Full-Text Search:
Home|About CNKI|User Service|中文
Add to Favorite Get Latest Update

Latitude argument difference expression based on orbit element difference

TANG Weiwei(School of Astronautics,Northwestern Polytechnical Univ.,Xi'an 710072,China)  
To avoid a set of coupled nonlinear differential equations while solving the relative orbit under different relative distance,a method of orbit element difference is used to solve the problem.Firstly,an orbit element difference vector is defined and rewritten by introducing a component which describes the satellite angular position.Secondly,the expressions of relative orbit difference and latitude argument difference are established to make sure that the latitude argument difference is only the desired variable to illuminate a relative orbit.Finally,the latitude argument difference expressions of relative orbits are obtained under different relative distance conditions,and the necessity of distinguishing the relative orbits under the different distance conditions is explained.The simulation is done according to the deduced relative orbit expressions which are based on orbit element difference,and shows that it is correct to use the expressions based on the latitude angle difference to solve the relative orbit.
Download(CAJ format) Download(PDF format)
CAJViewer7.0 supports all the CNKI file formats; AdobeReader only supports the PDF format.
©CNKI All Rights Reserved