American ephemeris and nautical almanac 美国天文年历和航海年历
2.
Effect of ephemeris error on the positioning accuracy of double - star positioning system 星历误差对双星定位系统定位精度的影响
3.
200s ttff - cold ( with current almanac , position , time and ephemeris ) 50s ttff - warm ( with current almanac , position , and time ) Ttff温启动典型值50秒（当拥有当前的天历、位置和时间数据时）
4.
The orientation information of the sun , the moon and the earth , together with ephemeris are utilized to develop autonomous navigation algorithm , as well as its realization by dsp hardware 在小样本观测数据情况下,研究利用日地月方位信息和日月星历表进行航天器自主导航以及利用dsp实现航天器自主导航器的技术。
5.
Some message described in the thesis , such as the basic structure of gps - oem , the consists of positioning system , the binary format of almanac and ephemeris , the method and the skill of processing orignal data through singlechip , and so on , is very useful for studying gps and its applications in integrated navigation , and re - development on gps - oem 同时亦可与gis (地理信息系统)配套使用，实现在crt上地图背景下的运动轨迹显示。第二个产品， gps时钟/同步系统，利用全球卫星定位gps卫星的标准utc时间，可在全球得到同步的准确时间。设备采用motorola的12通道gpsoem接收机。
6.
To sum up , tested and validated by data sets of shenzhou iv unmanned spacecraft and precise orbit ephemeris , the algorithms presented in the thesis can improve orbit accuracy and reduce random noise considerablely . derived conclusions have important value for reference , and lay the firm technological foundation for future applications 总之，经过神舟四号飞船实测数据计算和精密星历检验，表明本文提出的各种定轨方法可以较好的提高定轨精度，减少随机噪声，所得出的结论对于实际应用具有重要的参考价值，并为将来的应用奠定了坚实的技术基础。
7.
In the stage of the sun and the moon in sight , azimuth of the sun , the earth and the moon in the spacecraft body coordinate system is simulated . combining the simulated azimuth with the ephemeris of the sun and the moon , the state equation and observation equation are modeled . the initial orbital parameters calculated by least square method are used in orbit state equation to predict spacecraft state and to realize autonomous navigation 在日月可见阶段,模拟日、地、月敏感器测量信息,即日、地、月在航天器本体坐标系下的方位信息,结合日月星历,建立状态方程及观测方程,通过最小二乘法得到历元时刻的轨道状态初始值,将其代入轨道状态方程进行自主导航。
