Or is provided by the righthand rule of eD and eY
Or is provided by the righthand rule of eD and eY , is shown in Figure 1. Note, whereY-axis inSun elevation angle with (in black) is generally alignedand u denotes and that the will be the the ECOM-based model respect towards the orbit plane, with that Compound 48/80 MedChemExpress Within the satellite attitude (in red). of the satellite Sun-fixed frametheconstructed by u and , exactly where the argument of latitude The so-called with respect to is Sun. Within a case of low , Equation is maySun elevationa collinear problem IQP-0528 web amongst e andand, u denotes the argument (1) the endure from angle with respect to the orbit plane, e specifically for the orbit of latitude=of the satellitemidnight (u to 180, exactly where a case of low , Equation (1) may perhaps noon (u 0 and orbit with respect = the Sun. Within the orbit anomalies are often endure from a collinear problem in between eD and ez , specifically for the orbit noon (u = 0 ) occurred. and orbit midnight (u = 180 ), where the orbit anomalies are regularly occurred.Figure 1. Relative geometry among the Sun, Earth, and GNSS satellite inside a Sun-fixed frame: satellite Figure 1. Relative geometry among the Sun, Earth, and GNSS satellite inside a Sun-fixed frame: satellite attitude in red and ECOM-based SRP model in black. attitude in red and ECOM-based SRP model in black.Inside the case of || = 90 , eD generally points to the Sun in the satellite body X side. Inside the case of || = 0 , D always the Sun the Sun from the satellite body – side. In comparison, when = 90 ee points topoints todirection from the satellite physique X Z, Z, In comparison, when, = , and 90 /270 , the Sun path from the satellitethe frequent and X side at u = 0 1800 e points to respectively. In the case of = 0 , body -Z, Z, and X side at u = 0 180 regions amongst respectively. In the Z, and = 0 the frequent variations from the illuminatedand 90270 the satellite physique X, case of -Z sides lead to an variations the yaw rate or even a locations amongst that requires physique X, Z, and -Z sides cause a rise in with the illuminatedyaw variation the satelliteto be handled. Otherwise, an error, raise inside the yaw rate or possibly a introduced in to the GNSS measurement [13]. In general, the named phase wind-up, will beyaw variation that requires to become handled. Otherwise, an error, known as phase wind-up, properly handled by the nominal satellite attitude. [13]. Generally, the phase wind-up error is will likely be introduced into the GNSS measurementHowever, when the phase wind-up error physical maximum threshold, satellite triggered Nevertheless, when the yaw rate exceeds the is properly handled by the nominal the errorattitude.by the non-nominal yaw rate exceeds the physical maximum threshold, the error caused by the non-nominal attitude handle may perhaps degrade the GNSS ranging measurement accuracy and hinder GNSSrelated options. The attitude misalignment generally happens around orbit noon (u = 0 ) attitude manage might degrade the GNSS ranging measurement accuracy and hinder GNSSand orbit midnight (uattitude misalignment typically happens about orbit noon (u = 0 connected solutions. The = 180 ), exactly where the yaw price may well exceed its physical limitation. The midnight expressed using nine yaw rate may possibly exceed its physical limitation. and orbitECOM1 is (u = 180, where thedeterministic coefficients as follows: The ECOM1 is expressed making use of nine deterministic coefficients as follows: D(u) = D0 DC cos u DS sin u, (four) (4) D u = D D cosu D sinu, Y(u) = Y0 YC cos u YS sin u, (five) (5) Y u = Y Y cosu Y sinu, B(u) = B0 BC cos u BS sin u, (6) (6) B u = B B cosu B sinu, where D, Y, and B ar.