y10S136/292 , Y10T16/61 , Y10T74/18848
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60.发明公开
公开(公告)号：EP0976655A1
公开(公告)日：2000-02-02
申请号：EP98114321.7
申请日：1998-07-30
IPC分类号： B64G1/44 , H01L31/052
CPC分类号： B64G1/443 , B64G1/222 , H01L31/0547 , Y02E10/52
摘要： Flexible, lightweight reflective sheets (62) are positioned to concentrate solar radiation upon spacecraft solar panels (46). The sheets are positioned with inner and outer spring members (68, 70) which urge each sheet towards a planar configuration and further urge the sheet in a rotation away from a solar panel face (57). Restraint members in the form of tethers (90) limit this rotation to place the sheet in a deployed position in which it defines an angle with the panel to reflect solar radiation onto the panel face. The increased incident radiation permits a reduction of the number of solar cells with consequent savings in spacecraft cost and weight. The spring members are configured to permit rotation to a stowed position behind the solar panel. In this position, the tethers are received into guides (110) which are configured to initiate automatic deployment of the spring members and their reflective sheets.
摘要翻译： 灵活的轻质反射片（62）被定位成将太阳辐射集中在航天器太阳能电池板（46）上。 片材定位有内部和外部弹簧构件（68,70），其将每个片材推向平面构造，并且进一步推动片材远离太阳能电池板面（57）旋转。 系绳（90）形式的约束构件限制了这种旋转，以将片材放置在展开位置，在该展开位置中，它与面板形成一个角度，以将太阳辐射反射到面板上。 增加的事件辐射允许减少太阳能电池的数量，从而节省了航天器的成本和重量。 弹簧构件被配置为允许旋转到太阳能电池板后面的收起位置。 在该位置，系绳被接收到引导件（110）中，引导件被构造成启动弹簧件及其反射片的自动展开。
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