In article the opportunity of use strapdown inertial navigation system (SINS) on the base of fiber-optic gyroscopes and quartz accelerometers corrected from star sensors and satellite navigation equipment (SNE) for perspective interplanetary spacecrafts motion control on phases of interplanetary trajectory insertion, trajectory correction, and braking during transition to Mars orbit is investigated. Results of onboard control complex accuracy characteristics estimation are presented at the given dynamic spacecraft scheme which is taking into account the liquid oscillations in tanks and structure elements elasticity. At modelling the errors of measuring devices installation, errors of SINS initial alignment and instrumental errors of SINS sensitive elements, variation of control engines parameters were taken into account. The structure of the developed complex of imitation modelling of interplanetary spacecraft controlled motion is resulted. Estimations of active flight legs realization accuracy were received by a method of statistical modelling of spacecraft controlled motion
Fiber-optic gyros and quartz accelerometers for motion control
IEEE Aerospace and Electronic Systems Magazine ; 22 , 4 ; 23-29
2007-04-01
3797369 byte
Article (Journal)
Electronic Resource
English
Fiber-Optic Gyros & Quartz Accelerometers for Motion Control
Online Contents | 2007
|Micromechanical Gyros & Accelerometers for Digital Navigation & Control
Online Contents | 2009
|Shock tests of gyros and accelerometers
AIAA | 1979
|