| 摘要 |
FIELD: transport. ^ SUBSTANCE: invention relates to control over orientation of spacecraft equipped with magnetometre designed to measure EMF intensity vector. Proposed method comprises measuring EMF intensity and spacecraft orbit parameters. Here, spacecraft is stabilised in inertial space, EMF vector direction if registered at the moment of stabilisation, and the angle between registered and current EMF vector directions is measured. The moment when acute measured angle reaches its maximum is registered and memorised, and EMF intensity modulus is measured for fixed moment. EMG intensity modulus for the same moment is calculated in spacecraft position in orbit for the same moment. Obtained EMF intensity modulus magnitudes are compared to determine magnetic interference from spacecraft. Now, spacecraft orientation is determined in EMF intensity vector fixed magnitudes during spacecraft stabilisation and when acute measured angle reaches its maximum with due allowance for magnitude of interference defined by formula ^ EFFECT: possibility to determine spacecraft three-axis orientation at whatever sections of spacecraft trajectory independent of Sun illumination intensity, higher accuracy of orientation determination. |
