Title :
Spacecraft inertial navigation errors nearby perigee and its elimination
Author :
Pu, Jia-Iun ; Cui, Nai-Gang ; Zhang, Li-Bin
Author_Institution :
Dept. of Astronaut. Eng., Harbin Inst. of Technol., Harbin, China
Abstract :
A practical problem on spacecraft inertial navigation system (INS) is described in the paper. Inertial Navigation System using in an elliptical orbit spacecraft causes a huge error when the spacecraft close to the perigee, The Causes for this error are discussed and the scale of it is estimated by simulation. Methods of eliminating the error are studied: the integrated navigation method and the compensation of initial orbit calculation method. Simulation results verify the validity of the proposed methods.
Keywords :
aircraft navigation; inertial navigation; space vehicles; elliptical orbit; error elimination; perigee; spacecraft inertial navigation errors; spacecraft inertial navigation system; Acceleration; Accelerometers; Aircraft navigation; Extraterrestrial measurements; Gravity; Inertial navigation; Missiles; Orbital calculations; Space technology; Space vehicles; INS error at perigee; initial orbit calculation; integrated navigation; spacecraft navigation;
Conference_Titel :
Mechatronics and Automation, 2009. ICMA 2009. International Conference on
Conference_Location :
Changchun
Print_ISBN :
978-1-4244-2692-8
Electronic_ISBN :
978-1-4244-2693-5
DOI :
10.1109/ICMA.2009.5244823
