| 摘要 |
FIELD: space.SUBSTANCE: invention relates to space engineering and can be used when determining microacceleration sensor error on spacecraft. Method for calibration microacceleration sensor in space flight, includes a comparison of measurements with calibrated values and determination of errors in sensor measurements, determining in related spacecraft coordinate system vectorwhich determines position of microacceleration sensor, measuring angular velocity of spacecraftand angular accelerationthereof, determining angular position and spacecraft's orbit, based on change of orbit of spacecraft and determined angular position, estimating density of atmosphere ρat flight altitude of spacecraft and acceleration of its braking, microacceleration calibrated value is determined by formula, where:- microacceleration in related spacecraft coordinate system; μ- Earth's gravitational parameter; r - distance from centre of Earth to centre of mass of spacecraft;- unit vector of axis of orbital coordinate system, directed by radius vector of spacecraft;- spacecraft velocity; c - ballistic coefficient of spacecraft, and comparing calibrated value of microacceleration and measured value, determining error in microacceleration sensor measurements.EFFECT: technical result is providing microacceleration sensor calibration in space flight.1 cl |
