FIELD: measurement equipment.
SUBSTANCE: solar battery (SB) of a space vehicle (SV), moving along the near-circular orbit around the Earth is rotated on two orbit passes, the values of current from SB are measured, and using them the values of the ground albedo are determined. Meanwhile in addition the height of SV orbit is measured, a half-opened angle Q of the Earth disk seen from SV is determined, two orbit passes, separated by the maximum time interval 24 hours, and this interval contains the moment, when the projection of the normal line to SV orbit plane to the equator plane is collinear the Sun direction projection to the equator plane with controlled pre-set trigonometrical relations between the Sun direction angle and SV orbit plane.
EFFECT: enlarging functional capabilities.
2 dwg
| Title | Year | Author | Number |
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|
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RU2558959C2 |
| METHOD OF SPACECRAFT SUN BATTERIES POSITION CONTROL AND SYSTEM FOR ITS IMPLEMENTATION | 2005 |
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RU2325311C2 |
