公开(公告)号：US06571156B1

公开(公告)日：2003-05-27

申请号：US10114826

申请日：2002-04-01

申请人： Grant Wang ,  Umesh Ketkar ,  Sadek W. Mansour ,  Sheng N. Sun

发明人： Grant Wang ,  Umesh Ketkar ,  Sadek W. Mansour ,  Sheng N. Sun

IPC分类号： B64G136

CPC分类号： B64G1/36 ,  B64G1/26 ,  B64G1/283 ,  B64G1/285 ,  B64G1/361 ,  B64G1/443

摘要： A simple, robust algorithm for power acquisition for power, thermal, and momentum safety for high heater-power spacecraft uses current sensors rather than sun sensors and includes a wing sun search phase, an xz slew phase, and a safe hold phase. Solar wing current is continuously monitored against a high current threshold and a low current threshold. Wing sun search phase transitions either to xz slew phase or safe hold phase. When current is too low, the xz slew phase is entered and slews the spacecraft about an axis in the xz plane until current is high enough. When current is high enough, the algorithm transitions or remains in safe hold phase and the spacecraft is spun about its wing axis. A low current persistence timer is longer than a high current persistence timer in order to bias the algorithm to prefer safe hold phase over xz slew phase.

摘要翻译： 一种用于高功率，高能量和动量安全功率采集的简单稳健算法，用于高加热器功率的航天器使用电流传感器而不是太阳传感器，包括机翼太阳搜索阶段，xz转换阶段和安全保持阶段。 依靠高电流门槛和低电流门槛连续监测太阳能机翼电流。 翼太阳搜索相转换到xz转换阶段或安全保持阶段。 当电流过低时，进入xz转换阶段，并绕xz平面中的轴旋转航天器，直到电流足够高。 当电流足够高时，算法转换或保持在安全保持阶段，航天器围绕其翼轴旋转。 低电流持续定时器比高电流持续时间定时器长，以便将算法偏置为比xz摆幅相位更安全的保持相位。

公开(公告)号：US06561462B1

公开(公告)日：2003-05-13

申请号：US10081468

申请日：2002-02-21

申请人： Hanching G. Wang ,  Umesh Ketkar ,  Albert A. Munoz ,  Sadek Mansour

发明人： Hanching G. Wang ,  Umesh Ketkar ,  Albert A. Munoz ,  Sadek Mansour

IPC分类号： B64G136

CPC分类号： B64G1/363 ,  B64G2001/245

摘要： A spacecraft power/sun acquisition method includes a pitch search phase in which the spacecraft is rotated about a pitch axis, stopped, quaternions reset to remember position, and yaw search phase is entered when a first TOA occurs from a first slit sun sensor, and a keyhole slew is performed when the first TOA does not occur. The method also includes yaw search phase in which a keyhole slew is performed by rotating the spacecraft about a yaw axis, stopping the spacecraft, and entering pitch search phase when the first TOA does not occur, and in which the spacecraft is rotated about a yaw axis, stopped, quaternions reset, and sun hold phase is entered when a second TOA occurs from a second slit sun sensor. Lastly, the method includes a sun hold phase in which the spacecraft is oriented to the sun and placed in spin at power safe attitude.

摘要翻译： 航天器功率/太阳采集方法包括：俯仰搜索阶段，其中航天器围绕俯仰轴线旋转，停止，四元数复位为记忆位置，并且当第一狭缝太阳传感器发生第一TOA时进入偏航搜索阶段，以及 当不发生第一个TOA时执行锁孔旋转。 该方法还包括偏航搜索阶段，其中通过围绕偏转轴旋转航天器，停止航天器并且当第一TOA不发生时进入俯仰搜索阶段执行锁孔，并且其中航天器围绕偏航旋转 轴，停止，四元数复位，并且当从第二狭缝太阳传感器发生第二TOA时进入太阳保持相位。 最后，该方法包括太阳保持阶段，其中航天器被定向到太阳并以功率安全的姿态旋转。