Spacecraft pointing performance via optimized solar array orientation
AssigneeHughes Electronics Corporation
InventorRay E. Mcvey
Life of this patent
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Abstract
An improved satellite system that limits or eliminates the dynamical rotational response of a satellite body to solar array asymmetrical and symmetrical flexing. The improvement is made by rotating one of a pair of solar arrays to an angle relative to the other solar array along a satellite pitch axis. The solar arrays are then rotated to a position wherein a maximum surface area of solar panels located on the pair of solar arrays is exposed to direct sunlight. The improvement enhances the ability of the satellite to maintain high precision angular stability under operational disturbances without costly and complex structural stiffening solutions.
Claims10
A satellite comprising:
- a satellite body;
- and
- a first and a second solar array deployed from opposite sides of said satellite body, said first solar array and said second solar array having a first angle therebetween relative to a satellite pitch axis, wherein said first angle is set to minimize the dynamic rotational response of the satellite in response to assymmetrical flexing of said first and said second solar array.
A method of decreasing dynamic rotation in a satellite in response to asymmetrical flexing of solar arrays in the satellite, where each solar array has a plurality of solar panels, the method comprising the step of:
- deploying a first solar array and a second solar array from opposite sides of a satellite body, said first solar array and said second solar array having a first angle therebetween relative to a satellite pitch axis.
Dependencies are inferred from the claim text.