• DocumentCode
    3354735
  • 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
  • fYear
    2009
  • fDate
    9-12 Aug. 2009
  • Firstpage
    4539
  • Lastpage
    4543
  • 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;
  • fLanguage
    English
  • Publisher
    ieee
  • 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
  • Type

    conf

  • DOI
    10.1109/ICMA.2009.5244823
  • Filename
    5244823
    • Link To Document
    https://search.isc.ac/dl/search/defaultta.aspx?DTC=49&DC=3354735