| 摘要 |
FIELD: aircraft industry. ^ SUBSTANCE: invention refers to space equipment, to space vehicle electric power supply systems, and can be used during solar battery operation. Method for determining maximum power output of space vehicle solar batteries involves measurement of angle between the Sun direction and space vehicle orbit plane, the Sun direction elevation angle above the Earth horizon observed out of space vehicle, and maximum power output of double-sided solar batteries and solar batteries having positive power output of their back surface, which is defined as product of voltage and current values from solar batteries, which are measured at the moments when radiation reflected from the Earth enters solar battery panels from their end surface, which are defined from condition of equality of values of the Sun direction elevation angle above the Earth horizon observed out of space vehicle and one-half angle of sensitive area of solar battery panel operating surface. Maximum power output of single-sided solar batteries is defined as product of voltage and current values from solar batteries, which are measured at the moments when radiation reflected from the Earth enters solar battery panels from their end or back surfaces. System for determining maximum power output of solar batteries of space vehicle includes measuring unit of angle between the Sun direction and space vehicle orbit plane, unit for determining the loop of executing the determining operation of maximum power output of solar batteries, for measuring the Sun direction elevation angle above the Earth horizon observed out of space vehicle, unit for determining the moment of determination of maximum solar battery power output, and a key. ^ EFFECT: eliminating negative influence of radiation reflected from the Earth. ^ 2 cl, 6 dwg |
