FIELD: astronautics.
SUBSTANCE: invention can be used for detection of electric field intensity on surface of spacecraft structure. Essence of the invention consists in the fact that the miniature meter of the spacecraft electrification parameters includes the following: microsystem vibratory modulator consisting of metal frame, printed circuit boards, inductance coils, movable shielding electrode, sensitive electrode, and electrical conversion circuit consisting of in-series connected current amplifier and analogue-to-digital converter, wherein input of current amplifier is connected to sensitive electrode, material of movable shielding electrode is selected from ratio E = E0k, where E is Young's modulus, E0 - Young's modulus in normal conditions, k is coefficient characterizing change of Young's modulus of used material in temperature range from -150 °C to +150 °C, coefficient value is within 1.0 ≤ k ≤ 1.1.
EFFECT: technical result is enabling possibility of reduction of weight and size parameters, reduction of power consumption of device, increase of system serviceability in conditions of open space, and also resistance to rigid temperature conditions of operation.
6 cl, 2 dwg
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Authors
Dates
2019-07-19—Published
2018-03-01—Filed