| 摘要 |
FIELD: transport, space engineering. ^ SUBSTANCE: propose method designed to determine spacecraft solar battery maximum output comprises measuring the spacecraft orbit altitude for the angular half-width of the Earth disk visible from the spacecraft (Qz) and the angle of elevation of atmosphere top boundary () above the Earth horizon visible from the spacecraft, determining the angular half-width of the Sun disk visible from the spacecraft (Qs) and measuring spacecraft orbital angular velocity (ë). It includes also measuring the angle between direction to the Sun and spacecraft orbit plane (), measuring the angle of elevation of direction to the Sun above the Earth horizon visible from spacecraft (g) and maximum solar battery output at the batteries minimum temperature. The system, to this end, comprises the unit to measure the angle between direction to the Sun and spacecraft orbit plane, unit to measure the angle of elevation of direction to the Sun above the Earth horizon visible from spacecraft, the unit to measure spacecraft orbital angular velocity, the unit to measure the spacecraft orbit altitude variation, the unit to determine the angle of elevation of atmosphere top boundary () above the Earth horizon visible from the spacecraft, the unit to determine the angular half-width of the Sun disk visible from the spacecraft. It incorporates also the unit to determine the orbit whereon solar battery maximum output is determined, the unit to generate identification parameters of solar batteries temperature conditions and key. ^ EFFECT: higher accuracy of determining solar battery maximum output. ^ 2 cl, 4 dwg |
