American ephemeris and nautical almanac 美國(guó)天文年歷和航海年歷
Effect of ephemeris error on the positioning accuracy of double - star positioning system 星歷誤差對(duì)雙星定位系統(tǒng)定位精度的影響
200s ttff - cold ( with current almanac , position , time and ephemeris ) 50s ttff - warm ( with current almanac , position , and time ) Ttff溫啟動(dòng)典型值50秒(當(dāng)擁有當(dāng)前的天歷、位置和時(shí)間數(shù)據(jù)時(shí))
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 在小樣本觀測(cè)數(shù)據(jù)情況下,研究利用日地月方位信息和日月星歷表進(jìn)行航天器自主導(dǎo)航以及利用dsp實(shí)現(xiàn)航天器自主導(dǎo)航器的技術(shù)。
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 同時(shí)亦可與gis (地理信息系統(tǒng))配套使用,實(shí)現(xiàn)在crt上地圖背景下的運(yùn)動(dòng)軌跡顯示。第二個(gè)產(chǎn)品, gps時(shí)鐘/同步系統(tǒng),利用全球衛(wèi)星定位gps衛(wèi)星的標(biāo)準(zhǔn)utc時(shí)間,可在全球得到同步的準(zhǔn)確時(shí)間。設(shè)備采用motorola的12通道gpsoem接收機(jī)。
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 總之,經(jīng)過(guò)神舟四號(hào)飛船實(shí)測(cè)數(shù)據(jù)計(jì)算和精密星歷檢驗(yàn),表明本文提出的各種定軌方法可以較好的提高定軌精度,減少隨機(jī)噪聲,所得出的結(jié)論對(duì)于實(shí)際應(yīng)用具有重要的參考價(jià)值,并為將來(lái)的應(yīng)用奠定了堅(jiān)實(shí)的技術(shù)基礎(chǔ)。
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 在日月可見(jiàn)階段,模擬日、地、月敏感器測(cè)量信息,即日、地、月在航天器本體坐標(biāo)系下的方位信息,結(jié)合日月星歷,建立狀態(tài)方程及觀測(cè)方程,通過(guò)最小二乘法得到歷元時(shí)刻的軌道狀態(tài)初始值,將其代入軌道狀態(tài)方程進(jìn)行自主導(dǎo)航。