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    • 5. 发明授权
    • Offline apparatus for detecting attitude of artificial satellite in wide-band and method thereof
    • 用于检测宽带人造卫星姿态的离线装置及其方法
    • US06463364B2
    • 2002-10-08
    • US09942868
    • 2001-08-31
    • Toshiaki Yamashita
    • Toshiaki Yamashita
    • B64G132
    • B64G1/361B64G1/288B64G1/36B64G2001/245
    • This invention provides an offline attitude determining apparatus capable of detecting an artificial satellite attitude at a high precision in wide band. Averaging and addition processing are carried out on a low-frequency attitude interpolation signal generated by interpolating a low-frequency attitude detection signal obtained by inputting an attitude angle determination signal generated by a sequential Kalman filter computation device and a high-frequency attitude detection signal obtained by inputting a high-frequency attitude angle sensor detection signal extracted by a high-frequency attitude angle sensor data extracting device into a band pass filter computation device, so as to generate a high-precision attitude detection signal. By combining the low-frequency attitude detection signal with the high-frequency attitude detection signal with an interpolation processing computation device and an attitude data generator, the attitude can be determined at a high precision in wide band.
    • 本发明提供了能够在宽带中以高精度检测人造卫星姿态的离线态度判定装置。 对通过内插通过输入由顺序卡尔曼滤波计算装置生成的姿态角确定信号而获得的低频姿态检测信号和获得的高频姿态检测信号而生成的低频态插值信号进行平均加法处理 通过将由高频姿态角传感器数据提取装置提取的高频姿态角传感器检测信号输入到带通滤波器计算装置中,以产生高精度姿态检测信号。 通过使用内插处理计算装置和姿态数据发生器组合低频姿态检测信号与高频姿态检测信号,可以在宽带中以高精度确定姿态。
    • 9. 发明申请
    • Apparatus, method, and program for correcting time of event trace data
    • 用于校正事件跟踪数据时间的装置,方法和程序
    • US20050193277A1
    • 2005-09-01
    • US11062930
    • 2005-02-23
    • Takashi HorikawaToshiaki Yamashita
    • Takashi HorikawaToshiaki Yamashita
    • G06F11/34G06F11/00
    • G06F11/3495G06F11/3476G06F2201/875
    • A time correcting apparatus includes a data input section which inputs all event trace data generated for each event executed on computing devices and outputs the event trace data in order of occurrence time of the event data. An inter-machine communication-time-table generating section extracts transmission and reception events from the output event trace data and generates a communication time table indicating communication times between computing devices based on the differences in occurrence time between the corresponding transmission and reception events. A time-offset deriving section generates a time offset table indicating a time offset value for each computing device based on the communication time table. A time correcting section corrects the event occurrence times of all event data based on the time offset table. A data integrating section inputs all event data whose occurrence times have been corrected and outputs the event data in order of corrected occurrence time.
    • 时间校正装置包括数据输入部分,其输入为在计算装置上执行的每个事件生成的所有事件跟踪数据,并且以事件数据的发生时间的顺序输出事件跟踪数据。 机间通信时间表生成部从输出事件跟踪数据中提取发送接收事件,根据相应的发送接收事件的发生时间的差异,生成指示计算装置之间的通信时间的通信时间表。 时间偏移导出部根据通信时间表生成表示各计算装置的时间偏移值的时间偏移表。 时间校正部根据时间偏移表来校正所有事件数据的事件发生次数。 数据积分部分输入发生时间已被校正的所有事件数据,并按照校正发生时间的顺序输出事件数据。
    • 10. 发明授权
    • Maneuver device for artificial satellite
    • 人造卫星机动装置
    • US06622969B2
    • 2003-09-23
    • US10078109
    • 2002-02-20
    • Toshiaki Yamashita
    • Toshiaki Yamashita
    • B64G128
    • G05D1/0883B64G1/26B64G1/283B64G2001/245
    • The present invention provides a maneuver device for an artificial satellite, which causes small attitude error during maneuver and which requires a shorter period of setting time for obtaining a target attitude. The maneuver device is provided with: a feed forward torque instruction signal generator 8 which outputs a feed forward torque instruction signal 11 based on a maneuver plan; a thruster 10 which outputs control torque based on the feed forward torque instruction signal 11; and an attitude control signal calculator 6 to which an attitude angle and an angular velocity of the artificial satellite as well as a target attitude angle and a target angular velocity are input and which outputs an attitude control signal 13. The maneuver device is further provided with a disturbance compensating signal calculator to which the feed forward torque instruction signal 11 and a detected angular velocity signal 16 are input, and which generates and outputs a disturbance compensating signal 12. The maneuver device is yet further provided with a reaction wheel 7 which generates control torque based on the attitude control signal 13 and the disturbance compensating signal 12.
    • 本发明提供了一种用于人造卫星的操纵装置,其在操纵期间导致小的姿态误差,并且需要较短的设定时间来获得目标姿态。机动装置设置有:前馈转矩指令信号发生器8, 基于机动计划输出前馈转矩指令信号11; 基于前馈转矩指令信号11输出控制转矩的推进器10; 并且输入人造卫星的姿态角和角速度以及目标姿态角和目标角速度的姿态控制信号计算器6,并且输出姿态控制信号13.该操纵装置还设置有 输入前馈转矩指令信号11和检测角速度信号16的干扰补偿信号计算器,并产生并输出干扰补偿信号12.该机动装置还具备反作用轮7,其产生控制 基于姿态控制信号13和干扰补偿信号12的转矩。