Determination of the optimal beta gimbal angles for the solar arrays of the space station using a neural network

Abstract

The current baseline solution for minimizing the potential of dynamic loads being imparted onto the solar arrays of the Space Station during proximity maneuvers by the Space Shuttle is to lock the position of the solar arrays throughout the approach/departure of the Space Shuttle. However, if the a priori locked position does not optimally feather the solar arrays throughout the Shuttle's approach/departure, excessive dynamic loads could result, producing a structural failure in the solar arrays. A more robust solution would involve feathering the position of the solar arrays throughout proximity maneuvers by the Space Shuttle. The robust solution will be implemented using a neural network as an open loop predictor/controller. >